Abstract:The development of VTOL vehicles has been summerized in present paper, especially for the vehicles researched in recent years. More attention has been paid to the innovative design and new concepts. According to the kinds of VTOL vehicle driving power, all VTOL vehicles have been classified to four types. Every type vehicle has been listed and discussed briefly. The relevant important technology has been pointed out. Finally, the future possible developments of VTOL vehicles have been commented on.

Abstract:composite stiffened panels have considerable post-bucking potential capacity load that can substantially increase loading efficiency in aircraft design. In this paper, review on the EU research of design and analysis of stiffened composite panels including post-buckling are recommended. The relevant literatures are reviewed from the aspects of background, objectives, work packages, achievements, and analysis methods of projects. Finally, the trend of future fiber composite panel is introduced and the enlightenment of what these researches bring to us is also summarized.

Abstract:The common surrogate models used in aerodynamic optimization are mostly established based on empirical risk minimization, which have two problems: firstly, the precision of prediction is highly dependent on sample population size, however the computational cost is large by training samples with computional fluid dynamic (CFD) method, secondly, the over fitting problem can not be avoided due to reducing training error blindly. In order to solve the problems, the idea of building a surrogate model based on the principle of structural risk minimization is proposed, and a new kind of surrogate model is established through support vector regression (SVR). The model uses kernel function mapping the practical problems to high dimensional feature space, and reduced the Vapnik-Chervonenkis (VC) dimension by using linear discriminant function instead of non-linear discriminant function. The method has better generalization ability and can avoid the complexity for high dimension problem, which is proved by comparing with other surrogate model in case of little samples. An aerodynamic optimization is done for transport’s wing based on SVR surrogate model, it indicates that the surrogate model by SVR method can predict the aerodynamic characteristics quickly and accurately, by which the efficiency of the aerodynamic optimization can be improved, and the optimal results are reliable and controllable.

Abstract:Nowadays most general airplanes are still designed using similar methods with middle or large transport aircraft, which means that they use few optimization method, leading to low aerodynamic efficiency and high economic cost. To change this situation, some design features of general airplanes are analyzed and summarized from basic aerodynamic principles, which include two contradictions. Then an effective strategy was put forward for improving aerodynamic efficiency, different with traditional general airplane design methods and middle or large transport aircraft design methods. This strategy presents some new requirements on design methods of new general airplanes. A conceptual optimization design example was used to prove the effectiveness of this new strategy.

Abstract:A correction panel method was presented and applied to calculate the aerodynamic center location which is an important parameter in static aeroelasticity problem. The method which based on the CFD data at different attack angle corrected the downwash of the elastic deformation sectionally. Correction panel method fills the drawback of the panel method by including the nonlinear factor. Taken m6 wing aerodynamic center calculation as examples, this method keep high accuracy as well as CFD but performance higher efficiency. The method can get the aerodynamic center location and the aerodynamic center location changes correctly which the traditional panel method cannot handle. This slope corrected method is suitable for design stage of structure project.

Abstract:Researching on the nose landing gear of a certain pilotless aircraft,On the basis of the establishment of the hydraulic cylinder pressure differential equations,shimmy damper hydraulic model has been build. ThroughStheSsimulationSanalysisSofShydraulicSmodels,StheSareaSofSpowerSdiagramSdecreasesSbyS44%SwhenStheSoilSgasScontentSincreasesSfromS0.05%StoS0.5%.STheSco-simulationSofSkineticSmodelSandShydraulicSmodel,SbasedSonSLMSSVirtual.LabSMotionSandSAMESimSrespectively,ScompareStheSdynamicSresponsesSofSaircraftSyawSangleSinSdifferentSoilScompressibility. WithSdifferentSworkingSconditionsSofStheSshimmySflightStestSsimulation,StheSresultsSshowSthatStheSshimmySstabilitySisSverySsensitiveStoStheSoilSliquidScompressibility.SOilSgasScontentSwhichSisSnotSsoSlargeS(greaterSthanS0.12%),SisSenoughStoScauseSshimmySinstability.

Abstract:In order to reduce the structural weight of aircraft, structural optimization design for a Lift-fan UAV with ANSYS parameter design language(APDL) is carried on in this paper. Considering the special structural characteristics and flight conditions of the lift-fan UAV, the geometry optimization of the components was mainly conducted. At first, establishing the parametric analysis procedures for the structural optimization design of the lift-fan UAV was necessary. According to this procedures, the parametric modeling, loading and solving of the lift fan UAV were achieved. Then, using ANSYS optimization module was to complete the structural optimization. Finally, the results of the optimization were analyzed effectively. It shows that the method is rationality and validity.

Abstract:To carry out research of static steering ground torque for aircraft single nose wheel; Military Aircraft and modern civil aircraft requirement for nose wheel steering torque was raised; Composition of static steering torque for aircraft single nose wheel was discussed; Some defects to calculate component steering torque in different mentioned reference documents were summarized; Studied every component torque character; Every component torque formulation is deduced; Combined with one calculation case some useful results are gained: Steering torque against nose wheel ground friction force is maximum; Steering torque against main wheel rolling friction force and steering torque against lifting aircraft are big when steering nose wheel with wide angle.

Abstract:For liquid cooling system special on the plane, because the change of the flight altitude the ram air temperature and flow rate of change, so that the system has some changes, at the beginning of the system design, the huge amount of computation and the complex working conditions, based on this, this paper uses Simulink simulation platform Matlab, to establish the dynamic mathematical model of main parts of liquid cooling system at on the basis of previous studies, and establishes the system simulation model and simulation analysis of system. Comparing the simulation results with the experimental data, verify the simulation analysis are in high accuracy, prove that the simulation system can play an important role in the design and optimization of the follow-up of the liquid cooling system.

Abstract:To resolve the issue of manual dimming for lightplate lighting system in civil aircraft cockpit that increase pilot’s work loading, and not easily to precisely control the brightness of lightplate according to cockpit luminous environment, digital self-adjusting dimming control system of lightplate has been proposed. The background luminance is accurately measured with ambient light sensors, and based on luminance curve model, each lightplate illumination is computed, to realize self-adjusting of lightplate luminance combined with manual compensation and PWM dimming control technology, self-adjusting dimming effects of lightplate brightness is realized finally. Based on above solution, the design of system architecture and scheme design of main system components are completed. By simulation，prove that self-adjusting dimming control system can realize the expected objective. It can adjust the luminance of the lightplates exactly, and provide an effective way to improve the human ergonomics of aircraft lightplate lighting system.

Abstract:In order to characterize the microstructure and properties of matrix of porous carbon foam, phenolic-based carbon were synthesized by curing and carbonization of base-catalysis thermo-setting phenolic resin. Microstructure, compressive properties and fracture toughness of syntactic phenolic-based carbon were studied. The results showed that phenolic-based carbon mainly contained three phased: resin-derived carbon, micropores and microcracks; and carbon element existed in the form of sp₃-rich amorphous carbon. The compressive strength of phenolic-based carbon is 8.58 MPa, whose compressive fracture characteristic is brittle fracture. Its fracture toughness is worse, which was marked by the energy in compressive fracture of 0.135 MJ.m_-3.

Abstract:As a method of describing and evaluating the reliability of product, analysis of reliability data has been an important component of reliability engineering. The idea is put forward that the usage environment can be transformed into the test environment to fusion the test data and usage data based on the equal damage principle and then the reliability of product life can be analyzed by using the data fusion. After the data fusion, the technique states of usage product and test product are assumed to be the same and they come from the same matrix. The parameters of distribution function can be estimated by the maximum likelihood estimate method when the product life obeys some typical distributions, then the reliability of product life is analyzed by using the data fusion. The examples indicate that the sample capacity is increased after the data fusion, and the analysis accuracy of product life reliability can be improved under the same reliability and confidence level.

Abstract:With the development of the times, the durability of the wing wall analysis accuracy and calculation speed demand is increasing day by day. We must consider the transition from manual calculation to the program calculation. The AFAS software of ASRI is developed for military and civilian aircraft durability analysis of practical engineering application. This paper introduces the durability analysis process of wing wall structure by using DFR method calculating program based on AFAS. The result of analysis of the software of the wing panel reliability life is quite similar with the test results. These results suggest that the accuracy of the DFR method can meet the requirement and the software AFAS can be used as a a fast and exact calculation tool of the panel design and analysis.

Abstract:As the representative of the new generation large commercial aircraft, the design of a large quantity of big cabin windows on A380 is one of the key points. It shows the research and analysis of the window frame assembly and window frame structure from the aspects of conception comparison, load condition of components, material selection and so on, aiming at introducing the experience of the design of cabin window frames of A380. It demonstrates a successful design case of large commercial aircraft cabin window frame, through the presentation of detail parts and joint, selection of materials for main structure and the comparison of FEM analysis result and static test data, provided as the design reference of the subsequent aircraft window frame.

Abstract:The ergonomics design of the civil flight deck is such a design philosophy which takes the loop of “Pilot-Flight-Environment” as an entire object in order to improve the flight safety. The ergonomics design philosophy and corresponding methods of the civil flight deck are demonstrated from aspects of display interface, arrangements of control devices and light environments in the civil flight deck, while some practical examples are also illustrated to show the effective result of the design methodin this paperIt is expected that the design of future advanced civil flight deck can significantly benefit from the methodperformed this paper.

Abstract:Criticality matrix analysis is an important method of product analysis and guide improvement measures. In order to solve the situation where experience determines the probability failure mode effect, the designers need to adopt a more practical and objective method. According to the principle and method of quantitative analysis of criticality matrix, the experience reference and ranges of the Failure mode effect probability are collected. Then, the method to achieve the failure mode effect probability based on the fault tree is put forward, and a calculation example is given. The process to determine the probability of failure mode effect is achieved in this article.

Abstract:In order to slove the Control problem of intake air amount of aviation aircraft engine , design a simple structure, high reliability Mach annunciator. when the Mach of Inlet reaches a set value M, the mach annunciator provides a signal to the engine inlet ramp-conditioning systems. Mach annunciator selection mechanical membrane cartridge as the sensor signal. Through theoretical analysis and calculation to measurement principle of M number, the mach annunciator is designed and manufactured according to the results of analysis，mach annunciator can meet the requirements of the engine inlet automatically adjust.

Abstract:The purpose of this study is to achieve the RNP training program for the flight simulator airport visual simulation database. Items from a specific requirement for the actual altitude airports RNP flight procedures training , studies the RNP procedures, the terrain mesh algorithm human intervention , guided terrain generation effectiveness and accuracy required , the finally, to meet flight verification and training requirements. Results of this study can be generalized to other similar airports visual simulation development.

Abstract:Considering the difficulties，which the design of fuel control system of aero engine may meet in face of a second-order unsteady actuator，the variable-structure control method，which makes the second-order unsteady actuator into an assured first-order inertial element, is introduced. This method is especially suitable to drive a pulse proportional valve, for it makes full use of its advantage, invariance, while having dodged its inherent disadvantage, chattering. Some key technologies to solve specific problems to implemente variable structure control on pulse proportional valve，such as precision problem of differential, and some necessary conditions in relation to the feasibility of this method are also specified. The patent number of this method : 201010610220.8。

Abstract:In view of the communication requirements and control strategy of the electro-mechanical integrated management system, the communication method based on redundant CAN bus is put forward, and a practical CAN application layer protocol based on CAN 2.0B is established. The setting and signification for each function field in the designed frame structure is explicated. Dual filter mode is applied in each node to support point-to-point and broadcast respectively. The simulation and verification environment of CAN bus communication for integrated management of airborne electromechanical system has been established based on this protocol. Experimental results indicate that this redundant CAN communication system works well, the application layer protocol has the advantages of low bus loads, reliability and real time.