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    Review
    Overview of all-electric/hybrid helicopter powertrain and transmission system
    Meng Di, Han Bing, Ning Fangli, Hu Zhian, Tang Xianju, Chen Ce, Deng Wenxing
    2026,17(4):1-18. DOI: 10.16615/j.cnki.1674-8190.2026.04.01
    [Abstract] (136) [HTML] (235) [PDF 7.54 M] (153)
    Abstract:
    With the increasing demands for environmental protection and energy efficiency in the aviation industry, the electrification of helicopters has become an important direction for the development of aviation power technologies. This paper provides an in-depth analysis and review of the power systems and transmission systems of fully electric and hybrid helicopters. First, the paper surveys the current and planned fully electric and hybrid helicopters, as well as innovative electric vertical takeoff and landing (eVTOL) aircraft, focusing on performance indicators such as maximum passenger capacity, takeoff weight, cruising speed, power, and range. Based on this, the power system architectures of fully electric and hybrid helicopters are categorized and reviewed, with a detailed discussion on the technical characteristics of the power coupling transmission system. Finally, the paper analyzes and forecasts the future direction of aviation power technologies for helicopter electrification. The work presented in this paper is of significant reference value for advancing the development of helicopter electrification technologies in China.
    Theoretical Research
    Prediction Model of landing load on aircraft landing gear based on multi-task learning
    yanguangyun, xuheyong, LIAN Xiaofeng, LI Rongqiang, GE Zihang
    2026,17(4):19-26,35. DOI: 10.16615/j.cnki.1674-8190.2026.04.02
    [Abstract] (84) [HTML] (52) [PDF 1.97 M] (124)
    Abstract:
    Building a predictive model between flight parameters and landing load on landing gear is of great significance for the stress analysis and safety life assessment of landing gear structures, as well as predictive maintenance. This paper presents a landing gear landing load prediction model based on multi-task learning framework, using a Multi-gate Mixture of Experts (MMoE). The input features of the MMoE model were determined by Pearson correlation analysis on the flight parameter dataset, achieving accurate prediction of the landing gear landing load and comparing the performance with Single-Task model and Shared-Bottom model. The results show that the framework based on the MMoE model significantly improves the prediction ability of load data. Compared with the other two models, the MMoE model exhibits greater robustness, and the mean square error (MSE) on the test set is reduced by more than 66%.
    Research on the stability of helicopter ground steering motion based on bifurcation analysis method
    Wang Jiawei, Yin Qiaozhi, Sun Hao, Wang Zhongting, Wei Xiaohui, Nie Hong
    2026,17(4):27-35. DOI: 10.16615/j.cnki.1674-8190.2026.04.03
    [Abstract] (75) [HTML] (43) [PDF 1.23 M] (82)
    Abstract:
    Due to the lack of rudder, high center of gravity, short wheelbase and other factors, heavy helicopters are prone to accidents that seriously threaten the safety of life and property such as rushing out of the runway or oversteering when taxiing on the ground. In order to obtain the stable parameter area of helicopter taxiing on the ground and improve the stability of helicopter taxiing on the ground, the bifurcation analysis method is proposed to study the stability. In this paper, a six-degree-of-freedom nonlinear dynamic model of helicopter ground taxiing is established in MATLAB/Simulink. The highly nonlinear forces such as tire force and rotor tension are introduced into the model, which can truly simulate the force of the helicopter when it is on the ground taxiing. Based on the bifurcation theory and the numerical continuation tool AUTO, the stability of the helicopter ground steering direction is studied. The single-parameter stability bifurcation analysis with the front wheel angle as the bifurcation parameter is carried out, and the influence of the front wheel angle on the stability of the helicopter ground steering direction is analysed. Combined with the factors such as helicopter tire force and yaw angle, the Hopf bifurcation phenomenon in the unstable state of the system is analysed. The results show that the essence of the helicopter ground steering instability is that the lateral friction of the tire cannot provide the centripetal force required for the helicopter ground steering.
    Research on the Influence of Assembly Gap on the Connection Strength of Composite Overlap Structures Caused by Curing Deformation
    zhuxiaolong, zhaoyumeng, wangguoyue, yanwei, wangle, songluyang, zhengxitao
    2026,17(4):36-47. DOI: 10.16615/j.cnki.1674-8190.2026.04.04
    [Abstract] (75) [HTML] (76) [PDF 3.31 M] (94)
    Abstract:
    The assembly structure of aircraft has a large number of components, large dimensions, high precision requirements, and complex coordination processes. The solidification deformation of composite materials greatly affects the forming accuracy of structural components, resulting in assembly gaps during subsequent assembly processes, leading to significant assembly stresses and even inability to assemble properly, thereby affecting the overall structural strength and aerodynamic efficiency of the aircraft. This article proposes a "thermal coupling pre-treatment method" to study the effect of assembly gaps caused by solidification deformation on the connection strength of composite lap structures. For composite single lap structures, a porous laminated plate model is established for thermal mechanical coupling analysis, and a porous laminated plate model with solidification deformation is obtained. Based on this model, a composite single lap structure model with assembly gaps is established, and numerical simulation of tensile tests is carried out to obtain the tensile strength of composite single lap structures. The tensile strength of composite single lap structures is compared with that of composite single lap structures without solidification deformation, and the influence of solidification deformation on the mechanical connection strength of composite materials is analyzed.
    Study on Surface Morphology of Light Alloy Based on External Cylindrical Turning Mechanism
    WangFulin, YangXiao, TangNengyi, TangDianya
    2026,17(4):48-59. DOI: 10.16615/j.cnki.1674-8190.2026.04.05
    [Abstract] (55) [HTML] (23) [PDF 6.44 M] (80)
    Abstract:
    The construction of the prediction model of light alloy turning surface morphology is of great significance for the optimization of turning parameters and the improvement of part surface quality. Based on the mechanism of cylindrical turning, the simulation model of workpiece surface topography is established considering the influence of tool geometry, machine vibration and cutting elastoplastic deformation.Cutting experiments were conducted to verify and compare the surface morphology obtained from simulation and experiments.The trend of peak height variation tended to be consistent under different cutting parameters;Three-dimensional surface roughness arithmetic mean height Sa and root mean square height Sq are used to characterize the surface topography. The average relative error of Sa is 3.95% and the average relative error of Sq is 8.34%,,indicating that the model is accurate and has good prediction effect, and can reflect the surface quality of the workpiece.Finally, with cutting efficiency and surface roughness as optimization objectives,the cutting parameters were optimized using Non-Dominated Sorting Genetic Algorithm II (NSGA-II), and the non-dominated solution set of cutting parameters was obtained for reference by decision makers.
    Engineering Application
    Analysis of influence of wingtip spacing variation on aerodynamic of combined solar UAV
    Li Xian, ma xiaoping, Ying Pei
    2026,17(4):60-67. DOI: 10.16615/j.cnki.1674-8190.2026.04.06
    [Abstract] (71) [HTML] (65) [PDF 2.49 M] (105)
    Abstract:
    To explore the variations of tip vortices and their influences on aerodynamic characteristics and energy consumption during the docking process of a combined solar-powered unmanned aerial vehicle (UAV), a CFD approach employing the RANS control equation and the SST k-ω turbulence model was utilized to conduct research on a type of solar-powered UAV. Through the reduction of the spanwise spacing between two solar-powered UAVs, the situation where two UAVs combine in the air through tip-linked wings was simulated. The results indicate that a pair of vortices with opposite rotational directions on the wing tips of the two solar-powered UAVs start to merge when the tip spacing is reduced to 20% of the average aerodynamic chord length, and changes occur in terms of morphology and characteristic parameters. The combined strategy of tip-linked wings enables the lift-to-drag ratio of the solar-powered UAV to increase by up to 23.5% and the power consumption during flight to decrease by up to 12.2%, demonstrating the potential for reducing the capacity requirement of energy storage batteries and enhancing the overall performance of solar-powered UAVs.
    Numerical study on the aerodynamic performance of ice ridge airfoil with dual synthetic jets actuator
    YANG Shengke, ZUO Chenglin, LIU Senyun, WANG qiao, YI Xian
    2026,17(4):68-75,89. DOI: 10.16615/j.cnki.1674-8190.2026.04.07
    [Abstract] (47) [HTML] (60) [PDF 2.29 M] (81)
    Abstract:
    The ice ridge formed during the anti/de-icing or under the condition of supercooled large droplet will seriously damage the aerodynamic performance of the airfoil and affect flight safety. In order to improve the flight performance of ice ridge airfoil, the active flow control method based on dual synthetic jet was adopted. The aerodynamic performance control of NACA0012 ice ridge airfoil based on dual synthetic jet was studied through numerical simulation. The effect and mechanism of dual synthetic jet on improving the aerodynamic performance of ice ridge airfoil, and the influence of parameters such as momentum, frequency, angle and position of dual synthetic jet were explored. The results show that adding dual synthetic jet at appropriate position on the wing surface can effectively improve the lift, reduce the drag and expand the stall angle of attack. The dual synthetic jet control parameters have a significant impact on the control effect. The larger the jet momentum coefficient, the better the control effect, the optimal control effect is achieved when the dimensionless control frequency is around 0.2, the jet angle has a good control effect within the range of 30°-75°, and the control effect is best when the jet outlet is located near 0.2 times the chord length.
    Numerical simulation of aerodynamic/flow field of carrier-based UAV landing in sea wind field
    GENG Yansheng, XU Xiaoping, ZHOU ZHou
    2026,17(4):76-89. DOI: 10.16615/j.cnki.1674-8190.2026.04.08
    [Abstract] (79) [HTML] (76) [PDF 3.29 M] (103)
    Abstract:
    During the landing phase of a carrier-based fixed-wing unmanned aerial vehicle (UAV), the aircraft must traverse a highly complex aerodynamic environment characterized by the intricate wind field over the sea surface and the turbulent flow field at the ship"s stern, the latter being significantly affected by the superposition of the ship"s multi-degree-of-freedom motion. A comprehensive evaluation of these aerodynamic and flow field characteristics is essential for the development and implementation of robust control strategies to ensure the safe and precise landing of carrier-based aircraft. In this paper, the complex ship/deck flow field and unsteady aerodynamic characteristics of carrier-based unmanned aerial vehicle (UAV) landing process under sea wind field are numerically simulated. A high-fidelity simulation model of the flow field/aerodynamic during the landing process of carrier-based UAV is established, which includes sea wind field, ship motion mode, landing trajectory of carrier-based UAV and dynamic overset grid technology. The dynamic flow field of ship/deck and unsteady aerodynamic characteristics of carrier-based UAV in stationary and moving state are analyzed. The results show that: The velocity distribution in the W direction on the landing trajectory of the carrier-based aircraft is typical "Rooster Wake", and the vertical cutting velocity is very obvious; the maximum vertical velocity variation of the flow field is close to 12m/s due to the coupled motion of ship pitch/heave mode; The aerodynamic characteristics of UAV in the process of landing are strongly unsteady, and the lift coefficient shows a trend of first increasing and then decreasing.
    Numerical Research on Static Aeroelasticity of Highly Flexible Wing Based on CFD/CSD Coupling
    LIU Zheng, JIANG Panpan, WANG Guoliang, LI Xia
    2026,17(4):90-95,107. DOI: 10.16615/j.cnki.1674-8190.2026.04.09
    [Abstract] (81) [HTML] (51) [PDF 1.43 M] (97)
    Abstract:
    High altitude long-endurance UAV uses lightweight wings, which are highly flexible. The wings are significantly different in shape before and after being loaded. It is difficult to generate the meshes and to control the meshes’ quantity. To solve these problems, this paper adopts the unstructured CFD meshes and couples the static mechanics solving program. Just in a few coupling steps, the analysis converged to the stable equilibrium state. The CFD’s meshes used in coupling have high fidelity under the wing’s stall angle, which is verified by fine meshes. When the angle of attack is small, the CFD/CSD coupling results agree with traditional panel method when taking airfoil into account. When the angle of attack increases, the CFD/CSD coupling method can simulate a certain degree of separation. What’s more, this method can count geometric nonlinearity and aerodynamic forces of curved surface. In addition, the CFD/CSD coupling method is efficient and worth promoting.
    Experiment and simulation research on the effect of aircraft flexibility on landing load
    LIUSUIBUFU, LIUXIAOCHUAN, HUIXULONG, BAICHUNYU, LIXIAOCHENG, ZHOURUIPENG
    2026,17(4):96-107. DOI: 10.16615/j.cnki.1674-8190.2026.04.10
    [Abstract] (71) [HTML] (69) [PDF 2.66 M] (115)
    Abstract:
    In order to research the influence of aircraft flexibility on landing load, an experiment piece of full scale aircraft simplified structure with landing gears has been designed. Meanwhile, a rigid-flex coupling full aircraft landing dynamics simulation model was established based on the theory of mode superposition.Otherwise, landing gear drop experiment and full scale aircraft drop experiment were carried out respectively. The influence of aircraft flexibility on landing load was further studied through the simulation model, which was verified through the experiment data, and the results show that the experimental method can effectively obtain a series of data such as landing gear vertical load, buffer stroke, and acceleration at the center of gravity. The landing gear dynamics model and full scale aircraft landing dynamics model have an error of less than 5% compared to the experiment, the reliability of the simulation model was verified. The influence of aircraft flexibility on landing dynamic response cannot be ignored. Considering the flexibility of the aircraft, the peak vertical ground load and acceleration at the center of gravity of the landing gear will decrease, the pulse-width of the vertical ground load and the acceleration will increase, and the landing power absorbing and buffering efficiency of the landing gear will decrease. The results provide reference for aircraft weight reduction and landing gear design.
    Simulation of the Vector Jet Effect on the Aircraft Engine
    zhangjunfeng, wangtao, caojiping
    2026,17(4):108-114,125. DOI: 10.16615/j.cnki.1674-8190.2026.04.11
    [Abstract] (75) [HTML] (39) [PDF 3.58 M] (90)
    Abstract:
    Based on the NNW-FSI V1.0 software, the flow past Fifth generation fighter configuration is simulated. The flow with and without jet are all studied. Aerodynamic force coefficient, pressure distribution and flow pattern on the surface are analyzed. The deflection of the nozzle, change from the angle of attack and the vector jet effect that influence the aerodynamic characteristics of the Fifth generation fighter configuration standard model are studied. The numerical results agree well with the experimental data. The deflection of the nozzle change the lift character, the jet effect accelerates with the angle of attack.
    Numerical Simulation Study on Flow and Heat Transfer Characteristics of RP-3 Aviation Kerosene in a Dimple-type U-tube
    Deng Zhibin, Xu Ziyang, Zhao Liang, Liu Xiang, Zhang Tianlai, Chen Yonggang, Li Shilin
    2026,17(4):115-125. DOI: 10.16615/j.cnki.1674-8190.2026.04.12
    [Abstract] (68) [HTML] (33) [PDF 9.56 M] (91)
    Abstract:
    To enhance convective heat transfer in the U-tube through surface structure optimization, this study proposes an improved heat transfer design for aviation kerosene air-oil heat exchangers using a dimple-structured U-tube. Numerical simulations were conducted to systematically analyze the coupled flow and heat transfer mechanisms of RP-3 aviation kerosene under high-pressure (3–5 MPa) and high-heat-flux (500–800 kW/m2) conditions. The results demonstrate that the combined effects of dimple structures and centrifugal forces in the bend region induce adverse pressure gradients and promote secondary flows in the boundary layer, significantly amplifying turbulent kinetic energy and generating unique vortex structures distinct from conventional Dean vortices. These dimple-induced vortices propagate toward the tube core, enhancing heat transfer performance. The U-bend section achieves Nusselt numbers 2.4–3.0 times higher than those of straight tubes, with a performance evaluation criterion (PEC) of 1.96–2.71. Notably, increasing operating pressure/heat flux or reducing flow rate further improved PEC values, highlighting the superiority of the dimple-type U-tube in convective heat transfer enhancement through synergistic structural and flow effects.
    “中国民用航空飞行学院建校 70 周年”专栏
    A Review of UAV-based Inspection and Detection Methods for Urban Tunnel Defects
    ZHAO Zi-shun, YANG Ming, ZHU Xinyu, WANG Nan-nan
    2026,17(4):126-139. DOI: 10.16615/j.cnki.1674-8190.2026.04.13
    [Abstract] (63) [HTML] (47) [PDF 1.77 M] (92)
    Abstract:
    As the scale of urban tunnels continues to expand, traditional manual and vehicle-based inspection methods are increasingly unable to meet the demands of efficient and intelligent operation and maintenance. With their mobility, flexibility, and high operational efficiency, unmanned aerial vehicles provide a new approach for tunnel defect inspection. However, environmental characteristics inside tunnels, such as GNSS signal loss, insufficient lighting, confined spaces, and repetitive structural features, impose higher requirements on UAV positioning and navigation, data acquisition, and defect recognition. Focusing on UAV-based defect inspection in urban tunnels, this paper systematically reviews the current development of inspection methods, positioning techniques in GNSS-degraded environments, traditional image processing and machine learning approaches, deep learning-based defect detection algorithms, and their deployment adaptability on UAV platforms. Future development directions are further discussed from the perspectives of engineering implementation, airworthiness verification, and digital twins, with the aim of providing a reference for research and practical applications in urban tunnel inspection.
    Research on Key Bottlenecks and a Multi-dimensional Collaborative Development Path for UAV System Applications in Plateau Environments
    ZHANG Shu-yi, YANG Ming, WANG Nan-nan
    2026,17(4):140-152. DOI: 10.16615/j.cnki.1674-8190.2026.04.14
    [Abstract] (110) [HTML] (51) [PDF 1.40 M] (114)
    Abstract:
    The plateau environment poses severe challenges to the flight performance and mission reliability of unmanned aerial vehicle (UAV) systems. As a core carrier of the low-altitude economy, UAVs show broad prospects in plateau regions. However, existing studies have often focused on macro-level policies or isolated technical issues, lacking an integrated analysis of the systematic linkages among flight platforms, policy/standards, and ground support—thereby limiting holistic guidance for large-scale deployment in plateau environments. Drawing on existing literature and practical cases, this study systematically reviews key technological bottlenecks and adaptive development pathways for plateau UAV applications across three dimensions: flight platforms, policy and standards, and ground support. At the platform level, progress is discussed in high-lift airfoil design, turbocharging-based power compensation, multi-source integrated navigation and positioning, and low-temperature battery adaptability. At the policy and standards level, the current regulatory framework is examined, and directions are proposed for establishing airworthiness standards and technical specifications tailored to plateau conditions. At the ground support level, practical experience is synthesized from representative cases, including the UAV test flight site in Shannan, Tibet, and the intelligent grazing IoT system in Aba, Sichuan. The results provide theoretical and practical references for technology development, platform selection, and policy formulation for UAV systems operating in plateau environments.
    Few-Shot Prediction Method of NPD Curves for Cross-Type Aircraft Noise Assessment
    wang ke, SHEN MAOCHI, WEI DONGDONG, GUI Li
    2026,17(4):153-163. DOI: 10.16615/j.cnki.1674-8190.2026.04.15
    [Abstract] (70) [HTML] (46) [PDF 1.52 M] (86)
    Abstract:
    To address the challenge of early noise airworthiness assessment for new aircraft caused by the lack of complete Noise-Power-Distance (NPD) data, this paper proposes a few-shot probabilistic prediction method based on Conditional Neural Processes (CNP). The method learns the cross-type function distribution using historical data from certified aircraft in the EASA ANP database. It integrates aircraft design parameters via Feature-wise Linear Modulation (FiLM) and incorporates physical consistency monotonicity constraints to enhance prediction stability. Experimental results under leave-one-out cross-validation show that, with only a single observation point, the method achieves a Mean Absolute Error (MAE) of 1.12 dB for SEL and 1.26 dB for LAmax, with a 90% prediction interval coverage rate of 91.3%–93.2%. This approach effectively reconstructs NPD curves and provides calibrated probabilistic outputs under extreme data scarcity, offering a reliable quantitative basis for noise risk assessment of new aircraft.
    Large-Model–Driven Automatic Analysis and Evaluation for Flight Training
    CUI Xianhui, Zejian Lang, Huang Hong, ZHAO Yunxiang
    2026,17(4):164-171. DOI: 10.16615/j.cnki.1674-8190.2026.04.16
    [Abstract] (65) [HTML] (50) [PDF 1.12 M] (102)
    Abstract:
    Flight training assessment faces challenges such as high data dimensionality, complex standard operating procedures (SOPs), and strong dependence on instructor experience, making it difficult to achieve individualization, traceability, and executability. Existing data processing methods are prone to defects such as averaging that masks weak points, unverifiable evidence chains, and difficulty in implementation. This study constructs an integrated process of "checkpoint importance-retrieval-augmented generation (RAG)-controlled generation-consistency verification", and builds an automatic flight training assessment system that is interpretable, traceable, and executable. In real training data and blind evaluation, the results achieved a "recommended" rating and above about 80.0%. It has strong practical and reference value, can significantly improve assessment and teaching, and has strong implementation and promotion feasibility.
    Research on Improved MLP-Based Assessment Method for Pilot Manual Control Performance
    NIE Haonan, QIAN Yu, LI XIUYi, SUN JING
    2026,17(4):172-180,201. DOI: 10.16615/j.cnki.1674-8190.2026.04.17
    [Abstract] (64) [HTML] (28) [PDF 1.29 M] (91)
    Abstract:
    To address the problems of overreliance on instructors’ subjective experience, poor evaluation consistency, and limited scalability in the quantitative assessment of manual control performance during the final approach and landing phase of flight training, an automated grading method based on TOPSIS-assisted labeling and an improved multi-layer perceptron (MLP) is proposed. With expert-determined indicator weights and grading thresholds, TOPSIS is applied to 186 flight-sortie samples to generate training labels with three levels (Exemplary manner/Effectively/Adequately). An improved MLP incorporating residual connections and batch normalization is trained on standardized features, while Dropout regularization and a dynamic learning-rate schedule are employed to mitigate overfitting. Random Forest, Support vector machine (SVM), Decision Tree, and K-nearest neighbors (KNN) are used as baseline methods, and performance is evaluated by accuracy and weighted F1-score under 5-fold cross-validation. Experimental results indicate that the proposed method achieves an accuracy of 86.51%, with an average per-sample inference time of approximately 0.007 ms, providing fast and accurate decision support for large-scale data in practical training scenarios.
    A Comprehensive Assessment Method for Air Traffic Controller Fatigue Risk Based on Visual-Audio-Heart Multimodal Indicators
    GAO Xin, GUAN Xian, WANG Kai, BAI Junqi, ZHU Min
    2026,17(4):181-190. DOI: 10.16615/j.cnki.1674-8190.2026.04.18
    [Abstract] (65) [HTML] (33) [PDF 835.97 K] (84)
    Abstract:
    Traditional air traffic controller competency assessment methods suffer from significant limitations in real-time capability and objectivity, making it difficult to meet the dynamic risk management requirements of air traffic control. To address this issue, this paper proposes a comprehensive fatigue risk assessment method based on visual-audio-heart rate multimodal fusion. Firstly, an evaluation system is constructed, comprising three criterion layers (visual fatigue, speech behavior, and heart rate variability) and eleven specific indicators. Secondly, the Analytic Hierarchy Process is employed to determine the comprehensive weights of each indicator. Furthermore, by integrating the fuzzy comprehensive evaluation method, a quantitative mapping model from multimodal indicator data to a five-level fatigue risk scale is established, and an experimental platform is developed for validation. The results show that, under laboratory conditions, the model can effectively quantify controller fatigue states and distinguish between different fatigue levels, and that PERCLOS value, average single eye-closure duration, RMSSD, and LF/HF ratio are key indicators influencing fatigue assessment. This study provides a feasible technical solution for implementing dynamic and precise fatigue risk monitoring and early warning for air traffic controllers.
    Research on Operational Load Assessment Model for Civil Aviation High-Plateau Routes Based on LSTM-XGBoost
    Zhangxianhao, Wangchenxu, Fengjiangyao
    2026,17(4):191-201. DOI: 10.16615/j.cnki.1674-8190.2026.04.19
    [Abstract] (61) [HTML] (26) [PDF 1.08 M] (94)
    Abstract:
    In the operation of civil aviation plateau air routes, the coupled effects of complex meteorological environments and special plateau working conditions significantly increase the difficulty of operational load evaluation, and single models fail to meet the demands of high-precision modeling. To address this issue, this paper proposes a fused evaluation model combining Long Short-Term Memory (LSTM) and Extreme Gradient Boosting (XGBoost) for plateau air route scenarios. In accordance with CCAR Part 121 and Flight Operational Quality Assurance (FOQA) advisory circulars, 22 initial indicators are selected from three dimensions of aircraft performance, meteorological environment and flight operation, and 15 key indicators are screened out by gray relational analysis and the entropy weight method. Taking 8640 groups of measured Quick Access Recorder (QAR) data from six plateau air routes operated by A320 aircraft of an airline as samples, after data preprocessing, LSTM extracts temporal dynamic flight features, which are fused with static features and then input into the XGBoost model to realize quantitative evaluation and hierarchical discrimination of operational loads on plateau air routes. The model performance is comprehensively evaluated by accuracy, Root Mean Square Error (RMSE) and Mean Absolute Error (MAE), and robustness verification is carried out under typical complex working conditions. The results show that the evaluation accuracy of the model on the test set is 96.30%, with RMSE and MAE of 0.042 and 0.031 respectively. Its accuracy remains above 92% under typical complex working conditions, and its overall performance is superior to each comparative model. The research results can provide theoretical and engineering references for quantitative evaluation of operational loads on plateau air routes and decision-making for aviation safety operation.
    Airspace Sectorization Based on Air Traffic Complexity
    LI Kenan, YANG Kaiqi, WANG Hongyong
    2026,17(4):202-210. DOI: 10.16615/j.cnki.1674-8190.2026.04.20
    [Abstract] (68) [HTML] (26) [PDF 1.96 M] (80)
    Abstract:
    The structure of routes and air traffic complexity are the crucial factors influencing sectorization. To optimize the utilization of airspace resources, balance air traffic conditions across sectors, and ensure the safety of air traffic control, a sectorization method based on air traffic complexity is proposed. Firstly, a correlation model for waypoints is established based on their distribution and air traffic flow, and an airspace network topology is constructed by integrating air traffic complexity. Next, a weighted fuzzy C-mean clustering algorithm is used to process the airspace network topology map to determine the boundaries of airspace sectors. Subsequently, the NSGA-II algorithm is improved to reduce and equalize the air traffic complexity as the goal, while sector structural features are introduced as constraints to solve the sector division. Finally, by using the controlled airspace of Shanghai and the related trajectory data, an example simulation of air traffic complexity-based sector delineation is carried out, and compared with the existing sector structure and the flow-based sector structure. The results show that the sector division based on complexity can improve the balance of sector complexity and flow rate, effectively reduce the extreme values of complexity and flow rate, improve the stability of airspace division, and validate the reasonableness and effectiveness of the sector division method based on air traffic complexity.
    Research on the integrity and airworthiness compliance of BDS airborne receivers in NPA phase
    LIU Ruihua, Yu Lantao
    2026,17(4):211-222. DOI: 10.16615/j.cnki.1674-8190.2026.04.21
    [Abstract] (71) [HTML] (42) [PDF 2.27 M] (87)
    Abstract:
    The prerequisite for retrofitting BeiDou Navigation Satellite System (BDS)airborne equipment in civil aircraft is to meet its airworthiness requirements. However, due to the differences between BDS and the Global Positioning System (GPS) in terms of constellation structure, signaling system and functions, the current airworthiness standards related to the Global Navigation Satellite System (GNSS) are not fully applicable to BDS airborne equipment. According to the integrity requirements of different airspace in the required navigation performance (RNP), and combining with the relevant airworthiness standards such as Radio Council for Aeronautics (RTCA) and industrial standards, the airworthiness compliance technology of the integrity of the Beta class BDS airborne receivers is researched. The weighted parity vector method is used as the theoretical basis of receiver autonomous integrity monitoring (RAIM), and a standardized test environment is established to propose test conditions, test methods, test procedures and airworthiness compliance indexes. It is set that the fault-free receiver can correctly detect system faults and eliminate faulty satellites with 99.9% probability and the probability of false alarms is 0.002/hour under the ideal test environment without interference sources. The test uses a trouble-free receiver to receive the broadcast ephemeris of the BDS B1C signal on February 4, 2024, and evaluates the RAIM performance for the BDS-3 system and based on the non-precision approach (NPA) phase in static and dynamic scenarios on a global scale. The research results can provide corresponding theoretical and methodological support for the airworthiness verification of BDS airborne receiver integrity applicable to non-precision approach and the following operation stages.
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    Technology development trends, knowledge mapping and pathways for hydrogen fuel cell low-altitude aircraft
    caiyaozhong, zhangyuhuan, linzhijian, chenwenjia
    Available online:October 08, 2026, DOI:
    [Abstract] (25) [HTML] (0) [PDF 1.48 M] (0)
    Abstract:
    The vigorous development of the low-altitude economy and the strategic demand for deep decarbonization in the aviation industry have jointly driven the rapid development of hydrogen fuel cell low-altitude aircraft technology. Based on data from the incoPat patent database and Core Collection literature from Web of Science, this paper employs a knowledge mapping analysis method to conduct a systematic study of the development trends, innovation landscape, and collaboration networks of global hydrogen fuel cell low-altitude aircraft technology from 2003 to 2025. It identifies core technology clusters including fuel cell systems, hybrid power system architectures, energy management and control strategies, and hydrogen storage and supply systems. The study clarifies that global R&D has formed a multipolar competitive landscape with China, South Korea, Europe, and the United States as the main participants. It also points out that while China holds significant advantages in engineering applications and system integration, it still faces shortcomings in core fuel cell materials, hydrogen storage technologies, forward-looking technology deployment, and international patent protection. Finally, the paper proposes a comprehensive development path focusing on breakthroughs in core material research and system integration innovation, supported by precise overseas patent portfolio development, in-depth international R&D collaboration, and accelerated infrastructure and airworthiness system support. Looking ahead, continuous breakthroughs in key technical bottlenecks, industrial ecosystem construction, and participation in international rule-making will strongly promote China"s ability to secure a technological high ground in this cutting-edge field and achieve commercial implementation
    Research on analytical method for ice detector installation location
    ZhaoJingyu, ShenXiaobin, LinGuiping
    Available online:October 08, 2026, DOI:
    [Abstract] (26) [HTML] (0) [PDF 6.47 M] (0)
    Abstract:
    The installation location of an ice detector is crucial for the accurate measurement of aircraft icing information and ensuring flight safety. This study defines a spatial water droplet collection efficiency utilizing the Eulerian approach for the droplet field, considering the effects of liquid water content (LWC), droplet velocity, and the impact angle on the detector probe. An analytical method using this efficiency to determine the optimal installation location for ice detectors is established. Using a two-dimensional NACA0012 airfoil as the test object, the differences between the spatial water droplet collection efficiency method and the traditional LWC method for installation location analysis are compared. The effects of parameters on spatial collection efficiency and the feasible installation range for the detector are also investigated. The results demonstrate that the established spatial water droplet collection efficiency analysis method reduces the average error compared to actual conditions, thereby providing a more accurate description of the water droplet collection state at the detector probe. Furthermore, the feasible installation range for the detector is influenced by parameters such as inflow velocity, water droplet diameter, angle of attack, and installation angle. This research contributes to the design of ice detection systems and provides significant guidance for enhancing aircraft flight safety.
    Effect of fin-boat tail interference on the drag of projectile and rocket aircraft
    LIU Le, DOU Zihao, CHEN Xiaolong
    Available online:October 08, 2026, DOI:
    [Abstract] (15) [HTML] (0) [PDF 9.38 M] (0)
    Abstract:
    The boat tail configuration is an effective measure for reducing the base drag of aircraft. Since tail fins are frequently positioned at the rear end, they may interfere with the base flow. To investigate the interference effects of tail fins on the boat tail, numerical simulation was employed to study an aircraft equipped with tail fins and boat tail. The analysis focused on the influence of different tail fin installation positions on aircraft drag, as well as the variation in drag when modifying the boat tail shape under the interference of the tail rudder. The results demonstrate that as the tail fin is moved rearward, the total aircraft drag gradually increases. When increasing the round radius at the boat tail corner while moving the tail rudder rearward, the aircraft drag can be reduced. However, when increasing the boat tail angle under the same rearward movement of the tail rudder, the aircraft drag exhibits a trend of first decreasing and then increasing.
    Research on Design and Service Performance Evaluation of Aircraft Linkage Bay Door Mechanism
    Xiao Yuewei, Liu Hongwei, Wang Minghe, WangGang, ZengCen
    Available online:October 08, 2026, DOI:
    [Abstract] (29) [HTML] (0) [PDF 1.87 M] (0)
    Abstract:
    To meet the requirement of high maneuverability, the weapon systems of modern fighter jets generally adopt a linkage mechanism design. Traditional rigid bay doors often exhibit poor overlap tightness with the fuselage. To address this, modern fighter aircraft weapon compartments require follow-up bay doors with a pre-deformation design. This ensures a tight overlap with the fuselage when closed, thereby guaranteeing airtightness and surface flatness. This paper presents a parametric model of the pre-deformed follow-up bay door for linkage bay door mechanism of F-22. To evaluate its sealing and closing performance under service conditions, a flexible multibody dynamic model of the bay door mechanism was established. The effects of different flight speeds and pre-deformation amounts on the closing performance were analyzed, and the laws governing the flattening rebound load of the pre-deformed follow-up bay door as well as the overlap accuracy between its edge and the fuselage wall panel were obtained. The numerical simulation results show that: 1)The pre-deformation design must generate sufficient resilience to counteract the aerodynamic suction force acting on the bay door after closure; 2)The pre-deformation flattening process induces stress concentration at the hinge of the bay door mechanism, which requires reinforcement consideration in the design.
    Study on the Process of Deposition of Inner Cavity Coating on Blades by Pulsed CVD
    lizhijian, liusihang, songguihong, yuhaojun, wuqiang, zhanglina
    Available online:October 08, 2026, DOI:
    [Abstract] (38) [HTML] (0) [PDF 8.64 M] (0)
    Abstract:
    The deposition coating on the inner surface encountered significant difficulties due to the constraints on mass transfer. In this paper, based on an independently developed pulsed process, the aluminide coatings in the complex inner cavity surface of the turbine vanes of the gas turbine engine (K452 alloy) was prepared by a novel CVD pulsed aluminizing equipment. The microstructure, elemental distribution and phase composition of the aluminide coatings were studied by SEM, EDS and XRD. The mechanism of pulsed pressure aluminizing was discussed. The results showed that the pulsed process realized the forced transport of reactive gas in the complex inner cavity through the alternating positive and negative pressure. The coating thickness is 22.5–47.5 μm under positive-negative pressure pulse alternation process, completely covering different spatial geometric regions in the complex inner cavity. The coating has a typical double-layer structure, with the outer layer being a single dense β-NiAl phase (Al content 24.08 wt.%) and the inner layer being γ"-Ni?Al and refractory metal precipitates (Al content 8.21 wt.%). The CVD pulsed aluminizing thermal process had no significant influence on the high-temperature tensile and creep properties of the substrate material. This technique process enhanced the transport of reactive gas and the diffusion behavior of aluminum atoms through dynamic pressure regulation, providing a new approach for the engineering application of protective coatings in the inner cavity of the aero-engine blades.
    Advances and Future Prospects of Advanced Bio-Inspired Flow Technologies in Aerospace Applications
    Bao Han, Yu Jialei, Wang Qimin, Xie Ruixuan, SONG BIFENG
    Available online:September 24, 2026, DOI:
    [Abstract] (67) [HTML] (0) [PDF 17.87 M] (14)
    Abstract:
    Birds in nature possess remarkable flight capabilities. With the continuous advancement of bionics, learning from birds to develop advanced flow control technologies has become a critical approach to enhancing the aerodynamic efficiency and flight performance of future aircraft. This paper focuses on analyzing flow control strategies in flying organisms, specifically organizing and summarizing the aerodynamic mechanisms of four types of small-scale feather structures in birds. These mechanisms are clarified in terms of lift enhancement and drag reduction, separation control, and noise suppression. Subsequently, we review the progress in applying bio-inspired flow technologies to aerospace engineering, including explorations of bio-inspired flapping-wing aircraft and various small-scale flow control structures. Finally, we outline future directions for bio-inspired flow technologies, providing insights to facilitate their eventual large-scale engineering applications.
    Data-Driven Intelligent Design of Light Alloys: Methods, Applications, and Prospects
    Li Tianhao, Yan Zhini, Xie Haoyang, Rao Ziyuan, Zeng Xiaoqin
    Available online:September 24, 2026, DOI:
    [Abstract] (69) [HTML] (0) [PDF 1.31 M] (19)
    Abstract:
    Light alloys, which refer to alloys primarily composed of magnesium, aluminum, titanium, or a combination thereof, are characterized by low density and high strength. They are widely used in aerospace. Traditional try-and-error design methods for light alloys are limited by factors such as excessive reliance on intuition, lengthy development cycles, and high costs. More advanced approaches, such as computational materials engineering, also face drawbacks, including high computational demands and insufficient accuracy. With the advancement of computer processing power and algorithms, artificial intelligence methods are gradually becoming an essential compo-nent in light alloy design due to their powerful data processing capabilities and reliable accuracy. This paper first outlines the fundamen-tal processes and algorithms of data-driven methods. It then focuses on the typical applications of these methods in predicting the me-chanical properties and inverse design of Aerospace light alloys. Finally, it addresses current challenges, including the incompleteness of inverse design, limited extrapolation capability, and difficulties in integrating domain knowledge, and explores the potential for future integration with large language models (LLMs) in the field.
    Research progress on release and separation technology for air-launched rockets
    HONG Weijiang, GU Rui, LI Peibo, AN Bin, SUN Ming-bo, SUN Yongchao, YANG Kai
    Available online:September 24, 2026, DOI:
    [Abstract] (50) [HTML] (0) [PDF 19.82 M] (18)
    Abstract:
    Separation and release constitute a critical phase in the mission profile of air-launched rockets, directly determining mission success. Through years of development, pylon-mounted and internally-carried approaches have emerged as two primary technical routes. To compare their characteristics and applicability, and to provide guidance for practical engineering development, this paper first reviews the evolution of air-launched rocket systems. A comprehensive survey is then presented from four perspectives：separation and release mechanisms, separation trajectories, trajectory prediction methods, and ground and flight testing. Relevant engineering applications and recent research advances are introduced. Comparative analyses are conducted to illustrate the advantages and limitations of different technical approaches, along with summaries of their suitable application scenarios. Finally, toward future scaled deployment, several promising research directions are identified, such as the design of highly reliable and lightweight separation systems. Recommendations for air-launched rockets development in China are also provided, which may serve as a reference for decision-making and engineering implementation regarding separation and release technologies.
    The influence of hydrophobic coating above riblets on the linear development of Tollmien-Schlichting waves
    Zhang ZhaoPeng, Ye ZhengYin, Li DiChen, Wu KangLing, Ye Kun
    Available online:September 24, 2026, DOI:
    [Abstract] (54) [HTML] (0) [PDF 6.60 M] (19)
    Abstract:
    The use of riblets is currently the most practically applicable method for reducing surface drag in engineering. However, in practical applications, riblets are susceptible to contamination. Covering riblets with nano-scale hydrophobic coatings holds promise in alleviating this problem to a certain extent. To simulate the influence of hydrophobic coatings on flow with Navier-Stokes equation, a slip velocity boundary is adopted. The slip length Ls (0.01≤Ls≤0.05) is used to characterize the slip properties of hydrophobic coatings at different scales. Based on the direct numerical simulation method, this research systematically investigates the influence mechanism of hydrophobic coatings on the flow stability of riblet surfaces. Numerical results show that in the linear stability stage of the flow, the introduction of the hydrophobic coating significantly alters the boundary layer flow characteristics. Using the turbulent kinetic energy transport equation, this study reveals that the hydrophobic coating reduces the growth rate of turbulent kinetic energy by inhibiting the energy growth of both the production and dissipation of turbulent kinetic energy on the riblet surface. Consequently, this suppression effect shrinks the linear instability region of Tollmien-Schlichting waves, and the suppression effect strength with an increase in slip length. Furthermore, the slip boundary condition significantly weakens the gradient distribution of the dissipation of turbulent kinetic energy in the spanwise direction.
    Research on Digital Twin-Based Monitoring System for Aero-Engine Blade Manufacturing Workshop
    Wang Jun Jie, Zhang Hai Jun, Huang Jin Han, Huang Yi Liang, Liu Quan Wei, Peng Xi Ying, Wang Chao Shuai, Jia Chao Yang
    Available online:September 24, 2026, DOI:
    [Abstract] (64) [HTML] (0) [PDF 6.22 M] (14)
    Abstract:
    To address the challenges of low transparency in production processes and unstable grinding quality in traditional aero-engine blade manufacturing workshops, this paper investigates the application of digital twin and Open Platform Communications Unified Architecture (OPC UA) technology in workshop monitoring systems, while integrating machine learning algorithms to predict blade processing quality. First, based on the five-dimensional digital twin model, an overall framework for a digital twin-based monitoring system tailored to aero-engine blade processing workshops is constructed, establishing the technical roadmap for digital twin workshop design. Then, detailed discussions are presented on the construction of equipment digital twins, heterogeneous multi-source data acquisition and transmission via OPC UA, bidirectional virtual-physical control of workshop equipment, and prediction of blade processing quality. Finally, the proposed digital twin-based workshop monitoring system was implemented and tested in an actual aero-engine blade manufacturing workshop, validating the feasibility and effectiveness of the developed system.
    Heuristic Greedy Selection Inspection and Dispatch Method Based on CP-SAT
    LV Wei, ZHANG Qiang, DONG Yiwei
    Available online:September 24, 2026, DOI:
    [Abstract] (60) [HTML] (0) [PDF 620.91 K] (21)
    Abstract:
    To address the lack of personnel workload balance and the limited availability of empirical validation in aircraft heavy maintenance task assignment, this study proposes a task scheduling method that integrates a heuristic greedy selection strategy with a CP-SAT solver. The heavy maintenance cycle is first discretized into sequential time stages, within which precise execution time windows are defined. On this basis, a constraint satisfaction model is formulated that jointly incorporates rigid operational constraints and personnel workload balancing objectives. Leveraging the efficient constraint propagation and search capabilities of the CP-SAT framework, the proposed approach enables automated, end-to-end assignment from maintenance task cards to personnel. Validation in an operational production environment demonstrates that the system effectively reduces the standard deviation of personnel workloads, leading to a marked improvement in resource utilization and dispatch stability. The method has been successfully deployed on a commercial aircraft heavy maintenance production line, confirming its robustness and practical engineering value under real industrial conditions.
    MBSE Architecture of SINS/BDS Integrated Navigation System for Civil Aircraft and Route Operation Simulation
    LIU Riuhua, ZHANG Xiang
    Available online:September 24, 2026, DOI:
    [Abstract] (74) [HTML] (0) [PDF 5.10 M] (17)
    Abstract:
    Insufficient requirement traceability, performance validation, and inconsistent RNP information flow in traditional document-based designs hinder the navigation accuracy of domestic civil aircraft during en-route operations. In contrast to existing research focusing on terminal area RNP?1, this paper introduces a model?driven architecture design method based on the MagicGrid methodology to develop a multi?level system architecture model that spans requirements analysis, behavior modeling, structural design, and parametric simulation, thereby satisfying the en?route RNP?2 operational requirements. Focusing on the SINS/BDS loosely coupled navigation system, a co-simulation approach using the Systems Modeling Language (SysML) and MATLAB is proposed. This establishes an end-to-end MBSE implementation framework from requirements analysis to simulation validation, offering a reusable methodology and practical reference for designing complex civil aircraft navigation system architectures. Simulation results demonstrate that the proposed method effectively enhances requirements traceability and dynamic performance validation, ensuring that the integrated navigation system meets RNP 2 requirements during en-route operations.
    Research on Adaptive Feedforward-Feedback Compound Control Method for Variable-Pitch Propeller Speed Under Gust Disturbances
    sunhe, suotao, liuchuanchao
    Available online:September 09, 2026, DOI:
    [Abstract] (99) [HTML] (0) [PDF 2.60 M] (61)
    Abstract:
    The constant-speed control of variable-pitch propellers directly affects the power stability of aircraft and the service life of transmission systems. External gust disturbances are prone to cause speed deviations, and the conventional "immediate pitch adjustment" strategy will aggravate mechanism wear. This paper proposes an adaptive constant-speed control strategy based on disturbance source identification. By distinguishing between engine power changes and sudden aerodynamic load changes, it realizes slow pitch movement under gust conditions and active pitch adjustment when power changes. A coupled dynamic model of variable-pitch propeller-engine considering gusts is established, and a composite controller integrating extended state observer, feedforward compensation and variable-gain PI feedback is designed. The system stability is verified by Lyapunov theory. Sim-ulation and ground experiment results show that the proposed strategy and model are feasible and effective. While ensuring the steady-state accuracy of rotational speed, they significantly reduce the action frequency of the pitch actuator, providing an effective solution for improving the stability and service life of the variable-pitch propeller system.
    The study on control surface flutter characteristics in large civil aircraft
    yangshifu, LI Junlong, YANG Rong, ZHOU Lisheng
    Available online:September 09, 2026, DOI:
    [Abstract] (95) [HTML] (0) [PDF 2.84 M] (45)
    Abstract:
    Large civil aircraft typically use mass-imbalanced and irreversible hydraulic power-assisted control systems, and control surface flutter is a key aeroelastic instability issue that must be specifically addressed in aircraft design. By considering structural model adjustments and aerodynamic distribution characteristics, and performing precise theoretical model calculations, ensure that the aircraft"s control surfaces do not encounter flutter problems. Using the control surface flutter design of a certain aircraft as a case, based on aerodynamic correction theory in flutter analysis and the shape interpolation techniques, using pressure measurement wind tunnel test data, the control surface aerodynamic model is modified to study the effects on control surface flutter characteristics. Numerical examples indicate that after applying external aerodynamic modifications, the coupling type of the control surface flutter modes changes, transforming from an elevator divergence mode to a wing antisymmetric bending-torsion mode; using the control surface aerodynamic modification design methods and requirements discussed in this paper can provide a reference for the precise design of control surface flutter characteristics.
    Study on the implementation of aircraft structure integrity program standards
    sun wei, shu cheng hui, yang wei ping, liu xiao dong, dai ya guang, wang xin hao
    Available online:September 09, 2026, DOI:
    [Abstract] (104) [HTML] (0) [PDF 1.34 M] (53)
    Abstract:
    GJB 775A-2012 Military Aircraft Structural Integrity Program was revised with reference to the U.S. military standard MIL-STD-1530C (2005). The U.S. military further revised and released Revision D in 2016, and in recent years, the domestic demand for revising GJB 775A has become increasingly urgent.This paper interprets the connotations of aircraft structure integrity and the Aircraft Structure Integrity Program (ASIP), clarifying the significance and core technical requirements of ASIP. On this basis, it sorts out the development and implementation status of ASIP in the U.S. military and China. Taking the typical implementation process of ASIP in aircraft models as an example, the existing problems and the demand for standard revision are analyzed from three dimensions. A scenario model for the development and application of China’s ASIP is constructed, and the "requirement-standard correlation network diagram" method based on standard views is adopted to clarify the transmission path from application requirements to standard clause revisions. Finally, 23 improvement measures divided into 6 levels for GJB 775A-2012 and suggestions for the formulation and revision of supporting standards are proposed, laying a foundation for the revision of GJB 775A-2012.
    Optimization Design of Modular BWB UAVs with Multi-Airfoil Combination
    Li Jun, Huang Weihuang, Li Xihuan
    Available online:September 09, 2026, DOI:
    [Abstract] (126) [HTML] (0) [PDF 2.15 M] (49)
    Abstract:
    The Blended Wing Body (BWB) layout has broad application prospects, but there exists a coupled contradiction between its aerodynamic efficiency and longitudinal control performance. To further improve the lift-drag characteristics and longitudinal trim capability of BWB unmanned aerial vehicles (UAVs), a design concept of multi-airfoil combination is adopted based on the spanwise regional characteristics. Considering both planform parameters and airfoil parameters, the Class Shape Transformation (CST) method is adopted to realize the parametric representation of the entire aircraft configuration. The computational fluid dynamics (CFD) method based on the Reynolds-Averaged Navier-Stokes (RANS) equations is used to calculate the aerodynamic performance. The Radial Basis Function (RBF) surrogate model combined with the Non-dominated Sorting Genetic Algorithm II (NSGA-II) multi-objective genetic algorithm is selected to carry out the optimization design. Optimization results show that the center body airfoil section exhibits a more obvious characteristic of leading edge loading and trailing edge reflexing, while the outer wing airfoil have a flatter lower surface, which meets the design requirement for high lift-drag ratio. Under the condition of satisfying design constraints, the lift-drag ratio of the UAV is increased by 18.24%, and the pitching moment coefficient is increased from -0.0216 to -0.0009, indicating a significant improvement in pitching trim capability.
    Research on Online Measurement Technology for Particle Pollutants in Fuel
    li yu, zhang jia hao, yang hao zong, xu ri xin, wang fa quan, zhou wu
    Available online:September 09, 2026, DOI:
    [Abstract] (57) [HTML] (0) [PDF 3.29 M] (39)
    Abstract:
    To address the difficulty of online monitoring caused by the diverse types and wide size distribution of contaminants in fuel system anti-contamination tests, this study proposes an online measurement method for contaminant mass concentration in fuel based on spectral extinction. The method establishes a theoretical relationship between the measured spectral extinction value ln(I?/I) and particle mass concentration using the Lambert–Beer law, followed by experimental calibration to obtain a linear model between spectral intensity and mass concentration. The calibration was then validated, and the proposed method was further applied to industrial field tests, where its performance was compared with that of the membrane gravimetric method. The results show that the relative measurement error of the spectral extinction method does not exceed ±5% during calibration, and its relative error remains within 10% in industrial field applications. The proposed method enables accurate online measurement of contaminant mass concentration in fuel and provides an effective technical approach for fuel contamination evaluate.
    Research on Competency Evaluation Method for Medium and Long-Range UAV Flight Controllers
    liubang, YUAN Changsheng, YIN Shaofeng, XIE Zhenxuan, FU Saiqi, YAN Peng, HU Jingzhi, XUE Xiaofeng
    Available online:September 09, 2026, DOI:
    [Abstract] (94) [HTML] (0) [PDF 691.50 K] (45)
    Abstract:
    To address the lack of dedicated quantitative tools for assessing the competency of medium- and long-range unmanned aerial vehicle pilots, a comprehensive evaluation model integrating Game Theory Combined Weighting (GTCW) and Fuzzy Technique for Order of Preference by Similarity to Ideal Solution (F-TOPSIS) is proposed. Through systematic job analysis, a competency evaluation system with six primary indicators and 24 secondary indicators, strongly oriented towards military tasks, was established. The study uses game theory to coordinate subjective and objective weights, obtaining combined weights that reflect both experiential preferences and data characteristics; and employs the F-TOPSIS method to transform expert qualitative evaluations into sortable quantitative results. Case validation demonstrates that this model not only enables objective evaluation ranking and grading, but also accurately identifies weak links in individual competency structures, thus extending the evaluation function from mere quantitative scoring to structured diagnostic analysis. This study provides a more advanced quantitative decision-making tool for the scientific selection and precise training of flight controllers.
    Solid Oxide Fuel Cell/Gas Turbine Hybrid Power Systems and Engineering Technology
    Peng Feiyang, Gao Zibo, Lei Sheng, Li Yuansheng, He Changxiang, Zhang Haibin, Li Zhi-peng
    Available online:August 25, 2026, DOI:
    [Abstract] (116) [HTML] (0) [PDF 1.17 M] (59)
    Abstract:
    Solid Oxide Fuel Cell/Gas Turbine Hybrid Systems (SOFC/GT) are regarded as a significant development direction for distributed power generation due to their high efficiency and low emissions. This review summarises the operating principles, modelling and simulation methods of SOFC/GT systems, and explores the impact of different SOFC/GT system architectures on performance. Results indicate that pressurised SOFC/GT system typically exhibit higher efficiency, while internal reforming facilitates system simplification, and external reforming provides stronger fuel diversity and load fluctuation adaptability. Furthermore, SOFC/GT systems can achieve further efficiency gains and expanded application scenarios through combined cycle operation. Finally, this review discusses the application prospects and key challenges facing SOFC/GT systems.
    Aerodynamic optimization technique for ducted variable pitch propellers at multiple design points based on the momentum source method
    Ruan Lingfeng, Wang Haifeng, Du Chenxi
    Available online:August 25, 2026, DOI:
    [Abstract] (91) [HTML] (0) [PDF 7.16 M] (39)
    Abstract:
    Electric Vertical Take-off and Landing (eVTOL) aircraft equipped with ducted propellers operate over a wide range of inflow velocities during missions. A fixed-pitch design makes it difficult to simultaneously satisfy the thrust requirements in hover and the efficiency requirements in forward flight. To address this issue, a multi-design-point aerodynamic optimization method for ducted variable-pitch propellers based on the momentum source method is proposed. A fast propeller thrust and torque calculation model based on standard strip analysis is established, together with a rapid duct aerodynamic calculation model using a momentum-source-based CFD approach. By parameterizing the propeller and duct, a multi-design-point optimization framework is constructed and applied to the aerodynamic optimization of a 3.6m ducted propeller. The results show that the momentum source method calculates total thrust and torque with errors of less than 10%, meeting the accuracy requirements for optimization. After optimization, the total thrust at 0 m/s inflow velocity increases by 17.54%, while the aerodynamic efficiency at inflow velocities of 10 m/s and 15 m/s improves by 2.85% and 0.26%, respectively, effectively enhancing both hover and forward-flight performance of the eVTOL aircraft.
    Numerical analysis of directional static stability for multi-vertical-tail turboprop aircraft
    gaokun, weimeng, TYANG ZHIKANG, CHENG ZHIHANG, WEN QING
    Available online:August 25, 2026, DOI:
    [Abstract] (117) [HTML] (0) [PDF 4.50 M] (75)
    Abstract:
    A study was conducted on the yaw characteristics of a twin-engine turboprop aircraft with a multi-vertical-tail configuration during go-around conditions. The unsteady Reynolds-averaged Navier–Stokes equations were solved, and the sliding mesh technique was applied to simulate propeller rotation. The reliability of the numerical method was verified through comparison with wind tunnel test data. The effects of sideslip angle, angle of attack, and single-engine inoperative conditions on the yaw characteristics of the fuselage, vertical tails, and the entire aircraft were investigated. The results showed that, under small negative sideslip conditions, the yaw static stability of the right outboard vertical tail was weak, while the fuselage exhibited strong yaw static instability, leading to a reduction in the yaw static stability of the entire aircraft. As the angle of attack increased, the yaw static stability of the vertical tails changed little, whereas the fuselage yaw static instability became stronger, resulting in a further decrease in the yaw static stability of the entire aircraft.
    Vibration Analysis and Test Method Research of Aero engine External Pipeline System
    Wang Kai, LI WEI, JIN HAILIANG, ZHAO WEI, WAGN QINGPING, ZHAGN WEIFENG, HOU YANCHEN
    Available online:August 25, 2026, DOI:
    [Abstract] (197) [HTML] (0) [PDF 3.72 M] (48)
    Abstract:
    At present, the accuracy and efficiency of finite element analysis of aero engine external pipeline system is insufficient, and the traditional mode hammering test has limitations. In the aspect of simulation, how to improve the efficiency and accuracy of modeling through the selection and use of finite element modeling methods and reasonable connection building is studied, and different finite element modeling elements are used to discrete them. Based on the obtained metal pipeline mode data, the dynamic models of different elements are established based on the principle of finite element method and the two degree of freedom vibration model of the structure; The swept frequency vibration test technique is studied in the experiment. by comparing with the results of the mode analysis, the ability of obtaining the resonance frequency of the pipeline system rapidly and accurately is verified. Modal data of the pipeline are determined by shaking table test and verified by mutual reference, in which the error of natural frequency of simulation and test is no more than 10%, and the frequency response functions of both agree well. The rig test overcomes some limitations of traditional mode hammering method, and the effectiveness of finite element model is verified by shaking table test. The most accurate and efficient unit use and connection method in the mode analysis of pipeline system is determined,and the dynamic model of metal pipeline can be used in the engineering practice of vibration characteristics analysis of pipeline system.
    Design of a VPX-Based Airbone Mission Management Computer for UAVs
    PI zucheng, ZU jingwan, LI kaixuan, TIAN cong, Ma chunrong
    Available online:August 25, 2026, DOI:
    [Abstract] (97) [HTML] (0) [PDF 870.33 K] (70)
    Abstract:
    With the development of unmanned aerial vehicles (UAVs) toward intelligence, their flight missions have significantly higher requirements for levels of automation and intelligence. These missions not only need to support real-time processing of multi-task data and collaborative control of multi-sensors but also require the construction of a basic computing platform for multi-UAV collaboration and system-level collaboration. To address issues existing in current mission management computers, such as computing power bottlenecks, limited bus bandwidth, and insufficient flexibility of software architecture, this paper designs an onboard mission management computer for UAVs based on the VPX architecture by integrating mainstream embedded computer technologies. In terms of hardware, the 3U VPX architecture is adopted, equipped with modules including main control, intelligent processing, high-speed/low-speed processing, storage, and network switching. A star-shaped communication topology is established via SRIO and Ethernet to achieve high-bandwidth data transmission. In terms of software, a layered and modular design is adopted, with ZMQ and FlatBuffer as communication middleware. Combined with a distributed deployment strategy, this design enhances the openness and flexibility of the architecture; meanwhile, system reliability is ensured through health management and fault-tolerance mechanisms. Verification through engineering practice shows that this computer possesses intelligent processing capabilities, effectively improving the computing power and high-bandwidth data processing capacity of the mission management system. Additionally, it features flexible hardware-software adaptation and can meet the stable operation requirements of the mission system for a specific type of UAV.
    Research on the Control Technologies of Tiltrotor Pylon Conversion Actuation
    CAO Wei, Li Hailin, Yan Suwen, Zhu Mingjun, Si Jun, Zhu Shaokang
    Available online:July 31, 2026, DOI:
    [Abstract] (168) [HTML] (0) [PDF 2.46 M] (37)
    Abstract:
    This study focuses on the nacelle tilting actuation system, a core subsystem of tiltrotor aircraft, to improve control stability during the transition between helicopter mode and fixed-wing mode in tiltrotor aircraft. First, the actuation architecture and the principle of mode transition are introduced. Subsequently, the phenomena, causes, and suppression strategies of force fighting between dual systems in the active-active operating mode, as well as the asynchronization of left and right nacelles, are then analyzed with emphasis. Based on the actuation system modeling, the force fighting and synchronization control strategies are incorporated into the "position-velocity" dual-loop control algorithm. Finally, a complete servo control simulation model is constructed using Simulink and experimentally verified through a prototype. The dual-loop servo control strategy combining position loop and speed loop effectively ensures position accuracy and smooth motion of the single pylon. Under active-active operation mode, the introduction of a force equalization control algorithm can effectively suppress force fighting between the two systems. Between the left and the right pylon conversion actuation systems, the servo control strategy based on position equalization and speed equalization can effectively guarantee synchronization in position and stability in speed. This study provides an effective solution to the high-reliability control challenge during mode transition of tiltrotor.
    Development characteristics and enlightenment of aeroengine in the U.S.
    LINLIN, CHENG Long, WANG Jiamei
    Available online:July 31, 2026, DOI:
    [Abstract] (212) [HTML] (0) [PDF 2.17 M] (67)
    Abstract:
    This paper reviews the development history of U.S. aeroengine since the 1950s, outlines its current status, and identifies three key characteristics that have sustained America"s leadership in this field: First, continuous technological research programs such as ATEGG and IHPTET have driven rapid engine advancement. Second, persistent focus on core engine technology research and validation—for example, the F101 core engine spawned multiple derivative aeroengine series. Third, the establishment of advanced organizational management mechanisms, such as adopting phased, categorized management and dynamically adjusted procurement strategies, which effectively promoted high-quality and efficient engine development. Based on the above analysis, this paper proposes insights and recommendations for China"s independent development of aeroengines, including strengthening national strategic guidance, establishing sustained and stable pre-research investment and core engine research and development mechanisms, building an efficient and collaborative scientific research management system, and firmly securing autonomy over core technologies.
    Review of control techniques for structurally damaged aircraft
    Hao Peicheng, Han Qing, Cai Linxuan
    Available online:July 31, 2026, DOI:
    [Abstract] (118) [HTML] (0) [PDF 5.98 M] (55)
    Abstract:
    Structural damage to the shape of an aircraft will cause irreversible changes to its aerodynamic characteristics and mass-inertia characteristics, which will have a serious impact on flight safety and mission execution. To support the design and research of highly reliable flight control systems, it is particularly important to systematically summarize the current research status of dynamic modeling and control strategies for structurally damaged aircraft. This article systematically reviews the research progress of key technologies in this field. By analyzing the types of structural damage and their dynamic effects, the applicability of non-centroid and centroid modeling methods in scenarios such as centroid shift and changes in the inertia matrix was summarized. The research progress on the aerodynamic effects and control strategy design for damaged aircraft is reviewed; The key technologies and existing problems in the research field of control strategies for structurally damaged aircraft were analyzed, and the development trends in this field in directions such as intelligent control and flight tests were prospected. The technical analysis framework and trend judgment formed by the research can provide theoretical support and methodological reference for the control strategy research of structurally damaged aircraft
    Orthogonal Experimental Study on Ultrasonic Assisted Grinding of SiCf/SiC Ceramic Matrix Composites
    XIEZHIQIANG, DENGJUAN, ZONGCHUANHONG, LIUYU, MARONGMAN, BISHUAI, HUYUE, JIANGRUISONG
    Available online:July 31, 2026, DOI:
    [Abstract] (196) [HTML] (0) [PDF 5.96 M] (64)
    Abstract:
    SiCf/SiC ceramic matrix composites exhibit excellent properties such as high specific strength, high-temperature resistance, and corrosion resistance, making them highly promising for aerospace applications. However, SiCf/SiC composites are typically anisotropic and difficult to machine. To address common defects during grinding—such as fiber pull-out, matrix damage, and porosity—a systematic orthogonal test of ultrasonic vibration-assisted grinding was conducted on SiCf/SiC composites using a brazed diamond grinding head. Surface roughness (Sa) was used as the characteristic parameter to evaluate the surface quality of SiCf/SiC composite materials. The results of the orthogonal test were subjected to range analysis and variance analysis. It was found that ultrasonic-assisted grinding can significantly reduce the surface roughness of SiCf/SiC composites and improve surface quality. The results indicate that the degree of influence of the four variable factors on roughness is as follows: cutting depth > feed rate > ultrasonic amplitude > linear velocity. However, the analysis of variance shows that the four factors are independent of each other and that there is no significant difference among them.
    Experimental and numerical simulation study of aero-engine compressor casing containment
    Cao Miao, Xu Jian, Liu Zongxing, Gan Yuxi, Sheng Jiacheng, Li Yulong, Liu Jun
    Available online:July 31, 2026, DOI:
    [Abstract] (218) [HTML] (0) [PDF 7.78 M] (54)
    Abstract:
    Blade off events may occur due to high cycle fatigue, foreign object damage or overheating during the aro engine operation. The subsequent released high energy fragments can perforate the casing, leading the uncontainment accidents. This paper focuses on the high-pressure compressor casing to systematically study the containment process of casing and blade through combined experiments and numerical simulations. The containment tests were carried out on a vertical rotor tester and a corresponding finite element model was established in LSDYNA. The simulation results agreed well with test data, revealing two major impacts between the released blade and casing, with the second impact—caused by the blade platform—being particularly critical. Parametric analyses examined the effects of release speed, casing thickness, and multi-blade interaction. The results show that as the increase in released speed, the fracture mode of the casing transitions from bulging deformation to irregular tearing. The energy absorption of the casing increases as the casing thickness decreases, and when the absorbed energy reaches the maximum value, the casing fractured, leading to a decline in containment capacity. The trailing blades can alter the trajectory of the released blade and continuously supply kinetic energy to it. The findings provide valuable guidance for optimizing the design of compressor casings.
    Safety analysis and testing of power performance for tons-class tiltrotor eVTOL
    JING Yuyang, ZHANG Pengfei, DAN Min, SUN Shuang, ZHAO Ziqing
    Available online:July 03, 2026, DOI:
    [Abstract] (303) [HTML] (0) [PDF 3.57 M] (189)
    Abstract:
    The power battery is a critical core component that determines the takeoff weight and range of electric vertical take-off and landing (eVTOL) aircraft. Accurately describing its power supply characteristics is essential for the safety design of the aircraft. This paper takes a typical tiltrotor eVTOL as the research subject and establishes a power demand model for the electric propulsion system that comprehensively considers multiple safety constraints, including flight duration, state of charge (SOC), and discharge rate, based on its mission profile. Additionally, a battery power supply model incorporating voltage dynamic characteristics is developed, followed by an analysis of the severity of various safety constraints under different battery energy densities. Finally, the study conducts system-level experimental validation through a multi-propeller electric propulsion system integrated testing platform. The results indicate that for the 2-ton-class eVTOL example studied in this paper, the severity of the three safety constraints is closely related to battery energy density—when the energy density exceeds 340 Wh/kg, the flight duration constraint is the most stringent; whereas below this threshold, the discharge rate constraint becomes the dominant factor. This research can provide valuable references for the safety design and reliability analysis of electric propulsion systems in tiltrotor eVTOLs.
    Research on Lift Enhancement Scheme with surface-normal jet for Flying-Wing Aircraft
    ZhangWeiyuan, SHI ZHIWEI, ZHANG WEILIN
    Available online:July 03, 2026, DOI:
    [Abstract] (259) [HTML] (0) [PDF 1.41 M] (57)
    Abstract:
    Flying-wing aircraft generally suffer from low maximum lift coefficients and short tail arms, while conventional lift-enhancement methods such as trailing-edge blowing or blown flaps incur large trim penalties and limited net lift increment. To address this issue, a surface normal jet scheme on the lower wing surface is proposed to maximize net lift increment under pitch-moment balanced condition. CFD simulations on the NACA 0012 airfoil were performed to evaluate aerodynamic effects of jet position, slot width, and momentum coefficient. Symbolic regression was then applied to construct an accurate surrogate model for lift and pitching-moment increments. Based on this, a longitudinal aerodynamic increment model for a flying-wing UAV was established under trim constraints. Results indicate that elevator compensation for the jet-induced nose-down moment reduces part of the gain, with net lift determined by the combined effects of jet and control surface. The optimal slot lies at 80–90% chord, improving efficiency by over 5% compared to trailing-edge jets.
    Determination of Maximum Sink Speed for Land-Based UAVs Based on Measured Data
    ZHANG Yujie, ZHAO Yingjian, SUN Renjun, LIU Zhe
    Available online:July 03, 2026, DOI:
    [Abstract] (142) [HTML] (0) [PDF 641.73 K] (134)
    Abstract:
    The maximum sink speed is a critical parameter affecting the aircraft"s landing load and landing gear design. Two methods based on measured sink speed data were established to determine the maximum sink speed of an aircraft. One is the normal one-sided tolerance upper limit method and the other is the prediction method based on Pearson type III distribution. Additionally, the theoretical justifications were provided for the mean amplification factor and standard deviation amplification factor. The accuracy of the above methods was evaluated by using sink speed data from literatures. The relative errors between the maximum sink speed obtained by the normal one-sided tolerance upper limit method and the given values in the literature were below 1.71%. Furthermore, the maximum sink speeds for land-based aircraft calculated by the prediction method based on Pearson type III distribution aligned perfectly with the specified standard value. A comparative analysis of the two methods was conducted from three aspects: the input parameters required to calculate the standard deviation amplification factor, the calculation results of standard deviation amplification factor, and the probability distribution of sink speeds. The results indicated that the prediction method based on Pearson type III distribution was more suitable for determining the maximum sink speed of an aircraft. The maximum sink speeds of three types of unmanned transport aircraft were determined by using the prediction method based on Pearson type III distribution. The maximum sink speed ranges were from 2.16m/s to 2.24m/s, which were close to the lower limit specified by airworthiness standards. It showed that reducing the design value of the maximum sink speed for unmanned transport aircraft was feasible.
    Two-Level Modeling of Aircraft Wing Finite Element Analysis and Experimental Verification
    Li Mimi, Wang Xiaoyang, Li Dong, LI LEI
    Available online:July 03, 2026, DOI:
    [Abstract] (222) [HTML] (0) [PDF 1.75 M] (86)
    Abstract:
    The aircraft structure parts are tens of thousands, and the strength analysis is a huge engineering problem. In finite element simulation, computational scale and accuracy are the two core factors determining analysis efficiency. It involves the establishment and simulation analysis of detailed models for wing-fuselage connections, continuous large openings in wing panels. The results show that The two-level finite element modeling of the overall and details can meet the needs of both the overall force transmission analysis and the precise analysis. Solve the problem of computational efficiency and analytical accuracy. This analysis method was validated through experiments on cover plate connections, providing significant reference for multi-scale modeling and analysis of complex aircraft structures.
    Research and Application of Multi-Start-Stop Test Method for Aircraft Brake Control Unit
    renwenjie, HAN Honggang, GUO Yuan, PU Xuebin
    Available online:July 03, 2026, DOI:
    [Abstract] (211) [HTML] (0) [PDF 544.54 K] (91)
    Abstract:
    The Brake Control Unit (BCU) is a core component ensuring aircraft landing safety, and its reliability directly determines the operational stability of the brake system. Aiming at the prominent problems of "zero-hour" installation failure of current BCUs and the difficulty of identifying occasional faults via traditional static testing, this study proposes a customized multi-start-stop test scheme through fault mechanism analysis and system characteristic research. Firstly, a minimum brake system with 1:1 electrical connection is built to accurately reproduce the real working conditions of the aircraft. Secondly, differentiated start-stop sequences and environment combinations are designed according to different fault occurrence timings (power-on inspection, flight parameter inspection, etc.). Finally, a test device with real-time timing-counting-data acquisition functions is developed to form an integrated testing system of "system simulation - sequence control - data interpretation".Engineering verification shows that this method can reduce the "zero-hour" installation failure rate of the Brake Control Unit (BCU) by approximately 50%, effectively filling the gap of traditional testing in fault screening under dynamic conditions and providing key technical support for improving the reliability of aircraft brake systems.
    Multi-swarm Particle Swarm Optimization Algorithm and its Application in Aerodynamic Optimization
    Li Weiming, Liu Libin, QI Jiangjiang, LIU Chuanlei
    Available online:June 24, 2026, DOI:
    [Abstract] (119) [HTML] (0) [PDF 886.77 K] (90)
    Abstract:
    The Particle Swarm Optimization (PSO) algorithm is a heuristic optimization algorithm based on swarm intelligence, featuring strong robustness, easy implementation, and global optimization capabilities. However, for the PSO algorithm with a single inertia weight, there exists a problem that the global optimization ability and convergence efficiency cannot be balanced simultaneously. On the basis of researching and improving the performance of the standard PSO algorithm, this paper expands the algorithm from a single population to multiple sub - populations, proposes a new multi - sub - population collaborative optimization strategy, and designs the Multi - Subpopulation Particle Swarm Optimization (MSPSO) algorithm. To further enhance convergence efficiency and unleash global optimization performance, a new hybrid algorithm combining the simplex algorithm and the multi - subpopulation particle swarm optimization algorithm (SMMSPSO) is proposed. Case studies show that the improved algorithm achieves a good balance between global optimization ability and convergence efficiency. Finally, the improved algorithm is applied to the transonic aerodynamic optimization of airfoils, achieving excellent effects of drag reduction and lift increase: the lift coefficient is increased by 9.7%, the drag coefficient is decreased by 8.1%, and the lift - to - drag ratio is increased by 17.6%.
    Waverider-like Wing Planform Design and Lift Enhancement Efficiency Analysis
    Liu Xiaochi, He Yuelong, Cai Guodong
    Available online:June 24, 2026, DOI:
    [Abstract] (141) [HTML] (0) [PDF 3.90 M] (83)
    Abstract:
    Abstract：Traditional waveriders often suffer from low volume ratio, limiting practical applications. This paper proposes a waverider-like wing design method. By configuring wingtips that conform to the shockwave surface for a given fuselage, local waveriding effects are created at the wings, merging the fuselage"s high-volume characteristics with the wing"s high-lift features to enhance practical utility. It details the design principles, establishes a parametric model for the wing"s planform, and analyzes the impact of key parameters on aerodynamic performance. Results show that altering the leading edge shape while keeping the waveriding area constant barely affects the lift-to-drag ratio improvement efficiency. Extending the trailing edge forward enhances this efficiency. Furthermore, moving the waveriding position forward increases the efficiency. As the wing"s leading edge approaches the shockwave, high pressure concentrates windward, leading to nonlinear lift growth. The trailing edge shape and waveriding position significantly influence longitudinal static stability: trailing edge extension or aft movement of the waveriding point shifts the pressure center backward, improving stability.
    Research on Optimization of Civil Aircraft Maintenance Intervals Based on Multi-Source Data Fusion
    LI Ming, Cai Jing, Wang Zheng Lin, Zhang Yi Xin, Ma Chen Hang
    Available online:June 24, 2026, DOI:
    [Abstract] (265) [HTML] (0) [PDF 3.82 M] (97)
    Abstract:
    With the enhancement of aircraft design reliability, the data available for maintenance interval optimization has become increasingly scarce, exposing the limitations of traditional single?failure data?driven optimization models. Guided by the SASMO method (Statistical Analysis System for Maintenance Optimization), a systematic approach for extracting and processing maintenance item data is developed. This approach applies data mining techniques to operational data to establish a mapping model between operational data and service life data. To mitigate the issue of low model credibility resulting from data scarcity, historical failure data from similar aircraft are incorporated, and a combined fusion method based on multi?source data integration is proposed, offering a novel solution to data?shortage challenges in maintenance interval optimization. Through the analysis of six distinct operational cases, the application process of the new method is elaborated in detail. Results demonstrate that the proposed combined fusion method provides a feasible and effective means for optimizing maintenance intervals under data?scarce conditions. This work presents a new perspective for airline maintenance interval planning and introduces fresh strategies for maintenance decision?making through integrated data analysis.
    Analysis Method for Lightning Attachment Characteristics of Typical Metal Diversion Strips / Carbon Fiber Skin Structure of Aircraft
    SANG Long, XU Xiaomiao, HE Xiangyong³
    Available online:June 24, 2026, DOI:
    [Abstract] (189) [HTML] (0) [PDF 5.10 M] (109)
    Abstract:
    To address the challenge in evaluating lightning protection performance due to the reduced conductivity contrast between carbon fiber reinforced polymer (CFRP) skins and metal diversion strips, this study proposes a novel lightning attachment analysis method based on quasi-dynamic electric field simulation. A needle-plate electrode model compliant with the standard was established, integrating criteria such as electric field breakdown and field intensity priority. This model systematically simulates the electric field distortion during downward leader progression. Experiments utilizing woven CFRP laminates with aluminum diversion strips validated the simulation by varying diverter spacing. Comparing test/simulation results, the research findings indicate that the method accurately predicts attachment points and quantifies a critical spacing (Sc); when the spacing exceeds Sc, the risk of lightning attachment to CFRP increases significantly. This approach provides a reliable tool for the lightning protection design of CFRP aircraft structures.
    Reliability analysis of kinetic accuracy for cargo ramp door aerial opening and closing considering deformation-induced displacement
    Lu Mengzhao, Feng Yunwen, Chen Xianmin, Xue Xiaofeng, Chen Junyu, Zhuo Yi
    Available online:June 24, 2026, DOI:
    [Abstract] (188) [HTML] (0) [PDF 860.89 K] (66)
    Abstract:
    The deformation-induced displacements of the mechanism supports, the manufacturing and assembly errors can easily lead to insufficient kinetic, result in functional failure of the aerial operation, and even compromise mission execution or flight safety. This paper proposes a reliability analysis method for kinematic accuracy of mechanisms within deformation-induced displacement. Based on the aerial operation scenario of the cargo ramp door, the mechanism characteristics considering the displacement are analyzed. Subsequently, using design parameters and the Rodrigues rotation formula, an output response model of the mechanism without the displacement is established. By further analyzing the influence of structural deformation on model parameters, a response model incorporating deformation effects is constructed. Finally, reliability analysis of the mechanism’s kinetic accuracy is carried out. The reliability analysis of kinetic accuracy for the lock drive mechanism is performed based on the Latin Hypercube Sampling (LHS), neglecting the displacements, and the results verify the validity and accuracy of the proposed methodology. The probability of insufficient kinetic increases about 10000 times within the displacements, and the results prove that the displacements significantly interfere with the mechanism"s output response, and the displacements’ impact on the functional and mission-related performance of aerial door systems must be considered.
    Dynamic stability analysis of a scaled flying wing model under different loads
    Guo Zhouyun, zhao ran, Lei Ming, zhan jianning, Wang Shaonan, Wang Ruiwen, Xie Tianyu, Gu Yingsong
    Available online:May 27, 2026, DOI:
    [Abstract] (208) [HTML] (0) [PDF 945.52 K] (91)
    Abstract:
    Solar-powered unmanned aerial vehicles typically employ lightweight and highly flexible wings. After being loaded, the structures are prone to significant deformations, which cause changes in the aerodynamic characteristics of the aircraft and subsequently trigger a series of flight dynamics problems. To study the influence of wing deformation on flight dynamic characteristics, a scaled-down model is designed based on the Helios UAV as the prototype. The bending deformation characteristics of the scaled-down model under different overloads are analyzed by a loosely coupled static aeroelastic analysis, which integrates the vortex lattice method and nonlinear finite element method. Taking the proportion coefficient of the wingtip deformation relative to the half-span length as the control parameter, the variation trend of the moment of inertia of the scaled model under different deformations is analyzed. The aerodynamic derivatives before and after deformation are determined by the vortex-lattice method. The flight dynamic stability analyses are conducted for the scale models under various deformation states based on the linearized small-disturbance theory. The results show that, as the relative deformation of the wingtip gradually increases, the longitudinal static stability of the designed highly flexible flying wing scale model gradually enhances, the stability of phugoid and short-period modes deteriorates, and the lateral motion stability also degrades.
    Review of research on damage assessment methods for combat aircraft
    peng qian cheng, WANG WENKUAN, PEI YANG
    Available online:May 27, 2026, DOI:
    [Abstract] (190) [HTML] (0) [PDF 8.36 M] (106)
    Abstract:
    Combat aircraft, as the core equipment of modern air combat systems, play a crucial role in enhancing battlefield survivability, optimizing equipment design, and guiding tactical decision-making. This paper provides a systematic review of the development history, current research status, core methods, and future trends in the field of combat aircraft damage assessment. First, this paper traces the technological evolution of combat aircraft damage assessment, compares and analyzes the distinctive technical approaches and representative achievements in this field both domestically and internationally, and provides an in-depth analysis of the core processes and primary objects of combat aircraft damage assessment. The focus is on the damage modes of typical aircraft components and the underlying mechanisms when subjected to threat impacts. The paper also provides a comprehensive review of the core theories, research progress, and application status of existing mainstream damage assessment models and methods. Finally, in response to the current trend of diversified battlefield threats and the rapid increase in the complexity of aircraft systems, the paper outlines research directions including the unified quantification of damage criteria, autonomous and controllable multi-physics field simulation, and fusion of physical rules with explainable machine learning, aiming to provide references for the design of combat aircraft vulnerability reduction and the advancement of damage assessment technology.
    Research on the Method for Determining Initial Design Parameters of Aircraft Wing Box Section Structure
    Han Quanmin, wang qianping, han qing
    Available online:May 27, 2026, DOI:
    [Abstract] (260) [HTML] (0) [PDF 6.52 M] (111)
    Abstract:
    In order to solve the problem of quantifying the overall stiffness index of the aircraft wing box section structure and determining the preliminary structural parameters in the solution stage, two methods of overall deformation control and overall stiffness control were used to provide the quantified index of overall stiffness. By introducing the geometric layout of the wing surface, the equivalent elastic modulus of the material, and the allowable strain, combined with the aerodynamic total load/average wing load of the wing surface, based on the elastic strain of the wing box section section skin under bending, torsion and other loads, a mathematical integration method was used to establish a calculation formula to obtain the calculation methods for the overall deformation, overall stiffness and structural weight of each section of the box section. The results were compared and parameter iterated with the set two stiffness control quantification indexes to form the overall stiffness performance design of the wing main box section structure. The calculation method forms a set of operable and fast design processes, To lay the foundation for optimizing the stiffness performance of wing structures and designing preliminary structural parameters.
    Intelligent UAV Control Command Parsing Based on Large Language Model
    zhong fu, Lin Yuan
    Available online:May 27, 2026, DOI:
    [Abstract] (340) [HTML] (0) [PDF 1.26 M] (102)
    Abstract:
    To enhance the human-computer interaction experience and lower the operational barrier for unmanned aerial vehicles (UAVs), this paper proposes an intelligent UAV control command parsing method based on Large Language Models (LLM). This approach leverages the semantic understanding and generation capabilities of LLMs to automatically convert user-input natural language instructions into standard UAV control command sequences. By constructing a UAV control instruction dataset and fine-tuning it on open-source large language models, accurate parsing of various types of UAV control instructions is achieved. To verify the effectiveness of the proposed method, comparative experiments were designed including baseline methods such as keyword matching, traditional machine learning approaches, and BERT, along with ablation studies and case analyses of complex instructions. Experimental results show that the method achieves a command parsing accuracy of 92.3% on the test set, significantly outperforming traditional keyword-based matching methods. It can effectively handle complex and diverse natural language instructions, providing a solution for intelligent UAV control.
    Research on Aircraft Electro-Impulse De-icing Performance Prediction Using Hybrid Machine Learning Approaches
    wangxin, huangyongjie, nizhangsong, masai
    Available online:May 27, 2026, DOI:
    [Abstract] (314) [HTML] (0) [PDF 1.70 M] (86)
    Abstract:
    In view of the limitations of the numerical simulation method of deicing effect in aircraft icing safety protection, this paper proposes a wing electric pulse deicing effect prediction method based on machine learning algorithm. Through the electric pulse deicing finite element model simulation, the system builds a high-quality data set that takes into account the pulse force amplitude, tangent/normal adhesion strength, pulse action position (flap surface/below) and other deicing parameters. The applicability of four machine learning models, support vector regression (SVR), decision tree regression (DTR), gradient boost regression (GBRT), and multilayer perceptron (MLP) in the prediction of deicing effects was examined in comparison. The results show that the decision tree regression model has optimal predictive performance, with a coefficient of determination (R2) of 0.934, showing good predictive accuracy. Characteristic importance analysis indicates that the impulse force has the greatest influence on the deicing effect. This research can provide effective theoretical support and technical means for the optimal design of electric pulse de-icing system.
    Simulation and Experimental Study of Interference Noise Characteristics in Uniformly Decelerating State for Helicopter Rotor/Tail Rotor
    liyao, xusongding
    Available online:May 06, 2026, DOI:
    [Abstract] (177) [HTML] (0) [PDF 2.29 M] (66)
    Abstract:
    The aerodynamic noise generated by the rotor and tail rotor is a significant factor affecting helicopter performance and comfort. To investigate the aerodynamic noise characteristics and sound generation mechanisms of multiple rotating surfaces in helicopters, this paper focuses on the interference characteristics of rotor/tail rotor aerodynamic noise under uniformly decelerating conditions, conducting numerical simulations, simulation experiments, and theoretical analyses. Firstly, based on the CLORNS code and FW-H equations, a computational analysis method for interference noise from helicopter multiple rotating surfaces was developed. Subsequently, using a certain type of unmanned helicopter as the test platform, an onboard helicopter noise measurement system was established, and preliminary time-frequency domain characteristics of near-field rotor/tail rotor interference noise were obtained through experimental data. On this basis, using the established simulation analysis method, the unsteady aerodynamic loads and sound field distribution of the rotor/tail rotor for a certain type of unmanned helicopter were analyzed in detail, elucidating the generation mechanisms and radiation characteristics of rotor/tail rotor interference noise. The results show that under uniformly decelerating conditions, the reduction in forward flight speed leads to attenuation of lift from both the rotor and tail rotor. However, the overall lift trend exhibits periodic changes. Additionally, the sound pressure level on the advancing side of the rotor blades is significantly increased. The aerodynamic interference between the rotor and tail rotor vortices has a greater impact on the tail rotor than the rotor, displaying distinct radiation characteristics.
    A review of tilting structural design solutions for tiltrotors
    LU Yupeng, SHE Yixi, ZHANG Meiyu, TAN Wuzhong, LI Chaoyi, HAN Fenglin
    Available online:April 30, 2026, DOI:
    [Abstract] (338) [HTML] (0) [PDF 10.18 M] (102)
    Abstract:
    The tilting structure is a critical component of a tiltrotor for flight mode conversion, and its design significantly affects the safety and stability of this process. Based on literature research, this paper begins by analysing the requirements of the tilting process, identifying its characteristics of low-speed, heavy-load operation, and limited angular range. It then analyzes and summarizes the current state of three core structural and functional categories: tilting mechanism configurations, driving methods, and support structures for the pivot. Finally, through the analysis, it outlines common technologies and future development directions for tilting mechanisms, aiming to provide reference and recommendations for future research on tiltrotor tilting structures.
    Lightweight design of UAVs: advances in material-structure-manufacturing integration
    Huang Lirong, Zhu Jiangbo, Chen Yuhang, Fan Kuangang, MING Kai
    Available online:April 30, 2026, DOI:
    [Abstract] (526) [HTML] (0) [PDF 1.50 M] (174)
    Abstract:
    Lightweight design is crucial for enhancing UAV endurance and environmental adaptability. Its advancement relies on the deep integration of materials, structures, and manufacturing processes. This paper systematically reviews progress and challenges in this field. Material-wise, Carbon Fiber Reinforced Polymer (CFRP) dominates critical load-bearing components due to its high specific strength. However, its use is limited by high cost and interfacial defects. Engineering plastics and titanium alloys offer lightweight advantages for non-structural parts and high-temperature components, respectively. Yet they face bottlenecks in mechanical performance and processing. Structurally, topology optimization achieves 35%–40% weight reduction at the component level. Multidisciplinary Design Optimization (MDO) drives system-level performance enhancement by coupling aerodynamics, structural mechanics, and power systems. Manufacturing-wise, Additive Manufacturing (AM) enables complex structures (e.g., bionic topologies, lattices) with 30%–50% weight savings. However, this requires improved process reliability. Current challenges center on balancing material cost and performance, managing multi-physics optimization complexity, and resolving the contradiction between power and load requirements. Future efforts should integrate AI-driven optimization, digital twins, and low-carbon materials. This will advance lightweight design towards greater intelligence, reliability, and system integration.
    Research on full-scale test verification technology of composite structure of a certain type airplane
    liuxiuzhi, guoyilin, lushaowei, MA Hongtu, ZHENG Shuang, LIU Xinhua, MA Qiang
    Available online:April 30, 2026, DOI:
    [Abstract] (251) [HTML] (0) [PDF 9.14 M] (140)
    Abstract:
    The Building Block Approach (BBA) of composite structure is the material and structural strength verification method that must be followed in aircraft airworthiness certification, and it is also the key segment to ensure flight safety. As the highest level of BBA verification system, full-scale structure test is directly related to the success of composite structure airworthiness certification. In order to prove that the composite material airframe structure of a certain type of CCAR-23 normal category general aircraft complies with the relevant requirements of CCAR 23 and AC20-107B, firstly, this paper analyzes and discusses the planning and implementation techniques of full-scale static, fatigue and damage tolerance tests; Secondly, in order to solve the issue of wing root fractures failure during the first full-scale static test, a method combining computational analysis and experimental verification was used to propose a design modification and to design a wing root assembly test which was based on the BBA to verify the effectiveness of the improvement scheme. Finally, the optimized structure successfully passed the full-scale ultimate load test and the test results proved that the composite material airframe structure of this aircraft meets the relevant requirements of airworthiness regulations. The analysis, modification, test design and airworthiness certification process provide an important reference for the airworthiness compliance verification of similar type aircrafts.
    Dynamic Response Analysis of Airships in Vertical Landing with Single-Engine Out
    HUANG Jing, TIAN Rui, GUO LinXiang
    Available online:April 30, 2026, DOI:
    [Abstract] (197) [HTML] (0) [PDF 2.30 M] (116)
    Abstract:
    Based on a six-degree-of-freedom dynamics model of the airship, a Simulink simulation platform was established. Using this platform, comprehensive simulation studies were conducted to investigate the vertical landing process under thrust vector control. Furthermore, a comparative analysis was performed to evaluate the dynamic behaviors of the airship in response to various engine failure scenarios. The results show that, in the case of left engine failure examined here, the airship will experience slight roll and significant yaw motion. This causes its final landing point to deviate from the intended trajectory toward the left by a certain distance. Upon touchdown, the airship assumes a combined attitude characterized by leftward roll and rightward yaw. Further analysis reveals that, when total thrust is maintained at a constant level, the asymmetric distribution of lateral thrust has relatively little effect on longitudinal motion characteristics. Moreover, as the degree of lateral thrust asymmetry increases, the intensity of the airship"s dynamical response in that direction shows an obvious increasing trend.
    Risk Identification for the Collaborative Transformation of Dual-Use Advanced Aviation Technologies
    Lihan, Haoli, Fangwei, Fengbing
    Available online:April 30, 2026, DOI:
    [Abstract] (222) [HTML] (0) [PDF 610.49 K] (87)
    Abstract:
    The collaborative transformation of advanced dual-use aviation technologies, through a resource-sharing mechanism to break down technological barriers, promotes the deep integration of military and civilian scientific and technological innovation systems, constructs an integrated scientific research ecosystem, facilitates the strategic coupling of aviation technologies with the low-altitude economy industry, and comprehensively enhances the national technological competitiveness and economic resilience. However, the concealment and complexity of multidimensional risks in the technology transformation process make their identification and quantification face severe challenges, becoming a key bottleneck restricting the efficiency of military-civilian collaborative innovation.Based on the grounded theory framework, the systematic integration of interview data and literature resources and other unstructured information constructs a multi-level risk assessment model containing six core dimensions, including technological maturity risk, and 14 sub-dimensions such as technological maturity matching. Combining the Decision-Making Trial and Evaluation Laboratory (DEMATEL) method, a causal association network of risk factors is established. Through the dual perspectives of centrality and causality, the hierarchical roles and transmission logic of risk factors are analyzed, revealing the risk evolution mechanism of the transformation of military aircraft technologies for civilian use. The study shows that the risk of technological maturity level matching shows significant dominance in the causal network, while airworthiness risk shows prominent result dependency.
    Advances in Flexible Deployable Structures for Aerospace Engineering
    WANG Xiaoteng, Xu xu, LIU Qa, XUE Qiwen, LIU Xudong, HE Yiqian
    Available online:April 30, 2026, DOI:
    [Abstract] (188) [HTML] (0) [PDF 5.04 M] (122)
    Abstract:
    Flexible Deployable structures exhibit significant advantages, including compact stowage volume, low mass, and excellent buffering capabilities. Consequently, they are widely utilized during the landing and operational phases of various spacecraft. Research on deployable structures involves multidisciplinary and multiphysics considerations, necessitating the comprehensive integration of key technologies such as the intrinsic properties of flexible structural materials, packaging configurations, and the dynamic deployment process. Studying these structures not only advances the development of deployment technologies for flexible bodies but also holds substantial significance for China"s aerospace endeavors. This paper classifies deployable structures based on their function and application scenario. It reviews the core technologies involved in their design and performance evaluation, and summarizes the current state of research, encompassing numerical simulation, system-level structural testing, and material characterization. Finally, the paper identifies critical issues requiring future research focus and provides an outlook on the prospective applications and technological advancements of inflatable aerodynamic decelerators.
    A Review of the Impact of Near-Space Environment on Electronic Devices
    luojian, xuwenkuan, 苗景刚, haoyong, zhangqianghui, yangyanchu
    Available online:April 21, 2026, DOI:
    [Abstract] (211) [HTML] (0) [PDF 2.35 M] (155)
    Abstract:
    Near space, positioned between conventional aviation altitudes and orbital space, is recognized as having considerable potential for military applications and scientific missions. However, the unique atmospheric environment encountered in this region is known to impose stringent challenges on the reliability of onboard electronic systems. In this work, the environmental characteristics of aviation, space, and near space are comparatively analyzed, with the distinctive features of the latter—such as extreme temperature gradients, complex wind fields, elevated ozone concentration, and multi-source high-energy particle fluxes—being identified. The primary stressors influencing near-space electronic systems, including thermal environment, electric field disturbances, ozone-induced oxida-tion, and single event effects, are systematically examined, and their underlying mechanisms and impacts are elucidated. Advances in thermal control design, electric field shielding, ozone-resistance technologies, and radiation-hardening strategies have been reviewed, and their respective advantages and limitations have been assessed. Finally, future research directions are proposed to enhance the en-vironmental resilience of electronic systems operating in near-space missions.
    Research on Sliding Mode Active Disturbance Rejection Control for Quadrotor UAVs Based on an Improved Particle Swarm Optimization Algorithm
    wang you, xiongguangyan, fu gui, liu li wen, liu xiang ci
    Available online:April 21, 2026, DOI:
    [Abstract] (147) [HTML] (0) [PDF 1.25 M] (139)
    Abstract:
    To address the issues of suboptimal control and poor anti-disturbance performance in quadrotor UAVs under external disturbances, this study designs a sliding mode active disturbance rejection attitude controller and optimizes its parameters using an Improved Particle Swarm Optimization (GPSO) algorithm. First, sliding mode control (SMC) replaces the Nonlinear Error Feedback Control (NLSEF) module in traditional Active Disturbance Rejection Control (ADRC), simplifying the structure of the attitude controller. Second, an enhanced GPSO algorithm incorporating Good Point Set optimization and a golden sine operator is proposed to significantly improve search precision and convergence speed. Simulation results demonstrate that compared to classical ADRC and its parameter optimization methods, the proposed scheme achieves attitude angle tracking errors below 5% under external disturbances and markedly enhances tracking accuracy in planar flight.
    Structural Life extension Study of an Export Y12Ⅱ Aircraft
    menkunfa, WANG QINGLI
    Available online:April 21, 2026, DOI:
    [Abstract] (244) [HTML] (0) [PDF 2.70 M] (109)
    Abstract:
    An export Y-12 II aircraft, whose calendar life has reached its design indicator but in flight hours and takeoffs and landings still has significant margin. Underwent a life extension study based on structural safety considerations and user requirements. The Y12 II mainframe was designed with a safe-life concept and is protected by a metallic coating. The extension of the structure’s calendar life was conducted under the assumption that the coating remains intact. For environmental spectrum simplification, the principle of “coarse rather than detailed” was adopted, and a three-dimensional equivalent damage method was used to simplify the service area environmental spectrum. The calendar life of the aircraft’s structural coating was determined using the temperature-humidity (T-H) curve for aluminum alloy coatings. The theoretical calendar life was calculated under the condition of considering only metallic coating failure (without aluminum alloy base material failure) and accounting for one overhaul. A detailed inspection of the entire aircraft structure was performed on-site, revealing only minor damage. After repairing the damage and estimating the remaining calendar life, a 5-year extension of the aircraft’s structural calendar life was granted for this export Y-12 II, in accordance with the user’s requirements.
    Data-driven pitot tube fault feature extraction and fault prediction research
    zhong yuexin, QU Yishuai, LYU Bijiang, GAO Ke, CHEN Jie
    Available online:April 21, 2026, DOI:
    [Abstract] (232) [HTML] (0) [PDF 2.42 M] (186)
    Abstract:
    The pitot tube is a core sensor for the aerodynamic parameters of aircraft, and its failure may lead to serious flight safety hazards. The existing avionics systems lack direct monitoring of pitot tube heating failure. To address this issue, an early fault perception method based entirely on flight data recorder (FDR) data is proposed. First, flight record data is organized, and new parameters related to faults are constructed. Parameter selection is completed based on the importance assessment from a random forest, and then four fault characteristics are extracted as inputs for the subsequent fault prediction model using a dual criterion of stability and sensitivity. Next, a sliding window prediction model is constructed using statistical process control theory to set and optimize prediction rules, creating a comprehensive prediction model to achieve false alarm suppression and missed alarm compensation. The results show that the comprehensive prediction model is validated on multiple data sets, achieving an accuracy of 88% with no false alarms, demonstrating the validity of the proposed model for early perception of pitot tube heating failure.
    Construction of a Safety Assessment Process Knowledge Graph Based on Neo4j
    ZHANG Yixin, CAI Jing, LI Ming
    Available online:April 21, 2026, DOI:
    [Abstract] (162) [HTML] (0) [PDF 1.04 M] (141)
    Abstract:
    The systems and equipment of civil airborne platforms are crucial components of flight control systems. However, the high integration of civil airborne systems and equipment, coupled with the complexity of the safety assessment process, results in high labor costs for knowledge extraction, low knowledge supply rates, and unclear workflow interrelations. To address these challenges, we propose using knowledge graph retrieval methods to assist researchers in the safety assessment process. This paper constructs a knowledge graph for the safety assessment of civil airborne systems and equipment. By extracting knowledge from standard documents and engineering practices, designing an ontology, and defining relational rules, we develop a knowledge graph for the safety assessment process of airborne systems and equipment. The graph database Neo4j is employed for graphical storage and visual presentation of structural information. Applications demonstrate that the knowledge graph facilitates convenient querying of workflow related to the safety assessment process and reveals multi-dimensional relationships between workflows and dataflows in the safety assessment process. This reduces the complexity of knowledge extraction and improves the knowledge supply rate, ensuring the standardization and systematic nature of the work.
    Review of key technology development of airborne missile
    Shi Yuxin, Tian Deyu, Yang Wen, Wang Ling
    Available online:April 14, 2026, DOI:
    [Abstract] (278) [HTML] (0) [PDF 657.39 K] (141)
    Abstract:
    At present, the multi-dimensional perception detection system and anti-missile system make the strike efficiency of traditional airborne missiles face challenges, and the importance of survival and penetration ability and intelligent strike ability is becoming more and more significant. In order to analyze the technical emphases and difficulties faced by the development of modern missile technology, and to find out the future technical direction and design bottlenecks, the deployment and development process of typical airborne missiles in various countries are sorted out from the modern classic war cases, and the key technologies of missile research at present and in the future are put forward, including multi-missile joint cooperative strike technology, unmanned platform launch technology, advanced seeker and warhead technology, hypersonic technology, stealth technology and other five directions and technical branches. The results show that the multi-disciplinary integration system of intelligence, coordination, stealth and advanced single-machine system is the trend of missile overall technology, and it also paves the way for the follow-up research direction of high-tech airborne missiles.
    Research progress on aircraft structural load prediction technology based on neural networks
    CHEN Xingyi, LI Meng, XUE Jingfeng, WANG Wenjuan, ZHANG Mengjie
    Available online:April 14, 2026, DOI:
    [Abstract] (276) [HTML] (0) [PDF 5.43 M] (168)
    Abstract:
    Accurate acquisition of aircraft structural loads is crucial for optimizing structural design, ensuring flight safety, and extending service life. Compared with traditional load calculation methods, intelligent algorithms such as neural networks have powerful nonlinear data processing capabilities and can significantly improve the accuracy of load prediction. This paper first reviews the research progress of neural networks in aircraft structural load prediction. From the perspectives of the temporal characteristics and spatial distribution characteristics of loads, it focuses on different types of load regression problems in the fields of flight load measurement and flow field prediction. It then explores the application of multi-source data fusion technology in load prediction, which can achieve high-precision prediction while acquiring data at a low cost. Finally, it analyzes the challenges faced in aircraft structural load prediction based on intelligent algorithms in terms of model generalization ability and interpretability, and looks forward to the directions worthy of exploration in future interdisciplinary research.
    Study of Homogenization Modeling of Highly Curved Honeycomb Core Sandwich Composites
    baoyidong, tangmiaofei, caixiao, chiyeheng, anluling
    Available online:April 14, 2026, DOI:
    [Abstract] (132) [HTML] (0) [PDF 4.27 M] (166)
    Abstract:
    Homogenized models significantly enhance the computational efficiency of simulations for honeycomb sandwich structures. However, existing single homogenization methods exhibit substantial errors when applied to honeycombs with large curvatures. This study focuses on over-stretched aramid paper honeycomb sandwich structures to investigate the homogenized mechanical parameters of large-curvature cores. Bending simulations were performed on detailed geometric models of the honeycomb core to analyze the dependence of cellular morphology (specifically cell geometry) on core thickness and curvature. A refined homogenized model incorporating both thickness and curvature effects was developed and used to numerically simulate the curing process. The results demonstrate that key cell geometry parameters exhibit an exponential relationship with the core"s radius of curvature and a linear relationship with its thickness. Compared to the conventional single homogenization model, the refined model shows strong agreement with the deformation trends observed in experimental specimens and significantly improves the prediction accuracy of curing deformation for the honeycomb sandwich structure.
    Research on the design technology of lightweight composite air-cooled chassis
    zhangjiale, CHAGN Xuancang, FENG Zhixin, ZHU Yongqiang
    Available online:April 14, 2026, DOI:
    [Abstract] (195) [HTML] (0) [PDF 2.96 M] (174)
    Abstract:
    In order to achieve lightweight design of air-cooled chassis structure, a lightweight composite air-cooled chassis design technology is proposed based on comprehensive consideration of environmental adaptability, electromagnetic compatibility, hardness and wear resistance, and manufacturability. Taking a typical air-cooled chassis as an example, a carbon fiber lightweight chassis design was completed based on the random vibration 3σ rule, and random vibration, impact, and acceleration simulation analysis and experimental verification were carried out. The results show that the designed lightweight chassis scheme can meet the requirements of dynamic and static strength and stiffness, and reduce the weight by 851g compared to the original aluminum alloy structure, with a weight reduction ratio of about 25.7%. The method proposed in the paper can provide support for the lightweight design of airborne electronic equipment.
    A Semantic Risk-Graded Integrated Obstacle Avoidance Method for Unmanned Aerial Vehicles
    yangxuetao, yuxiaona, zhangkaomin
    Available online:April 14, 2026, DOI:
    [Abstract] (200) [HTML] (0) [PDF 711.93 K] (122)
    Abstract:
    Traditional path planning methods often exhibit limited responsiveness and flexibility when dealing with high-speed dynamic obstacles. To address this issue, this paper proposes an improved algorithm that integrates a semantic risk grading mechanism and a strategic yielding strategy into the Dynamic Window Approach (DWA) and Velocity Obstacle (VO) methods. While preserving the advantages of DWA in generating smooth trajectories and satisfying kinematic constraints, the VO algorithm is introduced to enhance the system’s ability to respond to dynamic obstacles. A semantic risk model is developed based on obstacle type, velocity level, priority, and predictability. When high-risk semantic targets are detected and traditional velocity filtering fails to ensure safe navigation, the system adopts proactive hovering and slowing strategies. A new scoring term is incorporated to guide unmanned aerial vehicles (UAVs) to yield to higher-priority targets without altering their heading, thereby improving planning stability and safety margins. Simulations were conducted in static, dynamic, and multi-semantic obstacle environments to compare the proposed method with conventional DWA and DWA-VO algorithms. Results show that the proposed approach significantly outperforms the baselines in terms of path efficiency, safety distance, and response time. The method demonstrates strong obstacle avoidance intelligence and offers promising potential for engineering applications in complex dynamic semantic environments.
    Study of DEP STOL aircraft conceptual design method and application
    Zhao Xin, zhouZhou, WangKele, LiXu
    Available online:April 05, 2026, DOI:
    [Abstract] (242) [HTML] (0) [PDF 2.46 M] (201)
    Abstract:
    There exists a strong coupling effect between the propeller slipstream and the wing of propeller-driven Unmanned Aerial Vehicles (UAVs) based on Distributed Electric Propulsion (DEP), which endows them with unique advantages in Short Take-off and Landing (STOL) performance. Therefore, the impact of their propulsion-aerodynamic coupling characteristics must be fully considered during the overall design phase. This paper proposes a method and process for the overall parameter design of distributed electric propulsion STOL aircraft that takes into account the propulsion-aerodynamic coupling effect, and constructs a mass estimation model and a propulsion-aerodynamic coupling model for the DEP system. In the preliminary estimation stage of overall parameters, by fully considering the complexity of the DEP system and the influence of propulsion-aerodynamic coupling, the error of initial design values can be reduced, the iteration cycle in the scheme phase can be shortened, and thus the design efficiency can be improved. A 400 kg-class DEP STOL UAV with an 8-propeller power configuration was used as a design case for scheme design, verifying the engineering applicability and feasibility of this method. The research results show that under the constraints of thrust and power, compared with the conventional single-propeller scheme, the multi-propeller lift-increasing layout during the takeoff phase can increase the maximum lift coefficient by more than 50%, which can effectively reduce the takeoff and landing distance; however, this layout will increase the drag coefficient by more than double, which in turn leads to an increase in the required thrust-to-weight ratio and the weight of the propulsion system. In addition, the aerodynamic-propulsion coupling estimation model can effectively characterize the slipstream lift-increasing effect. The estimation results of lift and drag coefficients are consistent with the trend of CFD calculation results, and although the estimation results are optimistic, the average error does not exceed 14%.
    Design method and parameter analysis of culvert propellers
    YU Zhongwei, ZHANG Helei, GUO Jingfang, LI Bing, QIN Haiyang
    Available online:April 05, 2026, DOI:
    [Abstract] (214) [HTML] (0) [PDF 3.70 M] (210)
    Abstract:
    Ducted propellers have attracted much attention in general aviation due to the advantages of high aerodynamic efficiency, high safety, and low noise levels. In this paper, an optimized design method for ducted propellers is proposed, using the leaf momentum theorem, ant colony algorithm, and CFD simulation. First, the ARA-D airfoil is selected and used for the preliminary design of the ducted propeller blades, with the blade element momentum theorem and the ant colony algorithm. Then, CFD method is used to simulate and analyze the propeller"s performance. Based the simulation results, the design of propeller blades is optimized. Then, a comparative analysis of the thrust performance of the propeller before and after optimization is conducted under different rotational speeds. Finally, the NACA4418 airfoil was selected to analyze effects on aerodynamic characteristics of the ducted propeller. The results show that this design method reduces design iterations and time. As the length of the middle section of the duct increases, the lift of the duct increases linearly, and the high-speed airflow area expands, but the impact on the lift and torque of the propeller is weak. As the propeller position moves downwards, the vortex and low-speed air masses inside the duct is increased, resulting in increased energy loss. Positioning the propeller closer to the lip shortens the airflow"s acceleration path and enhances duct lift. At 0.8 of the intermediate section length, the lift-to-power ratio of the ducted propeller is maximized at 2.96 g/W.
    Research on Temperature Control of Electric Aircraft Battery Packs Based on Fuzzy PID Algorithm
    LI Bing, ZHANG Helei, LAN Yingying, GUO Jingfang, YU Zhongwei, QIN Haiyang
    Available online:April 05, 2026, DOI:
    [Abstract] (175) [HTML] (0) [PDF 2.00 M] (235)
    Abstract:
    In this paper, a fuzzy-PID-based temperature control strategy for liquid cooling systems is proposed to address the response lag and poor parameter adaptability in the cooling system for electric aircraft power battery packs with the traditional-PID control under variable conditions. An AMESim-Simulink co-simulation model is established for the battery pack liquid cooling system, and the fuzzy-PID control is applied to achieve adaptive adjustment of pump speed with heat generation fluctuations. The system performance is compared and analyzed with that of traditional-PID control under constant discharge current and flight conditions. Simulation results demonstrate that, compared with the traditional PID algorithm, the fuzzy-PID control strategy reduces the response time for the battery pack temperature from 40℃ to 30℃ by 65.7% under flight conditions, shortens the response time for the same temperature drop by 45.83% under constant discharge current conditions, and achieves higher temperature difference control accuracy. This confirms the fuzzy-PID control"s universality advantage in regulating the nonlinear and time-varying thermal model.
    Analysis on multi-dimensional evaluation and improvement methods of aircraft combat integrity
    yuanjunjie, ZOU Gang, GENG Haiquan, LI He
    Available online:April 05, 2026, DOI:
    [Abstract] (166) [HTML] (0) [PDF 781.46 K] (143)
    Abstract:
    Aircraft operational integrity is the core attribute for measuring the comprehensive effectiveness of modern combat aircraft, and effective evaluation methods and improvement measures are of significant importance for ensuring air combat superiority. This paper systematically constructs a multi-dimensional evaluation system that encompasses mission capability rate, integrity rate, and survivability, and deeply analyzes the impact mechanisms of key factors such as equipment technology, logistics support, combat utilization, and personnel management on operational integrity. Aiming at existing shortcomings, systematic improvement strategies for technological innovation, logistics support, combat utilization, and personnel management are proposed.These recommendations serve as actionable references for the development, deployment, maintenance, and combat application of advanced aviation equipment.
    An investigation of the hot corrosion-creep life and failure mechanisms of DD6 single crystal superalloy specimens under pre-deposition of sodium salt
    Yang bai shun, Libiao, Zouwei, Liuzonghao
    Available online:April 05, 2026, DOI:
    [Abstract] (166) [HTML] (0) [PDF 7.12 M] (252)
    Abstract:
    This paper aims to investigate the creep rupture behavior and mechanisms of DD6 single crystal superalloy under hot corrosion. Creep tests were conducted on DD6 specimens at 950°C under salt-coated and air environments. Utilizing materials characterization methods such as Scanning Electron Microscopy (SEM) and X-ray Energy Dispersive Spectroscopy (EDS), the fracture morphologies and cross-sectional microstructures of the specimens were analyzed in detail. The creep test data and microstructural observations revealed that hot corrosion severely destroys the dense structure on the surface and near-surface regions, significantly reducing the creep life of the specimens. Hot corrosion and creep loading exert a pronounced synergistic effect on the failure process of the specimens. Compared to the γ" strengthening phase, the γ matrix phase is more susceptible to creep damage
    Research on Modular Assembly of Multi-Rotor UAV Based on Octagonal Truss Lattice
    chencunyong, xuyuanming
    Available online:March 23, 2026, DOI:
    [Abstract] (261) [HTML] (0) [PDF 6.82 M] (183)
    Abstract:
    To adapt to diverse mission scenarios and achieve flexible customization of unmanned aerial vehicles (UAVs) according to mission requirements while ensuring structural strength, this paper innovatively proposes a preparation strategy for modular assembly of multi-rotor UAVs based on lattice structures. Firstly, a flexible and scalable standardized lattice unit cell module and a detachable and reconfigurable connection method were designed; Subsequently, research on the mechanical properties of lattice single-cell modules and assembly structures was carried out; Finally, the design and manufacture of a multi-rotor unmanned aerial vehicle based on this strategy were completed, and it was verified through a combination of theoretical simulation and actual aircraft verification. The results show that this strategy realizes the diversity of multi-rotor unmanned aerial vehicle configurations and the scalability of size, can be customized and adjusted according to mission requirements, and demonstrates excellent applicability in practical applications.
    Deep Reinforcement Learning-Based Station-Keeping Control of Stratospheric Airships in Unknown Wind Fields
    Fang Xinyi, Zhu Ming, Zheng Zewei, Chen Tian, Zhang Yifei
    Available online:March 23, 2026, DOI:
    [Abstract] (221) [HTML] (0) [PDF 5.39 M] (193)
    Abstract:
    Traditional controllers for stratospheric underactuated airship station-keeping rely heavily on accurate models and struggle with unknown wind disturbances. This paper introduces a Deep Reinforcement Learning (DRL) algorithm to achieve stable station-keeping. By integrating a Weather Optimal Positioning Control guidance loop and the Twin Delayed Deep Deterministic Policy Gradient (TD3) algorithm, we establish a Markov Decision Process constructed through the design of state space, action space, and reward functions, which enables model-free attitude control. Simulations confirm superior performance under unknown winds, achieving efficient station-keeping. This work advances intelligent control for complex environments.
    Research on Lightweight Fault Detection in Embedded Cloud-Native Environments
    CHANG Yiwen, ZHANG Zeyuan, LI Weigang, LI Yi, WU Junsheng
    Available online:March 23, 2026, DOI:
    [Abstract] (169) [HTML] (0) [PDF 870.55 K] (268)
    Abstract:
    Containerized architectures in embedded cloud-native environments improve resource scheduling flexibility but face resource constraints and real-time challenges. Using a real airborne system platform, a tri-modal ECNF dataset integrating traces, metrics, and logs was built. A lightweight fault detection method combining graph neural networks and spatiotemporal Transformer attention models multimodal data to capture hidden correlations, improving average F1-score by 9.5%. An adaptive pruning strategy based on data missing rates dynamically removes low-importance temporal features, boosting runtime efficiency by 49.4%. Experiments confirm the method’s effectiveness and practical value.
    Multi-objective gates allocation model based on Monte Carlo-genetic al-gorithm
    xiaoheng, yangbin, weidan, zhangkaomin, daijie
    Available online:March 23, 2026, DOI:
    [Abstract] (470) [HTML] (0) [PDF 908.75 K] (168)
    Abstract:
    In the aviation transportation system, passengers, airports, and airlines, as participants in travel, should have their interests fully considered. This paper constructs a multi-objective parking space allocation model with airport boarding bridge utilization rate, aircraft taxiing distance, and passenger walking distance as objective functions, where the weights are random variables. To systematically consider the interests of all three parties and seek a balance among them, a genetic algorithm based on the Monte Carlo method is designed. The random sampling characteristics of Monte Carlo simulations enhance global search capabilities, while heuristic algorithms improve local optimization efficiency. Experiments were conducted to explore the influence patterns of weight variables on the objective functions through sensitivity analysis, ultimately deriving the optimal weight combination and parking bay allocation scheme. Experimental results indicate that when the weight parameter combination is 0.60, 0.21, and 0.19, the model achieves synergistic optimization of the three parties" benefits: the airport boarding bridge utilization rate increases to 98%, an improvement of 28% over the original scheme; the aircraft taxiing distance and passenger walking distance are reduced by 91,338 meters and 16,541,163 meters, respectively, representing reductions of 24.8% and 49.8% compared to the original scheme, effectively validating the effectiveness and practicality of the model and algorithm.
    Research on the Impact of Pilot Control Skills on Flight Safety during Approach Stage
    Mao Haitao, Zhang Zhuzhu, Hu Wenlin, Liu Yulin
    Available online:March 23, 2026, DOI:
    [Abstract] (173) [HTML] (0) [PDF 1002.18 K] (189)
    Abstract:
    In order to evaluate the impact of pilot control skills on the safety risks during the approach stage, an approach stage flight dynamics model considering the pilot"s skill level was established based on flight dynamics. The pilot"s skill level was transformed into a probability distribution function of flight control variables, and a pilot control model was established. The pilot"s approach control process was reconstructed based on Monte Carlo simulation method, achieving a quantitative evaluation of the pilot"s control skills on the safety risks during the approach stage. The research results indicate that the model proposed in this paper can effectively simulate the impact of different pilot skill levels on approach flight safety deviation; The improvement of pilot control skills significantly increased the success rate of approach. When the standard deviation of the probability distribution of pilot control variables decreased from 1.5 to 0.75, the success rate of approach increased from 67.36% to 99.69%. The research results can provide reference for flight safety risk assessment and pilot control skill level evaluation.
    Recent Advances in Flapping Wings with Swept Morphological Characteristics
    Ma Xiquan, Song Bifeng, Ma Dongfu
    Available online:March 01, 2026, DOI:
    [Abstract] (242) [HTML] (0) [PDF 1.77 M] (271)
    Abstract:
    The sweepback feature, developed through long-term avian evolution, is a crucial factor in enhancing the aerodynamic performance of flapping-wing vehicles. This paper first analyzes the fundamental wing structure of birds based on anatomical principles and discusses it in conjunction with existing morphometric studies. Subsequently, it provides a comprehensive review of current research on the role of sweepback in stabilizing leading-edge vortices, delaying dynamic stall, and improving yaw stability. Building on this foundation, representative design approaches and application cases of bio-inspired structures incorporating sweepback features are summarized. Finally, key scientific questions are distilled, and future research directions are outlined, providing theoretical support for the design of bio-inspired flapping-wing aircraft.
    Research on the transportation effectiveness evaluation method of tiltrotor aircraft oriented to task scenarios
    Chen MuYao, Shang Dan, Zhu Qinghua
    Available online:March 01, 2026, DOI:
    [Abstract] (284) [HTML] (0) [PDF 967.47 K] (316)
    Abstract:
    Addressing the challenges of incomplete metrics, ambiguous hierarchies, and the high variability/subjectivity of models in tiltrotor transport efficiency evaluation, this study develops a systematic assessment framework. Based on representative mission profiles, the V-22 and V-280 aircraft are analyzed as case studies. A dual-pathway methodology, correlating the airframe with its mission trajectory, establishes a clear four-level indicator hierarchy: Mission Effectiveness, Capabilities, Performance, and Fundamental Parameters. The Analytic Hierarchy Process (AHP) determines objective weights, while the Fuzzy Comprehensive Evaluation Method quantifies qualitative metrics, followed by data normalization. A novel multi-model integration framework synergizes the ADC (Availability, Dependability, Capability) model, the Exponential method, and a Weighted Standard Deviation approach. Normalization and a Least Squares algorithm optimize the weight synthesis, reducing bias from any single model. Case study results demonstrate consistent and rational evaluations, effectively converging outcome disparities. This framework provides a robust and structurally coherent solution for tiltrotor transport efficiency analysis.
    Effects of exposed antennas on the aerodynamic performance of cruise missile submerged inlet
    ZHANG Yang, JIANG Shengju, ZHU Ninghua, ZHOU Zhou
    Available online:March 01, 2026, DOI:
    [Abstract] (197) [HTML] (0) [PDF 5.07 M] (225)
    Abstract:
    Regarding the impact of exposed antennas on the performance of submerged inlet, this paper compares the performance differences of inlet under different angles of attack(AOA), sideslip angles, and Mach numbers with the influence of antennas through numerical simulation. The impact mechanism is analyzed from the perspectives of AIP total pressure recovery, boundary layer along the missile body, and total pressure recovery along the inlet duct. The results indicate that at 0.5 Mach, the maximum total pressure loss caused by different angles of attack and sideslip with the influence of an antenna is slightly higher than that without an antenna by approximately 0.52%. At the same angles of attack and sideslip, the influence of the antenna is limited at lower Mach numbers, but as Mach numbers increase to 0.8, the total pressure loss compared to the state without an antenna reaches 2.02%. The main impact of an exposed antenna is its wakes inject low-energy flow into the boundary layer, exacerbating flow field disturbances, which lead to reduction of the total pressure recovery coefficient, but with little effect on the distortion index. The influence range of the antenna wake can be roughly estimated by the geometric angle difference between the antenna and the inlet, which can then be used to select an appropriate antenna placement location.
    Numerical Simulation of Bird Moving Trajectory in Curved Inlet
    Liu Meng, Xie Xuan, Liu Songzheng, Zhao Yinchun, Zhang Fengqi, Luo Gang
    Available online:March 01, 2026, DOI:
    [Abstract] (224) [HTML] (0) [PDF 3.92 M] (243)
    Abstract:
    There is a significant difference in the state of bird ingestion between engine with an inlet and without one. In order to study the motion state of the bird after being ingested into the inlet and reaching the engine fan , a modeling and experimental verification of bird motion under wall collision and airflow effects were carried out. A simulated curved inlet was designed, and a validated method was used to establish a bird motion analysis model after bird ingestion in the inlet under simulated takeoff conditions. The exit velocity and position of the bird after being ingested by the curved inlet at different inlet positions were obtained through numerical simulation. The results showed that the inclined inner wall of the inlet first forced the bird to change direction and decelerate, and the bird that slid into the airflow after deceleration was affected by aerodynamic forces, causing the bird to relatively concentrate on the right front side of the engine when landing in front of the engine.
    Time-Variant Reliability Analysis of Aircraft Seat Based on Adaptive PC-Kriging
    pangjunpeng, liyanjun, zhoumaohui, maxinyu, haozehang
    Available online:March 01, 2026, DOI:
    [Abstract] (239) [HTML] (0) [PDF 1.98 M] (211)
    Abstract:
    As a core moving component of aircraft seats, the recline mechanism is prone to structural damage after prolonged cyclic operation. Its time-dependent reliability analysis is particularly challenging due to numerous influencing factors and a high degree of nonlinearity. To address this, a time-dependent reliability analysis method for complex mechanisms based on adaptive PC-Kriging is proposed in this paper. First, leveraging the high accuracy of PC-Kriging in handling high-dimensional systems, an adaptive time-dependent reliability model is developed. Then, based on theoretical analysis, simulation, and airworthiness requirements, a time-dependent reliability model of the seat recline mechanism considering clearance wear is constructed. Finally, the proposed method is applied to both numerical examples and the recline mechanism. The results show that the reliability of the mechanism remains stable initially but decreases rapidly with increasing cycles. The method proposed in this paper provides an important analytical approach for the reliability assessment of the aircraft seat recline mechanism.
    Feasibility study on blind rivets for aircraft intake duct based on comparative vibration fatigue testing
    liuqiue, MA Jiangzhao
    Available online:February 18, 2026, DOI:
    [Abstract] (257) [HTML] (0) [PDF 1.35 M] (208)
    Abstract:
    In aircraft structure，particularly inaccessible or enclosed areas, blind rivets are increasingly replacing traditional rivets for connection. However, to prevent engine damage caused by blind rivet failing, a Feasibility study on using blind rivets in the air intake duct was conducted. Based on typical connection structures in the inaccessible of the air intake duct, different components were designed according to the type of fasteners used, while considering the impact of assembly tress. A vibration fatigue test system was established to compare the vibration fatigue performance of different structural components under resonance frequency and identical stress levers. The test results demonstrated that replacing 3.5mm diameter traditional rivets with 4.0mm diameter blind rivets in the air intake duct is feasible. This conclusion providers a basis for using blind rivets in air intake ducts, and this methodology can be extended to comparing the life of other components primarily affected by vibration fatigue.
    Application of Deformation Compensation Technology in Hollow Composite Spar Structures
    Liu Qidi, Han Dong, Sheng Zhanqi, Li Lili
    Available online:February 18, 2026, DOI:
    [Abstract] (317) [HTML] (0) [PDF 4.47 M] (224)
    Abstract:
    To address the geometric accuracy control challenges arising from large-curvature complex surface deformation during the thermo-compression curing process of hollow composite spars for helicopter blades, this study proposes a deformation compensation method based on reverse modeling and iterative optimization, leveraging deformation compensation technology. The true morphology of the component was acquired using 3D scanning technology, and finite element analysis was employed to elucidate the mechanisms of mold expansion and curing deformation. An iterative optimization workflow comprising "scanning measurement - reverse modeling - deviation analysis - compensatory modification of mold profiles" was established. Experimental results demonstrate that this method significantly enhances forming precision: the maximum deformation of the mold during curing was reduced from 1.4 mm to 0.98 mm; after two process iterations, the dimensional deviation of the spar product was effectively controlled within ±0.5 mm. This study provides an effective engineering solution for the precision forming of large-scale composite components with complex curved surfaces.
    Computational Investigation on Aerodynamic Characteristics of Swift-Inspired Rough Airfoil
    ChenJunpeng
    Available online:February 18, 2026, DOI:
    [Abstract] (314) [HTML] (0) [PDF 4.87 M] (166)
    Abstract:
    This study focuses on the flow mechanism of the feather-like wrinkled airfoil of swifts, aiming to reveal the influence mechanism of non-smooth surface structures on flow characteristics by comparing the aerodynamic performance of wrinkled airfoils and equivalent smooth airfoils under low Reynolds number conditions.Computational fluid dynamics (CFD) methods were used to conduct numerical simulations on the flow field structures, lift, and drag variations of the two airfoils within the angle of attack (AOA) range of 0°to20°.The study emphasized analyzing the action laws of the concave and convex structures on the wrinkled airfoil surface in low Reynolds number flows.The results show that the non-smooth structures of the wrinkled airfoil significantly enhance aerodynamic efficiency in the medium AOA range (6°–10°) by reducing drag through vortices in concave grooves and increasing lift via low-pressure zones formed by convex structures. Specifically, the aerodynamic efficiency of the wrinkled airfoil increases by 19% compared to the smooth airfoil at 8° AOA. The aerodynamic advantages are insignificant when the AOA is less than 6° or exceeds 16°. An increase in Reynolds number enhances the pressure difference between the upper and lower surfaces of the airfoil, thereby improving the lift-to-drag ratio. Under static conditions, the feather-like wrinkled airfoil demonstrates remarkable optimization in aerodynamic characteristics within the medium AOA range.
    Research on Modeling of Aircraft Support Activities for Digital Simulation
    wangzhiyao, yimingxu, tianyongliang, yangsichao
    Available online:February 18, 2026, DOI:
    [Abstract] (324) [HTML] (0) [PDF 4.41 M] (172)
    Abstract:
    With the evolution of modern warfare, aircraft support activities have become increasingly critical to ensuring operational effectiveness. To address the limitations of traditional modeling approaches, such as coarse granularity and insufficient dynamic interaction, this paper proposes a fine-grained modeling method for aircraft support activities oriented towards digital simulation. By introducing the Multi-Agent System theory and Discrete Event System modeling mechanism, a multidimensional integrated modeling framework encompassing spatial environment, task process, and behavior mechanisms is established. A fine-grained modeling workflow for support activities is developed. Based on the proposed method, a digital simulation and deduction system for aircraft support activities is constructed to verify the effectiveness of the modeling approach in accurately reflecting resource coordination, spatial interactions, and dynamic task evolution. Simulation results demonstrate that the fine-grained modeling method significantly enhances the authenticity and precision of support activity simulations and provides strong support for maintainability evaluation and optimization during aircraft design phases.
    Change impact analysis algorithm for airborne software engineering changes
    niu shuang yue, xu si qiang, wu peng wei, long bin, wang jian
    Available online:February 18, 2026, DOI:
    [Abstract] (301) [HTML] (0) [PDF 1.18 M] (365)
    Abstract:
    At present, the development of aviation equipment in China is rapid, and the scale and changes of software are increasing sharply. The digital management platform has emerged as a replacement for traditional paper documents as a means of change control. However, risks such as manual updates and post-event filing mechanisms still exist. Therefore, this paper proposes a change impact analysis algorithm for airborne software engineering changes based on the software configuration management model and the change process control model. According to the changes in software versions and validity before and after the change, the changes are classified into new version software upgrades, validity changes of software to be changed, and validity changes of affected software versions for change operations. The results show that the change impact analyzer developed based on this algorithm, when integrated with the engineering change control process, can efficiently control the configuration status, fully meet business requirements, ensure the accuracy, real-time nature, and traceability of product data, and has been widely applied in key national models. The framework that is scalable for multiple aircraft types and business scenarios can be rapidly promoted to other models.
    Design and research on an ice adhesion strength measurement device and its visualization analysis
    Ma Hailang, Jia Yangyang, Li Kangshuai, Zhang Fengwei, Kong Linhao, HeQiang
    Available online:February 18, 2026, DOI:
    [Abstract] (274) [HTML] (0) [PDF 4.04 M] (216)
    Abstract:
    To address the issues of insufficient applicability and limited accuracy in measuring the adhesion strength of ice layers on typical aerospace materials, an ice adhesion force measurement device was developed to measure the adhesion force between ice columns and substrates. Based on this, a complete ice adhesion strength measurement setup was constructed in combination with digital image correlation (DIC) equipment. The system was primarily developed using a hybrid programming approach with Matlab and C++, with a focus on the ice adhesion strength measurement system. This system employs a non-contact measurement method to visualize the displacement and strain fields of the ice column and substrate with characteristic points. In addition, aluminum and silicone rubber substrates, representing hard and soft materials, respectively, were selected as test objects to verify the feasibility of both the hardware device and software system. Experimental results show that the brittle adhesive strength of the ice-aluminum interface is 35.96 MPa, and the shear creep adhesive strength of the ice-silicone rubber interface is 24.71 MPa. The maximum displacement when the ice column detaches from the hard substrate surface is 140 pixels, with a maximum principal strain of 1%, while the maximum displacement when detaching from the soft substrate surface is 550 pixels, with a maximum principal strain of 3%. These results validate the capability of the ice adhesion strength measurement system to determine the adhesion strength between ice and various substrates, providing critical parameters for de-icing in aerospace engineering.
    Application and Future Development Trends of FPV Dronesin Modern Warfare
    Long Keyu, Lu Yafei, Wang Yujie, Chen Qingyang
    Available online:February 05, 2026, DOI:
    [Abstract] (687) [HTML] (0) [PDF 2.42 M] (323)
    Abstract:
    First-person view (FPV) drones, with their high maneuverability, low-altitude concealment, and cost-effectiveness, have become a powerful weapon increasingly used by both sides in modern warfare. This paper focuses on FPV drones, introducing their technical features, combat advantages, and typical application modes. It also systematically discusses the developmental prospects of FPV drones in the context of current technical challenges, including the incorporation of autonomous control, target recognition with terminal guidance technologies, as well as improvements in maneuverability, stealth, endurance, and anti - jamming capabilities in communication - denied and navigation - denied environments. Additionally, it explores the evolution of FPV drones towards swarm and cooperative operations and multi - platform deployment from aerial and vehicle - based systems. This paper may offer certain insights for the innovative development of China"s drone technology.
    A Review of the Development and Application of Tactical Reconnaissance UAVs Equipment
    sunshaofang, luyafei, shaoshuai, wangyujie, chenqingyang, xiyangyang
    Available online:February 05, 2026, DOI:
    [Abstract] (367) [HTML] (0) [PDF 10.08 M] (287)
    Abstract:
    Tactical reconnaissance unmanned aerial vehicles (UAVs) play an important role in combat tasks such as intelligence, surveillance and reconnaissance (ISR) on modern battlefields and are the focus of the development of military UAVs in major military powers around the world. This review introduces the related concepts and battlefield applications of tactical reconnaissance unmanned aerial vehicles , analyzes the current equipment status of tactical reconnaissance UAVs abroad, interprets the technical characteristics of the latest tactical reconnaissance UAVs from the United States, Russia and Europe, and discusses the main development trends and key technology requirements of tactical reconnaissance UAVs in the future. Finally, this review puts forward several suggestions for the future development of tactical reconnaissance unmanned aerial vehicle systems in our country.
    Aerodynamic Characteristics Impact and Drag Reduction Optimization of Motor Arms in Compound-Wing UAVs
    Liu Zhanhe, Zhou He, Wang Jing, Li Longlong, Yang Yunkang
    Available online:February 05, 2026, DOI:
    [Abstract] (401) [HTML] (0) [PDF 3.37 M] (215)
    Abstract:
    The design of combination the conventional aerodynamic configuration with multi-rotor is one of the crucial technical solutions for current low-altitude compound-wing unmanned aerial vehicles (UAV). During level flight, motor arms become significant contributors to drag. Based on conventional layout compound-wing UAVs, an analytical method for evaluating the aerodynamic influence of motor arms and a design for drag reduction optimization through airfoil modification are adopted. The lift-drag characteristics, pressure nephograms, and airflow around cross section of motor arms for three configurations of UAVs: clean configuration, motor arm-equipped configuration and drag-reduction optimization design, are studied in detail by N-S equations and the K-ω-SST turbulence model. The results indicate that motor arms primarily affect drag coefficient and lift-to-drag ratio, while it has less impact on lift coefficient. Complex flow characteristics are observed at leading edges, trailing edges of motor arm, and also the junctions with wing. And the main reason of drag increase is the additional high-pressure zones. With the design of drag-reduction optimization, the lift coefficient improved by 9.51%, drag coefficient reduced by 9.81%, and lift-to-drag ratio increased by 21.41% when the angle of attack is 6°. And besides, the flow characteristics around motor arms is significantly improved, which enhancing lift performance. These findings all could provide valuable insights for existing compound-wing UAVs’ performance optimization.
    Virtual Test Verification of Aircraft Static Electricity Discharge Current
    zhenguoshuai, zhangting, sunhongpeng
    Available online:February 05, 2026, DOI:
    [Abstract] (295) [HTML] (0) [PDF 799.04 K] (285)
    Abstract:
    The dissipation of deposited electrostatic charge on aircraft is a necessary measure to ensure the safety of pilots and the aircraft. The electrostatic discharge (ESD) performance of aircraft static dischargers has always been a research hotspot. This paper proposes a virtual testing method for the dissipation current of deposited electrostatic charge on aircraft based on digital electromagnetic modeling and simulation technology. The method integrates the distribution of the aircraft"s electrostatic field intensity and the Fowler-Nordheim equation. The average prediction error of the discharger"s dissipation current is less than 1 dB. The method is validated through virtual testing of the dissipation current of deposited electrostatic charge on an F-22 aircraft model. This approach can not only accelerate the design of new static dischargers but also guide the layout design of static dischargers on new aircraft.
    Uncertainty Quantification of Composite Structural Performance via Hyperparameter Search-Coordinated Neural Network
    FENG Yunwen, CHEN Junyu, REN Hantao, LU Chen, XUE Xiaofeng, SONG Zhicen, LU Jun
    Available online:February 05, 2026, DOI:
    [Abstract] (310) [HTML] (0) [PDF 8.74 M] (314)
    Abstract:
    To address the problem of multi-scale uncertainty quantification in composite materials, a Hyperparameter Search-Coordinated Neural Network (HSCNN) method integrating hierarchical scale decomposition and multi-stage hyperparameter search is proposed. This method systematically organizes the nested transfer relationships of multi-scale uncertainty propagation through hierarchical scale decomposition and constructs uncertainty transfer functions across scales using backpropagation neural networks. Based on real-time feedback from performance indicators during the uncertainty quantification process, it dynamically adjusts hyperparameter values through multi-stage searches to continuously improve network performance. The effectiveness of the method in cross-scale uncertainty quantification is verified using a T800 carbon fiber/epoxy composite as a case study. Results show that HSCNN enables efficient quantification of multi-scale uncertainties through the orderly construction of nested transfer relationships and hyperparameter optimization, providing support for the reliability design of composite materials.
    Optimal design of composite sandwich structures for aircraft radomes
    Zheng Haoran, Li Wei
    Available online:January 28, 2026, DOI:
    [Abstract] (425) [HTML] (0) [PDF 960.91 K] (275)
    Abstract:
    This study focuses on the multi-objective coupled optimization design of composite radomes for civil aviation airliners, aiming to ensure the reliability of the radome design while simultaneously achieving the improvement of its wave-transparency efficiency and the reduction of its structural mass. The study proposes an improved particle swarm optimization algorithm by constructing an optimization model containing multiple design variables, which takes wave transmittance maximization and weight minimization as the dual-objective optimization function, and introduces Monte Carlo simulation to quantify the material uncertainty. Finally, comparative experiments with other optimization algorithms are conducted to verify the effectiveness of the proposed method. Results show that the optimized radome exhibits a 16.3% increase in wave transmittance and a 20.8% reduction in weight, and the maximum stress and deformation satisfy the constraints, and the probability of failure is controlled within 5%, demonstrating the coordinated optimization of the radome’s “wave-transparency, lightweight, and reliability” performance.
    Integrated Aerodynamic-Stealth Optimization of Airfoil Based on Co-Kriging Multi-fidelity Surrogate Model
    HU Dezhao, JIA Gaowei, YANG Xixiang, YU Ke, CHEN Suqi
    Available online:January 28, 2026, DOI:
    [Abstract] (479) [HTML] (0) [PDF 2.71 M] (270)
    Abstract:
    To adapt to the complex electromagnetic environment, modern unmanned aerial vehicles (UAVs) face more design constraints and stricter design requirements in terms of aerodynamic, stealth, etc. The dimensions of design variables and optimization objectives are elevated. Aiming at the problems of high computational resources demands for surrogate model construction and low efficiency of traditional multi-objective optimization methods, the optimization method based on Co-Kriging multi-fidelity surrogate model is investigated. Firstly, a Co-Kriging surrogate model is constructed for the aerodynamic-stealth performance of airfoils. Secondly, the model is combined with the multiobjective evolutionary algorithm based on decomposition to construct a surrogate-based optimization framework, and then solved to obtain the Pareto optimal solution set. Finally, three optimized airfoils on the Pareto front are selected for aerodynamic-stealth performance comparison and evaluation. The results show that: the Co-Kriging surrogate model constructed in this paper is comparable to the traditional surrogate models in terms of accuracy, and has advantage in terms of computational resource consumption. The lift coefficient of the optimized airfoil is significantly increased, and the drag coefficient and radar scattering cross-section are significantly reduced.
    Research on the
    Hu handong, Wang wenkai, Jiang xiong, Liu fujun, Si fangfang
    Available online:January 28, 2026, DOI:
    [Abstract] (382) [HTML] (0) [PDF 1.02 M] (250)
    Abstract:
    Free-drop separation tests in high-speed wind tunnels are typical unsteady aerodynamic experiments, which involve unsteady flow, unsteady motion, and the coupling between flow and motion. For multi-body interference and separation cases, the free drop process includes four main characteristic times: the characteristic time of the flow, the characteristic time of translational motion of the separation body"s center of mass caused by gravity, the characteristic time of translational motion of the separation body"s center of mass caused by aerodynamic forces, and the characteristic time of rotation around the center of mass. In wind tunnel tests, using different characteristic times means that the correspondence between test results and actual flight results varies, which can be used to judge the validity of the wind tunnel test method. Therefore, selecting appropriate characteristic times is crucial for improving the similarity and effectiveness of free drop tests. This paper uses a linearized aerodynamic model and rigid body motion equations to derive the correspondence between free drop tests in wind tunnel models and real flight parameters. Taking the characteristic time of translational motion of the center of mass as the primary similarity parameter, the similarity criteria that scaled model tests should satisfy are derived. This similarity criterion is universal and includes existing free drop test similarity simulation criteria such as the "heavy model scaling(HMS) , "light model scaling (LMS) , and "Fr scaling(FRS) . It can be conveniently used for the design of free drop tests and the analysis and evaluation of test results, thus it can also be considered as a "unified model" method for guiding the similarity design of free drop tests.
    Robust Optimization of eVTOL Based on High-Precision Adaptive Surrogate
    zhupianpian, wangyu
    Available online:January 28, 2026, DOI:
    [Abstract] (417) [HTML] (0) [PDF 1.09 M] (298)
    Abstract:
    Electric vertical take-off and landing (eVTOL) vehicles are a key focus of advanced aircraft. To address the heavy computational burden in robust design optimization of eVTOL vehicles, an infill-sampling strategy tailored for high-fidelity adaptive surrogate models is presented. The proposed DDMSE-LC criterion refines model accuracy from both global and local perspectives by integrating (i) a sample–sparsity index (DD), (ii) local complexity (LC), and (iii) the mean squared error (MSE) into a multi-dimensional assessment framework. A leave-many-out cross-validation (LMOCV) scheme is also introduced to accelerate accuracy validation of the surrogate model. Mathematical problems and a practical engineering problem confirm the efficiency of the method. Based on the resulting high-fidelity adaptive surrogate model, conventional and robust optimizations of an eVTOL configuration were carried out. Results show that the DDMSE-LC criterion, combined with LMOCV, improves prediction accuracy and surrogate-construction efficiency; moreover, robust optimization based on the high-fidelity adaptive surrogate model enhances the robustness of the eVTOL performance and mitigates the design risk.
    A non-dynamic estimation method for the angular and linear motion state of an aircraft
    hu fang fang, nan shang han, zhou ze bo, wang chun yang
    Available online:January 28, 2026, DOI:
    [Abstract] (389) [HTML] (0) [PDF 2.53 M] (252)
    Abstract:
    Accurate and stable linear/angular state estimation serves as the fundamental prerequisite for autonomous stable flight of aircraft, where acceleration dynamics critically determine the kinematic characteristics. To address the estimation bias induced by noisy measurement data, this study proposes a dynamics-independent methodology for real-time denoising and reconstruction of linear/angular acceleration. A window recursive algorithm is developed to establish temporal correlations through state transition matrices constructed from multiple historical epochs. The key innovation lies in creating a data smoothing mechanism based on information redundancy theory for non-model-based acceleration estimation. The algorithm features adaptive weight adjustment within the sliding window to optimize historical data utilization while enabling synchronous outlier detection and rejection. Simulation experiments demonstrate significant improvements: For linear acceleration estimation, the proposed method achieves 61% reduction in root mean square error (RMSE) compared to conventional differential methods. Angular acceleration estimation shows even greater gains with 44% RMSE reduction. These results validate the method"s effectiveness in overcoming the limitations of dynamics model dependency while providing reliable acceleration estimation solutions for autonomous aerial navigation.
    Reliability-based topology optimization based on improved bi-directional evolutional structure optimization method
    Song Shufang, LYU Yaqing, ZHANG Xi, XIANG Yunheng
    Available online:January 19, 2026, DOI:
    [Abstract] (432) [HTML] (0) [PDF 4.17 M] (271)
    Abstract:
    Reliability topology optimization design, which combines topology optimization and reliability analysis, is an important branch in the field of structural optimization. In order to improve optimization efficiency, an improved Discrete Variables Bi-directional Evolutional Structure Optimization method (DV-BESO) is firstly developed for non-volume constrained topology optimization problems. The element sensitivity can be solved on the basic of Lagrangian method, and the design variables will be updated based on the bi-directional evolution criterion. Taking into account the objective uncertainties of engineering structures, the reliability topology optimization design (RBTO) based on DV-BESO is carried out. Performance measure approach (PMA) is used to handle probability constraints, and Sequence optimization and reliability assessment method (SORA) is employed to decouple the complex nested double-loop optimization process. Finally, the feasibility and effectiveness of the established DV-BESO reliability topology optimization are verified and validated.
    Digital Twin Modeling and Model Self-Updating Technology for Civil Aircraft Power Distribution System
    LI Xuhui, WEI Shihao, LI Minhao, JI Songchen, MA Cunbao
    Available online:January 19, 2026, DOI:
    [Abstract] (515) [HTML] (0) [PDF 2.06 M] (274)
    Abstract:
    The civil aircraft power distribution system serves as the energy hub for airborne electrical equipment, characterized by extensive interconnections with other systems. However, system performance degradation or anomalies are often difficult to detect, and internal data variations prove challenging to track. This study proposes a digital twin architecture for civil aircraft power distribution systems based on digital twin technology. A mechanism-based twin model is established through Simulink implementation. To address high-fidelity requirements, a data-driven self-updating technology is developed for twin models, effectively enhancing their capability to reflect real-time system state changes in civil aircraft power distribution systems. The results demonstrate that the proposed architecture achieves transparent logic mechanisms and visualized operational data. The self-updating technology significantly improves real-time monitoring of system anomalies, providing effective technical support for health management of aircraft power distribution systems. This research holds significant engineering application value for enhancing digital operation and maintenance capabilities in airborne systems.
    Design method for hull water resistance reduction of large amphibious aircraft
    HUANG Miao, WU Bin, CAO Kai, GAO Xian-jiao
    Available online:January 19, 2026, DOI:
    [Abstract] (444) [HTML] (0) [PDF 1.20 M] (285)
    Abstract:
    The AG600 aircraft is China"s first large amphibious aircraft designed to meet the requirements of CCAR-25 standards, possessing complete independent intellectual property rights and having obtained TC. In order to achieve the acceleration design target, technical personnel conducted research on hull drag reduction methods. Firstly, optimization design was conducted on the hull layout, forebody parameters, and main planning surface, analyzing the drag reduction effects. Subsequently, further research was carried out on drag reduction based on flow field control. This analyzed the impact of adding deflectors at the spray compressor exit, on the hull bottom, and inside the spray compressor on the magnitude of the resistance peak and the speed at which this peak occurs. Experimental verification demonstrated that: Through hull shape optimization, the resistance coefficient peak can be reduced from 0.226 to 0.181, a reduction of 19.9%. Adding deflectors inside the spray compressor can further reduce the resistance coefficient peak to 0.169, a reduction of 6.6%, while simultaneously reducing the peak speed by 15.2%. Through the combined application of these two methods, the goal of the remaining acceleration at the resistance peak is not less than 0.1g was successfully realized.
    Research on Anti-skid Control Method and Braking Torque Experimental Verification for Full Electric Braking of UAVs
    WuChao, YangFan
    Available online:January 19, 2026, DOI:
    [Abstract] (403) [HTML] (0) [PDF 1.22 M] (250)
    Abstract:
    The all-electric braking system, characterized by structural simplification, rapid response dynamics, and precise control capabilities, has emerged as an important development direction for small-to-medium unmanned aerial vehicles (UAVs). This study establishes a comprehensive taxiing model for a specific UAV platform, integrating aircraft dynamics and tire-runway adhesion models. An anti-skid braking control algorithm based on the slip velocity gradient was developed. Through simulation analysis, the taxiing simulation results of the UAV under three different runway conditions: dry, wet, and icy are obtained. Experimental validation conducted on a brake torque test bench demonstrated close alignment with simulation outcomes. The results demonstrate that: The established UAV taxiing model and anti-skid control model exhibit favorable simulation performance; The slip velocity-based anti-skid control strategy enables effective slip ratio maintenance on icy runways while preventing complete wheel lockup and brake system failure.
    Research on the Effects of Static Aeroelasticity on High-Aspect-Ratio-Wing & Twin-Tail Configuration Aircraft
    WuHongyu, Wei Haisu, Liu Qinghang, Li Ni
    Available online:January 12, 2026, DOI:
    [Abstract] (418) [HTML] (0) [PDF 1.70 M] (244)
    Abstract:
    The high-aspect-ratio-wing & twin-tail configuration aircraft significantly improves flight performance by enhancing low-speed aerodynamic efficiency. However, the deformation of its flexible structure under aerodynamic loads has a non-negligible impact on aerodynamic characteristics and stability/control characteristics. To enhance design reliability, this study investigates the effects of static aeroelasticity on aerodynamic characteristics. A three-dimensional aerodynamic grid and a structural dynamics model were established, and fluid-structure coupling static aeroelastic simulations were conducted using finite element simulation and mesh deformation techniques. The results indicate that static aeroelastic deformation significantly alters the longitudinal and lateral aerodynamic characteristics as well as the control surface efficiency. Specifically, the lift slope increases by 10%–20%, the aerodynamic center shifts forward by 1%–8% of the mean aerodynamic chord, the side force coefficient slope decreases by 5%–10%, the yaw moment coefficient slope decreases by 10%–23%, the roll moment coefficient slope increases by 10%–34%, and the control surface efficiency varies by 10%–40%. This study provides a theoretical basis for the aeroelastic correction and optimization design of this configuration.
    Analysis of the influence of component uncertainty on the selection of cycle parameters of turbofan engine
    Fan Wei, Hu Bingqian, Lao Xinpeng, Shu Yue
    Available online:January 12, 2026, DOI:
    [Abstract] (425) [HTML] (0) [PDF 764.98 K] (308)
    Abstract:
    Uncertainty analysis effectively enhances the robustness of aero-engine design. This study proposes a method that integrates Monte Carlo simulation to develop an engine performance prediction model that accounts for component-level parameter uncertainties. By generating a sample set of cycle parameters combinations, the uncertainty distribution of engine performance parameters and their compliance probabilities under different operating points are obtained. The performance realization levels at specified confidence levels are analyzed. The cycle parameter scheme meeting the design requirements is determined through comprehensive trade-offs between implementation risks under current technical capabilities and performance design margins. During the preliminary design phase of engine system concepts, the proposed method can effectively enhance the robustness of the design outcome and mitigate development risks. By comparing with the design specifications and experimental data of a specific engine type, both the rationality of its cycle parameter selection and the feasibility of the method proposed herein are demonstrated.
    Research on Flight Trajectory Prediction Based on an Improved Transformer Approach
    qinmingqi, yuanyige, mengxiaoyue, yangyang
    Available online:January 12, 2026, DOI:
    [Abstract] (478) [HTML] (0) [PDF 1.65 M] (269)
    Abstract:
    Accurate flight trajectory prediction is essential for trajectory-based air traffic management (TBO). To address the inherent complexity of the trajectory prediction problem and the limitations in current prediction accuracy, this study proposes an enhanced Transformer-based prediction method incorporating a Spatial Attention Mechanism (SAM). The encoder integrates the SAM structure to enable joint modeling of spatiotemporal features within flight trajectory data. The flexible design of the encoder allows it to capture global dependencies while simultaneously enhancing local pattern awareness. This improved architecture significantly enhances the model’s ability to learn trajectory-related features, thereby improving the overall prediction accuracy. Experimental results demonstrate that the proposed method achieves superior performance in both longitude and latitude predictions, indicating that the integration of the spatial attention mechanism effectively enhances the precision of flight trajectory forecasting.
    Research on Autorotation Landing Manipulation Strategy Based on CNN-GRU-SE
    weihaixing, CHEN DAWEI, WU DONGSU, LIU HUI, DONG KEQING
    Available online:January 12, 2026, DOI:
    [Abstract] (404) [HTML] (0) [PDF 1.12 M] (299)
    Abstract:
    To address the issue of safe flight following helicopter engine failure, a method based on a deep learning model is proposed to predict pilot manipulation strategies during autorotation landing. This approach employs the CNN-GRU-SE framework to establish phased pilot control models. By leveraging the powerful spatial feature extraction capabilities of CNN, the temporal sequence modeling strengths of GRU, and the channel recalibration function of the SE module, the method effectively captures spatiotemporal correlations in the dataset. The autorotation landing process is divided into three phases: rapid descent, stable descent, and deceleration landing, with specific manipulation strategy models constructed for each phase to enhance model specificity and accuracy. Model performance is validated using simulated flight test data, showing high prediction accuracy and the ability to provide effective manipulation strategies for pilots during engine failure, thereby increasing the likelihood of a safe landing.
    Research on Heading Error Fault Prediction Based on STL and BI-MLLSTM
    Guo Jiansheng, Ren Bo, Zeng Hang, Jia Xiangyang, Niu ling
    Available online:January 12, 2026, DOI:
    [Abstract] (376) [HTML] (0) [PDF 2.21 M] (384)
    Abstract:
    The increasing density of flight schedules and the complexity of flight routes have raised higher demands for the accuracy of aircraft heading precision. Therefore, accurately predicting Heading Error Fault Events (HEFE) is of significant importance for flight safety and the optimization of maintenance strategies. However, the mechanism of HEFE is complex, showing seasonal, nonlinear and irregular fluctuations. In light of this, this paper proposes a method that combines Seasonal and Trend Decomposition using Loess (STL) with a Bi-directional Multi-layer Long Short-Term Memory Network (BI-MLLSTM) for predicting HEFE. Firstly, the STL method is employed to decompose the HEFE data into highly interpretable seasonal components, trend components, and residuals. Secondly, a predictive model is constructed by leveraging the bidirectional learning and temporal processing advantages of BI-MLLSTM. Finally, compared with the traditional time series prediction model, the MAE and RMSE errors of the proposed model are reduced by 33.6 % and 33.2 % on average, which can effectively realize the HEFE prediction.
    Digital Twin Technology in Aero-Engine Manufacturing: Current Applications and Future Prospects
    li jian, chen yu, hu sijia, fan lingsong, wubaohai
    Available online:December 31, 2025, DOI:
    [Abstract] (873) [HTML] (0) [PDF 4.24 M] (301)
    Abstract:
    As a key enabling technology in the era of Industry 4.0, digital twin technology has important application value in the field of aero-engine manufacturing. This paper systematically reviews the application status, key technologies, and development trends of digital twin technology in the field of aero-engine manufacturing. Firstly, the basic theoretical framework of digital twin technology is expounded, and its five-dimensional model characteristics and the principles of system construction in the field of aero-engine manufacturing are analyzed in detail. Secondly, the specific applications of digital twin technology in intelligent manufacturing and process optimization, quality control and traceability, and digital management of the assembly process are mainly discussed. Through the analysis of typical cases such as the manufacturing of core components of engines and the intelligent manufacturing of turbine blades, the remarkable effects of digital twin technology in improving manufacturing efficiency, ensuring product quality, and reducing manufacturing costs are elaborated in depth. At the same time, this paper systematically summarizes the current technical challenges such as data acquisition and processing, model accuracy and real-time performance, system integration and interoperability, and looks forward to the future development trends such as intelligent and autonomous decision-making, full life cycle management, and cross-domain integrated applications. The research shows that the application of digital twin technology will significantly promote the development of aero-engine manufacturing towards intelligence, precision, and high efficiency, and it has important theoretical guiding significance and practical value for improving the manufacturing level of aero-engines.
    Some Thoughts on the Development of
    sunzhixiao, wenxiaoling, aixiaotian, hanzhuoyan, jiangmengcen
    Available online:December 31, 2025, DOI:
    [Abstract] (509) [HTML] (0) [PDF 1.19 M] (319)
    Abstract:
    With the rapid advancement of aviation technology, traditional aircraft design is undergoing significant transformation. Modern aircraft rely on software for 80% of their functionalities, with hardware platforms becoming standardized, while software iteration drives capability upgrades, giving rise to the concept of "software-defined aircraft." Through features such as hardware-software decoupling, modular functionality, and service-oriented architecture, aircraft upgrades and maintenance have become more flexible and scalable, enabling rapid response to user needs and customized capability generation, akin to automobiles and smartphones. This paper first reviews the development of software-defined aircraft and analyzes the characteristics of software-defined systems. Then, from three dimensions—emerging technological innovation, design paradigm shifts, and ecosystem construction—it explores related technologies with practical cases. Finally, the paper highlights that "software-defined" has become a key driver for upgrading production methods, transforming production relations, and fostering new industrial development. Future efforts should focus on unleashing its innovative potential, overcoming bottlenecks, and advancing modern aviation industry development.
    Research on Quality Management of Complex Equipment Integration Systems Based on Digital Background
    wang jiamin, Han Zhenghao
    Available online:December 31, 2025, DOI:
    [Abstract] (452) [HTML] (0) [PDF 1.80 M] (255)
    Abstract:
    During the integration of complex equipment, a key issue is the difficulty in quantifying, controlling, and optimizing the quality of the integration system, which impacts the equipment"s performance and delivery. To address this, we first conduct an in-depth analysis of the quality of the complex equipment integration system. Based on customer, result, and process orientation, a quality control model is established, forming a Quality Composite Index (QCI) algorithm to reflect the system"s dynamic quality trends. Next, focusing on the key elements of personnel, machinery, materials, methods, environment, and measurement, we optimize quality control based on process, responsibility, and data. Finally, taking an aeronautical complex equipment integration system as an example, empirical research confirms the feasibility of the model and algorithm, as well as the effectiveness of QCI-driven quality improvement measures. Our findings show that, in the digital and intelligent context, the QCI algorithm and quality control model for complex equipment integration systems actively contribute to quality enhancement.
    Research of Airworthiness Certification Regulations and Means of Compliance for Installed Physical Secondary Barrier
    XIE Jiang, TAN Jinyu, XI Xulong, SHI Xiaopeng
    Available online:December 31, 2025, DOI:
    [Abstract] (416) [HTML] (0) [PDF 1.62 M] (264)
    Abstract:
    The Installed Physical Secondary Barrier is a new equipment of security of civil aviation aircraft which used for offering additional protection when the cockpit door is open during flight. In 2023,Federal Aviation Administration (FAA) issued Amendment No.25-150,No.121-389 and Advisory Circular (AC) 25.795-10 and set requirements for the airworthiness of the Installed Physical Secondary Barrier and providing recommendations for means of compliance. However, there is no content or requirements related to the Installed Physical Secondary Barrier within the existing civil aviation regulatory system in China. Based on the relevant regulations issued by the FAA, this paper interprets and analyzes the airworthiness requirements, compliance methods, specific design concepts, and post-implementation benefit-to-cost ratio of installed physical secondary barrier. It integrates relevant patents, research reports, and materials related to installed physical secondary barrier published aboard. Research has found that some requirement should be considered at the same time such as barrier can delay behavior of attack for at least 5 seconds, provide clear visibility on both sides of the barrier, people can’t touch the flight deck door by through the barrier and so on when develop the regulations of airworthiness of Installed Physical Secondary Barrier. At present, administration can only propose installation requirements to aircraft which newly delivered that are operated by airlines under Part 121 because of considering the combination of whole safety and cost effectiveness.
    Research on defect detection of inertial navigation PCB based on PNC-YOLOv8
    MA Pengsen, HAO Wei, LIN Xingwei, SHI Shengzhi, GAO Kejin
    Available online:December 31, 2025, DOI:
    [Abstract] (479) [HTML] (0) [PDF 8.92 M] (250)
    Abstract:
    In order to solve the problems of high complexity, low accuracy and low efficiency of circuit board defect detection in inertial navigation maintenance, an improved YOLOv8 algorithm PNC-YOLOv8 was proposed. Firstly, a high-resolution small target detection layer is introduced to construct a multi-scale feature pyramid, which effectively enhances the feature expression ability of small defects. Secondly, a new NAMAttention attention mechanism is embedded in the backbone network to improve the feature discrimination ability in complex backgrounds by establishing cross-channel long-range dependencies. Finally, the CBAM attention module was integrated in the feature fusion stage, and the reinforcement of local key features was realized through the channel-space collaborative attention mechanism. The results on the dataset PKU-Market-PCB show that the average accuracy of PNC-YOLOv8 network reaches 93.8%, which is 3.9% higher than that of the basic network YOLOv8, and the performance is also significantly improved compared with other mainstream detection networks, and its single-frame detection speed reaches 100ms. The PNC-YOLOv8 network provides a new solution for circuit board defect detection in inertial navigation maintenance, which has certain application value.
    A Review of the Development of Rotorcraft Transmission System Configurations
    Wang Haiwei, Li Huijie, Kang Lixia, She Yixi, Xu Wenbo
    Available online:December 22, 2025, DOI:
    [Abstract] (585) [HTML] (0) [PDF 2.71 M] (327)
    Abstract:
    With the widespread application of rotorcraft in both military and civilian fields, their transmission systems are evolving toward higher speed, intelligence, and unmanned operation. Based on rotor configuration and propulsion mode, this paper categorizes rotorcraft into three types: compound rotorcraft, tiltrotor aircraft, and hybrid/electric rotorcraft. The structural characteristics of the transmission systems for these types are analyzed in detail. Additionally, the future development trends of rotorcraft transmission systems are explored, focusing on technologies such as power split technology, variable-speed transmission, non-tilting engines, and electric tail rotor drives. Through a comprehensive analysis, this paper concludes that future rotorcraft transmission systems will primarily evolve toward three configurations: coaxial rotorcraft with propellers, tiltrotor aircraft, and hybrid/electric rotorcraft, it aims to provide valuable references for the development of rotorcraft transmission systems.
    Review of air traffic flow prediction based on spatio-temporal characteristics
    shen di, peng yating, gao yiran, yu fuping
    Available online:December 22, 2025, DOI:
    [Abstract] (390) [HTML] (0) [PDF 731.53 K] (229)
    Abstract:
    With the continuous growth of air traffic flow, air traffic congestion and delay problems are becoming more and more prominent, which puts forward higher requirements for air traffic management system. This paper reviews the research on air traffic flow prediction based on spatio-temporal characteristics, and focuses on the key spatio-temporal characteristics of air traffic flow, such as chaotic characteristics, fractal characteristics and multi-scale characteristics, and discusses the application of these characteristics in air traffic flow prediction model. This paper systematically reviews the research context of air traffic flow prediction in recent years, summarizes three main prediction technologies based on 4D trajectory prediction method, model-driven method and data-driven method, and looks forward to the future development direction of air traffic flow prediction based on spatio-temporal characteristics, in order to provide theoretical reference for the development of intelligent air traffic management.
    Application of integration of FMEA and key characteristics analysis on civil aircraft airborne product
    XU Liangjun, SHEN DaLin, NA Hong, ZHANG Aiguo
    Available online:December 22, 2025, DOI:
    [Abstract] (419) [HTML] (0) [PDF 615.43 K] (390)
    Abstract:
    In order to solve the problem that quantitative analysis method and analysis process for key characteristics (KCs) analysis are lacked, current research status is analyzed, relationship between Failure Mode and Effect Analysis (FMEA) and civil aircraft airborne product development process, standard definitions of KCs, relationship between FMEA and KCs analysis are also analyzed. Furthermore, the integrated model and process of FMEA-KCs analysis are built, KCs are identified by evaluating failure effects through FMEA method and mapping relationship between functional KCs and KCs. It is demonstrated through an example that the integration of FMEA and KCs analysis contributes significantly to product development application.
    Research and application of civil aircraft requirement validation methodbased on RAAD analysis
    SHEN Yongguang, LIN Dingfa, ZHAO Zhiqiao
    Available online:December 22, 2025, DOI:
    [Abstract] (469) [HTML] (0) [PDF 1.17 M] (327)
    Abstract:
    The requirement validation process of civil aircraft is one of the important process of an aircraft development and airworthiness certification. Common civil aircraft requirement validation methods mainly include requirement tracing, review, analysis, similarity, modeling and testing. The existing civil aircraft requirement validation methods cannot systematically characterize the sources of requirement, the correlation between requirement, requirement allocation, and the analysis and action of requirement. In this paper, based on the existing civil aircraft requirement validation methods and considering the relevant factors of systematic requirement validation, a requirement validation method based on Requirements Allocation and Analysis Document(RAAD) is proposed, and has been used in the development of civil aircraft and systems. The application results show that this method further confirms the correctness and completeness of civil aircraft requirements, and reduces the iterative cycle of civil aircraft requirements.
    Research on visual tracking system of quadrotor target based on DSST
    anqianjun, Nie Qin, Han Jianfu
    Available online:December 04, 2025, DOI:
    [Abstract] (452) [HTML] (0) [PDF 2.21 M] (257)
    Abstract:
    With the rapid development of image recognition technology, achieving high-precision target tracking for unmanned aerial vehicles (UAVs) in complex dynamic environments has become a key issue in the field of intelligent flight control. This paper addresses the challenge of small target tracking in high-altitude strong disturbance scenarios by deeply integrating the Discriminative Scale Space Tracker (DSST) algorithm with the motion control system of a quadrotor UAV. By constructing a highly adaptive PID controller to achieve dynamic speed regulation and combining it with a speed command mean filtering algorithm, the response lag and motion jitter problems in traditional methods for three-dimensional space tracking are effectively solved. Experiments show that the optimized control system can achieve three-degree-of-freedom (pitch, yaw, and altitude) coordinated tracking control at a flight altitude of 20 meters and maintain a stable tracking speed of 5 m/s for moving targets with small feature sizes. The control strategy proposed in this study provides a reliable technical solution for the continuous tracking of targets by UAVs in complex scenarios such as emergency rescue and border patrol.
    A selective ensemble collaborative surrogate modeling method for reliability assessment of low-cycle fatigue
    Li Zhenao, Dong Xiaowei, Feng Yunwen, Lu Cheng
    Available online:December 04, 2025, DOI:
    [Abstract] (453) [HTML] (0) [PDF 1.39 M] (256)
    Abstract:
    Low-cycle fatigue reliability assessment of mechanical structures is crucial for ensuring the safety and service life of structures. To effectively conduct low-cycle fatigue reliability assessment, an elective ensemble collaborative surrogate modeling (SECSM) method was proposed based on collaborative modeling method, basis function selection strategy, and Stacking ensemble learning. First, the collaborative modeling method is used to decompose the analysis problem into sub-objectives and main objective. Then, leave-one-out cross-validation is applied to exclude surrogate models with poor precision from the basis function model family. Finally, base learners and meta-learner are selected from the remaining models for Stacking ensemble learning. The modeling characteristics and simulation performance of different surrogate models are verified through the low-cycle fatigue reliability assessment for high-pressure turbine blisk of an aeroengine under flow-thermal-structural coupling. The results show that the SECSM method has a low mean absolute error, high goodness of fit, and simulation precision, demonstrating excellent modeling characteristics and simulation performance. It provides valuable insights for low-cycle fatigue reliability analysis of mechanical structures.
    Research and principle verfication of LVC training technology for advanced trainer aircraft
    liwei, yufuzhang, zhaopingjun, wangxin, chenxiaodong
    Available online:December 04, 2025, DOI:
    [Abstract] (601) [HTML] (0) [PDF 1.62 M] (329)
    Abstract:
    LVC training is one of the important means for military powers to achieve joint tactical confrontation at low cost and systematically. In order to expand the tactical training tasks of the trainer aircraft, improve the training efficiency and reduce the training cost, an LVC training system with the characteristics of the trainer was studied. This paper analyzes the concept, training capability and technical connotation of LVC training system for foreign fighter and trainer aircraft, and focuses on the system architecture, technical architecture and key elements of LVC training for advanced trainer aircraft. Based on the LVC training architecture of the advanced training aircraft, combined with the actual situation, the LVC principle demonstration and verification environment of the advanced training aircraft is briefly explained. The communication protocol and interaction logic between the implementation node, simulator node and virtual soldier node in the training machine system are verified by simulation. The results show that the analysis of the LVC training structure and key elements of the advanced trainer meets the engineering requirements, and provides technical support for the construction of the LVC training system of the trainer.
    The aerodynamic analysis of the transition mode for a tilting wing UAV Based on the unsteady momentum source method
    Zhang Kaixu, He Guoyi, PENG CHENGBO
    Available online:November 19, 2025, DOI:
    [Abstract] (462) [HTML] (0) [PDF 6.52 M] (306)
    Abstract:
    The Tilting Wing UAV is a type of vertical take-off and landing (VTOL) unmanned aerial vehicle, during the transition mode, the interaction between the rotor slipstream and the freestream flow affects the tilting wing, creating strong unsteady aerodynamic disturbances that significantly influence the UAV"s performance. This study used the unsteady rotor momentum source method, simulate a real rotor by adding the momentum source in a dynamically changing sector areas. Using the sliding mesh technique, continuous tilting is simulated. Through numerical analysis of non-rotor, fixed-tilt, and continuous-tilting configurations, studying the influence of freestream velocity and tilting rate on the aerodynamic interaction between wings and rotors, to provide a reference for the design of a reasonable tilting mode for tilting wing UAV in take-off transition mode The results show: rotor slipstream can effectively delay the stall angle of attack; Significant discrepancies between the computational results of fixed tilt angles and continuous tilting highlight the non-negligible unsteady aerodynamic characteristics inherent in the continuous tilting process; During low-speed flight, a faster tilting speed is beneficial for increasing lift. In transition mode, The tilting wing UAV require real-time adjustment of rotor speed to maintain flight attitude stability.
    The Safety-II concept and its application in the development process of flight control systems
    PENG Wensheng, XU Ming, WANG Junran
    Available online:November 19, 2025, DOI:
    [Abstract] (474) [HTML] (0) [PDF 966.38 K] (318)
    Abstract:
    The airborne flight control system, as a core subsystem of civil aircraft, demands strict safety requirements during the development process. It is necessary to satisfy rigorous airworthiness requirements and enhance the system"s dynamic adaptability and operational resilience. The traditional safety method based on accident causation and fault analysis (termed Safety-I) emphasizes fault prevention, yet it has limitations such as insufficient efficiency and flexibility in the development of complex systems. This thesis, targeting the theoretical connotation of Safety-II, analyzes its notion of enhancing safety by understanding and reinforcing the successful operation mechanisms of the system and discusses the applicability of Safety-II in the development of complex airborne systems. With the airborne flight control system as the object, this thesis systematically analyzes the application process of Safety-II in all stages of the entire life cycle, from requirement decomposition to operation and maintenance. Based on the Safety-II theoretical approach, by concentrating on the optimization of normal operating conditions, it analyzes the effects on the efficiency of requirement decomposition, the ability of dynamic design adjustment, the efficiency of test verification, and the airworthiness certification process, and presents case analyses. The research of this thesis offers practical references for improving the development efficiency and safety of the flight control system and lays a foundation for the promotion and application of the Safety-II theory in the aviation manufacturing industry.
    Research on the Layout Method of Electrostatic Discharger for Aircraft
    Shaofeng ZHANG, Xiong Xiu, KONG Deliang, HAO Nana
    Available online:November 19, 2025, DOI:
    [Abstract] (587) [HTML] (0) [PDF 1.21 M] (312)
    Abstract:
    During flight, aircraft accumulate high-potential precipitation static on their surfaces due to air friction and particle collisions, which can interfere with communication and navigation systems or even damage critical equipment. Electrostatic dischargers are essential protective measures, and their layout is critical to effective static discharge. This study, based on the mechanisms of static generation and empirical formulas, investigates key aspects such as the calculation of the required number of dischargers, optimization of installation locations, the impact of device performance parameters, and simulation-based validation methods. By integrating theoretical analysis and simulation validation, a scientific layout method for electrostatic dischargers is proposed, significantly enhancing the safety and efficiency of static protection design. The findings provide valuable technical references for the static protection design of aircraft.
    Research of Fault Diagnosis and Prediction for a Certain Cabin Pressure Regulator
    Xue Zhaoming, Zhao Yuxin, Wan Fangyi, Xi Zeyang, Liang Zhenyu
    Available online:November 19, 2025, DOI:
    [Abstract] (452) [HTML] (0) [PDF 2.76 M] (284)
    Abstract:
    The cabin pressure control system, consisting of a regulator, sensors, and control units, is a complex and critical component of modern aircraft. Comprehensive fault diagnosis and prediction of this system contribute to enhancing aircraft reliability and safety, reducing maintenance costs, and improving the efficiency and service quality of air transportation.To improve the performance and reliability of the cabin pressure control system, this paper proposes a fault diagnosis method based on machine learning and deep learning. Focusing on the cabin pressure regulator as the core diagnostic component, a system-level data acquisition and processing framework is established to extract features from multi-source sensor signals. Support Vector Machines (SVM) and Convolutional Neural Networks (CNN) are employed to classify and predict the operational states. Experimental results show that the proposed method can accurately identify abnormal conditions of the regulator, significantly enhancing fault prediction capability and providing technical support for intelligent maintenance of the aircraft cabin environmental control system.
    Structure Reliability analysis of civil aircraft based on improved Kriging based on classification enhancement strategy
    Xu Guiqiang, FENG Yunwen, CHEN Junyu, ren qizhen
    Available online:October 21, 2025, DOI:
    [Abstract] (420) [HTML] (0) [PDF 3.98 M] (302)
    Abstract:
    The reliability analysis performance of civil aircraft structures directly affects whether the corresponding functions can be realized normally. To improve the accuracy and efficiency of reliability analysis of nose wheel steering gear, an improved Kriging based on classification enhancement strategy (IK-CES) is proposed. The classification enhancement strategy aims to achieve global optimization of the design point for the failure domain through population classification and individual incentives. Improving Kriging by incorporating the indicative impact of samples on the overall functional function into the Kriging modeling mechanism, which adaptively simulates the functional relationship between input variables and output response. Taking the bending stress of the nose wheel steering gear of civil aircraft as a case study, the effectiveness of the proposed method in functional function modeling and failure probability estimation is verified by combining finite element analysis data. The case results show that the proposed IK-CES method can capture the optimal design point and minimize the indication error, improve the reliability analysis performance of the bending stress of the nose wheel steering gear of civil aircraft, and ensure the functional realization of the nose wheel steering gear of civil aircraft.
    Vibration reduction of bending-torsion coupling dry friction oscillator based on two-dimensional normal load distribution
    huyanhua, tangxianju, huzhian, hanbing, zhaoxiong
    Available online:October 13, 2025, DOI:
    [Abstract] (504) [HTML] (0) [PDF 2.08 M] (320)
    Abstract:
    Attaching dry friction dampers to turbine blades can effectively reduce vibration and suppress high-cycle fatigue failure. As the design speed of engines continues to increase, dry friction damping blades may excite torsional vibration modes during service. Considering the micro-slip characteristics of interface and bending-torsional coupling vibration, in this paper, a bending-torsional coupling dry friction oscillator with a mass of finite dimensions is introduced. By modeling distributed friction force through multiple contact points and discretizing the two-dimensional dry friction interface, the dry friction contact element for analyzing the bending-torsion coupling vibration and the discrete numerical calculation method are established. Three typical normal load distributions (uniform, convex, and concave) are designed, and the steady-state vibration energy reduction rate and displacement amplitude reduction rates are introduced as evaluation criteria for overall and all directions vibration reduction effects, respectively. Combined with micro-slip contact analysis of interface, the fourth-order Runge-Kutta method is applied to solve the dynamic response of the bending-torsion coupling dry friction oscillator. The influence of key parameters on the vibration reduction characteristics of bending-torsion coupling vibration under different normal load distributions is deeply researched. Simulation results demonstrate that the proposed numerical method for the bending-torsion coupling dry friction oscillator has high computational efficiency. Among the different normal load distributions, the concave and uniform distributions have better vibration reduction effects than convex distribution. Furthermore, the vibration reduction effect of the system is significantly improved through the design of normal load distributions. The conclusions provide valuable insights for the engineering design of bending-torsion coupling dry friction damping systems.
    Data Fusion-Based Method for Reconstruction of Aerodynamic Thermal Sparse Wind Tunnel Test Data
    Wang Ze, Li Yang, Cheng Siye, Liao Menghao, Song Shufang
    Available online:October 13, 2025, DOI:
    [Abstract] (454) [HTML] (0) [PDF 3.29 M] (299)
    Abstract:
    Data-driven modeling methods have become one of the main techniques for predicting aerodynamic thermal behavior in hypersonic applications. However, due to the limitations of wind tunnel experimental conditions, the spatial distribution of aerodynamic thermal wind tunnel experiment data is often sparse, and the sample size is relatively small. This poses challenges in constructing high-performance data-driven aerodynamic thermal prediction models. To address these issues, this paper proposes a reconstruction method for sparse aerodynamic thermal wind tunnel experiment data, integrating a multi-fidelity data fusion modeling approach. First, low-fidelity simulation data for aerodynamic thermal calculations are introduced based on the sparse aerodynamic thermal wind tunnel experiment data to construct a training set for the deep neural network (DNN). Then, a weighted loss function for the DNN is designed. The weighted loss function consists of two components: the loss from the wind tunnel experimental data and the loss from the low-fidelity simulation data. Finally, the DNN is trained to obtain the reconstruction results of the sparse aerodynamic thermal wind tunnel experiment data. Aerodynamic thermal reconstruction is conducted using aerodynamic thermal sparse wind tunnel experiment data from hypersonic wind tunnels for different geometries, including double-ellipsoid, blunt-cone, bicone, and 25°/55° bicone. The results indicate that not only is the normalized root mean square error of the aerodynamic thermal reconstruction results within 9% of the wind tunnel experimental data, but the volume of the reconstructed aerodynamic thermal data is also comparable to that of the low-fidelity numerical simulation results, allowing for a detailed visualization of the aerodynamic thermal distribution in cloud plot form.
    Research on aircraft ground test methods for aircraft lighting system
    Zhang Dongmei, ZOU YUBO, HE BINBO, MA PINGSHE, GONG Liang, GAO XINGSHENG
    Available online:October 13, 2025, DOI:
    [Abstract] (509) [HTML] (0) [PDF 1.91 M] (261)
    Abstract:
    The external lighting system of the aircraft is an important system affecting the safety of the aircraft. In addition to carrying out necessary equipment qualification tests, the aircraft system usually also needs to carry out on-board ground tests of the lighting system, which is a quantitative test of the performance of the lighting lamps. In China, there are some HB and GJB documents that introduce the test content of lighting, but only put forward detailed testing requirements for the quantitative test of lighting, and do not explain the testing methods and equipment, and the actual test cannot be effectively carried out according to the testing requirements. In view of the testing requirements of the standard documents, this paper analyses the detection principle of the in-flight ground test, explains what kind of testing equipment is selected, and finally forms a complete set of in-flight ground test implementation methods and steps for the aircraft external lighting system. Taking the on-board ground test of the lighting system of a typical aircraft as an example, the test criteria and test data processing instructions are listed in detail. This paper can provide guidance for various types of aircraft to carry out on-board ground tests of lighting systems, and provide a reference for airworthiness certification tests.
    Design of Composite Wing-Battery Integrated Structure for VTOL Fixed-Wing UAVs
    Yinghui Zhao¹, Kaomin Zhang¹, Haiting Xia¹, Fenglin Tian¹, Zhenhu Miao¹, Xiaoyu Yang¹
    Available online:September 30, 2025, DOI:
    [Abstract] (506) [HTML] (0) [PDF 2.21 M] (320)
    Abstract:
    This paper focuses on a light vertical takeoff and landing fixed-wing unmanned aerial vehicle (UAV) with a maximum takeoff weight of 30kg. It addresses the layout of batteries in the UAV wings and the integrated design of wing-battery structures. A composite material wing-battery integrated structure was designed, and its load-bearing performance was analyzed through simulation to address key issues such as the transmission of forces in the structural battery in high-altitude flight environments and overall performance optimization. Utilizing ABAQUS finite element analysis software, the structure"s performance is simulated and analyzed. Post-optimization results indicate that under the load limit, the peak values of stress, strain, and deflection reduced by 8.5 MPa, 76.5με, and 0.6 mm, respectively. These represent optimization rates of 4.7%, 29.1%, and 6.3%. Furthermore, post-optimization assessments reveal a more even load distribution across the wing-battery integrated structure. The first six modal frequencies have increased, leading to enhanced overall structural Vibration resistance. Notably, there is a significant improvement in stiffness, bolstering its adaptability to the complex wind conditions encountered at high altitudes.
    Study on Cooling Performance of Ribbed Flame Tube Walls in Micro Combustor
    FU Yu, YAN Xu, YU Jnnli, LIN Han, ZUO Hongfu
    Available online:September 30, 2025, DOI:
    [Abstract] (460) [HTML] (0) [PDF 2.92 M] (364)
    Abstract:
    Micro-combustor features small size and compact layout, leading to poor heat dissipation. Applying ribbed cooling design to micro-turbojet engine combustion chambers significantly improves heat dissipation performance. A simplified model of the flame tube was established, with ribs added at different positions on flame tube walls. Three groups of ribs were arranged at varying positions to analyze the effects on airflow within combustor across an inlet velocity range of 10 m/s to 100 m/s, as well as the impact of different rib configurations on heat dissipation. Results show that adding ribs compresses airflow channels, causing acceleration in upstream sections. As airflow passes over ribs, compression effect diminishes, leading to reduced velocity. At the same inlet velocity, temperature variation in the third flame tube is greater, as ribs are closer to inlet and less affected by internal environment, providing better cooling. When ribs are positioned farther from airflow inlet, rear wall influence leads to more turbulent airflow and less stable heat dissipation. At lower airflow velocities, between 10 m/s and 60 m/s, rib cooling effect becomes more pronounced, but at higher velocities (60 m/s to 100 m/s), increased flow rate weakens cooling. These findings hold theoretical significance and practical value for ribbed heat dissipation structure design in micro-combustors.
    Study of vibration and flutter characteristics of sandwich panel with a magnetorheological fluid core in supersonic airflow
    gao ze hao, zhou jian, xu ming long
    Available online:September 23, 2025, DOI:
    [Abstract] (418) [HTML] (0) [PDF 936.41 K] (304)
    Abstract:
    Modern supersonic aircraft employ large-area skin panels to enhance aerodynamic performance and stealth characteristics. However, in complex and harsh mechanical environments, the risk of panel flutter is increasing. This paper aims to improve the flutter stability of the panels by introducing a magnetorheological fluid (MRF) sandwich structure, and to investigate its vibration and flutter characteristics in supersonic airflow. The three-node mindlin plate element (MIN3) and first-order piston theory aerodynamic force with an airflow yawed angle have been employed to establish the aeroelastic equation of three-dimensional MRF sandwich panel. Under the simply supported boundary condition, the influence of parameters such as magnetic field strength, thicknesses of MRF layer and upper and lower surface layers, and airflow yawed angle on the modal frequency and critical flutter dynamic pressure of the sandwich panel is studied by solving the eigenvalue. The results indicate that the modal frequency and flutter critical dynamic pressure of MRF sandwich panel increase with the increase of magnetic field strength. However, when the magnetic field strength increases to a certain value, they will decrease by the increase in magnetic field strength. When the magnetic field strength is constant, the modal frequency decreases with the increase of the MRF layer thickness, and increases with the increase of upper surface layer thickness. The flutter critical dynamic pressure of the panel decreases first and then increases with the increase of the MRF layer thickness, and increases with the increase of the upper surface layer thickness. When other parameters remain unchanged, the flutter critical dynamic pressure of the panel gradually decreases with the increase of the airflow yawed angle.
    The Mechanism and Effect of Pump Case Return Oil on the Temperature of Aircraft Piston Pump
    SHI Hongyu, WANG Xiaowei, KONG Ziqi, YAN Feiyun, WANG Zhanxi
    Available online:August 08, 2025, DOI:
    [Abstract] (493) [HTML] (0) [PDF 930.32 K] (388)
    Abstract:
    Aircraft piston pumps generate a significant amount of heat due to reasons such as leakage flow and mechanical friction, which often leads to overheating failures. The piston pump dissipates heat through the casing return oil, and the flow rate of the casing return oil not only determines the working efficiency of the piston pump but also affects its temperature characteristics. Based on the analysis of the heat generation mechanism and heat transfer process of the piston pump, a temperature characteristic model of a constant pressure variable displacement piston pump is established and simulated using hydraulic simulation analysis software. The temperature variation of piston pump under different volumetric and mechanical efficiencies in typical working conditions are obtained. Analysis of the temperature variation trends reveals that in the early stages of the piston pump"s operation, the lower the volumetric efficiency, the more pronounced the temperature rise of the pump itself and the casing return oil. After the piston pump has been working for a while, the lower the volumetric efficiency, the greater the casing return oil flow, and the more obvious the heat dissipation effect of the casing return oil. It is also found that as the mechanical efficiency of the piston pump decreases, the heat generation of the system increases significantly, leading to a substantial rise in the temperature of the pump casing and the casing return oil. In the actual operation of the aircraft piston pump, it is necessary to consider the issue of overheating failure of the piston pump caused by wear and other reasons leading to a decrease in mechanical efficiency.
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    Research and Analysis on Overheating Protection Design of Aviation Oil-cooled Generator
    SunLiRong, LaiShuaiLei, LiuZhuo
    2023,14(6):153-159. DOI: 10.16615/j.cnki.1674-8190.2023.06.17
    [Abstract] (747) [HTML] (522) [PDF 2.60 M] (12536)
    Abstract:
    The thermal field distribution of generator has a great influence on the failure phenomenon of the overheat protection component, which is the key parameter to be considered in the design. Based on the steady-state pressure solver and turbulence model in ANSYS software, the internal thermal field distribution of the motor under fault mode was simulated. The thermal field distribution of the stator, rotor and shell circulating oil circuit were obtained. The results show that the simulated thermal field is consistent with the actual temperature field distribution. The temperature gradient of low-melting alloy in the thermal trip mechanism is accordance with the internal thermal field distribution of the generator. It is helpful to protect the motor from overheating by changing the melting points of some key parts and the special softening temperature points of materials.
    Safety and Hazards Analysis for Unmanned Aerial Vehicle System
    Lian Tingting, cui li jie
    2020,11(4):517-523. DOI: 10.16615/j.cnki.1674-8190.2020.04.009
    [Abstract] (1813) [HTML] (0) [PDF 833.51 K] (10351)
    Abstract:
    The tactical performance and advantages of unmanned aerial vehicle (UAV) system will play an increasingly important role in future high-tech warfare and civil aviation. However, due to the different characteristics of manned and unmanned aerial vehicle flight accidents, the safety analysis and management measures of manned aerial vehicle are not suitable for UAV system. Therefore, the safety and hazard analysis of UAV system is carried out to construct the UAV security management framework. Firstly, according to the statistical analysis of UAV system flight accidents, the characteristics of UAV system accidents are concluded. And then the safety of UAV system is defined, the classification of severity and its corresponding acceptability for UAV system are presented. Finally, hazard analysis is carried out from design, crew training and operation fields.
    A Survey on Anti-UAV Technology and its Future Trend
    ZHANG Jing, ZHANG Ke, WANG Jingyu, LV Meibo, WANG Pei
    2018,9(1):1-8. DOI: 10.16615/j.cnki.1674-8190.2018.01.001
    [Abstract] (4744) [HTML] (0) [PDF 1.89 M] (10189)
    Abstract:
    Recently, with the continuous development and improvement of UAV technology, it not only plays an important role in the military field but also has been widely used in the civil field. However, the continuous reduction in the use of the UAV brings tremendous convenience to people"s life and production. At the same time, the abuse of UAV also pose a huge safety hazard to the country, society and citizens. Therefore, the demand for countermeasure and pro-tection against low-altitude drones is very strong in the military and civilian areas. This article focuses on the ap-plication of UAV in different fields, introduces the safety problems caused by UAVs flying at low altitude, and discusses the types and sources of threats. On this basis, this article focuses on the domestic and foreign anti-UAV technology in-depth analysis of the status quo, systematically on the existing anti-UAV technology and related systems, advantages and disadvantages are introduced. In addition, the future development trend of key technologies of detection and protection in low-altitude anti-aircraft UAV is analyzed and discussed based on the intelligent, integrated and autonomous research and development of low-altitude UAV systems.
    Development and Trend Analysis of VTOL Fixed Wing UAV
    WANG Kelei, ZHOU Zhou, MA Yuewen, DU Wanshan, GUO Jiahao, LI Xu, ZHANG Yang, SUN Pengbo
    2022,13(5):1-13. DOI: 10.16615/j.cnki.1674-8190.2022.05.01
    [Abstract] (2096) [HTML] (1977) [PDF 3.67 M] (8676)
    Abstract:
    The vertical takeoff and landing (VTOL) fixed wing unmanned aerial vehicle (UAV) has many advantages, such as low requirements for takeoff and landing site, good maneuverability, high cruise speed and long endurance, etc., which is a hot topic in the aviation field. This paper describes the existing VTOL fixed wing UAV development status and their features around the world, and then analyzes the technical problems faced by these different types of VTOL fixed wing UAVs. It indicates that the VTOL fixed wing UAV with higher cruise speed, longer battery life, and stronger ability of task load seems to be the main developing direction and inevitable trend in the future. Although the tilting rotor configuration and tailstock configuration are still the mainstream configuration of the VTOL fixed wing UAV in nowadays, the distributed electric propulsion (DEP) VTOL fixed wing UAV technology will become the hottest issues in the field of aerospace, therefore, it is necessary to enhance the evolutionary research in the new-concept configurations and new principles of the high-performance VTOL fixed wing UAVs.
    Analysis of Development Trend and Design Technology of Refueling Boom
    Wang Xiuxiang, Gao Xu, Gao Yakui
    2020,11(3):302-307. DOI: 10.16615/j.cnki.1674-8190.2020.03.002
    [Abstract] (1894) [HTML] (0) [PDF 1.65 M] (7715)
    Abstract:
    Air refueling technology to a certain extent reflects the strength of a country’s air force,and this technology has been widely concerned. the paper summarizes the development history of hard type air tanker. Then suggests a concept of generation about hard type air tanker. The typical feature of the first generation was that the bomber being used as the refitting platform, which limited by the payload of the carrier and only provided limited external fuel supply. The typical features of second generation were refitted on the transporter, the effective external oil supplywas increased, and the fuel for the high-speed receiver at that time was added. . The third generation had a certain transportation capacity, equipped with advanced hard refueling device system, and set up a special refueling operator. The fourth generation had a certain cargo transportation capacity and developed to soft and hard three-point refueling. It had an advanced hard refueling device system. The fuel dispenser directly observed the fuel receiver and operated in a comfortable environment.The fifth generation required soft and hard refueling capability, air receiving capability, cargo and personnel transportation and medical evacuation capability, command, control and communication capability, network center capability and high survivability. The key technologies, such as general layout design technology, structure and mechanism design technology, control system design technology, were extracted to provide technical support for future equipment reform.
    An Overview on Development of Small Turbine Engines for Missiles
    Xue Ranran, Li Fengchao, Ren Lilei
    2018,9(1):18-27. DOI: 10.16615/j.cnki.1674-8190.2018.01.003
    [Abstract] (3428) [HTML] (0) [PDF 1.88 M] (7490)
    Abstract:
    To provide superior cruise thrust for high subsonic intermediate-long range missiles, small turbojet and turbofan engines have become the competitive focus for militarySpowers. The turbine engines for missiles are characteristic of low cost, short life, small size, high speed, low pressure ratio, severe volumetric heat release rate and various starting or ignition methods. They were widely equipped on strategic and tactical weapons, such as cruise, anti-ship and air-to-ground missiles. The development situation of small turbine engines within 100～700daN since 1970s is summarized and analyzed comprehensively in this paper, including well-known products, main technical parameters, basic features, application status and development trend. The study can provide references for the research work on missile propulsion systems. Lower cost, less fuel and fewer parts will be the future goals. The propfan engines have advantages of nice high subsonic performance and low fuel consumption, and the pulse detonation turbine engines possess high thermodynamic cycle efficiency and simple structure. They are both important development directions of advanced turbine engines for missiles.
    Simulation of the Expansion Process of Different Folded Cylindrical Airbags
    xueqiwen, wangxiaoteng, heyiqian, guomin, liuxudong, ezhijia
    2021,12(3):161-170. DOI: 10.16615/j.cnki.1674-8190.2021.03.20
    [Abstract] (1375) [HTML] (0) [PDF 8.07 M] (7138)
    Abstract:
    The process of folding and inflating the cylindrical airbag is complicated, and there are many inconveniences in using experimental methods to study its expansion process. Two different folding methods are proposed for the cylindrical airbag and the corresponding numerical analysis models are established respectively. The nonlinear dynamics software is used to study the dynamic application characteristics of the cylindrical airbag after being folded, which will affect the skin stress during the airbag expansion process. The factors of volume and internal pressure curve change are analyzed, and the influence of different folding methods and external environmental parameters on the dynamic characteristics of the cylindrical airbag is discussed. The results show that the two folding methods have their own advantages in storage space and material strength. In addition, in the environmental parameters, the external pressure has a greater impact on the stable state of the airbag after expansion, while the temperature has no obvious effect.
    Analysis of Classifications and Characteristic of Additive Manufacturing (3D Print)
    Yang Yanhua
    2019,10(3):309-318. DOI: 10.16615/j.cnki.1674-8190.2019.03.003
    [Abstract] (2401) [HTML] (0) [PDF 1.21 M] (6815)
    Abstract:
    The Additive Manufacturing(3D Print) was widely studied and used in recent years, but there wasn"t a systematic, distinct and accurate classification about the Additive Manufacturing. The Additive Manufacturing was divided into 3 sorts and 13 sub sorts according to the category and state of the added materials and heat source of the manufacturing in this paper, as well as the principle, characteristics and trend of the each sorts of the Additive Manufacturing method were analyzed.
    Airborne Software Quality Assurance and Management Based on DO-178C
    ZHOU Pei
    2021,12(6):161-166. DOI: 10.16615/j.cnki.1674-8190.2021.06.20
    [Abstract] (1525) [HTML] (0) [PDF 533.70 K] (6438)
    Abstract:
    DO-178C clearly requires that the software quality assurance (SQA) process must be included in the airborne software integration process as an acceptable compliance standard for airborne software airworthiness. Based on the software life cycle definition, process and data of airborne software, this paper analyzes the implementation of the software quality assurance process based on DO-178C from the three aspects of objectives, activities, and compliance review. With software project quality management techniques and tools, the DO-178C-based software quality management method is explored from the three processes of planning software quality management, managing software quality, and controlling software quality, and some practical engineering suggestions are given. By using both software quality assurance and quality management, evidence of airworthiness requirements can be generated to provide confidence in civilian airborne software that meets the requirements, effectively ensuring its quality and continuous improvement.
    Review on the Research of Airspace Gridding Method and its Application in Air Traffic Management
    ZHU Yongwen, XIE Hua, PU Fan, ZHANG Ying, HE Weiwei
    2021,12(4):12-24. DOI: 10.16615/j.cnki.1674-8190.2021.04.02
    [Abstract] (2031) [HTML] (0) [PDF 1.57 M] (6282)
    Abstract:
    The traditional airspace theory is faced with a series of problems such as the rapid growth of traffic density and the complex multi-class heterogeneity of the airspace controlled objects. Therefore, it is urgent to make research on the digital modeling of airspace and develop a new four-dimensional space-time framework of air traffic, then to launch a new collaborative management of airspace and air traffic flow on this basis. This paper focuses on the summary of the horizontal grid model and the three-dimensional airspace grid model, and surveys the research on the application of airspace grid method in air traffic management. On this basis, the research emphasis and development trend of the airspace gridding and digitalization are comprehensively analyzed. The research results aim to provide scientific guidance for the sustainable development of theory and application for airspace gridding and digitization.
    The Design Optimization and Strength Analysis of a Heavy-duty Quadrotor UAV
    LIU feng, YU Hui, GAO Hong-jian, DAI Hai-liang, MA Jia
    2018,9(1):99-106. DOI: 10.16615/j.cnki.1674-8190.2018.01.013
    [Abstract] (3441) [HTML] (0) [PDF 1.77 M] (6201)
    Abstract:
    A heavy-duty quadrotor UAV which has the features of foldable, light weight, high strength is designed according to the performance requirements. The maximum payload of this UAV is 10kg. The finite element model of the quadrotor structure is established. Static and buckling analysis of the UAV arm and central plate are carried out based on the actual loading cases. The layer structures of the arm and central plate are optimized. The strength, stiffness and stability of the UAV are verified. Compared with the initial layer structures, the weight of the arms drops by 43%, and the weight of the central plate drops by 35%. The weight of the UAV structure drops by 560 grams. The lowest weight requirement is achieved. An UAV static test platform is built, and the structure static loading test is completed. The strain relative error between the test value and the analysis value is less than 15%. The reliability of the UAV finite element model and the optimized layer structures is verified.
    A Survey of Low Altitude UAV Path Planning Algorithms
    LiuQinjian, ShuLisheng, liu gang, li ao
    2023,14(2):24-34. DOI: 10.16615/j.cnki.1674-8190.2023.02.03
    [Abstract] (2044) [HTML] (1827) [PDF 1.07 M] (5863)
    Abstract:
    With the diversification of UAV application scenarios, many scholars have studied UAV path planning algorithms. This paper summarizes the UAV path planning algorithms commonly used by scholars in recent years, summarizes the principles, applicable scenarios, advantages and disadvantages of the algorithm, and makes a prospect of UAV path planning algorithms based on the development status of UAVs.
    Overview of Wireless Avionics Intra-Communication Network Technology
    Fan Xianghui, CHEN Changsheng, SHI Yan, YANG Jianxi
    2021,12(1):129-135. DOI: 10.16615/j.cnki.1674-8190.2021.01.017
    [Abstract] (2068) [HTML] (0) [PDF 1.19 M] (5855)
    Abstract:
    The Wireless Avionics Communication Technology in the civil aircraft will be an important technology for the development of the next generation aircraft, which can further reduce the weight of the aircraft, enhance the safety of the aircraft, and improve the operation economy of the civil aircraft. This paper describes the definition of wireless Avionics Intra-Communication (WAIC) network, summarizes the research status of WAIC network at home and abroad, analyses the characteristics of WAIC network, and gives the key technologies, such as network architecture, time synchronization, network management, network security and hardware design in the process of WAIC network design. It also puts forward the realization of 4.2GHz-4.4GHz wireless communication based on software defined radio in WAIC network.
    Preliminary Thoughts on the Combination of Artificial Intelligence and Aerodynamics
    zhangtianjiao, qianweiqi, zhouyu, helei, shaoyuanpei
    2019,10(1):1-11. DOI: 10.16615/j.cnki.1674-8190.2019.01.001
    [Abstract] (2815) [HTML] (0) [PDF 562.11 K] (5720)
    Abstract:
    There are a great deal of influence on many fields of society as a result of the new round of technological revolution and industrial revolution centered on artificial intelligence. All the aerospace powers have conducted many useful experiments and explorations in the combination of artificial intelligence and aerodynamics. The development history and status quo of artificial intelligence technology are reviewed in this paper, the applications of artificial intelligence in wind tunnel test, numerical calculation and flight test are discussed in the background of big data era, the role of artificial intelligence in assisting mass aerodynamic data analysis and knowledge discovery is analyzed in detail, the application values of artificial intelligence in aerodynamic modeling and advanced aircraft design are investigated, the future development direction and challenges of combination of artificial intelligence and aerodynamics are prospected.
    A Review of the Study on the High-angle-of-attack Flight Problems of Military Aircraft
    zhangzijun, zhaotong, sunye, li hongxin
    2022,13(3):74-85. DOI: 10.16615/j.cnki.1674-8190.2022.03.09
    [Abstract] (1273) [HTML] (1067) [PDF 2.69 M] (5597)
    Abstract:
    WVR air combat is still inevitable in future. Accurate and agile nose-pointing capability at high-angle-of-attack is still essential and significant for fighter to survive and gain air superiority . This paper in terms of military fighter configura-tion reviews the technology and design considerations of high angle of attack problems of which wind tunnel experi-ments, aerodynamic modeling, nonlinear flight dynamics analysis, control law design and flight test are discussed. The research direction of high-angle-of-attack flight in the future is prospected.
    Review of aeroengine casing containment research
    TanYi, YangShuyi, zuo jianhua, guo xiaojun, sun yaobing
    2022,13(6):17-28. DOI: 10.16615/j.cnki.1674-8190.2022.06.02
    [Abstract] (1566) [HTML] (1135) [PDF 4.25 M] (5473)
    Abstract:
    Casings are key components for the aero engine, and its containment performance is a necessary condition for ensuring flight safety. The types and structural forms of the casing related to containment are briefly introduced. Impact response, damage mechanism and containment ability of casings are summarized from aspects of theoretical researches, simulation analyses and experimental tests. Besides, test methods about casing containment and its researches progresses are analyzed. Numerical simulation researches about casing containment are introduced according to types of casing material. Finally, the containment research status of casings is summarized and the development tendency of casings containment is proposed from aspects of working condition, loading situations and optimization design.
    Analysis on Integrated Design of Military Aircraft PHM System
    jingbo, huangsonglin, wangshenglong, cuizhanbo, shengzengjin
    2022,13(3):64-73. DOI: 10.16615/j.cnki.1674-8190.2022.03.08
    [Abstract] (1329) [HTML] (1353) [PDF 1.74 M] (5284)
    Abstract:
    Aiming at the problems of lack of design standards, high complexity and low accuracy in the design and engineering application of prognostic and health management (PHM) system for military aircraft, the design requirements of data, structure and function dimensions of PHM system are analyzed. Based on the study of the relations and characteristics of the three dimensions, the three-dimensional multiphase iterative design criteria is proposed. A three-in-one design architecture of real-time health management based on embedded system, knowledge logic visualization based on knowledge graph, and PHM system modeling based on MBSE is proposed. The PHM system design process is constructed by analyzing the PHM system design strategy, which provides a method for the engineering application of military aircraft PHM system.
    Research Status of Thermal Barrier Coatings in Aero-engine Application
    PENGRUI, CHANGZHENDONG, SUNLILI
    2020,11(3):308-315. DOI: 10.16615/j.cnki.1674-8190.2020.03.003
    [Abstract] (2058) [HTML] (0) [PDF 1.36 M] (5033)
    Abstract:
    With the increasing worse environment for aero-engine, the challenges for thermophysical properties and thermostability were put out. This article introduced methods of thermal barrier coatings and the choices of material at present. Besides, up-to-date research of material for better thermophysical properties and better performance in CMAS resistance were discussed, which provided a direction for further research on TBCs.
    Key Technologies of Turbofan Engine for High Altitude Long Endurance UAV
    Wenzhanyong, Duanya
    2020,11(2):159-166. DOI: 10.16615/j.cnki.1674-8190.2020.02.002
    [Abstract] (2135) [HTML] (0) [PDF 1.20 M] (4777)
    Abstract:
    High Altitude Long Endurance (HALE in short ) UAV has made great development since its birth and participation in war. With the expansion of combat mission to high-risk confrontation battlefield, HALE fly-wing UAV has become a hotspot in the world today. In this paper,the requirements of HALE fly-wing UAV for turbofan engine are described, effect of key design parameters on the performance of turban engine is analyzed based on the basic principle of aero engine, the key problems and research progress of HALE fly-wing UAV are summarized. This paper has important reference value of the selection of turbofan engine for HALE fly-wing UAV and the improvement of its adaptability design.
    Research on the influence of bleeding and cooling model to the performance of turboshaft engine
    HU Qiu-chen, CHEN Yu-chun, JIA Lin-yuan, HUANG Xing
    2014,5(1):109-115. DOI:
    [Abstract] (4674) [HTML] (0) [PDF 2.89 M] (4607)
    Abstract:
    For free turbine turboshaft engine with high thermodynamic parameters and high-bleed, a new turboshaft performance calculation model which considers bleed position and cooling air expansion work. The model of air bleeding in the middle of the compressor corrects the flow balance and power balance at the same time. The turbine cooling model considers the cooling air expansion work. The calculation results obtained by the new model are analyzed and compared with that of simple turbine bleed and cooling model, which proves that the new model can obtain the influence of the amount of bleeding and bleeding position to the performance of turboshaft engine. The new model are close to the true physical process of turboshaft engine, and can offer input to the air system.

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