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    Review
    Research Progress Analysis on Risk Assessment of Runway Excursion
    Zhaodingyi, QI Xinge, WANG Lei
    2025,16(1):1-8. DOI: 10.16615/j.cnki.1674-8190.2025.01.01
    [Abstract] (53) [HTML] (33) [PDF 771.66 K] (205)
    Abstract:
    Runway excursion ranks second among the most catastrophic symptoms. Research on the risk assessment of runway excursion has been done by domestic and international civil aviation research institutes, specialists, and academics in an effort to lessen both its likelihood and its effects. Several important contributing variables have been the subject of recent study, including unfavorable weather circumstances, runway surface conditions, pilot mistakes, and mechanical issues. These issues can be resolved by improving runway maintenance and improving pilot training. The accomplishments and flaws are compiled by looking at the current designs of both domestic and international experts on the runway excursion occurrences. The study directions and contents of local and international experts are compared, and a summary of the risk factors for runway excursion events is produced. The techniques for predicting and analyzing the danger of a runway excursion are described, and suggestions for more research are made for future study.
    Research progress on online monitoring technology of wear particles in aviation lubricating oil
    Zheng Shanhong, Wu Haijun, Li Xiangyouzhi, Zheng Yunlong
    2025,16(1):9-17. DOI: 10.16615/j.cnki.1674-8190.2025.01.02
    [Abstract] (30) [HTML] (28) [PDF 1.28 M] (89)
    Abstract:
    Due to the wear particles in lubricating oil contain important information about the wear of engine components, wear particle monitoring is an effective method for judging the health status of engines and providing early fault warning. Online monitoring technology can provide real-time equipment status information. This article introduces the current online monitoring technologies for lubricating oil and abrasive particles, including capacitance method, resistance method，magnetic induction method, optical method, and acoustic method monitoring technologies. It discusses the monitoring principles, research results, advantages and disadvantages of each technology, analyzes the application status of the five monitoring technologies, and finally discusses the future development trend of lubricating oil and abrasive particle online monitoring technology.
    Theoretical Research
    Optimization for conceptual design of STOL aircraft with distributed electric propulsion
    LV Minghao, YU Xiongqing
    2025,16(1):18-25. DOI: 10.16615/j.cnki.1674-8190.2025.01.03
    [Abstract] (58) [HTML] (132) [PDF 1.17 M] (161)
    Abstract:
    The short takeoff and landing aircraft using distributed electric propulsion is a novel concept, for which the design method of its key parameters needs to be explored. In this paper, taking the conventional turboprop aircraft retrofitted with distributed electric propellers as an illustrative aircraft, the design problem of the aircraft key parameters is formulated as an optimization problem, and then the design optimization process for the key aircraft parameters is presented using the optimization method with surrogate model. Multidisciplinary analysis for the such aircraft conceptual design is used to evaluate the values of objective and constraint functions in optimization problems. The multidisciplinary analysis consists of several analysis modules including geometry, aerodynamics, propulsion, weight and performance. After optimization for the key parameters of the illustrative aircraft concept, the demanding requirements for the ground roll distance during takeoff and landing can be met at the minimum weight penalty. The ground roll distance during takeoff is less than 100m; the ground roll distance during landing is less than 70m. The optimal results also indicate that the distributed propellers are installed beneath the wing at a certain angle of inclination with moderate rotation speed and diameter, the wing area is increased slightly and required power for the turboprop engine is reduced significantly.
    Rotor position optimization of a hybrid configuration UAV based on orthogonal test
    Wang Xiaolu, Liu Weiwei, Chen Changning, Zhang Yifan
    2025,16(1):26-36,44. DOI: 10.16615/j.cnki.1674-8190.2025.01.04
    [Abstract] (36) [HTML] (72) [PDF 2.63 M] (102)
    Abstract:
    As rotor positions have significant effect on aerodynamic characteristics of hybrid configuration Unmanned Aerial Vehicle(UAV), it is necessary to investigate the criteria of rotor positions arrangement. The aerodynamic characteristics of a typical hybrid configuration UAV is analyzed by numerical method. Taking the lift-to-drag ratio and longitudinal static stability as the optimization objectives, a three-factor four-level orthogonal experimental of the chordwise, spanwise and vertical positions of the rotor is designed. The effects of three factors of rotor position are discussed by means of intuitive analysis and computational analysis. The results show that the maximum lift-to-drag ratio of the optimized design parameter combination obtained by the orthogonal test design result is about 2 times larger than that of the initial design parameter combination, and the slope of the pitch moment coefficient curve increases by about 15%. For present configuration, the results show that the effect of factors on the lift-to-drag ratio and the slope of the pitch moment coefficient curve are in a descending order as follows: chordwise, spanwise and vertical positions.
    The Sensitivity Analysis of Coupling Parameters Between All-Day Cruise Altitude and Wing Load of Solar-Powered Airplane
    qiufusheng, dong yihang, du yimin
    2025,16(1):37-44. DOI: 10.16615/j.cnki.1674-8190.2025.01.05
    [Abstract] (30) [HTML] (60) [PDF 1021.37 K] (97)
    Abstract:
    Compared to conventional powered aircraft, the solar-powered aircraft have characteristics of high-altitude and long-endurance. They can modularly change the task loads and carry out related special tasks. Based on the working principle of long endurance solar-powered aircraft, the coupling relationship between the all-day cruising altitude and wing load of solar-powered aircraft under the energy balance design system was analyzed. The coupling parameters, including aerodynamic parameters, solar panels efficiency and paving rate, propulsion system efficiency and load power factor, flight season and flight latitude, were systematically analyzed for sensitivity, The results indicate that the design or optimization of appropriate lift and drag coefficients should be the first consideration for long endurance solar-powered aircraft to achieve best aerodynamic efficiency; When the efficiency of solar panels reaches 0.35 or above, increasing the installation rate of solar panels has a weaker impact on the all-day cruising altitude, but it helps to increase the upper limit of wing load. The research results can serve as a reference for the overall design and improvement optimization of solar-powered aircraft.
    A Novel Aircraft Maneuver Division and Recognition Method based on 2D Flight Path and Perceptually Important Point of Time Sequence
    Yin Zhiping, Huang Yongsheng, Tian Jiawei, Cao Shancheng
    2025,16(1):45-53. DOI: 10.16615/j.cnki.1674-8190.2025.01.06
    [Abstract] (27) [HTML] (39) [PDF 1.15 M] (102)
    Abstract:
    Aircraft maneuver recognition is an important basis for flight action evaluation, flight load spectrum research, flight simulation and other research work. Aiming at overcoming the disadvantage that most of the existing maneuvers are based on the existing standard actions, combined with the important points of the time sequence, an adaptive maneuver recognition method based on horizontal and vertical plane flight trajectory projection merging is proposed. This method extracts the maneuvers in the flight data according to the trend of the two-dimensional plane trajectory data and combines and refines the maneuvers with the idea of maneuvers splicing. A maneuver recognition case study is carried out with complete aircraft takeoff and landing data. It is found that this proposed method can enhance the recognition efficiency of flight maneuvers and the division efficiency.
    Adaptive Robust Anti-disturbance Attitude Control for Quadrotors
    LI Tongshuai, CHEN Longsheng, PengYun, SHI Tongxin, JIN Feiyu
    2025,16(1):54-63. DOI: 10.16615/j.cnki.1674-8190.2025.01.07
    [Abstract] (35) [HTML] (42) [PDF 1.46 M] (90)
    Abstract:
    The high-performance attitude controller can effectively suppress comprehensive effects caused by uncertainties and external dynamic disturbances, and ensure that the quadrotor can safely and reliably fly to complete the designated mission. Therefore, nonlinear uncertainties of quadrotor flight systems are approximated by a radial function neural network (RBFNN) quadrotor, and an extended state observer is designed to estimate lumped disturbances caused by RBFNN approximation errors and external disturbances in this paper. The black box problem of RBFNN is solved by using a model identification error and a tracking error as decision variables. Then, an adaptive robust anti-disturbance attitude tracking controller is designed for quadrotor flight systems based on dynamic surface control and Lyapunov stability theory, and an auxiliary system is constructed to suppress the effect of filtering error on the closed-loop system performance. Finally, Simulation results show that the quadrotor can precisely track the desired attitude angles, and the proposed controller has strong robustness and stability in the presence of uncertainties and disturbances.
    Engineering Application
    Investigation on the influence of aerodynamic characteristics of GAW-1 two-element airfoil with slot
    ZHANG Zhihao, HAO Lishu, GAO Yongwei, LV Wenhao
    2025,16(1):64-74. DOI: 10.16615/j.cnki.1674-8190.2025.01.08
    [Abstract] (28) [HTML] (63) [PDF 5.08 M] (108)
    Abstract:
    Airfoil slotted is a passive flow control technology to improve the stall characteristics of airfoil by using slot jet. In order to explore the influence of the slot parameters change on the aerodynamic characteristics of multi-element airfoil, the CFD method is used to study the slotting of GAW-1 two-element airfoil in the paper. Nine kinds of slot configurations are designed, and the geometric relations among three types of slot configurations, namely straight line, curve and deflector, are given, and a curved trapezoidal slot configuration is proposed. It is found that the slot position is the key factor to restrain the stall development of airfoil, and the optimal slot position of curved trapezoidal slot configuration is 13.5% c; the slot has the strongest ability to restrain stall, the stall angle of attack of airfoil is delayed by 7°, and the maximum lift coefficient is increased by 19.5%, reaching 3.89. Finally, the influence of the deflector slot configuration on the aerodynamic characteristics of the airfoil is studied. The deflector slot configuration can not only weaken the damage of the slot to the aerodynamic characteristics at a small angle of attack, but also slow down the stall development and improve the stall characteristics of the airfoil. In this paper, the research ideas and results of slotted multi-element airfoil can provide a reference for the subsequent research of other slotted multi-element airfoil.
    The key technologies of tiltrotor pylon conversion actuator
    Li Hailin, Si Jun, Dang Kexin, Zhang Wei, Liu Longfei, Wang Xudong
    2025,16(1):75-81,92. DOI: 10.16615/j.cnki.1674-8190.2025.01.09
    [Abstract] (38) [HTML] (280) [PDF 3.95 M] (211)
    Abstract:
    Tiltrotor which combines the advantages of helicopters and fixed wing aircraft, is a key direction for future aviation equipment development. This article focuses on the key component of tiltrotor - pylon conversion actuator. The tilting actuation principle of tiltrotor is introduced, the advantages and disadvantages of V-22 and BA609 pylon conversion actuator configurations are analyzed and compared, and the key technologies of pylon conversion actuator of tiltrotor are discussed, including power summing technology, double-layer telescopic ball screw technology, ball screw end shock damper technology. The power summing technology can realize double-system synthesis by speed summing or force summing, which is the key to improve the reliability of pylon conversion actuator. Double-layer telescopic ball screw can effectively shorten the volume after the actuator is retracted, reduce the space on the aircraft nacelle, and greatly improve the safety of the actuator; Shock damper is a means to effectively restrain the impact caused by the screw end collision, which is very suitable for linear output mechanism such as ball screw.
    Analysis of Spin-up and Spring back Loads of Landing Gear Based on Slip Rate
    WU Ming, NIE Hong, ZHANG Ming, SHI Xia Zheng
    2025,16(1):82-92. DOI: 10.16615/j.cnki.1674-8190.2025.01.10
    [Abstract] (27) [HTML] (36) [PDF 2.13 M] (89)
    Abstract:
    The landing gear spin-up and spring back loads are an important part of the aircraft landing load, and the dynamic analysis method can be used to analyze it effectively at the beginning of the design stage. In this paper, the landing gear drop test dynamic model is established by using the nonlinear spring damping system at the axle to simulate the strut elasticity, and the spin-up and spring back loads and its corresponding slip rate change trend under the two motion forms of wheel reversal and wheel start-up are analyzed. The effects of aircraft heading speed, track slip rate curve and wheel pre-rotation speed on landing gear spin-up and spring back loads are analyzed. The results show that reducing the heading speed of the aircraft, giving the wheel pre-rotation speed and reducing the friction coefficient between the tire and the ground can reduce the spin-up loads.
    Design and implementation of a spliced tilting dual rotor and its LADRC flight control
    LIU Kun, XU Jinfa
    2025,16(1):93-100. DOI: 10.16615/j.cnki.1674-8190.2025.01.11
    [Abstract] (28) [HTML] (46) [PDF 1.71 M] (85)
    Abstract:
    The configuration characteristics of multi rotor unmanned aerial vehicles determine that they are difficult to adapt to complex flight missions. To meet different mission requirements, combining and assembling specific configuration aircraft should be a feasible development direction. Before and after assembly, various flight characteristics of the aircraft change to varying degrees, and the impact of external disturbances also varies, posing great challenges to the design and verification of flight control systems. This article designs a spliced tilted twin rotor aircraft and establishes its flight dynamics model. Based on this, the control strategy of the pre and post assembly aircraft and the position and attitude controllers based on linear active disturbance rejection control (LADRC) are designed, and the simulation verification of aircraft control in gust interference environments is completed. Compared with traditional PID controllers, the superiority of LADRC has been verified. Finally, a real aircraft attitude stability control verification was conducted, and the research results showed that the spliced tilt-rotor dual rotor aircraft and its linear active disturbance rejection controller had strong anti-interference and robustness. The aircraft had good flight control effects before and after assembly.
    Impact of Visual Guidance Error on Automatic Carrier Landing Performance
    ZHEN Chong, QU Xiaolei, WANG Yifeng, ZHANG Yuxiang, HAN Fengming
    2025,16(1):101-107，116. DOI: 10.16615/j.cnki.1674-8190.2025.01.12
    [Abstract] (25) [HTML] (28) [PDF 823.78 K] (89)
    Abstract:
    The performance of guidance system is the key factor of automatic carrier landing system. The positioning principles, measurement errors and effects on automatic carrier landing of airborne visual guidance architecture are investigated. The coplanar P4P relative positioning issue by means of cooperative landing aids is studied firstly, and by analyzing measurement error factors, types, probability distributions of the imaging devices, the three-axis positioning results affected by the errors are obtained using calculated coordinate transformation and the guidance error systems are modeled. Considering F/A-18A carrier-based aircraft automatic landing, the simulated positioning measurement accuracy of airborne visual guidance from gliding to touchdown are estimated. Further, the disturbances of automatic carrier landing system delay, airborne sensor noises, air-wake and deck motion are introduced, multi-factor coupled simulation system is modeled and touchdown position standard errors are calculated based on Monte-Carlo simulations influenced by the disturbances. The positioning accuracy and automatic landing performance of the proposed airborne visual guidance architecture achieves the performance of traditional guidance architectures. The deck motion and air-wake play important roles in automatic carrier landing performance.
    Research on Prediction of Turning Deformation of Domestic 7050 Aluminum Alloy Thin-wall Bearing Frame
    MAXIUWEI, HUYUE, YAOWENLI, JIANGRUISONG
    2025,16(1):108-116. DOI: 10.16615/j.cnki.1674-8190.2025.01.13
    [Abstract] (13) [HTML] (7) [PDF 6.31 M] (72)
    Abstract:
    Researching the deformation prediction of domestic 7050 aluminum alloy aviation thin-walled parts during turning processing and establishing an accurate finite element model for predicting turning deformation is of great significance for ensuring the machining precision and dimensional stability of aviation thin-walled parts, as well as improving the structural strength and reliability of aircraft. This thesis employs simulation and experimental demonstration methods to study the influence of the coupling effect between the initial residual stress of domestic 7050 aluminum alloy and the turning residual stress on the deformation of thin-walled bearing frames during processing. Firstly, based on the machining process of aviation thin-walled bearing frames, a turning deformation simulation model of the bearing frame was established using the birth and death element method. Further, the initial residual stress field of the bearing frame blank and the turning surface residual stress were obtained through the blind hole method and turning experiments, respectively. Lastly, based on the turning deformation simulation model, the deformation of the bearing frame under the coupling effect of the initial residual stress field and turning residual stress was predicted and experimentally verified. The results show that the error of the bearing frame deformation simulation prediction model is less than 15%. The conclusions of this thesis can provide technical support for the control of bearing frame machining deformation.
    Research on Aero-engine Performance Modeling Based on General Simulation Framework
    Gao yang, wang xin, Liu zhen gang
    2025,16(1):117-126. DOI: 10.16615/j.cnki.1674-8190.2025.01.14
    [Abstract] (17) [HTML] (10) [PDF 2.87 M] (58)
    Abstract:
    At present, the in-depth application of aero-engine performance model in the field of test flight has become a hot spot under the background of digital test flight, which is of great value and significance to the planning and organization of test sites in the process of flight test, risk identification and analysis, and auxiliary analysis and evaluation of test flight results. This paper studies the performance modeling of a two-rotor hybrid turbofan engine based on a general object-oriented simulation architecture. The model is constructed according to the actual air path connection and rotor physical connection between components, and considers the uneven distribution of fan outlet section parameters, the influence of high / low pressure turbine cooling and variable heat effect on the engine performance. In order to improve the model prediction accuracy, a correction method of the characteristics of rotating components based on the actual joint working line, and the deviation of the performance parameters under different working conditions is less than 3%; Finally, through the steady performance and transient performance of the model under different working conditions, the performance characteristics of the engine in the working envelope and the thrust transient characteristics of the sea level standard atmospheric environment are presented.
    An example analysis of the effect of different obstacle-surmounting modes on take-off performance
    Chen Hongying, Xu Mengyu, Ni Maolin
    2025,16(1):127-132. DOI: 10.16615/j.cnki.1674-8190.2025.01.15
    [Abstract] (22) [HTML] (8) [PDF 894.18 K] (69)
    Abstract:
    In operation of civil aircraft, the maximum takeoff weight is limited by the performmance when one engine fails, and it"s of great significance to optimize takeoff performance by excuting different obstacle clearing methods to increase the maximum takeoff weight. Based on the theoretical analysis of the takeoff flight path defined in the regulations, this paper calculated the maximum takeoff weight corresponding to the standard second segment, extended second segment, and fourth segment obstacle clearing method, and analysed their obstacle clearence, climb gradients, and takeoff distance to ascertain the key factor which limits the maximum takeoff weight. Different distances and gradients are combined to simulate various terrain conditions, and the takeoff weights of standard second segment and forth segment obstacle clearing method in those terrain conditions are calculated. The result shows that using of fourth segment obstacle clearing method can effectively improve the maximum takeoff weight of the aircraft. And the larger the gradient of the obstacle is, the more significant the improvement is. At plateau airports with complex terrain, the use of fourth segment obstacle clearing method can significantly improve takeoff performance and operational efficiency.1\
    “第三届飞行器服役（作战）完整性”专栏
    Aerodynamic Integrity of Military Aerocraft
    ZHANG Dengcheng, HE Yuting, ZHAO Zaihao, ZHANG Teng, ZHANG Yanhua
    2025,16(1):133-138. DOI: 10.16615/j.cnki.1674-8190.2025.01.16
    [Abstract] (17) [HTML] (17) [PDF 374.60 K] (70)
    Abstract:
    In view of the fact that there is no one that can comprehensively characterize the aerodynamic quality characteristics of military aerocraft, the concept of aerodynamic integrity is proposed for the first time and its research is carried out. It is believed that the aerodynamic integrity of military aerocraft can comprehensively characterize its aerodynamic mass characteristics in the process of combat use. Firstly, the process and definition of the concept of aerodynamic integrity are introduced, and the basic connotation and basic characteristics are discussed. It is believed that the aerodynamic integrity of military aerocraft is the basis of the combat effectiveness of aerocraft. The characterization method of Aerocraft aerodynamic integrity is introduced, and the main influencing factors of military aerocraft aerodynamic integrity are analyzed. The new concept of aerodynamic integrity of military aerocraft is introduced aims to provide reference for the development of military aerocraft design, manufacturing, testing and support in China.
    Research progress of aircraft fault diagnosis method integrating multi-source heterogeneous data
    MA Chao, Zou Ziyang, Gu Zhengbo, Zhao Shujie
    2025,16(1):139-150. DOI: 10.16615/j.cnki.1674-8190.2025.01.17
    [Abstract] (29) [HTML] (20) [PDF 1.05 M] (79)
    Abstract:
    With the improvement of the digitization degree of the aircraft, a large amount of multi-source and heterogeneous data will be generated throughout the full lifecycle of an aircraft, which plays a crucial role in ensuring its safety. This article reviews common types of data sources within the aircraft"s lifecycle, including initial airworthiness design data, operational reliability data, operational maintenance data, and onboard equipment data. By combining the data characteristics of different data source types, the article introduces measures for the fusion application of multi-source heterogeneous data and provides a detailed analysis of the four stages that data fusion technology has undergone. On this basis, the fault diagnosis method of fusion data is introduced. Compared with the fault diagnosis analysis of traditional single data source, it is concluded that the fusion application of multi-source heterogeneous data can analyze the fault causes more accurately, and play a role in assisting troubleshooting and maintainability design, which is the development trend of data application technology in aircraft fault diagnosis.
    Research on Loads Predicting Method of Key Structure of Aircraft Based on Neural Network
    xue haifeng, ZHANG YANJUN, NING YU
    2025,16(1):151-157，168. DOI: 10.16615/j.cnki.1674-8190.2025.01.18
    [Abstract] (21) [HTML] (26) [PDF 1.77 M] (75)
    Abstract:
    The load prediction based on the data used in aircraft plays an important role in the damage analysis and life prediction of aircraft, which can provide technical support for the active on-condition maintenance of aircraft. In this paper, forward neural network is used to establish the load model of shear force, bending moment and torque of the tail wing root of a large transport aircraft. Compared with the load calculated by finite element model, the prediction errors of the neural network model meet the engineering requirements, and compared with the prediction results of the multivariate linear regression model, the results show that the prediction accuracy of the neural network model is better than that of the multivariate linear regression model. The neural network model provides a feasible method for measuring the loads on key structures of a large transport aircraft.
    Preliminary structural design methodology for modular wing
    fanfulei, liyi, chenchunying, jiazhaohu
    2025,16(1):158-168. DOI: 10.16615/j.cnki.1674-8190.2025.01.19
    [Abstract] (19) [HTML] (15) [PDF 1.22 M] (72)
    Abstract:
    Aircraft modular design can increase the types of missions and reduce costs. In the initial stage of wing modular structure design, the unclearness of wingtip deformation limits the ability to assess the contribution differences of structural stiffness characteristics among wings with different spans to the system objective function (minimal structural weight).Aiming at the above problems, this paper introduces the weight coefficients of each subsystem level in the system level on the basis of the sensitivity coordinated optimization method to simulate the phenomenon that different subsystems contribute differently to the objective function of the system in the actual design work, and gives the computation methods of weight coefficients of the wing structures with different spreading lengths (different subsystems levels), forming the sensitivity coordinated optimization method with subsystem level weights. Finally, the preliminary structure design method of modular wing is verified by solving the modular truss and modular wing structure optimization example. The results show that the sensitivity-coordinated optimization method that includes subsystem weights can obtain a modular wing preliminary structure that satisfies both strength requirements and a certain degree of stiffness.
    Integrated Wing Force Transfer Analysis Method And Structural Design Considering Connection Design
    Suiguoxiang, Jinhaibo
    2025,16(1):169-176. DOI: 10.16615/j.cnki.1674-8190.2025.01.20
    [Abstract] (16) [HTML] (13) [PDF 1.30 M] (67)
    Abstract:
    Sensor aircraft and integrated wings embody the integrated design concept of integrating functional components and structures. However, there are problems with discontinuous skin force transmission and difficult connection in the wing structure, making the connection strength of functional skin a control factor in the design process. Therefore, this article combines the functional requirements and structural characteristics of the integrated wing, adopts a simplified connection calculation method, conducts force transfer analysis and connection characteristics analysis on the key sections at the separation surface of the functional skin design, obtains the ideal connection load and connection parameters at the separation surface, completes the connection design and size design, and verifies it through finite element analysis and optimization analysis. The results show that the estimated bending moment distribution of the box section using this force transfer analysis method is consistent with the finite element analysis results; The calculated size distribution of each section of the box section structure is similar to the optimization results, which can meet the requirements of connection strength and stability; The larger the effective height of the wing beam in the box section structure, the greater the load it bears, and the more consistent the optimization results with the force transfer analysis results.
    Study on mechanical properties of aeronautical composite interference-fit structures in hygrothermal service
    QIU Hongjun, Zhong Zipeng, Liang Weiying, Liu Chao, Cheng Xiuquan
    2025,16(1):177-186. DOI: 10.16615/j.cnki.1674-8190.2025.01.21
    [Abstract] (21) [HTML] (14) [PDF 6.17 M] (54)
    Abstract:
    In order to reveal the influence of hygrothermal environment on the mechanical properties of aeronautical composite connection structure, a numerical simulation model of composite interference-fit structure was established based on the mechanical ontological relationship and continuous damage model of composites under the hygrothermal environment with the object of composite interference-fit structure. The model was utilized to analyze the static strength and damage failure of interference-fit structures in the hygrothermal cycle of 0 days, 30 days, 60 days, 90 days and 120 days respectively, and was validated with the hygrothermal aging experiment. The results show that the ultimate load of the composite interference-fit structure decreases by 3.33%, 5.63%, 8.83% and 10.81% respectively, as the hygrothermal cycling period increases from 0 days to 120 days; the hygrothermal environment causes the aging reaction within the composite matrix, results in a rapid deterioration of the matrix performance, while has little effect on the fiber damage. The validity of the numerical simulation model was verified by comparing the experimental results with the simulation results.
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    A survey of deep reinforcement learning technologies for intelligent air combat
    Ni Li, Yunxiao Lian, Pan Zhou, Feng Xie, Zhili Tang, Haoran Zhou, Jun Chen
    Available online:March 20, 2025, DOI:
    [Abstract] (137) [HTML] (0) [PDF 2.53 M] (3)
    Abstract:
    With the gradual unmanned, intelligent, and clustered development of aircraft, the air battlefield is gradually entering the era of intelligent air combat. Major aviation powers such as the United States and China, as well as related research institutions, are also focusing on exploration and research of key technologies for intelligent air combat. Deep reinforcement learning combines the perceptual ability of deep learning with the decision-making ability of reinforcement learning, demonstrating significant advantages in the emergence of air combat capabilities. This article, based on the urgent needs of intelligent air combat development, analyzes and summarizes the mainstream algorithms in the field of deep reinforcement learning, and explores the points of integration with the air combat field. From the perspective of algorithm implementation, it identifies key technologies of deep reinforcement learning in air combat. By sorting out the current cutting-edge technological achievements in the field of air combat, it is concluded that the future research on deep reinforcement learning will develop from single-to-single air combat to cluster air combat. Finally, the challenges algorithm faces are proposed, providing reference and guidance for the development of intelligent algorithms in intelligent air combat.
    Research on Autonomous Indoor Target Search Solution for MAVs
    Tang Dongyang, Han Qing, Tian Keyuan, Liu Xing
    Available online:March 20, 2025, DOI:
    [Abstract] (22) [HTML] (0) [PDF 3.33 M] (1)
    Abstract:
    To accomplish the task of searching for specific indoor targets with a drone, even when system power consumption and platform weight are constrained, a low-cost, low-power, small-size drone design for autonomous indoor target search is proposed. Firstly, a suitable UAV hardware architecture based on constraints is chosen, and the controller is designed using saturation control. Besides, a simple sensor combination comprising three TF-Luna laser sensors is employed to gather environmental information. In the obstacle avoidance algorithm design, the avoidance logic of the Bug algorithm is referenced, achieving the design of the UAV"s autonomous cruising mode. Then, the image acquisition chip is used to obtain real-time image information in the drone"s flight direction. The chip integrated with the YOLO-v2 algorithm detects target information in the images. Furthermore, a central region following strategy is employed to achieve real-time tracking of the target. Finally, the simulation and actual flight of the autonomous cruise and target detection tracking tasks were completed at a speed of 1m/s in a 6m x 6m Simulink simulation environment and real-world scenarios.
    Research on Model Predictive Control Strategy of Hybrid Electric UAV
    MAN YI
    Available online:March 20, 2025, DOI:
    [Abstract] (56) [HTML] (0) [PDF 646.59 K] (3)
    Abstract:
    Compared with conventional fuel aircraft or electric aircraft with a single battery source, the adoption of hybrid power in UAVs has become an increasingly popular research direction because it will reduce carbon emissions, reduce energy consumption or increase flight time.However, due to the complex operating conditions and drastic load changes of UAV, the power demand cannot be satisfied by fuel cell alone. It is necessary to add energy storage elements such as lithium battery or super capacitor as its auxiliary power supply. Therefore, the research on energy management strategy of hybrid power system with fuel cell as the main power supply is of great significance to solve the problem of UAV endurance time. Focusing on the UAV hybrid system based on fuel cell-lithium battery-supercapacitor, a model predictive control energy management strategy based on the minimum equivalent hydrogen consumption algorithm is proposed in this paper. The strategy applies the minimum equivalent hydrogen consumption strategy to the model predictive control framework, which not only meets the system load demand, but also improves the fuel economy. Finally, the simulation results show that the hydrogen consumption of the system is reduced effectively and the optimal power distribution is realized.
    Wind Tunnel Flow Visualization Experimental Study on the Influence of Vortex Generators on the Low-Speed Characteristics of Civil Transport Aircraft
    Yan Wei, xuhuiwen, wangqinmin, chenmengying, zhangmeihong, zhaokeliang, jiaorenshan, niuzhongguo, wangfei, zengwepin
    Available online:March 20, 2025, DOI:
    [Abstract] (25) [HTML] (0) [PDF 10.71 M] (1)
    Abstract:
    In order to improve the take-off and landing performance of civil transport aircraft, it is necessary to control the flow separation on the suction surface of the wing. The vortex generator is a simple passive flow control technology that has potential positive benefits for delaying the separation of the fluid boundary layer and improving the take-off and landing performance of the aircraft. Research on rectangular vortex generators was carried out through civil transport aircraft model wind tunnel tests. The rectangular vortex generator was installed near the leading edge of the inner wing of the wing. The test used smoke flow technology, fluorescent tuft technology and PIV particle image velocity measurement technology. Through smoke flow experiments and fluorescent tuft experiments, the conclusion that rectangular vortex generators can improve the separation of the inner wing downstream area of the wing was qualitatively captured; Through the PIV particle image velocimetry experiment, we quantitatively obtained a pattern of the use of a rectangular vortex generator at a designated station downstream of the inner wing of the wing, which can force the separation flow in the separation area to become an airfoil-attached flow again. Based on the test results, the rectangular vortex generator can significantly improve the low-speed characteristics of civil aircraft.
    Research on turning machinability of a new GH4198 superalloy
    JIN Qichao, ZHANG Jinqi, TAN Haibing, LI Fulin, FU Rui, GUO Lei
    Available online:March 20, 2025, DOI:
    [Abstract] (174) [HTML] (0) [PDF 1.94 M] (1)
    Abstract:
    The new GH4198 nickel based superalloy is a key material for high-performance aviation engine hot end components, and its turning workability has a significant impact on surface quality and service performance. Conduct turning experiments based on single factor method and study the influence of turning parameters on turning force, turning temperature, and surface roughness. The experimental results show that within the range of experimental parameters, both turning force and turning temperature increase continuously with the increase of turning parameters. Among them, the factor that has the greatest impact on turning force is turning depth, with a maximum turning force of 685.2N; The factor that has the greatest impact on turning temperature is turning speed, with a maximum turning temperature of 484.8 ℃; The feed rate has the greatest impact on surface roughness, with a minimum surface roughness of 0.346 μm. Therefore, during rough machining, a turning speed of v=130m/min, a feed rate of f=0.14mm/r, and a turning depth of ap=0.8mm can be selected to achieve efficient material removal. During precision machining, a turning speed of v=90m/min, a feed rate of f=0.06mm/r, and a turning depth of ap=0.3mm can be selected to improve surface quality, providing a theoretical basis for the processing of the new material GH4198.
    Key technologies for future development of intelligent variant aircraft
    CAO Xin, LI Congjian, GAO Chuan, WEI Zhenglei, WANG Lulu, MA Xiaoyong
    Available online:March 13, 2025, DOI:
    [Abstract] (9) [HTML] (0) [PDF 3.56 M] (5)
    Abstract:
    Intelligent variant aircraft is one of the important development directions of advanced aircraft in the future, and it is also an innovative research frontier in the aerospace field, with potential important value in the future civil and military fields. The overall performance advantages of intelligent variant aircraft are mainly reflected in aspects such as cross speed domain and cross medium. The width of the aircraft"s airspace and speed domain determines the size need of the variant. Especially the transonic variant aircraft, which has good takeoff and landing, acceleration performance, and supersonic flight capabilities can better perform tasks such as economic cruising, wide-area monitoring, rapid arrival, and successful breakthrough. Combined with intelligent OODA autonomous closed-loop, it is expected to become an important intelligent aircraft unit/platform in the future. In this paper, the research progress and future key technologies of intelligent variant aircraft are analyzed, and the concept and application prospect of a new large-scale variant aircraft are introduced and prospected. The above analysis can be used as reference for related research fields.
    Development in aerodynamic design of tiltrotor aircraft
    Wang Zonghui, Yang Yunjun, Zhao Jiaxiang
    Available online:March 13, 2025, DOI:
    [Abstract] (12) [HTML] (0) [PDF 2.12 M] (4)
    Abstract:
    The tiltrotor aircraft has both traditional helicopter vertical takeoff and landing, airborne hovering capabilities, and high-speed cruising performance of fixed wing aircraft. The excellent flight performance of tiltrotor aircraft has enormous potential for development and application in the aviation field. However, at the same time, it also brings many challenges to research and design. The development of the overall aerodynamic configuration of tiltrotor aircraft has undergone decades of iterative optimization, and there are still many key technologies in the aerodynamic design of tiltrotor aircraft that need to be further explored. This article focuses on the research status of optimizing the shape design of tiltrotor blades, aerodynamic interference of tiltrotor aircraft, and aerodynamic elastic stability of whirl flutter. Based on the current situation, the next step of aerodynamic design research for tiltrotor aircraft is discussed, and several suggestions for research directions are provided.
    Design, analysis and verification flight test of control law for combined aircraft
    hu fang fang, zhang sheng, zhu zhe, huang jiang tao, du xin
    Available online:March 13, 2025, DOI:
    [Abstract] (81) [HTML] (0) [PDF 2.52 M] (2)
    Abstract:
    The neutral point, center of gravity and flight attitude of the carrier aircraft will change dramatically after the separation of the combined aircraft. Aiming at this problem, this paper studied a flight control method suitable for combinational aircraft and carrier aircraft. The state space model including tracking signal is established, and the longitudinal/lateral heading flight control law suitable for the composite aircraft is developed by using the robust servo. The control law is composed of guidance loop/angular outer loop and angular rate inner loop, and the robustness of the system to external disturbances is improved by integrating in the inner loop of the angular rate. The closed-loop system characteristics are analyzed using the frequency domain method, and the validity and robustness of the control law are verified by Monte-Carlo simulation in time-domain under consideration of various error sources. Finally, a verification flight test of the combined aircraft is carried out. During the flight, the carrier aircraft and the child aircraft are separated safely, and the attitude is controllable throughout the flight. This further verifies the reliability of the robust servo flight control law proposed in this paper.
    Design and Validation of a Micro Turbine EngineSpeed Control System
    Yuan Xingyu, Xu Jinfa
    Available online:March 13, 2025, DOI:
    [Abstract] (15) [HTML] (0) [PDF 1023.52 K] (4)
    Abstract:
    The control system of a micro turbine engine plays a crucial role during engine operation. This paper focuses on the design of a speed control system for a specific micro turbine engine. Starting from the overall architecture, the control structure of the system is designed. A speed control law design method based on Linear Active Disturbance Rejection Control (LADRC) technology is proposed. Subsequently, research is conducted on hardware implementation and software development using the STM32F103VET6 embedded microprocessor to develop the hardware controller for engine speed control. Addressing the potential issue of direct conduction in the half-bridge fuel pump drive circuit, a delay circuit is designed to control the conduction time of MOSFET. A three-layer software architecture is utilized for the design, development, and debugging of programs for speed measurement, closed-loop control, and other functions. Finally, a speed control system experimental verification platform is constructed to test and validate the fuel pump drive circuit, delay circuit, and speed control system. Experimental results demonstrate that the drive circuit exhibits stable and reliable on-off characteristics. The engine speed can rapidly follow the target speed, with a steady-state error of less than 1%, meeting the application requirements of the micro turbine engine control system.
    Probabilistic Analysis of Mechanical Properties of SiCf/SiC Composites Considering Internal Damage Randomness
    XieXueXin, LiHongShuang
    Available online:March 13, 2025, DOI:
    [Abstract] (57) [HTML] (0) [PDF 6.63 M] (6)
    Abstract:
    Ceramic matrix composites(CMCs) will experience internal damage such as fiber pulling out and matrix cracks during usage, which will affect the mechanical properties of braided CMCs. For SiCf/SiC 2.5-dimensional braided CMCs, a microscopic finite element model of fiber bundle and a meso finite element model of braided CMCs were established, respectively. Considering the randomness of internal damage quantity and location, the probability distributions of mechanical parameters of the meso-scopic level model was identified, and the influence of damage rate on the strength limit and Young"s modulus of the material was studied. Both parametric and non-parametric methods were used to fit the probability distribution of mechanical properties of CMCs. The results show that, with the increase of damage rate, the strength limits decrease faster than the stiffness. In addition, the probability density function curve of strength limit and Young"s modulus obtained by non-parametric method match the frequency histogram of the sample well.
    Research on Landing Distance of A Civil Aircraft Based on Bayesian Network
    wangke, shaojingwen, yangjun
    Available online:March 13, 2025, DOI:
    [Abstract] (24) [HTML] (0) [PDF 589.43 K] (2)
    Abstract:
    Combined with the actual operation data of a domestic civil aircraft and the simulation and validation data of aircraft performance software, the landing distance was compared and analyzed to provide quantitative support for the improvement of the aircraft"s operation capability. The key conditions Required for performance simulation calculation are extracted from the actual operation data to obtain the Required Landing Distance (RLD) and distance difference under the same conditions. The landing-related data is discretized by the quartile method, and the modeling methods are compared and selected. Finally, the network structure is learned by PC algorithm. Bayesian estimate learning network parameters to construct the risk model of actual landing distance exceeding RLD. The posterior probability and maximum posterior hypothesis of exceeding RLD state are obtained by using Bayesian network accurate reasoning. The results show that the probability of exceeding RLD can be effectively reduced by flattening to ground time of about 7s and grounding to ground speed of 40 knots between 18-24s, and some suggestions are put forward to reduce the risk of exceeding RLD by combining relevant parameters.
    Overview of the current research status of new energy aviation engines
    liuxiang, zhuhongjie, zhangailing, weihongsen, liuwenqi, wanhengcheng
    Available online:March 06, 2025, DOI:
    [Abstract] (118) [HTML] (0) [PDF 4.20 M] (10)
    Abstract:
    In recent years, China"s economy has continued to grow, and the demand for clean energy has become increasingly urgent. The aviation industry has also been actively exploring clean and low emission energy technologies. The use of new fuels and new energy for new aviation engines is considered an important solution to reduce carbon emissions. This article provides an overview of the research status of new energy aviation engines. Firstly, the development history of aviation engines is introduced in chronological order. Then, the research status of new fuel aviation engines, electric aircraft, fuel cell aviation engines, etc. is introduced. Finally, the future research of new energy aviation engines is discussed.
    Application Research on Improved Artificial Potential Field Method in Three-Dimensional Path Planning for UAV Formation
    XU Haitao, CHEN Longsheng, WANG Yuxiang
    Available online:March 06, 2025, DOI:
    [Abstract] (35) [HTML] (0) [PDF 1.01 M] (5)
    Abstract:
    Path planning for unmanned aerial vehicle (UAV) formation is particularly crucial when interacting with complex real-world environments. The artificial potential field method exhibits shortcomings such as goal nonreachable with obstacle nearby and local minimum when guiding unmanned aerial vehicle formation in three-dimensional path planning. This paper addresses these issues improving the traditional artificial potential field method"s repulsion calculation formula to resolve the problem of goal nonreachable with obstacle nearby. Furthermore, classify local minimum and employ different repulsion calculation methods for different types of local equilibrium points. effectively overcoming the problem of potential local minimum that the traditional artificial potential field method encounter. Finally, the improved artificial potential field method, combined with leader-follower method, is applied to the path planning problem of unmanned aerial vehicle formation. Simulation results indicate that the studied three-dimensional path planning algorithm for unmanned aerial vehicle formation, based on the improved artificial potential field method, effectively resolves obstacle avoidance and path planning issues in a static environment.
    Performance analysis and experimental verification of the main landing gear retraction system of a certain type of aircraft
    LIU Lei, LIU Chenglong, YAO Xionghua, YIN Yin
    Available online:March 06, 2025, DOI:
    [Abstract] (53) [HTML] (0) [PDF 1.11 M] (7)
    Abstract:
    Landing gear retracting system is a complex system integrating mechanical, electrical and hydraulic. With the development of simulation technology, it is convenient and fast to study the performance of retracting and retracting system by computer simulation. Aiming at the present situation that the single software simulation method is difficult to realize this kind of complex system, a method combining theoretical analysis and multidisciplinary simulation technology analysis is proposed, which provides a more accurate analysis means for the landing gear retracting system. In this paper, the mechanical dynamics model of the retraction system is established according to the retraction principle of the landing gear model, and then the simulation model of the hydraulic system is established according to the hydraulic principle. On this basis, a multidisciplinary co-simulation model combining the two is completed. Finally, the results of co-simulation under various operating conditions are compared with the experimental results, and the accuracy and convenience of co-simulation technology in the analysis of landing gear retracting system are verified.
    Sensitivity Analysis and Optimization Method of Partition Surrogate Model Based on Physical Knowledge
    shaomengying, xialu, zhangwei, zhaoke
    Available online:March 06, 2025, DOI:
    [Abstract] (52) [HTML] (0) [PDF 3.29 M] (5)
    Abstract:
    The problem of "dimensionality disaster" of design variable is a key technical problem that restricts the application of current surrogate-based optimization algorithms. In order to solve the problem of declining accuracy and poor optimization effect of surrogate model caused by dimensionality disaster problem, this paper improves a sensitivity analysis method based on physical knowledge driven partition surrogate model optimization. Based on physical knowledge and manual design experience, the design space is partitioned, and the molecular space units are divided by three-dimensional wing design section to achieve dimension reduction. In order to further improve the design effect of the partition optimization, the sensitivity of different partition design variables to the objective function is studied. On the basis of the sequential partition optimization, the sensitivity is taken as the order of the partition surrogate model optimization. The results show that the partitioning surrogate model optimization algorithm based on physical knowledge-driven sensitivity analysis can search for a better optimal solution, and the time spent on establishing the surrogate model is much lower than that of the EGO algorithm, and it can maintain good accuracy of the surrogate model, which can provide a new idea for the dimension disaster problem, and has certain engineering reliability and applicability.
    Development status and key technology analysis of commercial high-altitude manned balloons
    zhang shuqi, huang wanning, WANG Zihao, gao xiaofeng, zhu rongchen
    Available online:March 06, 2025, DOI:
    [Abstract] (26) [HTML] (0) [PDF 11.00 M] (8)
    Abstract:
    High-altitude balloons have been employed for space science experiments and verification for over 70 years. This extended history has resulted in a mature technical foundation for manned high-altitude balloon flight tests, which have been conducted on numerous occasions throughout history. Compared to other options, manned high-altitude balloons offer a potentially more economical and safer method for near-space exploration and tourism. Recent business plans from domestic and international companies targeting edge-of-space tourism are examined in this article. The article also conducts a comparison of the defining characteristics associated with each company"s manned high-altitude balloon space tourism plan. Furthermore, an analysis of some key technologies crucial for high-altitude balloons in the context of edge-of-space tourism is provided. Suborbital flight, the primary competitor to manned high-altitude balloons, is introduced in the article. It then proceeds to offer a comparison of the advantages and disadvantages of suborbital flight relative to high-altitude balloon travel. Finally, the article explores the potential for commercialization within the space tourism industry and presents various viewpoints on this developing field.
    DO-178C-based Parameter Data Item Airworthiness Certification Strategy
    ZHONG Xuxu, TAN Yunfeng, ZHANG Hongtao, LI Yanlin
    Available online:March 06, 2025, DOI:
    [Abstract] (22) [HTML] (0) [PDF 518.33 K] (10)
    Abstract:
    In terms of the airworthiness of parameter data item, domestic software manufacturers have some problems, such as unclear certification strategy and insufficient evidence of conformity. Based on the international general software standard DO-178C, combined with the shortcomings of domestic airworthiness certification work and certification practice, the airworthiness objectives and requirements of parameter data item are analyzed, and the suggested airworthiness certification strategy of parameter data item is put forward. Practice shows that this strategy effectively solves the problems existing in the airworthiness work of parameter data item in domestic software manufacturers, and provides high confidence proof of conformity for the airworthiness certification of parameter data item.
    Optimization Method for Civil Aircraft Maintenance Tasks with Obvious Operational Effects of Faults
    Lai Tao, Cai Jing, Assila Achraf
    Available online:February 25, 2025, DOI:
    [Abstract] (48) [HTML] (0) [PDF 620.51 K] (24)
    Abstract:
    In the maintenance planning of civil aircraft, the initial maintenance tasks based on the MSG-3 standard for civil aircraft are set conservatively due to the lack of usage data support, resulting in problems such as excessive maintenance and poor economy in practice. In response to this situation, this study proposes an optimization method for civil aircraft maintenance tasks based on the guidance of IP 44 and the optimization process of Boeing SASMO. Firstly, sort out the characteristics of obvious operational impact faults based on their impact categories; Secondly, collect all planned and unplanned maintenance data related to this category of maintenance tasks; Then, establish a maintenance event chain to fuse multi-source maintenance data into a failure cycle and conduct statistical analysis, fitting the failure probability curve of the maintenance project; Finally, based on engineering analysis and comprehensive evaluation, output optimization suggestions for maintenance task intervals. The effectiveness of the method has been confirmed through the analysis of airline examples, providing theoretical support for the optimization of such maintenance tasks. The conclusion indicates that the initial maintenance interval decision-making process tends to be conservative, and as aircraft service data accumulates, maintenance tasks should be optimized to reflect actual usage conditions and maintenance needs.
    Optimal design for low-boom based on CoKriging surrogate model
    ZHANG Hanqi, XU Yue, ZHONG Min, LI Yan
    Available online:February 24, 2025, DOI:
    [Abstract] (62) [HTML] (0) [PDF 1.09 M] (24)
    Abstract:
    Accurately predicting and effectively reducing sonic boom levels is one of the key issues in the development of the new generation of green supersonic civil aircraft. In order to improve the efficiency of low-boom optimal design for supersonic civil aircraft, a multi-fidelity optimal design program for low-boom was developed based on the CoKriging surrogate model combined with fast sonic boom prediction method and high fidelity sonic boom prediction method. The sonic boom prediction results of the TU-144 model are basically consistent with the experimental results, verifying the reliability of the two prediction methods. A parameter sensitivity analysis and optimal design were conducted on the wing shape of a certain supersonic civil aircraft model. The results showed that Stevens’ loudness level of the ground sonic boom was more sensitive to three parameters: the half span length of the outer wing, leading edge sweep angle of the outer wing, the half span length of the inner wing. After optimization, the maximum ground sonic boom overpressure was reduced by about 4Pa, and the Stevens’ loudness level was reduced by 4.26dB. Compared with the Kriging model that only uses high fidelity sample data, the CoKriging model integrates high and low fidelity sample data, saving about 43% of time cost while ensuring a certain prediction accuracy.
    Study on Correction Technology of Aircraft Angle of Attack Signal Based on Estimation of Side Slip Angle
    Xue Yuan, Liu Shimin, Wei Jianlong
    Available online:February 24, 2025, DOI:
    [Abstract] (63) [HTML] (0) [PDF 757.35 K] (25)
    Abstract:
    The angle-of-attack signal is very important for modern fly-by-wire flight control system aircrafts. The inconsistency of the local airflow on both sides of the nose will cause the difference of the angle-of-attack signal. The signal-monitoring logic of the flight control system will judge the angle-of-attack signal and make the angle-of-attack availability decrease. By studying the relationship between the lateral overload and the side slip angle, the side slip angle is estimated by the lateral overload, and the angle of attack signal correction method based on the side slip angle estimation is established to improve the availability of the angle of attack signal under the condition of large side slip. The simulation results show that the proposed method is successful in estimating the side-slip angle, and the angle-of-attack signal on both sides of the nose is consistent with the modified side-slip angle, which solves the problem of over-error of the angle-of-attack signal caused by the large side-slip state and has good correction effect.
    Adaptability Design and Simulation Study of Cabin Pressure Regulator for High Altitude Airports
    XUE Zhao-ming, WANG Jiang-hui, WANG Kai-xiang
    Available online:February 24, 2025, DOI:
    [Abstract] (27) [HTML] (0) [PDF 1.26 M] (22)
    Abstract:
    In response to the problem of excessive cabin pressure rate of change when using typical pneumatic cabin pressure regulators for fighter jets under high altitude airport conditions, this paper proposes a solution to add an exhaust bypass controlled by a high-speed solenoid valve to the outflow valve control chamber. The working principle of this solution is analyzed, a mathematical model of the cabin pressure regulation system is established, and a control law for cabin pressure increase and decrease rate is designed, The dynamic characteristics of the cabin pressure regulation system under high altitude airport conditions were calculated on the MATLAB/Simulink software platform. The calculation results showed that through a reasonable design of the cabin pressure increase and decrease rate control law, the high-speed solenoid valve can effectively control the cabin pressure increase rate during the pressurized flight process and the cabin pressure decrease rate during the landing stage of the high altitude airport, verifying the effectiveness of the proposed solution.
    Study on the Airworthiness Verification Technical system and key contents of aircraft Tire burst
    Zhou chang wei, Wang Zhaodong
    Available online:February 24, 2025, DOI:
    [Abstract] (70) [HTML] (0) [PDF 2.62 M] (22)
    Abstract:
    Aircraft tire burst is a specific risk in aircraft design. Civil aircraft airworthiness regulations have clear requirements for tire burst.The research on tire blasting approval technology is of great significance to promote aircraft forensics and improve aircraft safety.In order to further promote the development of tire burst airworthiness technology and standardize the technical system, the development status and differences of applicable tire burst airworthiness regulations in various countries are tracked and investigated. Based on the engineering practice of domestic civil aircraft on the latest international tire burst airworthiness certification, the requirements of CS 25.734 are interpreted.The results show that the newly revised proprietary clause CS 25.734 of the EASA requires higher requirements and clearer tire burst modes.The airworthiness certification technology system of aviation tire burst is established according to the CS 25.734 clause, and the verification process, verification object, related clauses and certification technical indicators are detailed, and the expected safety level of CS 25.734 is fully interpreted. Focusing on the key contents of airworthiness certification, the certification elements and suggestions that need to be paid attention to are put forward, which have been verified in the airworthiness certification of a large domestic civil aircraft, and can provide guidance for the reviewers and designers in relevant industries.It represents the latest breakthrough in the field of domestic verification technology.
    Aero-engine fault diagnosis based on time series anomaly detection
    wangyinru
    Available online:February 24, 2025, DOI:
    [Abstract] (98) [HTML] (0) [PDF 1.43 M] (17)
    Abstract:
    Abstract: The fault diagnosis of aero-engines was confronted with a data skew issue, where the number of fault samples was sig-nificantly fewer than normal samples, and the fault samples couldn"t adequately represent the entire operating conditions, resulting in poor generalization ability of conventional classification models. To address this issue, an improved deep support vector data descrip-tion-based time series anomaly detection model was proposed. Initially, a Long Short-Term Memory Recurrent Neural Network (LSTM) was employed to map the inputs and outputs of samples, forming temporal anomaly vectors with actual collected outputs. Subsequently, deep support vector data description (SVDD) incorporating Variational Autoencoder (VAE) was utilized to achieve anomaly detection for aero-engine time series data. Experimental results on a certain type of aero-engine ground test platform demonstrated that compared to contrastive methods such as Isolation Forest (IF), Transformer-based Anomaly Detection Model (TranAD), and GANomaly, the proposed algorithm achieved an Area Under the Curve (AUC) value of 0.9878, indicating su-perior anomaly detection performance. Therefore, the proposed algorithm can effectively be applied to various anomaly detection and fault diagnosis tasks in aero-engine systems.
    Study on the Factors Affecting Flight Training for Flight Students
    ZHAO Yunxiang, LIANG Zejian, HUANG Hong, LIANG Aimin, XU Haiwen
    Available online:February 24, 2025, DOI:
    [Abstract] (76) [HTML] (0) [PDF 819.51 K] (20)
    Abstract:
    In the field of aviation, the flight skills of trainee pilots are directly related to aviation safety and operational efficiency. Enhancing the flight skills of trainees through training has been one of our school"s objectives and is a core method for improving the safety of civil aviation flights. Based on the training data of flight trainees from a branch of our school, we introduced the Pearson correlation coefficient to evaluate the strength of the relationship between features and the target variable. Based on the correlation coefficients, key factors influencing flight training were identified, and a novel decision tree model based on Pearson correlation coefficients was established. By optimizing the model with various thresholds and tree depths, its performance in accuracy, precision, recall, and F1 score was enhanced. Comparative analysis against classical machine learning models such as Random Forest, MLP, Logistic Regression, Decision Tree, and enhanced Gradient Boosting Decision Tree showed superior performance of the new model. This study not only provides effective guidance for flight training but also offers theoretical support for the evaluation of flight training.
    Tower View Object Detection Based on ECIOU Structure Embedded in YOLO
    Qian Jide, YanHao, LiangYan, Zeng Changchang, Mou Yihao
    Available online:February 24, 2025, DOI:
    [Abstract] (11) [HTML] (0) [PDF 2.88 M] (19)
    Abstract:
    In view of the problems that the existing tower view target detection system is prone to large positioning deviation and low small target detection accuracy, this paper proposes an aircraft target detection method based on the ECIOU structure embedded in the YOLO v8 model from the tower view to improve the accuracy and efficiency of detection. Based on the traditional YOLO v8 model, the CBAM module is first added to enhance the discriminability of target features. Then, the GConv and SENet attention mechanisms are introduced to optimize the Bottleneck structure to enhance its feature extraction ability. Thirdly, the ECIOU Loss is used to replace the original CIOU loss function to improve its detection performance in complex environments. Lastly, the small target detection head PWHead is reconstructed to better capture the details of small targets. The model is evaluated on the Roboflow public dataset and its performance is compared with other mainstream models. The experimental results show that the accuracy of the improved YOLO v8 is 90.2%, and the mAP@50 is 86.9%, which is 2.2% and 1.3% higher than that of YOLO v8n respectively, and the detection efficiency is improved. This provides reliable technical support for remote towers to monitor aircraft in real-time.
    The Optimization of a Rigid-Flexible Coupling Skin Scheme for the Continuous Variable Curvature Trailing Edge Wing
    Xu Rupeng, Zhang Zijian, Zhang Guoxin, Xue Jingfeng, Song Kunling
    Available online:February 07, 2025, DOI:
    [Abstract] (29) [HTML] (0) [PDF 1.32 M] (28)
    Abstract:
    Variable camber wing structure is becoming a research hotspot. In this paper, a mathematical model is established for the rigid-flexible coupling type of continuously varying cambour trailing edge structure, and the Latin hypercube sampling method is used for stratified sampling, the correlation vector machine algorithm is used to build the model, and the differential optimization algorithm is used to optimize the model. According to the calculation results, the optimized rigid-flexible coupling skin improves the deformation accuracy by 67%, and the correlation coefficient of each variable to the deformation error is analyzed, which provides a reference for the design.
    Prediction and analysis of thermal drift in large-scale tooling reference points under non-uniform temperature field
    Yan Li, Shangan Zhang, Shouchuan Wang, Hongyang Wei, Shuanggao Li, Guoyi Hou
    Available online:February 07, 2025, DOI:
    [Abstract] (23) [HTML] (0) [PDF 7.52 M] (24)
    Abstract:
    In the digital measurement of aircraft assembly, the accuracy of large-size measurement field construction is highly dependent on the stability of the reference position laid on the tooling. The position of the reference points of a large tooling is highly susceptible to thermal drift due to changes in ambient temperature, leading to a reduction in the accuracy or even failure of the measurement field. Therefore, this paper takes a combined large-scale tooling as an example, and constructs a numerical model for predicting the thermal drift of the reference points of a large-scale tooling under the non-uniform temperature field by collecting the measured temperature and coordinate data at the reference points of the tooling in the field; based on the large amount of thermal drift data obtained from the simulation of the aforementioned model, the surrogate model for the thermal drift of the tooling is constructed by using BP neural network; and finally, the measured and the surrogate model are compared and analyzed in terms of the drift data of the reference points temperature-coordinate. The results show that the average relative errors of the simulation results are all below 18%, and the average relative errors of the BP neural network results are all below 22%, realizing the effective prediction of the thermal drift of the reference points.
    Research on the hit accuracy analysis of a certain type of target system
    XUE Jie, Ma Yuan
    Available online:February 07, 2025, DOI:
    [Abstract] (18) [HTML] (0) [PDF 469.16 K] (25)
    Abstract:
    Hit accuracy is the most important criterion for testing the combat capability of aviation weapons, and as a companion product, the circular probability error of the target is equally important. The accuracy index of a certain type of target simulating the American made JDAM series bomb is also an important part of interception tests for ground to air weapon systems. By sorting out the sources of errors in a certain target system, an error tree was established, and the accuracy of the target system was analyzed and studied. The accuracy of the landing point was calculated through theoretical analysis methods, and then simulated shooting analysis and live ammunition shooting were carried out to further verify the scientific and reasonable theoretical research methods. This allows for a relatively fast and lowly analysis of accuracy indicators in theoretical design, guiding subsequent design, and has certain theoretical and practical significance.
    Research on Crack Repair for IV-stage Guide Vanes of Aero-engine
    xu shiming, Zhou Jun, LI WEI, LIN KAIZHANG, WEI QING, GE HAIFENG
    Available online:February 07, 2025, DOI:
    [Abstract] (10) [HTML] (0) [PDF 8.54 M] (24)
    Abstract:
    Abstract: In order to meet the reliability of aero-engine and ensure the flight safety of helicopter, the welding repair of the crack fault of the IV stage guide is studied.The cracks are observed by scanning electron microscopy and optical microscopy to analyze the root causes of guide vanes failure. The high temperature box furnace is used to conduct properties recovery heat treatment of IV-stage guide vanes. The cracks are repaired by TIG welding. The microstructure, hardness, high temperature strength and thermal shock performance before and after repair are compared and evaluated.The repaired IV-stage guide vanes is installed on the engine for test verification. A large amount of σphase is generated at grain boundary during service, decreases the strength of grain boundary, and finally corrosion cracks are generated. Properties recovery heat treatment can lower the brittleness and improve the weldability of matrix materials. The welded joint of stage Ⅳguide vanes produced by TIG welding meets the standard requirements. The dimensions of stage Ⅳ guide vanes, on which property recovery heat treatment, TIG welding and stabilization treatment were conducted, meet the requirements of engine assembly. No cracks, spalling or other abnormalities were detected after engine test.
    Reverse modeling and numerical simulation for folding and deployment of inflatable aerodynamic decelerator
    leiqing, xueqiwen, yanghaitian, liufei, zhanghe, liuxudong, heyiqian
    Available online:February 07, 2025, DOI:
    [Abstract] (26) [HTML] (0) [PDF 9.24 M] (26)
    Abstract:
    The folding and development performance and aerodynamic bearing capacity of the inflatable aerodynamic decelerator are two key issues in its safety evaluation. In the simulation calculation of inflation expansion dynamics, the establishment of the folding model is the basis of numerical simulation. The inflatable aerodynamic decelerator includes sub-mechanisms such as a heat shield, multiple airbag torus and straps. For such a complex structural system, it is difficult to establish a folding model that conforms to the actual situation through direct folding methods. Therefore, this paper proposes a new reverse modeling-based simulation method for folding and development dynamics of an inflatable aerodynamic decelerator. The work of this paper takes the American IRVE-3 as an example. According to its actual folding process, step-by-step mechanical loading is used for compression, and cylindrical component constraints are used to simulate staged storage, and the overall folding model is obtained. Based on the commercial software LS-DYNA and the control volume method, the expansion and forming process was simulated and calculated, and the influence of the inflation rate, inflation internal pressure on the expansion process was discussed. Through the inflatable deployment simulation, the wrinkle formation process on the structural surface was obtained, and based on this, the aerodynamic bearing analysis was conducted to study the impact of the under-deployment state on the aerodynamic bearing capacity, and the entire process simulation of inflatable deployment and aerodynamic bearing was realized. This paper proposes a new method for folding modeling of complex flexible inflatable systems, and also provides an important numerical simulation technology for the performance evaluation and optimal design of inflatable aerodynamic decelerator.
    A Numerical Study on the Effects of High-Lift Devices on the Aerodynamic Characteristics of a Large Aircraft
    zhuguowang, wuhengbin, haungshenghong, nizao
    Available online:January 20, 2025, DOI:
    [Abstract] (37) [HTML] (0) [PDF 15.63 M] (33)
    Abstract:
    Aircraft incidents frequently occur during the low-speed phases of takeoff and landing, where the proper deployment of lift-enhancing devices is crucial for augmenting flight safety. This study evaluates the impact of various lift devices on the aerodynamic performance of domestic wide-body airliners during these critical phases. A fully structured body-fitted grid is adopted to discretize the large wide-body aircraft into hundreds of millions of cells, and the Reynolds-averaged turbulence model is applied to conduct numerical simulation on aerodynamic performance. The reliability of the numerical simulation method is verified by comparing with the wind tunnel experimental results. Four typical cases of Ma=0.2, incoming flow angle of 0°, 5°, 10° and 15° are selected, and the effects of lift devices such as flaps, slats, spoilers, etc. on the overall aerodynamic performance of the aircraft are analyzed. The study’s findings reveal that the fully structured grid employed herein accurately captures the three-dimensional mean flow field characteristics under various lift device configurations. Within an angle of attack range from 0° to 10°, the utilization of spoilers can reduce the aircraft’s lift coefficient and increase the drag coefficient during the landing phase. Furthermore, between 0° and 15° angles of attack, the application of slats and flaps provides additional lift, thereby enhancing takeoff performance and stall characteristics.
    Unscented Transformation Method for Robustness Verification of Helicopter Flight Control System
    liu changqi, li aijun, duan guangzhan, li zuo
    Available online:January 20, 2025, DOI:
    [Abstract] (42) [HTML] (0) [PDF 1.35 M] (32)
    Abstract:
    In response to the large computational load and extended processing time associated with the Monte Carlo method in the robustness verification of helicopter flight control systems, this paper proposes an Unscented Transform method for such verification. This method employs Particle Swarm Optimization for determining the uncertain parameters. Using the helicopter"s yaw channel as a case study, the Unscented Transform method"s performance in robustness verification was compared with that of the Monte Carlo method. Simulation results show that the Unscented Transform method significantly enhances computational efficiency while maintaining comparable accuracy to the Monte Carlo method in the robustness verification of helicopter flight control systems. By adjusting parameter values to modulate the distance between sampling points and the sample center, this method is also suitable for the robustness verification of high-dimensional helicopter flight control systems.
    Research on Electromagnetic Ultrasonic and Eddy Current Composite Detection Method for in Aircraft Aluminum Alloy Thin-wall Sheet
    MA Miandong, YU Hongwei, MA Rong, ZHOU Xin, FAN Xueling
    Available online:January 20, 2025, DOI:
    [Abstract] (35) [HTML] (0) [PDF 4.98 M] (33)
    Abstract:
    During major repairs of aircraft aluminum alloy thin-walled components, a large number of structural crack defects inevitably occur, and there is an urgent need to develop a fast and effective detection method. An electromagnetic ultrasonic guided wave and eddy current composite detection method based on electromagnetic ultrasound and electromagnetic eddy current technology is proposed, and experimental research on crack composite detection of thin-walled and large-area aluminum alloy plates is carried out. The influence of electromagnetic ultrasound guided wave rapid detection capability and probe characteristics is analyzed, and the effectiveness of eddy current in detecting defects in thin-walled parts is evaluated. the electromagnetic ultrasonic and eddy current composite detection method was used to conduct experimental research on the composite detection of cracks in thin-walled and large-area aluminum alloy plates, and the detection ability of thin-walled parts defects was analyzed. The experimental results show that the use of electromagnetic ultrasonic probes can achieve rapid detection and positioning of defects in large-area aluminum alloy thin-walled parts, and the electromagnetic eddy current probe can accurately detect defects on aluminum alloy flat plates, achieving comprehensive and efficient detection of crack defects. It provides technical reference for the practical application of electromagnetic ultrasonic and eddy current non-destructive testing technology in aircraft thin-walled parts.
    Research on the function hazard assessment of continuously varying systems based on fuzzy sets
    SUNKUAN, ZHANGSHUGUANG, wang zhu
    Available online:January 20, 2025, DOI:
    [Abstract] (41) [HTML] (0) [PDF 668.34 K] (33)
    Abstract:
    When assessing function hazard on time and function continuously varying systems, it is often difficult for the assessor to evaluate the effect of the function performance. The method based on SAE ARP 4761 has not provide an assessable way to evaluate continuous systems, but only addresses a limited number of failure modes. Therefore, we combine assessable function failure data with fuzzy set to establish membership functions. By introducing function performance and time into two-dimensional normal distribution function and its variants, we can divide function hazard into different levels. Taking the impact of UAS moto as an example, we apply the function hazard assessments based on fuzzy set and experience for a comparison. The results shows that the proposed models can be applied to the function hazard assessment.
    Numerical simulation study on wear of universal joints in aircraft high lift systems
    QUAN Li, KANG Ning, SHAO Qinwen, XI Bowei, LIU Zongxing
    Available online:January 20, 2025, DOI:
    [Abstract] (19) [HTML] (0) [PDF 4.15 M] (31)
    Abstract:
    Universal joint torque tube assembly is used in flaperon transmission system of high lift system. As an important part of aircraft, its performance determines the main function and fatigue life of aircraft. Wear between components seriously affects the transmission accuracy of universal joint. This paper takes the cross-shaft universal joint as the research object, uses the liquid metal friction and wear testing machine to measure the wear coefficient of the cross-shaft universal joint material. A numerical simulation model for friction and wear was established based on the Archard wear model, and compared with friction and wear tests. Subsequently, a validated numerical simulation model was used to study the friction and wear problem of the cross shaft universal joint. A model for analyzing the wear clearance angle of the cross shaft universal joint was proposed. Based on the analysis results and Archard wear theory, optimization suggestions were proposed to increase the hardness of the universal joint ear piece, and a comparison was made with the original structure"s full life wear clearance angle. The research results indicate that the numerical simulation results based on the Archard wear model have good consistency with the experimental results, and the numerical simulation results can predict the wear results well, thereby significantly shortening the test cycle and increasing design efficiency. Increasing the hardness of the universal joint ear can effectively reduce the wear clearance angle of the cross shaft universal joint. At 25 ℃, the full life wear clearance angle is relatively reduced by 24.5%, and at 400 ℃, the full life wear clearance angle is relatively reduced by 20.6%. The research results provide certain guiding value for the anti-wear design of universal joints.
    Status and challenges of UAV recognition methods based on deep learning
    liqiqin, yangming, renhaotian, changhaoliang, zhangxiaoqiang, zhuxinyu
    Available online:December 23, 2024, DOI:
    [Abstract] (40) [HTML] (0) [PDF 957.76 K] (60)
    Abstract:
    The wide range of military, civil, and commercial applications of UAVs has prompted the need for their recognition and classification. With the development of artificial intelligence, deep learning, as a machine learning technique, has shown good performance in the field of object detection, and is also applied to the field of UAV recognition. This paper firstly introduces the background and significance of UAV recognition, reviews the development history of deep learning, and introduces two important algorithm structures in object detection: two-stage detector and single-stage detector. Secondly, it describes the common algorithms for object detection and the backbone network in the algorithms, and then summarises the improvement strategies of improved algorithms for UAV recognition in recent years, and summarises the improvement effect and its shortcomings and limitations. Finally, the outlook and challenges are discussed with respect to the current research status of UAV recognition, which is expected to make greater breakthroughs in establishing UAV datasets, improving the accuracy and real-time performance of UAV detection, and promoting the application of UAV technology in various fields.
    Research on the impact of airplane inclination on passengers" emergency evacuation behavior
    YOU Qianqian, CHEN Kun, KOU Zhiyuan, FENG Zhenyu, CHEN Xiangming
    Available online:December 23, 2024, DOI:
    [Abstract] (68) [HTML] (0) [PDF 1.12 M] (57)
    Abstract:
    After a preventable catastrophe on the ground, emergency evacuation is a crucial means for airplane occupants to immediately flee danger. Although there has been a lot of research on emergency evacuation of aircraft in a horizontal attitude, the aircraft attitude is susceptible to tilt in the event of a reversible accident, and there hasn"t been enough research on the evacuation of aircraft occupants in an inclined attitude. A model of individual deceleration ratios and the sliding speed of various emergency slide angles under the tilted attitude of the aircraft was established based on experimental statistics in order to analyze the impact of the tilted cabin on the evacuation of passengers after an aircraft accident. A model of personnel movement in the tilted state was then added to the conventional social force model to create a simulation model of the evacuation of aircrew. To analyze the spatial distribution of bottlenecks and time for passenger evacuation for various inclination attitudes brought on by accidents. The findings indicate that in order to avoid overcrowding, it is crucial to promptly evacuate passengers who are in the upward-facing area of the cabin. To reduce the risks associated with overcrowding of occupants, special attention should be made to the evacuation of bottleneck exits in the cabin"s downward segment.
    Design of Marine Salt Spray Environment Adaptability for some Aeronautical Signal Light
    DU cui-ling, XU gang, LIU ke-gang, MEI yu-fei, ZENG Deng-feng, XU Yong-pan, CHEN ao-jie
    Available online:December 23, 2024, DOI:
    [Abstract] (51) [HTML] (0) [PDF 3.34 M] (56)
    Abstract:
    To solve the fracture failure problem of electric connection spring of some aeronautical signal light in the marine environment and its raw material are subject to import, which threatens the security of the national major equipment supply chains. Composition and mechanical properties of material were analyzed by means of SEM, material substitution analysis, the domestic 06Cr19Ni9 was selected as replacement of Japanese piano wire (swp) and British system unembroidered steel wire. Then experiments and tests of system-level key performance such as fatigue life and corrosion resistance to marine salt spray environment were studied after the structural design and production manufacturing with the domestic material. Electric connection spring made of domestic 06Cr19Ni9 through GJB 150.11A-2009 and the ultimate fatigue life is more than 300,000 times. Electric connection spring made of domestic 06Cr19Ni9 exhibits excellent marine salt spray environmental adaptability and high fatigue life, realized the rigid demand of localization. This research can provide scientific and effective verification ideas for China’s aviation equipment to overcome the “stuck neck” problem of core technology and ensure the security of national major equipment supply chain.
    Experimental and numerical simulation study of a light UAV impacting a typical airliner flat tail structure
    CHEN Feiying, CHEN Chi, LIU Jun, LI Jian, ZHANG Yingchun
    Available online:October 30, 2024, DOI:
    [Abstract] (26) [HTML] (0) [PDF 12.84 M] (86)
    Abstract:
    To evaluate the flight safety threat of UAV to other aircrafts in the air, experiments and numerical simulations of UAV impacting the aircraft structure must be carried out. Based on the launch test system of large caliber special-shaped air cannon developed for the first time in China, this paper carried out collision experiments between a light UAV and the flat tail of a typical airliner, established the corresponding finite element numerical simulation model of UAV impacting on the flat tail by using LS-DYNA software, and compared calculation results of the flat tail dynamic responses and damage morphologies with experimental results. The good consistency between them indicates the rationality of the numerical simulation method. On this basis, the numerical simulation method is used to study the effects of UAV attitudes on the impact damage of the flat tail. The results show that the UAV impact is easy to cause penetrating damage to the leading edge of the flat tail, the pitching and rolling attitudes have a few effects on the impact damage of the flat tail, and the heading attitude has a greater effect, and the UAV battery has the risk of invading the interior of the flat tail and causing explosion and fire during the impact process.
    The Current Status and Prospects of the Impact of Spaceflight on Astronauts
    Yuhui, Gaolina, Gaona, Niuchang, Huyanting, Guliangxian
    Available online:October 30, 2024, DOI:
    [Abstract] (37) [HTML] (0) [PDF 4.60 M] (87)
    Abstract:
    The completion of the Chinese space station marks the successful realization of China"s three-step development strategy for manned spaceflight. In the future, astronauts will routinely conduct spaceflights and remain in space for long-term stay to execute scientific missions. However, during spaceflight, astronauts are exposed to challenges such as hypergravity, microgravity, radiation, and isolation. These conditions directly threaten the normal functionality of their musculoskeletal, neurological, and immune systems. Notably, abnormalities in astronauts" cerebral neurological functions can impact their cognitive abilities, potentially jeopardizing the successful completion of space missions. Therefore, safeguarding the cerebral neurological functions of astronauts during spaceflight is of paramount importance. This paper examines the influence of spaceflight on astronauts" cerebral neurological functions from both spatial and temporal perspectives. It summarizes the current state and challenges of protecting these brain functions. Centering on the key issues at hand, this paper also offers a forward-looking perspective on future strategies for protecting astronauts" cerebral neurological functions, aiming to present new ideas and directions for ensuring their neurological wellbeing during spaceflights and the successful execution of space missions.
    Structure Design of Hybrid Wing eVTOL Motor Beam
    CHEN xiuxian, DONG Ming, DONG Wenjun, WU Weizhi
    Available online:October 30, 2024, DOI:
    [Abstract] (102) [HTML] (0) [PDF 3.27 M] (99)
    Abstract:
    The hybrid wing eVTOL motor beam is a key critical structure component, and the flight load is complex during the conversion and reverse conversion flight stages. Therefore, studying its structure design is of great significance. This article studies the propeller lift loads and flight overload of the motor beam during vertical takeoff, transition, fixed-wing flight, reverse transition, vertical landing flight stages. Under this load, a motor arm structure with dual transmission paths was designed, and the structure optimization of the motor seat was carried out under the given constraint conditions. The motor beam structure design is calculated through simulation analysis, ensure that the stress level of the composite materials and metal parts on the motor arm is lower than the design allowable value. Finally, design the experimental loading method based on the structural form of the motor arm, compare and analyze the strain and deformation during the measurement experiment with the strength calculation results through static strength tests and flight tests, verify the accuracy of the motor beam structure design and calculation results, meeting the stiffness, strength, fatigue design requirements of the motor beam.
    Research on hanging load control method of multi-rotor UAV based on Udwadia-Kalaba equation
    Luxiangyang, Ren Xianglong, Xue Jiuhui
    Available online:October 30, 2024, DOI:
    [Abstract] (116) [HTML] (0) [PDF 1.14 M] (99)
    Abstract:
    UAVs carrying loads by single aircraft for transportation are limited in carrying capacity, and multi-copter integration is a general trend. In the traditional rotor-load model, the treatment of constraints for UAV hanging load calculation of multi-rotor aircraft synergism requires the introduction of multiple auxiliary variables, and the modeling process is relatively complex, and the analytical effect needs to be improved. It is an effective attempt with the Udwadia-Kalaba (U-K) equations dealing with both ideal and non-ideal constraints co-existing systems, modeling rotary-wing UAV cooperative flight control to solve the problem of rotary-wing cooperative load transport. By establishing the kinematics model and dynamics model of the rotary-wing UAV, using the U-K equation to deal with the motion constraints, the treatment divides the load"s influence on the UAV into horizontal and vertical directions, which is input as a step signal to solve the calculation, and the series-level PID control model is designed for the control strategy of the system, which ensures that the rotary-wing UAV under the condition of multi-aircraft cooperative has good anti-jamming ability and Stability. Simulation analysis is carried out using Simulink model in Matlab environment, and the numerical simulation results show that the proposed control method achieves the stability, speed and accuracy of the formation system, and can achieve the goal of optimizing the effect of rotary-wing UAV cooperative control.
    A Modified Radial Basis Function Interpolation Method for Aerodynamic Load Application
    Zheng Wei, Xiong Jun, Liu Jian, Ji Kai
    Available online:October 30, 2024, DOI:
    [Abstract] (26) [HTML] (0) [PDF 736.42 K] (91)
    Abstract:
    Aerodynamic loads are an important type of load in finite element analysis of aircraft structures. Due to the mismatch between the mesh used in computational fluid dynamics (CFD) and the one in structural analysis, and the load can be given in the form of a coordinate-pressure table, three-dimensional interpolation of the aerodynamic load input is often required before it can be applied to the structural mesh. A modified radial basis function interpolation method is proposed, where neighboring space of the interpolation point is distorted according to its normal vector, thus reducing the interference of non-coplanar sampling points. Additionally, it enhances the algorithm efficiency by incorporating a KD tree data structure. This modified radial basis function interpolation method can obtain a load spectrum matching the structural mesh based only on the coordinate-pressure table. The feasibility of the method is demonstrated through interpolation of aerodynamic loads for several typical aircraft structures. The results show that the modified radial basis function interpolation method provides an effective means for accurately applying aerodynamic loads in the finite element analysis of aircraft structures, and has important application value.
    Research on Temperature Characteristics of Aeroengine Fuel Pipeline System
    dengzhibin, zhang, tanghaiping
    Available online:October 30, 2024, DOI:
    [Abstract] (92) [HTML] (0) [PDF 1.52 M] (81)
    Abstract:
    The aeroengine fuel pipeline system provides fuel for aviation engines and is an important component of aeroengine. To explore the changes in fuel temperature characteristics in aeroengine fuel pipeline systems, based on the basic structure and working principle of the fuel system, a simulation model of the aviation engine fuel pipeline system was established using AMESim. Based on heat transfer theory, important components such as fuel pumps, heat exchangers, and return pipelines in the system were studied under flight conditions, and the temperature characteristics of the system were studied and parameter sensitivity analysis was conducted. The results show that the speed of the fuel pump and the temperature of the aviation lubricating oil are the two most significant factors affecting the temperature characteristics of the system among various components. After the pump speed exceeds 6000r/min, the fuel temperature rise rate accelerates, and the fuel temperature at the nozzle can reach 140℃. There is a linear positive correlation between the system fuel temperature and the temperature of the aviation lubricating oil. This study lays an important data foundation for the safe operation and in-depth development of aeroengine.
    Surfel-based Lightweight LiDAR-Inertial SLAM system for UAV pose estimation
    liu chang, Zhao Zixu, Shang Yuanfeng, Qiu Dawei, Shi Jinglin, Liu Jie, Jiang Ji
    Available online:October 30, 2024, DOI:
    [Abstract] (8) [HTML] (0) [PDF 4.85 M] (89)
    Abstract:
    This paper proposes a lightweight LiDAR-Inertial SLAM (Simultaneous Localization and Mapping) system specifically tailored for UAV pose estimation, aiming to meet the requirements of small UAVs in terms of precision and real-time performance in satellite signal denied area. The system primarily comprises two essential components: (1) To enhance pose estimation accuracy in environments with few geometric features, a surfel-based LiDAR point cloud registration algorithm is proposed, this algorithm achieves point cloud registration and pose estimation by minimizing the distance between points and surfels, while reducing the algorithm"s computational complexity and ensuring lightweight operation by discarding un-stable surface elements. (2) The framework of integrating this algorithm into the Error-State Kalman filter (ESKF) based LiDAR-inertial system is designed. The proposed SLAM system is evaluated through experiments conducted on experimental datasets. The results demonstrate superior pose estimation accuracy compared to existing LiDAR-Inertial Navigation Systems. Furthermore, while maintaining the performance in terms of runtime, the proposed technique reduces the average position deviation by 37.63% and the average attitude deviation by 33.94% in outdoor satellite signal denied environments.
    Flight characteristics analysis of A320 and ARJ21 in the go-around phase based on flight director
    ZHOU Xin, WANG Qi, WANG Dong, SUN Hong, LIU Lili
    Available online:October 30, 2024, DOI:
    [Abstract] (61) [HTML] (0) [PDF 677.74 K] (91)
    Abstract:
    As an important function of the automatic flight control system of modern air transport aircraft, flight director provides flight attitude control instructions for the automatic pilot/pilot, which is of great significance for reducing the pilot"s workload, improving the pilot"s manual operating quality, enabling the aircraft to fly on the scheduled flight path and ensuring flight safety. At present, there are few researches on flight characteristics based on flight director, so A320 and ARJ21 are selected to analyze their flight characteristics of following the guidance in the go-around mode respectively. It is found that the pitch guidance of A320 aircraft during the go-around phase is to adjust the pitch first to quickly reach the positive climb rate, and then the pitch Angle instruction is given by the speed reference system to track the target speed principle under the premise of maintaining the minimum climb rate. The ARJ21 is given pitch Angle command in three stages, namely initial fixed pitch Angle control, pitch control based on target track Angle and pitch control based on target speed. Through curve similarity analysis of QAR data, it was found that the go-around guidance mode of the ARJ21 model has a better following effect. The research results provide a new perspective for subsequent pilot manual control quality evaluation and provide a new idea for the development of new aircraft models in the future.
    Research on Maintenance Procedures of Structural Standard Practices for Civil Aircrafts
    Liu Zhonghua, SHI HONGWEI
    Available online:October 25, 2024, DOI:
    [Abstract] (26) [HTML] (0) [PDF 461.83 K] (84)
    Abstract:
    The content scope and data sources need to be clarified for developing the maintenance procedures of structural standard practices in the aircraft maintenance manual. By researching on airworthiness regulations, industry specifications and aircraft maintenance manuals of international mainstream civil aircrafts, this paper summarizes the main contents to be covered by the maintenance procedures of structural standard practices in the aircraft maintenance manual, including corrosion prevention, internal and external finishes, airframe drainage and sealing, etc.. Combined with the development experience of domestic civil aircrafts, the main data sources required for the development of structural standard practices" maintenance procedures are pointed out, including aircraft design drawings/digital models, manufacture process specifications, supplier product data, maintenance task analysis data, technical reports and industry standards, etc.. At the same time, by considering the requirements of airlines to use maintenance procedures to develop task cards, the characteristics of the structural standard practices" maintenance procedures for domestic civil aircrafts are formed. The operation practices of domestic civil aircrafts show that the maintenance procedures of structural standard practices developed according to the content scope and data sources given in this paper meet the needs of aircraft maintenance very well.
    Study on Level of Repair Analysis Technology for Civil Aircraft Structural Components Based on S3000L Standard
    Wu Yixin, Zhang Xiaojing, ZHAGN YAJIE
    Available online:October 25, 2024, DOI:
    [Abstract] (143) [HTML] (0) [PDF 440.22 K] (83)
    Abstract:
    At present, the main manufacturers of civil aircraft in China often use empirical judgment to make repair level decisions for structural components, especially with limited decision-making experience in workshop repairs. Therefore, there is an urgent need to conduct research on repair level analysis technology. Level of repair analysis is not only one of the important links in the logistics support analysis of civil aircraft components, but also an important input for the planning and preparation of component maintenance manuals. Most international mainstream civil aircraft manufacturers have begun to adopt the S3000L standard for logistics support analysis. This article studies the Level of Repair Analysis (LORA) method provided in the S3000L standard, and combined with the experience of continuous airworthiness document organization to develop a repair level analysis process suitable for civil aircraft structural components. Practical examples are also used for feasibility verification. The research results indicate that using non-economic simplified LORA analysis method for structural components is more feasible at present. The analysis process provided in this article can provide reference for domestic main manufacturers to develop structural component maintenance manuals.
    Research on Automatic Generation of Civil AircraftConsumable Product Manual Based on S1000D Specification
    LiMengxia, YangYang
    Available online:October 25, 2024, DOI:
    [Abstract] (35) [HTML] (0) [PDF 524.38 K] (89)
    Abstract:
    In order to deliver aircraft manuals with accurate content, convenient use and friendly interaction, improve customer satisfaction and reduce publishing cost, the automatic publishing technology of civil aircraft Consumable Product Manual was studied. At present, Consumable Product Manual data is written manually, which wastes manpower and is easy to produce inconsistent manual contents. To solve this problem, a method of automatic generation of homologous manual based on S1000D standard is studied. This method is applied to guide the Consumable Product Manual of a certain civil aircraft type to carry out data planning, data management, data generation and system function development, which achieves automatic generation of structured and easily searchable PDF and electronic interactive Consumable Product Manual based on the same data source. The results indicate that this method can systematically and comprehensively analyze manual requirements, plan manual data, and guide the system to achieve automatic manual generation. It has good application prospects in the automatic generation of manuals that have the same data source for various aircraft types, such as Standard Manual, Quick Reset Manual, and Master Minimum Equipment List.
    Establishment of Civil Aircraft Abnormal Operation Procedure Item List
    Zhang Congyuan, Yang Yanyan
    Available online:October 24, 2024, DOI:
    [Abstract] (14) [HTML] (0) [PDF 1.80 M] (85)
    Abstract:
    Abnormal procedures are the important basis for the flight crew to handle emergency conditions. There is no current establishment method of procedures items, which makes unnecessary or omission may easily occur in the procedure items. This paper divides the abnormal procedures into four types: airworthiness regulation, function failure, route operation factor and model feature procedures, and provides the cooresponding procedure item establishment methods. Abnormal operation procedures are established based on “operation require”, through regulation inquiry, system security analysis (Failure Mode and Effect Analysis (FMEA) and Functional Hazard Analysis (FHA)), reference to similar type and etc. Those all makes the results more accurate. And then this result is iterated to optimize the CAS design. This method is verified to be able to establish procedure items by using it to develop some domestic civil aircraft fuel system abnormal operation procedures, and it makes the design result more in line with expectations of pilots.
    Feasibility Exploration Analysis of AR Virtual Verification Method of Civil Aircraft Maintenance Program
    sunhongli, wang hongchao, zhang yajie, qiao wanxin, zhaoxincan
    Available online:October 24, 2024, DOI:
    [Abstract] (29) [HTML] (0) [PDF 5.35 M] (86)
    Abstract:
    The verification resources are difficult to guarantee for current domestic civil aircraft maintenance manual verification work, A AR virtual verification method based on digital model is proposed in addition to table-top verification and on-object verification methods. This paper gives the workflow of maintenance program AR virtual verification based on the technical requirements of aircraft maintenance manual verification, and explores the feasibility of this method from the perspective of building consistency with real configuration aircraft and maintenance operation consistency. Comparing the implementation requirements of on-object verification and AR virtual verification, it is demonstrated that the AR virtual verification method is feasible for the disassembly and inspection maintenance procedures.
    Research on Evaluation Criteria of On-object Verification Requirement of Revised Civil Aircraft Maintenance Manual Procedure
    YI Jiuhuo, YU Weixuan, WANG Hongchao, ZHANG Rongning
    Available online:October 24, 2024, DOI:
    [Abstract] (15) [HTML] (0) [PDF 474.98 K] (91)
    Abstract:
    At present, researches on verification of civil aircraft maintenance manuals are focused on verification method, verification flow, quality control and so on. There are no relevant criteria and flow of on-object verification requirement of revised civil aircraft maintenance procedure, thus some researches are urgent needed. Evaluation criteria and flow of on-object verification requirement of revised civil aircraft maintenance procedure are concluded and summarized by analyzing whether the revised contents of maintenance procedures need to propose an on-object verification requirement or not, and in combination with manual verification experiences during flight test and operation of civil aircraft, also verified with instance. The results show that revision of common information, safety conditions etc. should not propose an on-object verification requirement, but revision of access method, test logic etc. should propose an on-object verification requirement. It will provide convenience for manual writers and manual verifiers when they make judgment.
    Research on UAV Path Planning Algorithm Based on Improved Virtual Spring Method
    xiao heng, zhang hui, zhou wen, mu zhen jie
    Available online:September 29, 2024, DOI:
    [Abstract] (63) [HTML] (0) [PDF 1.12 M] (117)
    Abstract:
    Aiming at the path planning problem of UAVs and the problems of target unreachability and easy oscillation of narrow channels in the path planning process of the virtual spring method, a UAV path planning algorithm that improves the virtual spring method is proposed. Firstly, the repulsive force formula between the UAV and the obstacle and the traction formula between the UAV and the target point are established to complete the local path planning of the UAV. Secondly, the concept of boundary force is introduced into the virtual spring method to solve the problems of easy oscillation and target unreachability in the narrow channel of UAV. Finally, the effectiveness of the proposed method is verified in combination with simulation experiments.The simulation results show that compared with the traditional virtual spring model and the improved virtual spring model, the improved virtual spring algorithm based on boundary force proposed in this paper forms a smoother path for UAV path planning in the narrow channel environment, and enables the UAV to reach the target point smoothly when the target is not reachable, and is able to plan UAV paths in a relatively complex environment.
    Research on Aircraft Engine Thrust Estimation Method Incorporating Attention Mechanism
    ZOU Yuhang, ZHAO Yongping
    Available online:September 29, 2024, DOI:
    [Abstract] (52) [HTML] (0) [PDF 1.11 M] (122)
    Abstract:
    This study aims to enhance the accuracy and practicality of thrust estimation models for aero engines. The research first constructs a multi-task LSTM-Attention model that integrates Long Short-Term Memory (LSTM) and attention mechanisms for time series forecasting. Additionally, to address the issue of thrust estimation under different flight conditions, this paper employs Fine-tuning and an improved Domain-Adversarial Neural Network (DANN) transfer learning method to strengthen the model"s adaptability to multiple operational conditions. The results demonstrate that LSTM combined with the attention mechanism can effectively model long time series data, rectifying LSTM"s insufficiency in global modeling capabilities, while also overcoming the limitation of the attention mechanism in capturing relative position information. The multi-task learning strategy can significantly improve the model"s prediction accuracy at the abrupt changes in the throttle levers, further enhancing the model"s accuracy. The study of thrust prediction under different conditions based on transfer learning methods indicates that Fine-tuning should be selected when there is limited target domain data, while the modified DANN method will yield a model with higher accuracy when there is sufficient target domain data. This research provides a more accurate solution to the problem of thrust estimation for aero engines and has significant reference value for future research and practical applications.
    Research on Board Level Certification Approval Strategy Based on DO-254
    LIU Runzhou, ZHU Hongli, ma limin
    Available online:September 29, 2024, DOI:
    [Abstract] (83) [HTML] (0) [PDF 389.65 K] (183)
    Abstract:
    (小5号黑正)：This article is to address the ambiguity in the current domestic certification practice based on the DO-254 Airborne Electronic Hardware Development Assurance Guidelines regarding the board level certification strategy and objectives for circuit boards. By comparing and analyzing the relevant objectives for circuit board level in Advisory Circular AC 20-152A and Memorandum CM-SWCEH-001 regarding DO-254, and combining the certification concept of foreign airworthiness authorities and the current domestic industrial circumstance, this paper proposes considerations and suggestions for the certification strategy and methods for domestic airborne electronic hardware circuit board level.
    Wind Tunnel Test Research for Influence of Passive Flow Control Technology on Low Speed Characteristics of Civil Transport Aircraft
    Wei Yan, Qimin Wang, Jingye Li, Huiwen Xu, Keliang Zhao, Feng Bei, Meihong Zhang, Renshan Jiao, Fei Wang, Weiping Zeng
    Available online:August 22, 2024, DOI:
    [Abstract] (56) [HTML] (0) [PDF 5.67 M] (195)
    Abstract:
    In order to optimize the low-speed characteristics of the high-lift configuration of civil transport aircraft and enhance the take-off and landing performance of the aircraft, it is necessary to control the flow separation of the wings. Through the wind tunnel test, the research on the selection of two passive control technologies, the wing-body fairing and outboard nacelle strake, was carried out. The best combination scheme that can optimize the low-speed characteristics has been found, and the area where the flow separation is suppressed by the optimization method has been presented through the flow visualization test. Under normal pressure conditions, the maximum lift coefficient is increased by about 7% under the effect of the optimal wing-body fairing, and the stall angle of attack is delayed by about 3°. Under the combination effect of wing-body fairing and outboard nacelle strake, the maximum lift coefficient is increased by about 9%. Under pressurized conditions, the combination of the optimal wing-body fairing and the outboard nacelle strake under the Reynolds number effect increases the maximum lift coefficient by about 5% on the basis of the normal pressure test results. The angle of attack is delayed by about 1.7°.
    Research on Residual Stress and Deformation Control of Domestic 7050 Aluminum Alloy Thin-wall Bearing Frame Turning
    HUYUE, ZHANGSHENGWEI, JIANGRUISONG, HUANGCHONGXIANG
    Available online:August 08, 2024, DOI:
    [Abstract] (48) [HTML] (0) [PDF 4.79 M] (239)
    Abstract:
    Researching the deformation control of domestic 7050 aluminum alloy aviation thin-walled bearing frame parts during turning processing is crucial for ensuring machining precision and performance while maintaining cutting efficiency with minimized radial deformation. This thesis employs a combination of experimental and simulation methods to investigate the optimization of turning residual stress deformation for domestic 7050 aluminum alloy aviation bearing frames. Initially, a three-dimensional turning residual stress simulation model was established and validated through experiments for the accuracy of the domestic 7050 aluminum alloy thin-walled bearing frame turning simulation model. Subsequently, an orthogonal experiment was conducted based on the three-dimensional turning simulation model to establish a mapping model between turning parameters and residual stress. Finally, with the objectives of turning efficiency and residual stress optimization, optimized turning parameters for the domestic 7050 aluminum alloy aviation thin-walled bearing frame were obtained using a genetic algorithm. The results show that the optimized machining surface residual stress was reduced to 15.6MPa, and the maximum radial deformation of the bearing frame was 1.59mm, which is about 19% less than the original turning parameters, achieving the goal of controlling and optimizing the processing deformation of the domestic 7050 aluminum alloy aviation thin-walled bearing frame.
    Study on aerodynamic design of 1/2+1 counter-rotating compressor
    LIU Jingyuan, WU Tianyuan
    Available online:August 08, 2024, DOI:
    [Abstract] (31) [HTML] (0) [PDF 4.23 M] (276)
    Abstract:
    It is of vital importance to develop counter-rotating compressor for military and national defense, and the aerodynamic design of counter-rotating compressors is a prerequisite for the purpose. A detailed analysis of the internal flow characteristics of the counter-rotating compressor was conducted, and the aerodynamic design ideas and methods of the counter-rotating compressor were explored. On the basis of balancing the aerodynamic and geometric design parameters, as well as the coordination and matching between the front and rear rotor design parameters, a 1/2+1 counter-rotating compressor aerodynamic scheme design was completed. The full three-dimensional numerical simulation results showed that the designed counter-rotating compressor meets the overall performance indexes with high aerodynamic performance.
    Design and Implementation of Civil Aircraft Test Database for Multi-discipline Integration
    Li Xinyang, Feng Yunwen, li jian, Lu Cheng, xie yajun, Yang LI
    Available online:August 08, 2024, DOI:
    [Abstract] (72) [HTML] (0) [PDF 1.49 M] (250)
    Abstract:
    The full life cycle test data of civil aircraft, as an important component of reflecting test information, can provide a basis for supporting the quality and efficiency of model development. However, due to the characteristics of large data volume and multi professional integration, the lack of integrated management leads to waste of data resources. A test data management business process based on airworthiness clauses has been proposed to control the testing data of multiple professional civil aircraft, and a database has been designed and implemented based on this. Firstly, conduct a demand survey on the technical center researchers and analyze the database functionality based on the survey results. Afterwards, based on the specific business requirements for storing multi-disciplinary test data and a comparison of market related database development technologies, an architecture design was carried out, and the logical relationships between the storage contents of each test module were sorted out. Taking the flight module as an example, the database module design was carried out. Finally, a database operation interface was built to verify the feasibility of the design, providing reference for the design of multi professional experimental databases.
    Research on constellation fault satellite replacement strategy based on Markov decision process
    LIN Ruoyu, FENG Yunwen, XUE Xiaofeng, ZHENG Xiaoyan, CUI Shuai
    Available online:June 12, 2024, DOI:
    [Abstract] (84) [HTML] (0) [PDF 484.15 K] (373)
    Abstract:
    With the large-scale constellation, the importance of a single satellite is reduced. When formulating a replacement strategy for faulty satellites, multiple replacement methods and the retention of faulty satellites should be considered. In response to this demand, a method for formulating constellation orbit satellite replacement strategy based on Markov decision process is proposed. The orbital state is divided according to the number of satellites working in orbit, in-orbit backup and ground backup. On this basis, combined with the different replacement strategies of faulty satellites and the corresponding ordering, storage and penalty costs, a return function model representing the expected maintenance cost is constructed. In order to minimize the expected maintenance cost of each decision cycle, a sequential replacement strategy is developed and applied to a constellation orbit. The results show that when the ground backup is used to replace the fault satellite, it tends to supplement the consumed backup satellite. The longer the mean time between failure, the lower the expected total maintenance cost, but the effect is gradually weakened. The increase of penalty cost will lead to the solidification of replacement strategy, and the upward trend of total maintenance cost is expected to be greatly slowed down. This method can make a sequential decision on the replacement mode of the faulty satellite according to the state of the constellation orbit, which makes the analysis more comprehensive and has certain value for the formulation of the constellation spare strategy.
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    Research and Analysis on Overheating Protection Design of Aviation Oil-cooled Generator
    SunLiRong, LaiShuaiLei, LiuZhuo
    2023,14(6):153-159. DOI: 10.16615/j.cnki.1674-8190.2023.06.17
    [Abstract] (342) [HTML] (85) [PDF 2.60 M] (11554)
    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.
    A Survey on Anti-UAV Technology and its Future Trend
    ZHANG Jing, ZHANG Ke, WANG Jingyu, LV Meibo, WANG Pei
    2018,9(1):1-8. DOI: 10.16615/j.cnki.1674-8190.2018.01.001
    [Abstract] (3625) [HTML] (0) [PDF 1.89 M] (9222)
    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.
    Safety and Hazards Analysis for Unmanned Aerial Vehicle System
    Lian Tingting, cui li jie
    2020,11(4):517-523. DOI: 10.16615/j.cnki.1674-8190.2020.04.009
    [Abstract] (1258) [HTML] (0) [PDF 833.51 K] (8071)
    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.
    Analysis of Development Trend and Design Technology of Refueling Boom
    Wang Xiuxiang, Gao Xu, Gao Yakui
    2020,11(3):302-307. DOI: 10.16615/j.cnki.1674-8190.2020.03.002
    [Abstract] (1292) [HTML] (0) [PDF 1.65 M] (6403)
    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.
    Simulation of the Expansion Process of Different Folded Cylindrical Airbags
    xueqiwen, wangxiaoteng, heyiqian, guomin, liuxudong, ezhijia
    2021,12(3):161-170. DOI: 10.16615/j.cnki.1674-8190.2021.03.20
    [Abstract] (771) [HTML] (0) [PDF 8.07 M] (5965)
    Abstract:
    The process of folding and inflating the cylindrical airbag is complicated, and there are many inconveniences in using experimental methods to study its expansion process. Two different folding methods are proposed for the cylindrical airbag and the corresponding numerical analysis models are established respectively. The nonlinear dynamics software is used to study the dynamic application characteristics of the cylindrical airbag after being folded, which will affect the skin stress during the airbag expansion process. The factors of volume and internal pressure curve change are analyzed, and the influence of different folding methods and external environmental parameters on the dynamic characteristics of the cylindrical airbag is discussed. The results show that the two folding methods have their own advantages in storage space and material strength. In addition, in the environmental parameters, the external pressure has a greater impact on the stable state of the airbag after expansion, while the temperature has no obvious effect.
    Analysis of Classifications and Characteristic of Additive Manufacturing (3D Print)
    Yang Yanhua
    2019,10(3):309-318. DOI: 10.16615/j.cnki.1674-8190.2019.03.003
    [Abstract] (1534) [HTML] (0) [PDF 1.21 M] (5806)
    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.
    Development and Trend Analysis of VTOL Fixed Wing UAV
    WANG Kelei, ZHOU Zhou, MA Yuewen, DU Wanshan, GUO Jiahao, LI Xu, ZHANG Yang, SUN Pengbo
    2022,13(5):1-13. DOI: 10.16615/j.cnki.1674-8190.2022.05.01
    [Abstract] (1418) [HTML] (1162) [PDF 3.67 M] (5639)
    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.
    An Overview on Development of Small Turbine Engines for Missiles
    Xue Ranran, Li Fengchao, Ren Lilei
    2018,9(1):18-27. DOI: 10.16615/j.cnki.1674-8190.2018.01.003
    [Abstract] (2697) [HTML] (0) [PDF 1.88 M] (5340)
    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.
    The Design Optimization and Strength Analysis of a Heavy-duty Quadrotor UAV
    LIU feng, YU Hui, GAO Hong-jian, DAI Hai-liang, MA Jia
    2018,9(1):99-106. DOI: 10.16615/j.cnki.1674-8190.2018.01.013
    [Abstract] (2562) [HTML] (0) [PDF 1.77 M] (5017)
    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.
    Preliminary Thoughts on the Combination of Artificial Intelligence and Aerodynamics
    zhangtianjiao, qianweiqi, zhouyu, helei, shaoyuanpei
    2019,10(1):1-11. DOI: 10.16615/j.cnki.1674-8190.2019.01.001
    [Abstract] (2163) [HTML] (0) [PDF 562.11 K] (4782)
    Abstract:
    There are a great deal of influence on many fields of society as a result of the new round of technological revolution and industrial revolution centered on artificial intelligence. All the aerospace powers have conducted many useful experiments and explorations in the combination of artificial intelligence and aerodynamics. The development history and status quo of artificial intelligence technology are reviewed in this paper, the applications of artificial intelligence in wind tunnel test, numerical calculation and flight test are discussed in the background of big data era, the role of artificial intelligence in assisting mass aerodynamic data analysis and knowledge discovery is analyzed in detail, the application values of artificial intelligence in aerodynamic modeling and advanced aircraft design are investigated, the future development direction and challenges of combination of artificial intelligence and aerodynamics are prospected.
    A Survey of Low Altitude UAV Path Planning Algorithms
    LiuQinjian, ShuLisheng, liu gang, li ao
    2023,14(2):24-34. DOI: 10.16615/j.cnki.1674-8190.2023.02.03
    [Abstract] (960) [HTML] (1133) [PDF 1.07 M] (4626)
    Abstract:
    With the diversification of UAV application scenarios, many scholars have studied UAV path planning algorithms. This paper summarizes the UAV path planning algorithms commonly used by scholars in recent years, summarizes the principles, applicable scenarios, advantages and disadvantages of the algorithm, and makes a prospect of UAV path planning algorithms based on the development status of UAVs.
    Overview of Wireless Avionics Intra-Communication Network Technology
    Fan Xianghui, CHEN Changsheng, SHI Yan, YANG Jianxi
    2021,12(1):129-135. DOI: 10.16615/j.cnki.1674-8190.2021.01.017
    [Abstract] (1380) [HTML] (0) [PDF 1.19 M] (4046)
    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.
    Research on the influence of bleeding and cooling model to the performance of turboshaft engine
    HU Qiu-chen, CHEN Yu-chun, JIA Lin-yuan, HUANG Xing
    2014,5(1):109-115. DOI:
    [Abstract] (4093) [HTML] (0) [PDF 2.89 M] (3959)
    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.
    Research on the Status and Key Technology of Adaptive Wings
    NI Ying-ge, YANG Yu
    2018,9(3):297-308. DOI: 10.16615/j.cnki.1674-8190.2018.03.001
    [Abstract] (1531) [HTML] (0) [PDF 3.91 M] (3632)
    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.
    Introduction of S5000F Specification and Its Application in Operational Reliability Analysis and Feedback of Civil Aircraft
    Feng Yun-Wen, Lu Cheng, Xue Xiao-Feng, Ma Xiao-Jun
    2020,11(2):147-158. DOI: 10.16615/j.cnki.1674-8190.2020.02.001
    [Abstract] (1790) [HTML] (0) [PDF 3.27 M] (3606)
    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.
    Key Technologies of Turbofan Engine for High Altitude Long Endurance UAV
    Wenzhanyong, Duanya
    2020,11(2):159-166. DOI: 10.16615/j.cnki.1674-8190.2020.02.002
    [Abstract] (1454) [HTML] (0) [PDF 1.20 M] (3575)
    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.
    Al-Li alloy properties and applications on the commercial aircraft
    Sun Jieqiong, Zhang Baozhu
    2013,4(2):158-163. DOI:
    [Abstract] (3775) [HTML] (0) [PDF 4.91 M] (3515)
    Abstract:
    Weight is one of the most important performances for the aviation productions. The most effective approach to weight saving is developing the lower density material. Introduce advanced Al-Li (Aluminum-Lithium) alloy with lower density, higher tensile strength, better damage tolerance etc. Compare to conventional aluminum alloys and trade-off study with advanced composites. Analysis the properties of 3rd-generation Al-Li alloy and the applications on advanced aircraft. Provide the proposals of applications in civil program. The research can be the reference of materials selection and weight saving for commercial aircraft, and benefit extending applications of Al-Li alloy.
    Review on the Research of Airspace Gridding Method and its Application in Air Traffic Management
    ZHU Yongwen, XIE Hua, PU Fan, ZHANG Ying, HE Weiwei
    2021,12(4):12-24. DOI: 10.16615/j.cnki.1674-8190.2021.04.02
    [Abstract] (1394) [HTML] (0) [PDF 1.57 M] (3383)
    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.
    High-performance propeller optimization design
    Wang Ce, Tang Zhengfei, luo jian
    2018,9(4):585-591. DOI: 10.16615/j.cnki.1674-8190.2018.04.017
    [Abstract] (619) [HTML] (0) [PDF 2.25 M] (3300)
    Abstract:
    In this paper, the methods of reverse reconstruction and parametric modeling of the propeller are mainly studied. The torsion angle distribution and the pattern of the leaf-type stacking of the existing propeller model are optimized. In this paper, the propeller is taken as an example, and its reconstruction and parametric modeling are carried out. Numerical calculation techniques based on high-precision algorithms such as structured rotating grid and N-S equation are established and tested by experiments. Based on this, the CFD calculation of the propeller, the analysis and optimization of the blade twist angle and the stacking method are carried out to provide the help of the existing blade pull-down power
    Airborne Software Quality Assurance and Management Based on DO-178C
    ZHOU Pei
    2021,12(6):161-166. DOI: 10.16615/j.cnki.1674-8190.2021.06.20
    [Abstract] (974) [HTML] (0) [PDF 533.70 K] (3286)
    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.

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