Governed by: Ministry of Industry and Information Technology of the People's Republic of China
Sponsored by: Northwestern Polytechnical University  Chinese Society Aeronautics and Astronautics
Address: Aviation Building,Youyi Campus, Northwestern Polytechnical University
  • Current Issue
  • Online First
  • Archive
  • Most Downloaded
    Select AllDeselectExport
    Display Method:
    2026,17(1):1-10. DOI: 10.16615/j.cnki.1674-8190.2026.01.01
    Abstract:
    UAV is the core carrier and key driving force in the low altitude economy. The UAV industry has gradually become a strategic emerging industry that takes into account the coordinated development of new productivity and industrial innovation. Based on the development status of low altitude UAV in China, this paper analyzes the current industrial scale and management classification of low altitude UAV. The main technical bottlenecks of large-scale commercial application of low altitude UAVs are analyzed. It is concluded that the industry development in the future needs to focus on three strategic technical fields, namely, UAV power energy, 5g satellite integrated communication and airspace intelligent management. Discussions are carried out around aircraft power solutions in low altitude economic environment, UAV communication and data processing technology, and low altitude airspace management and safety technology. It is proposed that these technological breakthroughs and industrial upgrading have significant synergistic effects, which can effectively enable the construction of intelligent and efficient low altitude economy industry, and is the key to unlock the huge potential of low altitude economy and ensure its safe and reliable operation.
    2026,17(1):11-23. DOI: 10.16615/j.cnki.1674-8190.2026.01.02
    Abstract:
    Large-scale civilian cargo UAVs refer to transport aircraft which can carry heavier and larger cargo and have longer flight times and ranges. They are usually used in fields such as cargo transportation, and material support, and can provide fast, safe, convenient, low-cost freight transportation services. In this paper, the development of large civilian cargo UAVs which have a payload of more than 100kg in our country are reviewed in the past 10 years, and the technical characteristics of those UAVs that have completed their maiden flights is analyzed. Besides, the scene application and market trend of large-scale cargo UAVs are emphatically analyzed. At the same time, the research and development of large-scale civilian cargo UAV in China requires strengthening infrastructure construction, strengthening ecological construction of the industry system, the continuous breakthroughs of key technologies and providing customized solution.
    2026,17(1):24-38,71. DOI: 10.16615/j.cnki.1674-8190.2026.01.03
    Abstract:
    Obtaining a type certificate (TC) is a necessary prerequisite for the commercial operation of person-carrying electric vertical take-off and landing (eVTOL) aircraft, it is necessary to conduct the relevant airworthiness research for TC certification. Based on the current development status of eVTOL aircraft, this paper analyzes the applicability and key points of airworthiness requirements related to person-carrying eVTOL aircraft that have been issued by the International Civil Aviation Organization (ICAO), the European Aviation Safety Agency (EASA), the Federal Aviation Administration (FAA) of the United States, and China. The shortcomings of the existing airworthiness requirements are summarized, and suggestions for establishing and improving the airworthiness requirements are put forward. Focused on currently domestic person-carrying eVTOL aircraft’s TC certification, six aspects of risks and challenges are analyzed and countermeasures are given, with the aim of providing reference for the establishment and improvement of airworthiness requirements, and the smooth progress of TC certification for domestic eVTOL aircraft.
    2026,17(1):39-50. DOI: 10.16615/j.cnki.1674-8190.2026.01.04
    Abstract:
    The tilt-rotor aircraft combines the capabilities of vertical takeoff and landing with efficient high-speed cruising, making it suitable for short-haul low-altitude transportation. However, the overall design of existing tilt-rotor aircraft does not consider the safety of forced landings during short-haul transport, and both the aerodynamic layout and control strategies need optimization. This paper introduces a novel dual-axis tilt-rotor aircraft. By comprehensively considering the integration of rotor blades and multiple flight modes, the overall layout of the aircraft is optimized. This enables the aircraft to perform a forced landing in fixed-wing mode on a single lane of a ground roadway with minimal impact on ground traffic, while still carrying a sufficiently large payload. Furthermore, a six-degree-of-freedom dynamic and kinematic model of the aircraft has been established. A control analysis of the six-degree-of-freedom flight under the new layout of the aircraft has been conducted, and a new control strategy has been proposed. The feasibility of the new control strategy has been verified through Simulink dynamic simulation. The research results indicate that the designed aircraft improves aerodynamic efficiency under a reasonable layout and can fully leverage the advantages of rotor blade integration, exhibiting good control performance. Overall, the aircraft design scheme can provide a reference for the development of tilt-rotor aircraft designed for low-altitude operations.
    2026,17(1):51-59. DOI: 10.16615/j.cnki.1674-8190.2026.01.05
    Abstract:
    By optimizing the design of electric motors for electric vertical take-off and landing (eVTOL) aircraft, significant improvements can be achieved in torque density and efficiency while reducing torque ripple, thereby enhancing the application potential of eVTOL vehicles in urban air mobility and improving their performance in noise control, payload capacity, and flight safety. This paper proposes an NSGA-III-based hierarchical optimization method for a dual three-phase drive motor used in an eVTOL aircraft, focusing on six stator structural parameters. After optimization, the motor achieves a torque density of 55.5 N·m/kg and efficiency of 93.55%, representing improvements of 6.05 N·m/kg and 1.35% respectively compared to the pre-optimized design, while reducing torque ripple from 3.96% to 2.54%. The reliability of the optimized solution is verified through both simulation and experimental results.
    2026,17(1):60-71. DOI: 10.16615/j.cnki.1674-8190.2026.01.06
    Abstract:
    With the vigorous development of my country"s low-altitude economy, low-altitude safety risks have become increasingly prominent and have become an important factor restricting its further development. This paper focuses on the safety management of low-altitude flight, aiming to build an effective system collaborative management mechanism to promote the safe and healthy development of low-altitude airspace. First, the connotation and characteristics of low-altitude safety are analyzed, and it is clarified that it involves multi-dimensional elements such as aircraft operation, personnel operation, environmental conditions and management measures; secondly, based on the four dimensions of man, machine, environment and management, the decision laboratory analysis (DEMATEL) method is used to quantitatively identify 11 key risk factors such as regulatory means, geographical environment, and meteorological conditions, revealing the core driving role of human factors and management factors; finally, a "five-coordination" management mechanism including governance coordination, environmental coordination, normative coordination, security coordination and man-machine coordination is proposed, and the systematic goals of risk prevention and control, regulatory efficiency improvement and social cognition improvement are achieved through multi-dimensional linkage. The research results provide theoretical support and practical paths for low-altitude safety management, and help promote the benign interaction between low-altitude industrial economy and safety management.
    2026,17(1):72-80,89. DOI: 10.16615/j.cnki.1674-8190.2026.01.07
    Abstract:
    In order to meet the arrival of large unmanned aerial vehicles and reduce the probability of accidents, the main roles and responsibilities and scenarios in the operation process were analyzed, and the control feedback structure in the operation process was constructed by using the System Theory Process Analysis Method (STPA) to identify the risk factors that lead to accidents. Based on the correlation between factors, the Bayesian network (BN) was constructed, and the GeNIe software was used to carry out forward causal inference on the risk probability, and the key factors were determined through reverse reasoning, sensitivity analysis and impact intensity analysis. The results show that control failure is the most critical factor leading to accidents. Navigation system failure, bad weather, and battery failure are highly sensitive factors, and the analysis results can provide a basis for the prevention and control of large-scale unmanned aircraft operation risks.
    2026,17(1):81-89. DOI: 10.16615/j.cnki.1674-8190.2026.01.08
    Abstract:
    When a manned airship is struck by lightning, in order to avoid damage to flight safety caused by lightning currents, we need to consider building lightning protection channels in the design of the manned airship and conduct airworthiness compliance verification during the development process. This article studies the lightning protection design and airworthiness compliance verification methods of AS700 manned airships. It simulates the lightning exposure of manned airships in thunderstorm and lightning environments, constructs the lightning current circuit of manned airships, and conducts lightning compliance tests on key components and materials to confirm that the lightning protection design of AS700 manned airships meets airworthiness requirements.
    2026,17(1):90-99. DOI: 10.16615/j.cnki.1674-8190.2026.01.09
    Abstract:
    Designing a suitable rotor tilt path in the tilt transition corridor is one of the key steps in the flight dynamics analysis and flight control of tilt rotor aircraft. In response to the above application background,this article establishes a flight dynamics model of a tilting quadcopter aircraft, and determines the 3-D conversion corridor of the forward flight velocity tilt angle acceleration of the tilting quadcopter aircraft through triming calculations. The characteristics of the conversion corridor boundary under different accelerations are analyzed. Comprehensive performance indicators involving flight attitude, total distance, and required power factors have been defined. The A * algorithm was used to search for the optimal conversion path of a tiltrotor quadcopter aircraft with the goal of minimizing the overall performance indicators. The research results indicate that 3-D conversion corridor can provide more information for tilting conversion and provide theoretical basis for determining conversion paths; The A * algorithm optimizes the 3-D conversion path search, which is beneficial for the safe and stable completion of tilt transition flight.
    2026,17(1):100-107. DOI: 10.16615/j.cnki.1674-8190.2026.01.10
    Abstract:
    Supersonic civil aircraft have significant changes in aerodynamic layout and design compared to subsonic civil aircraft, which will bring new risks and make some provisions of the current regulations inapplicable. By conducting a qualitative analysis of CCAR Part 25 and the special conditions while using computational fluid dynamics (CFD) methods, the aerodynamic characteristics of a small aspect ratio, large sweep angle supersonic civil aircraft in low-speed conditions are analyzed; Finally, the safety intent behind the minimum flight speed mentioned in the supersonic civil aircraft special conditions is revealed through a combination of qualitative and quantitative analysis. The results show that the stall speed reference defined by CCAR Part 25 is not applicable to supersonic civil aircraft. Supersonic civil aircraft adopt the minimum flight speed (Vmin) and zero climb rate speed (Vzrc) as new speed references to ensure stable flight while still having climbing ability.
    2026,17(1):108-115. DOI: 10.16615/j.cnki.1674-8190.2026.01.11
    Abstract:
    Glass-type brittle materials are widely used in aircraft windshield structures, located at the front of the aircraft"s windward side, making them susceptible to bird strikes and subsequent fracturing. Testing fracture parameters of brittle windshield glass is challenging. Typically, elastic-plastic constitutive models and failure strains are used to describe the stress deformation and failure of glass. However, using this traditional SPH (Smoothed Particle Hydrodynamics)-FEM (Finite Element Method) coupling method makes it difficult to simulate the propagation of fine cracks in the windshield glass after a bird strike. This paper, based on the numerical calculation of fracture problems using the DEM (Discrete Element Method), calibrated the microscopic parameters of organic glass fracture with experimental data and established a bird-strike numerical simulation model of flat windshield glass based on the SPH-DEM coupling analysis method. The calculation results indicate the fracturing process of the windshield glass under bird strike impacts. The fracture results of the glass show good consistency with the bird strike test results, demonstrating that the SPH-DEM coupling analysis method can more accurately simulate the fracturing of windshield glass under bird strikes. This provides a new research method and approach for the numerical simulation of bird strikes on aircraft windshield glass.
    2026,17(1):116-131,140. DOI: 10.16615/j.cnki.1674-8190.2026.01.12
    Abstract:
    During emergency landing, passengers using different anti-impact postures often produce different protective effects. A seat/passenger restraint system model based on the THUMS biomechanical dummy is established, comparing head and neck injuries in upright sitting posture, head and hand supported sitting posture, and head supported sitting posture under a 16g horizontal impact. A double-handed neck-holding anti-impact posture was proposed. By analyzing cervical axial tensile, compression force, anterior-posterior bending moment of the neck, the dynamic responses were analyzed, and the biomechanical response of the occupants, including vertebral stress, ligament elongation rate, intracranial equivalent stress, intracranial pressure, cranial equivalent stress, were analyzed. The damage assessment was conducted. Finally, the level of muscle activation was taken into consideration to explore the head and neck injuries of passengers in a state of muscle tension or relaxation. The results show that adopting an anti-impact posture can effectively reduce head and neck injuries, with the proposed double-handed neck-holding anti-impact posture reducing cervical axial force, bending moment, vertebral stress, and intracranial equivalent stress, but still carrying risks of neck soft tissue contusion and mild concussion. Tense muscles during impact can effectively reduce cervical axial force, bending moment, ligament elongation rate, intracranial equivalent stress and intracranial pressure.
    2026,17(1):132-140. DOI: 10.16615/j.cnki.1674-8190.2026.01.13
    Abstract:
    Compared with post-flight operations quality assurance, it is helpful to identify and pre-warn operation risks by monitoring streamed flight data. A risks identification method based on streamed flight data deep learning was studied, and the proposed method was further verified in aircraft approaching flight. A deep temporal network (DTN) was constructed by combining temporal convolutional networks (TCN) with gated recurrent units (GRU). Firstly, the DTN was used to extract the long-term memory and local time-dependent features based on the offline flight dataset. Secondly, the DTN was simplified to the DTN-R network which is suitable for online anomaly monitoring. The anomaly detection tests based on real streamed flight data show that the DTN-R is able to identify typical anomalies including high speed exceedance (HSE), glide slope deviation (GSD) and late flap setting (LFS), thus achieving the online risk monitoring. By studying different risk features, the DTN can be extended to identify other in-flight risks. Providing the score of risk confidence, the DTN-R is helpful to explain the causes of abnormal risks. Furthermore, the proposed methodology provides an effective way of assuring flight safety.
    2026,17(1):141-148. DOI: 10.16615/j.cnki.1674-8190.2026.01.14
    Abstract:
    Telescopic wing UAVs not only exhibit excellent flight performance across a wide speed range but can also utilize asymmetric wing extensions for flight control. This study focuses on a UAV with asymmetrically extendable wings. The extension process is discretized into distinct states, and a dynamic finite element model considering both structural and aerodynamic asymmetries is established to investigate the changes in flutter characteristics under asymmetric extension. The results show that both the flutter speed and flutter frequency in the asymmetric extension states are higher than those in the baseline symmetric state. As the asymmetry degree increases, the form of flutter transitions from body freedom flutter to bending-torsion coupling flutter, resulting in significant increases in both flutter speed and flutter frequency.
    2026,17(1):149-158,173. DOI: 10.16615/j.cnki.1674-8190.2026.01.15
    Abstract:
    In the application of flight simulator, it is required that the aircraft simulation model quickly relocates to a specific state according to the training subject requirements, so it is crucial to quickly obtain the initial state parameter values of the aircraft. This paper proposes a trimming algorithm based on an improved Powell algorithm and an aircraft flight dynamics model, obtaining state variables and control inputs that enable the aircraft to achieve stable flight, thus realizing the relocation of aircraft motion state parameters. Furthermore, based on the solved motion parameters and aircraft system simulation principles, a repositioning method for aircraft system state parameters is proposed, forming an algorithm architecture for flight simulator repositioning. This algorithm has been applied to a specific model of a flight simulator, ensuring stable flight during the initial phase of simulation, with minimal visual and motion platform disturbances, thereby enhancing the logical consistency and realism of the simulation training, and has a faster solving speed.
    2026,17(1):159-166. DOI: 10.16615/j.cnki.1674-8190.2026.01.16
    Abstract:
    The impedance distribution of low impedance conductive networks in aircraft has a significant impact on the electromagnetic coupling effect of onboard wiring harnesses. Studying the electromagnetic coupling characteristics of low impedance conductive networks in aircraft can significantly improve the accuracy of aircraft system level electromagnetic compatibility simulation. This article proposes an electromagnetic prototype modeling method for aircraft low impedance conduction networks. Based on the electromagnetic prototype, the impedance distribution characteristics and electromagnetic coupling characteristics of the aircraft low impedance conduction network are simulated and evaluated, and the aircraft actual test verification is completed. The simulation and test results show that the low impedance conductive network of the aircraft exhibits resistive and inductive characteristics in the frequency band below 0.1MHz, and alternating inductive and capacitive electromagnetic resonance characteristics in the frequency band above 0.1MHz.
    2026,17(1):167-173. DOI: 10.16615/j.cnki.1674-8190.2026.01.17
    Abstract:
    Carrier-based aircraft usually increase the take-off angle of attack by extending the nose landing gear suddenly at the end of the stroke during catapult take-off. The measurement of the sudden extension performance of landing gear is of great significance for the development of the model. A test scheme for the sudden extension of landing gear with double-chamber cushioning device has been designed. The nose landing gear of a certain type of aircraft has been analyzed and verified. By changing the test loading conditions, the influence of different loading conditions on the sudden extension performance of landing gear has been analyzed. The test results show that for the double-chamber landing gear, the temperature in the high-pressure chamber changes dramatically before and after the sudden extension, while the low-pressure chamber hardly changes. And the holding time after loading has a greater impact on the sudden extension performance of the cushioning device than the loading rate, which should be considered in ground verification tests.
    2026,17(1):174-181. DOI: 10.16615/j.cnki.1674-8190.2026.01.18
    Abstract:
    The inlet/engine matching principle of target drone propulsion system is important to evaluate the engine working characteristics. To obtain the inlet/engine matching performance of a target drone, the investigation of the S-shaped inlet and small turbojet engine matching characteristic is carried out in this paper, by combining inlet/engine matching ground test with inlet suction experiment. It concentrates the influence of the S-shaped inlet on the engine characteristics. And an engineering method is produced to evaluate the small engine characteristics on ground running, by building the connections between the inlet/engine matching ground test and inlet suction experiment. It"s shown that the performance of engine in matching ground test is mainly affected by the S-shaped inlet characteristic parameters. When the full scale S-shaped inlet installed, the engine performance is no longer as good as the craft inlet installed, but falls. As the engine rotating speed enhanced, the mass flow increases, and the inlet performance gets worse. The total pressure recovery coefficient at the inlet exit decreases and the distortion index rises, which has a negative effect on the engine performance, resulting in the thrust smaller and the fuel consumption larger. Moreover, the proposed method can reliably evaluate the small engine characteristic parameters under matching ground condition based on the experimental data, so it is effective on engineering application.
    2026,17(1):182-191,210. DOI: 10.16615/j.cnki.1674-8190.2026.01.19
    Abstract:
    The anisotropic low conductivity of composite materials leads to local current concentration and current conduction hysteresis in aircraft after lightning strikes. Currently, most aircraft lightning current simulation methods focus on the study of metal materials, which makes it difficult to effectively characterize the surface current density distribution and transient current conduction of composite aircraft after lightning strikes. To ensure the effectiveness of lightning protection design and analysis for composite civil aircraft, the anisotropic conductivity matrix of composite materials under the influence of various layers and fiber content is introduced into the three-dimensional time-domain finite difference method to analyze the principle of lightning current conduction in composite civil aircraft. EMA3D simulation software is used to analyze the lightning current of composite civil aircraft, which is used to explore the surface current distribution and transient current conduction performance of the composite civil aircraft under multi-channel lightning injection paths. Then, a 3D modeling and simulation of a certain equivalent composite civil aircraft is carried out to analyze the overall current distribution law and transient current change characteristics of civil aircraft under the influence of composite material properties. The results show that: (i) composite civil aircraft may experience current concentration in the local area of the impact point and sharp parts such as the front and rear edges of the wing after being struck by lightning without protective measures, the current density of which is relatively high; (ii) the current preferentially conducts along the axis of the fuselage when composite civil aircraft is struck by lightning at the nose, and the current preferentially conducts along the spanwise direction of the front and rear edges of the wing when lightning strikes from the wing; (iii) the transient current of composite civil aircraft has conduction hysteresis compared to metal civil aircraft.
    2026,17(1):192-200,210. DOI: 10.16615/j.cnki.1674-8190.2026.01.20
    Abstract:
    The existing drone risk assessment mostly focuses on small drones, and there is relatively little research on the aging assessment system of large drones. In addition, there are problems such as insufficient consideration of indicator weights and poor evidence fusion effect in the evaluation process. This study proposes an improved D-S evidence theory method, using a combination of subjective and objective weighting, combined with triangular fuzzy number processing expert scoring, to optimize evidence fusion and solve risk levels. Taking a large unmanned aerial vehicle system as the research object, a two-level 18 item evaluation index system is constructed from five dimensions including ground station system, aircraft platform, and initial defects. Empirical analysis is carried out by combining application patterns and historical data. The results indicate that the system is at a medium to low risk level, with a membership degree of 73%. Compared with similar methods, this method has significant advantages in handling complex weights and multi-source information fusion, and can provide accurate decision-making basis for risk warning and control of large-scale elderly unmanned aerial vehicle systems.
    2026,17(1):201-210. DOI: 10.16615/j.cnki.1674-8190.2026.01.21
    Abstract:
    In aircraft assembly, due to measurement errors, manufacturing errors,and coordinate conversion errors, the assembly accuracy and quality of components do not meet the requirements, and the assembly gap is unevenly distributed. In order to make the assembly clearance distribution as uniform as possible and the assembly quality meet the requirements, the optimal pose transformation parameters are calculated in advance before the assembly of the components. On the premise of ensuring that all the attitude adjustment datum points meet the tolerance requirements, the coordinate error of the target position of all the attitude adjustment datum points and their theoretical positions, as well as the characteristics of the mating surface (angle and clearance) of the mating plane, are optimized, and the optimal pose transformation parameters are solved by the multi-objective particle swarm optimization algorithm, and finally the virtual assembly is carried out in PolyWorks to complete the verification.
    2026,17(1):211-218. DOI: 10.16615/j.cnki.1674-8190.2026.01.22
    Abstract:
    Tire bursting is a common aviation accident that easily occurs during aircraft take-off and landing, seriously affecting aircraft safety.In order to minimize the harm of tire bursting to aircraft, the aircraft design characteristics were investigated.On the basis of summarizing the engineering practice of domestic civil aircraft on the latest international tire blasting clauses, and based on the civil aircraft system engineering concept, an aircraft tire blasting design technical system for CS25.734 has been established,and aircraft design technology research has been carried out in four typical stages from project establishment to airworthiness verification.The results showed that: Setting fusible plugs is not a perfect measure to prevent tire bursting. Active or passive design measures should be taken in the aircraft wheel cabin for heat sources to prevent aircraft tires from overheating and bursting; there are four failure modes for aviation tire bursting, and the impact area is related to the compression state of the landing gear ,which is affected by all ground conditions(weight and center of gravity envelope, temperature envelope, etc.);a series of design considerations, verification ideas and compliance criteria on system/structure/fuel fire protection have been verified in the airworthiness certification of a domestic large passenger aircraft,which can provide reference for tire burst protection design of large transport aircraft.
    Select AllDeselectExport
    Display Method:
    Available online:March 04, 2026, DOI:
    Abstract:
    In the early days, the structure and function of equipment were relatively simple, and the research on the quality characteristics of equipment was mostly carried out from the perspective of failure faults. With the continuous improvement of requirements for equipment, it is gradually becoming more complex and multi-functional, and along with this comes a greater variety of faults and failure modes. The quality control of equipment is no longer merely about preventing failure, but rather focuses on preventing the degradation of its functional performance, that is, preventing the equipment from becoming dysfunctional. In fact, the degradation of the equipment is manifested as the degradation of functional performance finally. This paper systematically reviews the process of quality control for equipment failure and faults, and elaborates the development process of equipment maintainability, reliability, safety, testability, survivability, repairability, etc. The quality control parameters that directly affect the functional performance of the equipment were summarized, and the development processes of equipment supportability, environmental adaptability, electromagnetic compatibility and system compatibility were analyzed. On this basis, the development process of equipment operational integrity discovery is introduced, and it is clarified that digital twin technology has become an important way to achieve and maintain the operational integrity of equipment.
    Available online:March 04, 2026, DOI:
    Abstract:
    Aircraft have become indispensable tools for modern warfare, convenient transportation, and economic development. With advancements in technology, aircraft are being assigned increasingly diverse mission requirements, presenting comprehensive opportunities and challenges for their design, manufacturing, operation, and maintenance. Structures play a crucial role throughout the entire lifecycle of an aircraft. In response to future design demands emphasizing safety, efficiency, economy, and environmental protection, this paper examines the development trends in aircraft structural materials, design, and manufacturing technologies. By comparing current practices with future requirements, it identifies six distinct design characteristics that will define future aircraft structures: overall high efficiency, multi-functional integration, intelligent adaptability, health monitoring capabilities, environmental friendliness, and cost-effectiveness equilibrium. This analysis aims to provide valuable references for the structural design of future aircraft.
    Available online:March 04, 2026, DOI:
    Abstract:
    Repair of damaged composite material structures is of great significance for ensuring the safe service of aircraft, extending their lifespan, and reducing usage costs. This paper proposes a remanufacturing repair method in view of the severe corrosion and debonding damage of the aluminum honeycomb sandwich structure of a certain aircraft, which exceeds the allowable repair limit given by the design guidance. The key technologies such as repair materials, reverse modeling, tooling design, and bonding inspection are analyzed, and the technological process of remanufacturing repair is given. The remanufacturing repair effect is evaluated in terms of mechanical properties, environmental adaptability, appearance morphology, bonding quality, weight variation, and assembly characteristics. The results show that for the damaged honeycomb sandwich structure of the spoiler studied in this paper, the repaired structures show good mechanical properties and anti-corrosion performance after remanufacturing repair. The morphology, weight, and assembly quality of the repaired structure meet the repair design requirements, which provides a new technology for the repair of aluminum honeycomb sandwich structures in aviation.
    Available online:March 04, 2026, DOI:
    Abstract:
    The separation of the solid-liquid interface and the morphological evolution of the free surface during cylinder water entry are closely correlated with surface roughness. Based on the Arbitrary Lagrangian-Eulerian (ALE) method, which accounts for the friction characteristics of rough surfaces, this paper establishes finite element models for the vertical and oblique water entry of rough cylinders. The study investigates the separation position and the characteristics of the free surface morphology. The validity of this numerical method is verified by comparing the simulation results with experimental data. Furthermore, the study focuses on analyzing the effects of varying surface roughness and entry velocities on the impact response and flow separation characteristics of the cylinder. The results show that: the free liquid surface change of the cylinder water entry process simulated by the ALE method is in good agreement with the test, and the upward speed of the solid-liquid-gas three-phase contact line of the cylinder water entry on the rough surface is lower than that on the smooth surface, so that the liquid surface is easier to be separated from the surface of the cylinder; with the decrease of roughness, the angle of separation shows the trend of increasing, then decreasing and then increasing, and the angle of separation of the column water entry is decreasing as the speed of the water entry increases. The angle of separation of cylindrical water decreases with the increase of water entry velocity.
    Available online:March 04, 2026, DOI:
    Abstract:
    Aircraft is inevitably subjected to environmental corrosion during service. By forming a moisture barrier,hydrophobic coatings significantly control the local corrosive environment, thereby improving the corrosion resistance of localized aircraft surfaces, it contributes significantly to flight safety assurance and service life extension of aircraft. The traditional hydrophobic agent has the drawback of being flammable due to the mixture of gasoline. Therefore, a safe hydrophobic agent is prepared in this paper by selecting non-flammable solvents and performing orthogonal experiments for the components. The preferred component ratio is determined through contact angle measurements. Subsequently, the basic properties of the safety hydrophobic agent are investigated. And comprehensive environmental corrosion tests of typical metal joint structures of aircraft were carried out to investigate the effect of safety hydrophobic agents on the corrosion behavior of connection structures. The performance testing and morphology analysis results indicate that, the prepared hydrophobic agent has the characteristics of transparency and non-flammability, and shows good compatibility with aviation coatings. And the corrosion resistance of the structures was significantly improved after hydrophobic treatment. Compared to pre-assembly treatment, post-assembly hydrophobic treatment more effectively suppresses the occurrence of structural corrosion.
    Available online:March 04, 2026, DOI:
    Abstract:
    Based on the nonlinear friction sliding model and the energy method calculation formula of the damping ratio, combined with the static and modal finite element analysis of the high pressure turbine(HPT) blades, a design process for the damping and vibration reduction of the under platform damper(UPD) has been built, and the influence rules of key parameters such as mass, friction coefficient, and geometric structure on the vibration reduction effect have been given. The design results show that, under the given working conditions, the UPD mass of the high pressure turbine blade has an optimal range, which can provide a reference for practical applications. Vibration excitation tests have been conducted on a rotational testing rig both without damper and with dampers of varying masses. The damper that demonstrated the most effective vibration reduction had a mass within the optimal range obtained during the design phase.
    Available online:March 04, 2026, DOI:
    Abstract:
    Based on the mode superposition method, this paper takes the consistency of structural dynamic effects under the two loads before and after equivalence as the core requirement, and deduces the transformation method from pulsating excitation to base excitation. Taking a typical section of the outer flap compartment as the research object, the specific implementation steps of load equivalence are described in detail. The effectiveness of the method is verified by analyzing the dynamic response of the concerned parts of the structure, and the contribution of each order of mode to the structural response after bandwidth truncation is explored.The research results show that the power spectral density of acceleration response and root-mean-square stress of the concerned parts of the structure are in good agreement with those under pulsating excitation, and the deviation of root-mean-square stress does not exceed 1.2%, which verifies the effectiveness of the proposed load equivalence method. Moreover, the contribution of the 2nd-order mode to the structural response reaches 98%, which provides a key theoretical basis for selecting the 2nd-order mode to carry out verification work in ground tests. Based on this, the random vibration test is carried out, and the damage location is completely consistent with the calculated dangerous location.
    Available online:March 01, 2026, DOI:
    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.
    Available online:March 01, 2026, DOI:
    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.
    Available online:March 01, 2026, DOI:
    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.
    Available online:March 01, 2026, DOI:
    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.
    Available online:March 01, 2026, DOI:
    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.
    Available online:February 18, 2026, DOI:
    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.
    Available online:February 18, 2026, DOI:
    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.
    Available online:February 18, 2026, DOI:
    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.
    Available online:February 18, 2026, DOI:
    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.
    Available online:February 18, 2026, DOI:
    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.
    Available online:February 18, 2026, DOI:
    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.
    Available online:February 05, 2026, DOI:
    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.
    Available online:February 05, 2026, DOI:
    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.
    Available online:February 05, 2026, DOI:
    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.
    Available online:February 05, 2026, DOI:
    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.
    Available online:February 05, 2026, DOI:
    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.
    Available online:January 28, 2026, DOI:
    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.
    Available online:January 28, 2026, DOI:
    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.
    Available online:January 28, 2026, DOI:
    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.
    Available online:January 28, 2026, DOI:
    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.
    Available online:January 28, 2026, DOI:
    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.
    Available online:January 19, 2026, DOI:
    Abstract:
    The trajectory prediction of civil aircraft Flight Management System (FMS) needs to consider the constraints of various constraints. The vertical trajectory prediction function is tightly related to the aircraft performance characteristics and directly affects the aircraft operating cost. Therefor it has been the research focus aircraft manufacturers and system suppliers. To solve the onboard FMS vertical trajectory prediction issue, the Performance Database (PDB) and motion model are formed by combining the key performance characteristics of a certain civil aircraft, and the vertical trajectory is decomposed into a multi-stage model taking those constraints into account. Then, Radau pseudo-spectrum method is used to transform the multi-stage optimal control problem into a nonlinear programming problem (NLP), and NLP solver is used to solve the parameters. In this process, the vertical trajectory parameters of the whole flight are calculated and optimized. Finally, several typical operation scenarios are selected, and the simulation results in this paper are compared with the real simulator test results under various initial conditions to prove the correctness of the method and feasibility of engineering application.
    Available online:January 19, 2026, DOI:
    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.
    Available online:January 19, 2026, DOI:
    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.
    Available online:January 19, 2026, DOI:
    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.
    Available online:January 19, 2026, DOI:
    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.
    Available online:January 12, 2026, DOI:
    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.
    Available online:January 12, 2026, DOI:
    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.
    Available online:January 12, 2026, DOI:
    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.
    Available online:January 12, 2026, DOI:
    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.
    Available online:January 12, 2026, DOI:
    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.
    Available online:December 31, 2025, DOI:
    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.
    Available online:December 31, 2025, DOI:
    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.
    Available online:December 31, 2025, DOI:
    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.
    Available online:December 31, 2025, DOI:
    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.
    Available online:December 31, 2025, DOI:
    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.
    Available online:December 31, 2025, DOI:
    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.
    Available online:December 31, 2025, DOI:
    Abstract:
    To enhance the role of satellite remote sensing data in the planning of aviation emergency rescue layout, this paper introduces a location selection method that integrates satellite remote sensing data with forest fire emergency rescue layout planning. The study encompasses the following key aspects: Firstly, leveraging the MODIS active fire dataset over the years, fire-prone areas are delineated as demand points. Secondly, considering the temporal constraints from fire detection to response, the factors influencing the location of aviation emergency rescue stations are analyzed based on forest fire characteristics. Utilizing ArcGIS software, relevant satellite remote sensing data of primary indicators are parameterized and weighted for superposition, yielding the areas suitable for constructing aviation emergency rescue stations. Subsequently, a set coverage mathematical optimization model is formulated to determine a rational location layout and construction priority. Lastly, through case analysis, the mode
    Available online:December 22, 2025, DOI:
    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.
    Available online:December 22, 2025, DOI:
    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.
    Available online:December 22, 2025, DOI:
    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.
    Available online:December 22, 2025, DOI:
    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.
    Available online:December 04, 2025, DOI:
    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.
    Available online:December 04, 2025, DOI:
    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.
    Available online:December 04, 2025, DOI:
    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.
    Available online:December 04, 2025, DOI:
    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.
    Available online:November 19, 2025, DOI:
    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.
    Available online:November 19, 2025, DOI:
    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.
    Available online:November 19, 2025, DOI:
    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.
    Available online:November 19, 2025, DOI:
    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.
    Available online:November 19, 2025, DOI:
    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.
    Available online:October 21, 2025, DOI:
    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.
    Available online:October 21, 2025, DOI:
    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.
    Available online:October 21, 2025, DOI:
    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.
    Available online:October 13, 2025, DOI:
    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.
    Available online:October 13, 2025, DOI:
    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.
    Available online:October 13, 2025, DOI:
    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.
    Available online:October 13, 2025, DOI:
    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.
    Available online:September 30, 2025, DOI:
    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.
    Available online:September 30, 2025, DOI:
    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.
    Available online:September 30, 2025, DOI:
    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.
    Available online:September 30, 2025, DOI:
    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.
    Available online:September 30, 2025, DOI:
    Abstract:
    In order to investigate the vibration modal characteristics of aviation fuel bend pipes, This article studies the influence of structural parameters of fuel bend pipes on the natural frequency of aircraft engines. Firstly, the modal analysis of a simple fixed support pipeline was conducted through simulation experiments. Secondly, the force hammer method is used for testing to verify the accuracy of the simulated data. Next, finite element modeling was conducted on fuel bend pipes with different external assembly parameters, and the changes in modal shapes and natural frequencies of each order were analyzed. Finally, based on the principles of dynamics, the reasons for the variation of natural frequency with assembly parameters were explained. The research results indicate that the first mode of vibration of the bent pipe is a bending deformation, with a maximum deformation of 96.63 mm, and the main vibration direction is in the Z direction; The second stage is the second bending deformation, with a maximum deformation of 78.20 mm, and the main vibration direction is in the Y direction. Radius, span, and bending radius are the main structural parameters that affect the natural frequency of bent pipes. The natural frequency is positively correlated with the radius of the pipeline and the bending radius. As the radius and bending radius increase, the stiffness of the pipeline also increases; The natural frequency is negatively correlated with the span of the pipeline, as an increase in span leads to an increase in pipeline mass and a decrease in pipeline stiffness.
    Available online:September 23, 2025, DOI:
    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.
    Available online:September 23, 2025, DOI:
    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.
    Available online:September 23, 2025, DOI:
    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.
    Available online:September 12, 2025, DOI:
    Abstract:
    Deep Reinforcement Learning (DRL) provides a new technological paradigm for the intelligent flight control of unmanned aerial vehicles. However, confidence in the "black box" Artificial Neural Network (ANN) intelligent model is the main obstacle to practical application. To validate the neural network-based intelligent flight control model designed with DRL through flight test, a longitudinal end-to-end intelligent flight control model that maps the flight state to the elevator/thrust commands is developed for a fixed-wing scaled model aircraft, based on the multi-dimensional continuous state input and action output DRL Proximal Policy Optimization (PPO) algorithm. The robustness of ANN control model is validated through the simulation, and its engineering implementation for the sim-to-real transfer is further carried out. A flexible onboard ANN controller is developed and the model flight demonstration is launched. The test results preliminarily verify the applicability and generalization performance of the ANN controller.
    Available online:September 12, 2025, DOI:
    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.
    Available online:September 12, 2025, DOI:
    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%.
    Available online:September 12, 2025, DOI:
    Abstract:
    When aero-engine blades are subjected to foreign object impact, the resulting blade damage may lead to fatigue fractures, which pose a serious threat to the reliability and operational safety of the engine. In order to investigate the effect of metallic foreign object damage (FOD) on the fatigue performance of aircraft engine blades, a high-speed light gas gun testing system was used to accelerate 3mm-diameter steel balls to speeds of 290–310 m/s for the pre-damage testing of the blades. Subsequently, a high-cycle vibration fatigue testing system was used to study the impact of metallic foreign object damage on the residual fatigue limit of stainless-steel blades. By analyzing the influence of notch size on the fatigue limit and using the Peterson model, the fatigue limit of the damaged blades was predicted. The results show that the residual fatigue limit of the damaged blades decreases significantly with increasing damage depth and width, with the notch depth having the most pronounced effect on the fatigue limit. According to the predictions from the Peterson model, the residual fatigue limit of the damaged blades falls within 1.5 times the scatter band, and most experimental values are lower than the predicted values.
    Available online:September 12, 2025, DOI:
    Abstract:
    In the digital transformation of next-generation aircraft assembly, digital-physical assembly plays a critical role. Rapid, high-precision reconstruction of key assembly features is central to accurately predicting on-site assembly outcomes. However, current methods for reconstructing complex hyperbolic ring surfaces face limitations in both accuracy and efficiency. In this study, we focus on point cloud data from the mating surface of an intake duct. First, a radius-based filter is applied to remove obvious noise points, and region-growing techniques are used to determine upper and lower thresholds for passthrough filtering, resulting in the target point cloud for reconstruction. Next, the point cloud is classified by importance, and voxel downsampling based on centroid selection is performed using grids of varying sizes according to priority. Then, segmentation is performed based on direction angle ranges determined through region growing using a normal vector threshold. Subsequently, surface fitting is conducted via rapid NURBS base surface construction and iterative optimization. Finally, the fitted annular mesh surface is merged using a zipper-based stitching approach. To validate the method, a mock intake duct and an annular metal frame were fabricated, and point cloud data of the mating surfaces were collected. Comparative experiments on fitting accuracy and efficiency demonstrated that this method, when compared to approaches in literature and commercial software, effectively reconstructs complex hyperbolic annular surfaces with high efficiency while maintaining fitting accuracy, meeting the high-fidelity requirements for intake duct fitting and assembly simulation.
    Available online:September 02, 2025, DOI:
    Abstract:
    In the process of air refueling, the oil joint of the tanker aircraft may break away from the air refueling hose and collide with the receiver aircraft, which can lead to significant damage to the receiver aircraft components and endanger the safety. In order to ensure the anti-impact ability of the receiver aircraft components, the dynamic simulation of the collision process between different parts of the receiver aircraft and the oil joint was carried out by using a transient nonlinear impact analysis, and the effects of different impact attitudes and different impact velocities of the oil joint on the impact damage of the receiver aircraft components were studied. It was concluded that the higher the impact velocity, the more serious the damage of the receiver aircraft, and the damage degree of that is non-linear with the impact velocity. Besides, the vertical impact of the oil joint head is more destructive than that of the oil joint tail. When the oil joint head impacts the windshield or the upper wall panel vertically, the center of the leading edge is the weakest location for the vertical impact. It was also found that the stiffness matching between the structural components should be considered in the anti-impact design of the receiver aircraft.
    Available online:September 02, 2025, DOI:
    Abstract:
    As a new type of combustion, hydrogen-enriched combustion has high potential for the application of the decarbonization in power equipment. The development and assessment of high-fidelity numerical simulation methods for hydrogen-enriched combustion is of great significance for better understanding of hydrogen-enriched combustion process and the development of engineering technology. In the present study, an adaptive Very-Large Eddy Simulation method (VLES) based on the k-ε model is developed according to the scenario characteristics of methane/hydrogen blended combustion using high-speed jet. On the basis, combining the Eddy Dissipation Concept (EDC), Thickened Flame method (TF), i.e. finite rate combustion model and flamelet tabulated combustion model, a high-fidelity turbulent combustion numerical method for hydrogen-blended combustion is developed and verified in detail. Numerical simulations were carried out for two different types of classical hydrogen-enriched flames, namely the JHC hot coflow jet flame with the low reaction rate MILD combustion, and the Sydney bluff-body stabilized high-speed jet flame HM1 with high reaction rate. The simulation predictions were compared with the available experimental and numerical data. The results show that the developed VLES-EDC method can accurately predict the strong unsteady combustion process of methane/hydrogen blended flames, and the prediction results of velocity, temperature, etc., under the two types of combustion conditions have satisfactory accuracy. For the hydrogen enriched combustion, compared with the finite-rate turbulent combustion model, the prediction accuracy of the flamelet combustion model is reduced, and the prediction accuracy under different combustion scenarios needs to be verified accordingly.
    Available online:September 02, 2025, DOI:
    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.
    Available online:September 02, 2025, DOI:
    Abstract:
    As an emerging complex equipment, tethered balloons feature intricate operation procedures and are highly influenced by environmental factors. Improper operation may affect the safety of products or personnel, and professional trained personnel are required to operate them. Direct training and training of physical equipment will affect the normal use of equipment, shorten the service life of equipment, cost a lot of money and have safety risks. Therefore, it is imperative to employ a simulation training system first, allowing trainees to acquire a solid foundation in theoretical knowledge and operational skills before proceeding to hands-on training with the actual equipment. This paper integrates the operational requirements and functional components of tethered balloons to design and develop a tethered balloon simulation training system. This system adopts a combined approach of scaled-down physical models and software. The scaled-down physical models encompass the balloon structure, telemetry and control subsystem, and launch-and-recovery subsystem. The software component comprises modules for balloon status monitoring, theoretical teaching, and equipment maintenance, supported by computer and network equipment. Through testing and application, the system has achieved simulations of balloon platform operations, launch-and-recovery procedures, status monitoring, and networking-based teaching. It also facilitates effective performance evaluation. The tethered balloon simulation training system, applied to both theoretical and practical training, can conserve training resources, enhance training efficiency, and mitigate training risks.
    Available online:August 22, 2025, DOI:
    Abstract:
    Electrical wires and cables, as critical foundational components of aircraft, are extensively distributed throughout the entire structure of the aircraft. Aviation electrical wires and cables serve as the conduits for energy, data, and signal transmission within aerospace electrical systems. Due to their wide deployment and significant proportion, any failure that occurs can result in substantial losses. Consequently, there are heightened requirements for the reliability of aviation electrical wires and cables. The paper begins by introducing the composition of the Electrical Wiring Interconnection System (EWIS) and analyzing its failure mechanisms. It subsequently discusses the typical failure modes and failure mechanisms of aviation electrical wires and cables during their operational life. Finally, it reviews the research status of reliability assessment for electric wires and cables, and summarizes the commonly used fault detection and life prediction methods for them. By summarizing advancements in the research on electrical wires and cables, this paper aims to provide valuable insights for the development of aviation electrical wires and cables in China.
    Available online:August 22, 2025, DOI:
    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.
    Available online:August 22, 2025, DOI:
    Abstract:
    Non-metal fuel water drain valve installed on the outer surface of the aluminum wing tank near the nacle of the aircraft engine shall meet the fire resistance requirements in accordance with the provisions of the Airworthiness standards. The transient thermal analysis of the valve with different body thicknesses is carried out. The influence of the thickness of the valve body on the combustion heat transfer and fuel seal is analyzed, and the results are verified by experiments. The results show that when the valve body is thickened to at least 13mm, the valve begins to have fire resistance, that is, in the case of high temperature flame combustion, it can neither fuel leakage nor overtemperature in the fuel tank.
    Available online:August 22, 2025, DOI:
    Abstract:
    After the completion of flight dynamics modeling, due to the impact of flight test data error and modeling error, the comparison results between automatic objective test simulation data and flight test data are often difficult to fully meet the requirements of simulator evaluation regulations. In order to further improve the test and verification results, the subjects in the airworthiness certification regulations are classified into three categories according to the flight dynamics characteristics of maneover and the purpose of the investigation of the subjects. Secondly, for the subjects that need to adopt assisted validation, the assisted validation strategy of test subjects is developed. Then, based on the formed strategy, a P-I-D assisted validation system is established. Finally, a flight simulation assisted validation method for automatic objective test of flight simulator is established. Through a flight simulation example of a civil aircraft, the effectiveness of the assisted validation method is compared and verified. The results show that the assisted validation method can effectively improve the test validation effect of simulation data and flight test data, and help meet the tolerance requirements of airworthiness regulations.
    Available online:August 08, 2025, DOI:
    Abstract:
    For conventional layout civil transport aircraft in a low-speed and high lift configuration, the advance of the stall angle of attack causes the aircraft"s approach speed to be too high. It is necessary to optimize the low-speed characteristics of the high-lift configuration and control the flow separation in the inner wing area of the aircraft wing. The aerodynamic study on the changes in the end face size of the inner slat was carried out through conventional force measurement wind tunnel tests and fluorescent oil flow wind tunnel tests. Under the conditions of the optimal solution, the lift coefficient has been significantly improved, and the pitching moment coefficient still meets the requirements of the classic criterion after aerodynamic optimization, meanwhile, the flow mechanism of flow separation controlled by the extension of the inner slat end face is explained, that is, the airflow passing between the extension part and the main wing can inject high-energy flow into the main wing surface boundary layer near the root of the downstream wing, enhancing the resistance to the ability to withstand adverse pressure gradients and delays local flow separation.
    Available online:August 08, 2025, DOI:
    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.
    Available online:August 08, 2025, DOI:
    Abstract:
    The aircraft hydraulic system plays a crucial role in controlling the movement and stability of various aircraft components. In actual use, it often encounters complex hydraulic variations. The priority valve, a type of sequential valve widely used in aircraft hydraulic systems, ensures that hydraulic pressure is prioritized for critical flight control systems when a sudden pressure drop occurs due to an increased demand for flow at the load end. The performance of the priority valve in supplementing pressure to downstream systems can be evaluated based on the outlet pressure image and the valve spool displacement vibration image. To ensure the safety and practicality of the priority valve during operation, it is necessary to study the structural parameters that affect its performance.This article first analyzes the working process of a certain type of priority valve and the causes of vibration, identifying the structural parameters that may affect its performance. Next, using hydraulic fluid simulation methods, the existing design of the priority valve is optimized, focusing primarily on the mass of the valve spool and the area of hydraulic force. By altering certain structural parameters affecting these aspects, the study analyzes the dynamic performance under the same operating conditions, examining how these changes influence the dynamic working performance of the priority valve. The results indicate that reducing the main valve spool mass decreases the amplitude of the spool during the pressure compensation phase. A smaller main valve seat orifice diameter leads to higher pressure at the load end, better pressure compensation performance, and reduced vibration amplitude. Additionally, increasing the mass of the main valve seat can reduce the amplitude of the spool during the pressure compensation phase.
    Available online:August 08, 2025, DOI:
    Abstract:
    The aeromedical rescue system is a necessary equipment for helicopter medical rescue, and retrofitting the medical rescue system will directly affect the safe operation of the aircraft, requiring strict airworthiness certification procedures. Airworthiness is the minimum safety requirement for the development of aeromedical rescue systems. The medical equipment industry generally lacks full process airworthiness experience, which seriously hinders the development of domestic aeromedical equipment industry. Starting from the basic composition and installation requirements of aeromedical rescue systems, this article introduces the classic configuration, functional requirements, and airworthiness test requirements of aeromedical rescue systems. Based on the corresponding provisions of Part 29 R2 "Airworthiness Regulations for Transport Rotorcraft" of the CCAR, the acceptable compliance methods of aeromedical rescue systems and the acceptable criteria in verification tests are analyzed. In addition to passing the medical equipment standard performance test, aeromedical rescue equipment also needs to undergo environmental testing in accordance with requirements, with a focus on testing the electromagnetic compatibility during the charging and discharging process of defibrillation equipment. During airworthiness certification, the Civil Aviation Administration of China should invite medical equipment experts to provide professional advice and judgments to assess whether it meets airworthiness requirements.
    Available online:July 29, 2025, DOI:
    Abstract:
    Airborne laser weapons, mounted on aircraft, hold significant potential within the military domain. In the context of information warfare, integrating airborne laser weapons into complex combat systems can effectively address the limitations of traditional weaponry, significantly enhancing both the combat capability and survivability of these systems. This paper reviews the historical development and current state of airborne laser weapon research, providing an analysis and summary of key aspects related to the collaborative combat systems in which these weapons operate. Specifically, it focuses on the assessment of damage inflicted by airborne laser weapons, target allocation strategies, combat system modeling, and system effectiveness evaluation techniques. Additionally, considering the systematic and intelligent nature of modern combat environments, this paper outlines future research directions for advancing key technologies in collaborative combat systems involving airborne laser weapons. The goal is to offer insights that may guide the optimization of airborne laser weapon resource allocation and improve the overall effectiveness of combat systems.
    Available online:July 29, 2025, DOI:
    Abstract:
    The control of accuracy breakaway load for emergency fuse-pin of civil aircraft main landing gear is crucial for mechanical design of fuse-pin. To propose requirements for heat and surface treatment process of fuse-pin and explore the mechanical property design index of fuse-pin material, a series of experiments were conducted to study the influence of tempering temperature (300°C、350°C和400°C) and surface treatments (shot peening, chromium plating and high-velocity oxygen-fuel) on microstructure and mechanical properties of 300M steel. The results reveal that the microstructure of 300M steel mainly consists of tempered martensite and bainite by tempering treatment of 300°C and 350°C, exhibiting the ductile fracture property, which ensuring the comprehensive mechanical properties. Moreover, due to the higher yield ratio(0.87) and better impact strength by 350°C tempering temperature, the breakaway load can be accurately controlled. All surface treatments are not change the microstructure and reduce the structural size of specimens, resulting in lower tensile force. Compared to shot peening and chromium plating, tensile force of specimen with HVOF treatment is the lowest because higher temperature of WC-10Co4Cr power melt the specimen surface and reduced its local size.
    Available online:July 29, 2025, DOI:
    Abstract:
    With the rapid development of civil aviation industry, green aviation has gradually become the focus of people"s attention. Taking into account factors such as aircraft performance, noise impact, and atmospheric environment in the terminal area, an optimization plan for aircraft departure trajectory has been proposed. Aiming at the problem that traditional Dynamic Window Approach (DWA) cannot effectively solve in aircraft departure trajectory planning, an improved Dynamic Window Approach combined with aircraft performance is proposed. Construct aircraft departure performance constraints based on the requirements of Base of Aircraft Data (BADA) and Continuous Climb Operations (CCO). At the same time, considering the noise impact of aircraft departure, the smaller the noise impact, the better the trajectory. Secondly, under the same research environment, analyze the methods with different index weights based on the duration and area of influence, and select the methods with the smallest comprehensive impact. Finally, based on the selected method, analyze the performance parameters such as thrust, speed, and path angle of the departing aircraft. The simulation experiment results show that the trajectory under the improved dynamic window method can meet the requirements of aircraft departure performance.
    Available online:July 29, 2025, DOI:
    Abstract:
    Existing aircraft performance software can determine obstacle weight limits when analyzing takeoff clearance. However, when it comes to clearing obstacles during the fourth segment, manual decision-making is required for a reasonable evaluation of the obstacle weight limit. Grounded in a comprehensive analysis of the intentions behind CCAR25 regulatory clauses, this paper proposes a precise simulation algorithm for gross and net takeoff flight paths and establishes a comprehensive model covering key constraints for full-segment obstacle clearance assessment. This model achieves an integrated calculation of obstacle clearance analysis through different level-off height strategies. Compared to traditional obstacle-clearance models, the simulation results demonstrate a possible enhancement of obstacle-limited takeoff weights by up to 24% in this model"s assessments. This research provides more reliable support for the efficient and safe operation of domestic civil aircraft.
    Available online:July 29, 2025, DOI:
    Abstract:
    Aviation safety is a global focus, and as the aviation system becomes increasingly complex, it becomes particularly important to conduct systematic risk analysis. This paper combines the HAZOP method with the WSR methodology to comprehensively identify critical risk nodes in aviation safety. By constructing a complex network model based on real-life case studies, the dynamic transmission process of risk elements in the aviation network is simulated. The risk grade and transmission probability were determined according to the difference of risks, and the transmission probability among different risks was differentiated based on the risk grade, so as to improve the susceptible-infection-susceptible (SIS) model and quantify the dynamic characteristics of risk transmission. Finally, through the analysis of 47 aviation cases, taking bird strikes as the scenario, the most likely to cause 10 high-risk nodes and their risk transmission chain are identified. The study shows that, compared with traditional SIS models, the risk quantitative analysis using the improved SIS model can more sensitively identify risks, providing reference for effective management of aviation safety.
    Available online:July 22, 2025, DOI:
    Abstract:
    Hydrogen-powered turbofan aircraft is powered by the direct combustion of hydrogen in the turbofan engine, which is an important development direction of green aviation. Aiming at the concept design of hydrogen-powered turbofan aircraft, a comprehensive analysis and optimization method is studied. According to the characteristics of hydrogen-powered turbofan aircraft, the liquid hydrogen system model is established based on physical principles, and the discipline analysis methods of conventional aircraft are updated and expanded. A multidisciplinary analysis method is developed, which consists of engine, liquid hydrogen system, geometry, weight, aerodynamic, performance, emission and cost modules. Based on the multidisciplinary analysis method, the primary parameters of the 150-class hydrogen turbofan aircraft concept are optimized, and the effects of the parameters of the liquid hydrogen tank on the aircraft weight and cost are investigated. The results show that the operating empty weight of the optimized aircraft is reduced by 1.63% and the direct operating cost is reduced by 1.79%. The shape of the liquid hydrogen storage tank and the characteristics of the insulation material have significant impacts on the aircraft weight and direct operating cost. The method presented in this paper can be effectively applied to the conceptual design of hydrogen-powered turbofan aircraft.
    Available online:July 22, 2025, DOI:
    Abstract:
    Modern large airliners and high-altitude unmanned aerial vehicles predominantly utilize high aspect ratio wings. Aircraft equipped with high aspect ratio wings can effectively reduce energy consumption; however, due to their structural characteristics, they experience considerable deformation under the influence of gravity and aerodynamic force. In order to investigate the landing response characteristics of a large flexible aircraft, a comprehensive landing dynamics model was developed, taking into account the flexibility of the airframe. This model was based on a high aspect ratio UAV as a reference sample and was integrated with a finite element model of the airframe. The analysis focused on the effects of the elastic modes and the initial attitude angle of the airframe on the landing loads and the dynamic response of the wings. Utilizing the response surface method, a surrogate model was created to optimize the parameters of the landing gear buffers. The results indicate that for large flexible aircraft, increasing the design travel of the landing gear buffers is beneficial in reducing both the landing loads and the dynamic response of the wings.
    Available online:July 22, 2025, DOI:
    Abstract:
    The re-entry vehicle will experience severe heat flow loads during its return to the atmosphere, requiring the design of an insulated tile-type thermal protection system for the vehicle. Due to the differences in the heat flow density distribution on the surface of the vehicle, a step in the thickness of the designed thermal protection system occurs, resulting in a poorly shaped internal surface of the thermal protection system, which is not smooth.The article proposes a smoothing algorithm for the endomorphic surface, which takes the position of the endomorphic surface type value points of the thermal protection system as the optimization object to smoothen the endomorphic surface, and fits the smoothened double-three times B-spline surface according to the coordinates of the processed endomorphic surface type value points, and the folding inflection angle of each node of the endomorphic surface is reduced to less than 10° which solves the thickness step problem of the thermal protection system, and the method is an effective smoothing algorithm.
    Available online:July 22, 2025, DOI:
    Abstract:
    This article studies the AC Motor Pump ACMP Starting Process with Ram Air Turbine RAT. The power generation capacity of RAT is affected by multiple factors such as temperature, airspeed, and altitude, while the ACMP is affected by the input frequency of the motor and the temperature of the hydraulic oil. These multiple factors make the analysis of the starting process very complex, and previous researchers have not conducted direct research on this. This article combines experiments with simulations and uses simulation models to calibrate the test results. During the calibration process, key parameters such as peak current and starting time errors are all within 5%, indicating that the model can demonstrate the starting process of the RAT starting ACMP. This article analyzes the most severe working conditions of the stamping air turbine starting ACMP and simulates the most severe work during the starting process. The simulation accuracy is controlled within 5%. A model for analyzing RAT starting ACMP in harsh scenarios is established, which can be used for subsequent design optimization of aircraft and detailed design of similar models.
    Available online:July 22, 2025, DOI:
    Abstract:
    In the aircraft design process, requirement capture is a key step to ensure that the product design meets stakeholders" expectations. In order to ensure the completeness of reliability requirements capture and the accuracy of requirements decomposition, firstly, multi-dimensional capture and decomposition of civil aircraft reliability requirements will be carried out from the scenario dimension and the stakeholder dimension. Secondly, combined with the MBSE process, the accuracy and completeness of civil aircraft reliability requirements capture and validation will be realized through the stakeholders identification, reliability requirements capture-validation-modeling, and reliability requirements decomposition- verification-modeling. Finally, using a typical civil aircraft system as a case study, the model-based civil aircraft reliability requirements capture and decomposition technology completes the scenario-based and stakeholder-based reliability requirements capture, modeling and validation. Besides, obtaining a typical system stakeholder reliability requirements MBSE model, which provides the requirements for the whole life cycle of the civil aircraft based on the MBSE reliability design process input. This research provides MBSE methods and solutions for system engineers involved in requirement capture and decomposition of civil aircraft.
    Available online:July 14, 2025, DOI:
    Abstract:
    Based on the traditional four-rotor configuration, the new six-rotor adds two main thrust propellers, which can fly forward quickly without changing the pitch Angle and realize yaw quickly. This paper designs an attitude control system based on a new type of six-rotor. The uncertainty of external interference during UAV flight brings great challenges to the design and verification of flight control system. The flight dynamics model of a new six-rotor UAV is established, the Control strategy is designed, and the attitude controller is designed using the Active Disturbance Rejection Control (ADRC). Through the attitude control simulation, the effect of the active disturbance rejection controller is superior to the PID controller. Particle Swarm Optimization (PSO) was used to optimize some parameters of the active disturbance rejection controller, and the control effect of PSO-ADRC was better than that of ADRC. The results show that the attitude ADRC controller has better anti-interference and robustness, which can ensure the fast and stable flight of the six-rotor UAV. Particle swarm optimization (PSO) further enhances the control effect of ADRC controller.
    Available online:July 14, 2025, DOI:
    Abstract:
    Porous media materials, due to their unique pore structure, can be used to simulate the permeability characteristics of bird wing feathers. This article takes the NACA0012 airfoil as the research object, covers the surface of the airfoil with porous materials to simulate bird wing feathers, applies the theory of porous media, and explores the influence of permeability parameters on the aerodynamic characteristics of the airfoil through CFD method.The results show that: 1) The semi covered porous airfoil can significantly improve the aerodynamic performance of the airfoil, especially the stall characteristics of the airfoil. The stall angle of attack increases by 2°, and the maximum lift coefficient increases by 16.2%; 2) The permeability characteristic parameters Darcy""s number and porosity have a significant impact on the aerodynamic characteristics of the airfoil. The aerodynamic performance of the airfoil deteriorates with the increase of Darcy""s number and improves with the increase of porosity; 3) Anisotropy has a significant impact on the aerodynamic characteristics of airfoils, among which the anisotropic porous airfoil with high permeability in the y-direction has the best aerodynamic characteristics, which is consistent with the bird wing feather structure. The surface covered porous medium airfoil scheme and its research conclusions adopted in this article can provide a reference for the design and research of bionic airfoil.
    Available online:July 02, 2025, DOI:
    Abstract:
    The tails often placed behind the propeller of the long endurance twin-boom UAV. In this case, the propeller slipstream will affect the aerodynamic characteristics. Based on the twin-boom UAV with inverted U-tail and inverted V-tail, Comparative analysis on the lift-drag characteristic and longitudinal static stability of two type UAV under propeller slipstream by numerical calculation method. The results show that when the longitudinal static stability of inverted U-tail/inverted V-tail UAV is similar, the tail capacity of inverted V-tail UAV is larger. The maximum increase of inverted U-tail UAV’s drag coefficient is 36.67%, the maximum increase of inverted V-tail UAV’s drag coefficient is 35.12%, the lift-drag ratio of inverted U-tail UAV is reduced by 4.14, The lift-drag ratio of inverted V-tail UAV is reduced by 4.32 under propeller slipstream, The effect of two type UAV’s lift-drag characteristic under propeller slipstream are basically same. The longitudinal static stability of inverted U-tail UAV is decreases by 2.09%, The inverted V-tail UAV is decreases by 0.99% under propeller slipstream. The longitudinal static stability of two type UAV become worse under propeller slipstream, And the inverted U-tail UAV becomes worse seriously. It provides reference for the design of the long endurance UAV’s tail with two-boom.
    Available online:July 02, 2025, DOI:
    Abstract:
    The occurrence of runway excursion is a frequent and dangerous safety issue in civil aviation, and reducing the probability of such incidents is a key focus in aviation operations.?This study first selects positive samples with the risk of runway excursion and negative samples without the risk from real flight data and determines crucial time point based on flight manuals and China Civil Aviation Industry Standard.Subsequently, repeated measure experiments to these samples are conducted to obtain important parameters affecting runway excursion and the temporal characteristics of these parameters.Finally, grey relational analysis is used to select parameters,and LSTM neural networks and these selected parameters are used to train models to predict the important parameters and off runway center line distance of all crucial time points .The experiments show that the MAE of each model is consistently less than or equal to 1.2, indicating high accuracy. In the future, the pre-trained models can be used with real-time approach data to achieve online warning for runway excursion.
    Available online:May 28, 2025, DOI:
    Abstract:
    In emergency rescue, the decision of air transportation of relief materials is very important, but the traditional method of relying on experienced experts has some problems such as long time consumption and low efficiency. Therefore, this paper introduces deep learning technology and constructs a decision-making system for air transportation of emergency relief materials. According to the task requirements, the system generates all feasible transportation schemes for different types of aircraft and different modes of transportation, and quantifies all kinds of factors that can affect the air transportation process. By using neural network to calculate and predict the task completion time, the prediction results of the completion time of all schemes are obtained. This paper also verifies the influence of various factors on the prediction accuracy under different conditions, and further improves the prediction accuracy of this system by using the improved neural network. Compared with the traditional empirical expert decision-making method, this system greatly shortens the decision-making time of transportation scheme and improves the emergency rescue efficiency. It solves the limitations of traditional methods and provides more flexibility and reliability for emergency rescue work..
    Select AllDeselectExport
    Display Method:
    2023,14(6):153-159. DOI: 10.16615/j.cnki.1674-8190.2023.06.17
    [Abstract] (591) [HTML] (374) [PDF 2.60 M] (12176)
    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.
    [Abstract] (4216) [HTML] (0) [PDF 1.89 M] (9868)
    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.
    2020,11(4):517-523. DOI: 10.16615/j.cnki.1674-8190.2020.04.009
    [Abstract] (1624) [HTML] (0) [PDF 833.51 K] (9736)
    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.
    2022,13(5):1-13. DOI: 10.16615/j.cnki.1674-8190.2022.05.01
    [Abstract] (1787) [HTML] (1540) [PDF 3.67 M] (7503)
    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.
    2020,11(3):302-307. DOI: 10.16615/j.cnki.1674-8190.2020.03.002
    [Abstract] (1671) [HTML] (0) [PDF 1.65 M] (7013)
    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.
    [Abstract] (3124) [HTML] (0) [PDF 1.88 M] (6647)
    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.
    2021,12(3):161-170. DOI: 10.16615/j.cnki.1674-8190.2021.03.20
    [Abstract] (1170) [HTML] (0) [PDF 8.07 M] (6638)
    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.
    2019,10(3):309-318. DOI: 10.16615/j.cnki.1674-8190.2019.03.003
    [Abstract] (1921) [HTML] (0) [PDF 1.21 M] (6470)
    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.
    2018,9(1):99-106. DOI: 10.16615/j.cnki.1674-8190.2018.01.013
    [Abstract] (3020) [HTML] (0) [PDF 1.77 M] (5774)
    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.
    2021,12(4):12-24. DOI: 10.16615/j.cnki.1674-8190.2021.04.02
    [Abstract] (1793) [HTML] (0) [PDF 1.57 M] (5537)
    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.
    2021,12(1):129-135. DOI: 10.16615/j.cnki.1674-8190.2021.01.017
    [Abstract] (1817) [HTML] (0) [PDF 1.19 M] (5486)
    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.
    2021,12(6):161-166. DOI: 10.16615/j.cnki.1674-8190.2021.06.20
    [Abstract] (1334) [HTML] (0) [PDF 533.70 K] (5361)
    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.
    [Abstract] (2592) [HTML] (0) [PDF 562.11 K] (5360)
    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.
    2023,14(2):24-34. DOI: 10.16615/j.cnki.1674-8190.2023.02.03
    [Abstract] (1421) [HTML] (1596) [PDF 1.07 M] (5311)
    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.
    2022,13(3):74-85. DOI: 10.16615/j.cnki.1674-8190.2022.03.09
    [Abstract] (1061) [HTML] (724) [PDF 2.69 M] (4963)
    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.
    2022,13(3):64-73. DOI: 10.16615/j.cnki.1674-8190.2022.03.08
    [Abstract] (1141) [HTML] (1124) [PDF 1.74 M] (4714)
    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.
    2020,11(2):159-166. DOI: 10.16615/j.cnki.1674-8190.2020.02.002
    [Abstract] (1865) [HTML] (0) [PDF 1.20 M] (4422)
    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.
    2014,5(1):109-115. DOI:
    [Abstract] (4493) [HTML] (0) [PDF 2.89 M] (4359)
    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.
    2020,11(2):147-158. DOI: 10.16615/j.cnki.1674-8190.2020.02.001
    [Abstract] (2234) [HTML] (0) [PDF 3.27 M] (4323)
    Abstract:
    To reasonably and efficiently guide the safe, reliable and economical operation of civil aircraft, we investigate the main contents and explore the application in operational reliability analysis and feedback of S5000F, i.e., international specification for in-service data feedback, which is organized by AeroSpace and Defence Industries Association of Europe (ASD). The compilation background and purpose of S5000F specification are first elaborated, and the main contents and the relevant business processes in the S5000F specification were then introduced. We finally discussed the application of S5000F specification in the operational reliability analysis and feedback of civil aircraft. In this paper, the S5000F specification is comprehensively interpreted, and its application in the operational reliability of civil aircraft is studied. In this case, we further extend this specification to the design phase and service phase of civil aircraft. The efforts of this study provide effective guidance for the life cycle management of civil aircraft.
    2018,9(3):297-308. DOI: 10.16615/j.cnki.1674-8190.2018.03.001
    [Abstract] (1894) [HTML] (0) [PDF 3.91 M] (4298)
    Abstract:
    This paper focuses on the research on the status of adaptive wing and summarizes from the adaptive compliant leading edge, the adaptive compliant trailing edge and the variable thickness wing, respectively. And the key technology that adaptive wing needs to be solved urgently is put forward, which can provide some technical reference for the design and implementation of adaptive wing structure.

Journal search

Submit

Click Ranking

External Links Links

WeChat

Mobile website