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    Review
    The technical roadmap of the development of variable pitch propeller governors for turboprop
    Chen Tingting, Guo Yong, Pan Zhongjian
    2025,16(5):1-13. DOI: 10.16615/j.cnki.1674-8190.2025.05.01
    [Abstract] (23) [HTML] (35) [PDF 2.31 M] (42)
    Abstract:
    The variable pitch governor controls the propeller to maintain a constant speed, so that the propeller can be energy-saving and efficient in a wider range of flight envelope; many foreign countries have developed variable pitch governor with electro-hydraulic servo through a number of advanced turboprop aircraft, while China has only few self-developed variable pitch governor products, many of which are mechanical-hydraulic type. This paper introduces the mechanism and background of the governor and reviews its current research status at home and abroad. Besides, the key technical problems such as insufficient lightweight reliability strategy, internal electro-hydraulic servo valve oil sensitivity, and difficulty in the integration of the propulsion system electronic control unit are analyzed for the electro-hydraulic servo type governor. Based on that, the paper also looks forward to the trends of electrification, digitalization, and intelligentization in the technology of variable-pitch governor for turboprop aircraft. The corresponding solution ideas are provided in order to provide reference for the further research of the advanced governor in China.
    Challenges of Implementation of Predictive Maintenance from the Perspective of Aviation Equipment Maintenance Experiences
    SONG Haifang, WANG Shijiao, LI Fan, LIU Jialin
    2025,16(5):14-27. DOI: 10.16615/j.cnki.1674-8190.2025.05.02
    [Abstract] (14) [HTML] (46) [PDF 2.15 M] (35)
    Abstract:
    Predictive maintenance (PdM) can improve the aviation equipment readiness in minimal cost, and PdM is also one key enabler to agile combat support. Problems and challenges were analyzed from the perspective of maintenance and support practices in this paper. Firstly, three maintenance methods were compared and each of their suitability was discussed. Secondly, organizations, events, and forms involved in PdM were analyzed. Then, problems against implementation of PdM were summarized in terms of reduction of the maintenance workload and improvement of aviation equipment readiness. The effects of the maintenance information system were also evaluated. Challenges were explained from the perspective of personnel resource, repair parts supply, technical and organizational culture. Lastly, some suggestions were proposed to implement the PdM in our aviation equipment maintenance and support.
    Theoretical Research
    Obstacle Avoidance Control of Consensus Formation Based on Leader-Following Strategy
    Zhu Xu, Wang Zhengning, Zhang Sheng, Kuang Yuheng, Zhang Bohan, Huang Jiangtao
    2025,16(5):28-41. DOI: 10.16615/j.cnki.1674-8190.2025.05.03
    [Abstract] (9) [HTML] (5) [PDF 5.31 M] (30)
    Abstract:
    Obstacle avoidance flight is an important problem to be solved in cluster formation flight of UAV in complex battlefield environment. In order to achieve efficient and reliable obstacle avoidance flight, based on the distributed leader-following consensus control strategy, the UAV cluster is divided into the leader in charge of path planning and the follower responsible for formation control. An improved RRT* path planning algorithm is proposed to provide real-time path planning for the UAV cluster in complex environments with dynamic obstacles. Based on the backstepping control method and taking the formation consensus protocol as the error, a distributed formation flight control law is developed to dynamically adjust the formation spacing according to the environment. By constructing three kinds of obstacle environments with different complexity to validate the formation obstacle avoidance algorithm, simulation results show that the proposed approach may generate feasible formation flight paths rapidly corresponding to the environment changes, and realize the accurate control of variable spacing formation flight of UAV cluster, which achieves the goal of efficient obstacle avoidance for the cluster formation flight.
    Quick Spectrum Sensing for Delay-constraint Cognitive UAV Networks
    Hao Chen, Haoyu Liang, Jun Wu, and Weiwei Cao
    2025,16(5):42-50. DOI: 10.16615/j.cnki.1674-8190.2025.05.04
    [Abstract] (12) [HTML] (18) [PDF 1.22 M] (24)
    Abstract:
    Unmanned aerial vehicles (UAVs) have gained much popularity for a wide variety of applications which do not require human operator, but also face the spectrum scarcity problem. In order to address this problem, a cognitive UAV network (CUAVN) framework based on cognitive radio (CR) technology is formulated in this paper. On the basis of this, sequential probability ratio test (SPRT) is used as a fundamental cooperative spectrum sensing (CSS) scheme to significantly reduce the average number sample, but the uncertainty of its detection delay has the negative impact on the spectrum sensing performance of CUAVNs. Considering the location flexibility and uneven distribution density of UAVs, we design an intra-frame CSS structure, with aim of achieving CSS between micro-sensing slots. Furthermore, a sequential maximal truncation (SMT) is proposed to realize a quick spectrum sensing for delay-constraint CUAVNs. Compared to uniform tail truncation (UTT), simulation results show that the proposed quick multi-band spectrum sensing with the help of SMT requires fewer sensing times in support of better sensing performance, especially under a strict delay constraint.
    Research on heavy landing risk prediction and evaluationof airplane based on LSTM
    HE Jian, QIAN Yu, TANG Shengxiang
    2025,16(5):51-57. DOI: 10.16615/j.cnki.1674-8190.2025.05.05
    [Abstract] (12) [HTML] (13) [PDF 1.08 M] (32)
    Abstract:
    Heavy landing of airplane is easy to cause airplane structural damage. Studying the prediction and assessment of heavy landing risks for airplane is very important and necessary for reducing the risk of heavy landing and improving the safety of civil aviation operations. A heavy landing risk prediction model is established by using QAR data and LSTM neural network. By calculating the probability density function of vertical acceleration, the possibility and severity of heavy landing are calculated to obtain the risk value; Based on the analysis of landing gear force during landing, vertical acceleration (landing load), descent rate, roll Angle, lateral acceleration and pitch Angle are selected as the influencing parameters of heavy landing. LSTM neural network is used to train the landing load of the flight, and the landing risk table is established. Through the parameter training of QAR data, the model is used to predict the landing load of the flight and verify its accuracy, and the risk of heavy landing is determined with reference to the risk grade table. The simulation results show that the RMSE and MAE of the predicted value and the actual value both reach the order of 10-3, and the quantitative heavy landing risk and heavy landing risk prediction are realized. The prediction model established by the research can provide theoretical basis for airplane landing safety risk management.
    LIU Ruihua1, LIU Zhiyang1,MA Zan2, Zheng Zhiming3, Zhong Kelin3
    liuruihua, liuzhiyang, mazan, zhengzhiming, zhongkelin
    2025,16(5):58-68. DOI: 10.16615/j.cnki.1674-8190.2025.05.06
    [Abstract] (18) [HTML] (18) [PDF 5.37 M] (30)
    Abstract:
    With the development of Global Navigation Satellite System (GNSS), satellite-based positioning technology has become an important data source for aviation navigation. However, in scenarios involving unmanned urban air mobility (UAM) applications, satellite positioning is susceptible to multipath (MP) and non-line-of-sight (NLOS) signals leading to deterioration in positioning accuracy, posing a challenge to aircraft safety. To address this problem, a proposed method utilizes the K-LSTM model for satellite positioning error estimation. Firstly, the K-means clustering method is used to detect MP/NLOS signals. Secondly, investigating the relationship between satellite observations and positioning errors in different environments and extending the network model. This extension involves adding a droupout layer, a ReLU layer, a fully-connected layer, and a regression layer on top of the Long Short-Term Memory (LSTM) neural network. Finally, using the extended LSTM model to estimate and correct the localization error caused by MP/NLOS signals. The experimental results reveal that in the static urban canyon environment, the localization errors of the clustered MP/NLOS signals are 0.6m, 0.9m, and 1.0m in the east, north, and up directions, respectively, after the correction by the extended LSTM model. Additionally, the localization errors in the dynamic reflection environment are 1.5m, 1.0m, and 2.5m in the east, north, and up directions, respectively. These results demonstrate significant enhancements in localization accuracies compared to the pre-correction errors.
    Engineering Application
    Wing aerodynamic design of amphibious aircraft with hybrid-wing-body configuration
    Ruan Yuan, Zhang Heng, Luo Ben, Dong Song Wen, Huang Long Tai
    2025,16(5):69-78. DOI: 10.16615/j.cnki.1674-8190.2025.05.07
    [Abstract] (22) [HTML] (22) [PDF 2.52 M] (41)
    Abstract:
    The Hybrid-Wing-Body(HWB) configuration is characterized with high cruising efficiency, large loading space, high structural efficiency and enough longitudinal stability. Compared with traditional configuration, the proportion of central body and inner wing section is larger, which provide sufficient optimization space for advanced ship-body design. These characters will comprehensively improve the seaworthiness of amphibious plane. Aimed to a wing-body configuration for a large amphibious aircraft based on the HWB concept, the aerodynamic performance design of high lift wings according to the requirements of lift and stall performance during takeoff and landing stages was carried out. The analysis results show that with the extension of stall point and the arrangement of nonlinear lift of airfoils, the stall angle of wing-body combination based on HWB configuration reaches 20°, while the maximum lift coefficient reaches 2.0. A reasonable stall-separation sequence between the root and tip of wing effectively and a gentle trailing-edge separation pattern are both realized, which ensures the aerodynamic safety during takeoff and landing.
    Analysis of S-duct’s fluid-solid-thermal coupling characteristic considering creep effect1)
    Lin Yuan, Sun Mingbo, Wang Chenglong, Shen Chibing, Tan Dongcai, Su Ang, Guan Banglei, Wan Minggang, Chen Qi, Li Zhang
    2025,16(5):79-90. DOI: 10.16615/j.cnki.1674-8190.2025.05.08
    [Abstract] (14) [HTML] (17) [PDF 1.68 M] (31)
    Abstract:
    For the hypersonic vehicle whose inlet and combustion chamber are not on the same axis, the S-duct is an important component, and its main function is to turn the air flow. However, the existing researches mainly focus on the flow field of S-duct, and few study the creep under the multi-field coupling effect of S-duct. In order to study the influence of multi-field coupling effect of creep material on the S-duct of hypersonic inlet, the numerical simulation of the S-duct of hypersonic inlet for long endurance was carried out by using the independently developed fluid-solid-thermal bidirectional coupling calculation and analysis platform. Firstly, the accuracy of the coupling platform is verified by the creep stretching calculation example and the heating experiment of the stainless steel round tube. Secondly, the stress relaxation caused by creep is analyzed. Finally, the influence of multi-field coupling calculation considering creep on flow field is studied. The results show that the location of the maximum creep strain in S-duct is changing, and the creep effect will lead to the relaxation of S-duct stress and affect the stress distribution and magnitude of the structure. The creep effect changes the solid structure of S-duct, and influences the wave structure, pressure and temperature of flow field under the multi-field coupling effect. Therefore, it is necessary to consider the creep effect of materials in the multi-field coupling calculation of S-bend of hypersonic inlet for long endurance.
    Research on Autonomous Indoor Target Search Solution for MAVs
    Tang Dongyang, Han Qing, Tian Keyuan, Liu Xing
    2025,16(5):91-102. DOI: 10.16615/j.cnki.1674-8190.2025.05.09
    [Abstract] (17) [HTML] (24) [PDF 3.64 M] (26)
    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
    2025,16(5):103-109. DOI: 10.16615/j.cnki.1674-8190.2025.05.10
    [Abstract] (15) [HTML] (19) [PDF 1.24 M] (27)
    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.
    Catapult Take off Control based on Model Predictive Control
    Qian Guohong, Wen Zixia, Qiu Xin, Huang Xudong, Shi Ziwei
    2025,16(5):110-115. DOI: 10.16615/j.cnki.1674-8190.2025.05.11
    [Abstract] (14) [HTML] (19) [PDF 785.86 K] (38)
    Abstract:
    After separating from the catapult and leaving the flight deck, carrier-based aircraft face multiple constraints including sink rate, angle of attack, and pitch rate to ensure flight safety and quality. Traditional angle-of-attack protection control methods tend to be overly conservative - when approaching the stall angle, the control system automatically lowers the aircraft"s attitude to reduce the angle of attack. While effective in preventing stall, this approach sacrifices partial lift, which is crucial for maintaining sufficient lift during the critical launch phase. To address these issues, a model predictive controller is designed that converts key performance metrics during catapult-assisted takeoff into linear matrix inequality (LMI) constraints. Through online receding horizon optimization, predictive feedback control laws are solved to guarantee asymptotic stability and robustness of the closed-loop system, enabling the aircraft to maintain maximum allowable angle of attack and sustain high-lift flight during the launch phase. Finally, nonlinear simulation cases validate the effectiveness of the proposed control method.
    Fatigue life analysis of main landing gear considering the shock absorber travel
    liupanglun, tanghaihong, DING JIANBIN, ZHANG JIE, YU HAOWEN, DUAN HENG, jiangbingyan
    2025,16(5):116-122，198. DOI: 10.16615/j.cnki.1674-8190.2025.05.12
    [Abstract] (10) [HTML] (27) [PDF 3.00 M] (27)
    Abstract:
    The assessment of fatigue life for landing gears is challenging due to the complexity of load conditions and the continuous variation of shock absorber travel (SAT). This paper focuses on the high-cycle fatigue (HCF) issue of the sliding tube (SL). Based on the whole geometric model of the main landing gear (MLG), the HCF is studied by considering the SAT under various fatigue load cases. Firstly, the method of unit load decomposition was explored based on MLG ground load spectrum. Then, a quasi-static finite element analysis model of the MLG was established using ANSYS Workbench to simulate stress response for 115 unit conditions under 5 different SAT. Finally, employing stress superposition method and nCode software, the fatigue life of SL structural in the MLG was analyzed. The results indicate that the minimum fatigue life of the SL is 49610 cycles, meeting the requirement of 48,000 cycles according to the design objective.
    Research on the hit accuracy analysis of a certain type of target system
    XUE Jie, Ma Yuan
    2025,16(5):123-128. DOI: 10.16615/j.cnki.1674-8190.2025.05.13
    [Abstract] (13) [HTML] (34) [PDF 749.09 K] (24)
    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 turning machinability of a new GH4198 superalloy
    JIN Qichao, ZHANG Jinqi, TAN Haibing, LI Fulin, FU Rui, GUO Lei
    2025,16(5):129-137. DOI: 10.16615/j.cnki.1674-8190.2025.05.14
    [Abstract] (19) [HTML] (16) [PDF 3.15 M] (30)
    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.
    Civil Aircraft System Process Assurance Application Based on ARP4754A
    ZHOU Pei, LI Jing, XIE Hongman
    2025,16(5):138-144. DOI: 10.16615/j.cnki.1674-8190.2025.05.15
    [Abstract] (11) [HTML] (25) [PDF 778.25 K] (30)
    Abstract:
    ARP4754A Guidelines for Development of Civil Aircraft and Systems is a recommended and accepted standard for the airworthiness of civil aircraft systems. It provides a structured development process assurance method to identify and correct development errors. Based on the life cycle process and data of civil aircraft system, the implementation of civil aircraft system process assurance based on ARP4754A is analyzed from the goal, plan, review and evidence of process assurance. The application of civil aircraft system process assurance based on ARP4754A is explored from three aspects of process assurance activity types, design quality assurance (DQA) audit and DQA participation. The implementation suggestions are given and verified with the actual project. The results show that the process assurance requirements of civil aircraft system based on ARP4754A are implemented into corresponding activities and the evidence of airworthiness requirements is formed, which effectively ensures the quality and continuous improvement of system process.
    Research on identification and classification of Airline Maintainable Parts based on forward maintenance design
    wangfang, YU NALUN, SUN TIEYUAN, WEI DUNSHENG
    2025,16(5):145-154. DOI: 10.16615/j.cnki.1674-8190.2025.05.16
    [Abstract] (6) [HTML] (20) [PDF 978.95 K] (13)
    Abstract:
    Airline maintainable parts of whole aircraft are one of the important products in forward maintenance design of civil aircraft. The traditional determination method is based on the composition of existing aircraft finished parts, strongly relying on the technical resources and support provided by suppliers. It cannot consider the needs of maintenance design at the beginning of product design, carry out independent forward maintenance design, and establish an economic comprehensive indicator system for monitoring and feedback. It cannot apply and practice direct maintenance cost analysis and control for civil aircraft throughout the entire life cycle, resulting in the final determined airline maintainable parts not meeting the needs of customers for replacement and maintenance and reducing maintenance costs. Based on the above shortcomings, this paper proposes a method for identifying and classifying airline maintainable parts of whole aircraft based on forward maintenance design, establishes the process of forward maintenance design of this method,analyzes the qualitative discrimination logic of this method,and determines the quantitative tradeoff index DMC of this method and establishes the engineering model for calculating the index.Finally,the method can be applied to the classification and tradeoff of airline maintainable parts through a numerical example.The results show that this research method establishes the maintenance forward design process for maintainable parts of the whole aircraft, can weigh and decide airline maintainable parts and classification of the whole aircraft, and can carry out maintenance activity design and economic index monitoring based on the maintainable parts of the whole aircraft. At the same time,it can iteratively update the redesign of airline maintainable parts and provide references for the redesign of airline maintainable parts.
    Research on Civil Aircraft Verification Test Data Retrieval Technology Based on Word Segmentation
    Feng Yunwen, Liu Wanyi, Lu Cheng, Chen Haibo, Yin Xiaolong, Luo Yuhang
    2025,16(5):155-163. DOI: 10.16615/j.cnki.1674-8190.2025.05.17
    [Abstract] (8) [HTML] (18) [PDF 1.32 M] (17)
    Abstract:
    There is a massive amount of unstructured data in civil aircraft validation tests, making it difficult to conduct data retrieval and application based on file content, and traditional segmentation retrieval methods cannot meet the segmentation retrieval requirements in the field of validation tests. Therefore, this article proposes a segmentation retrieval method based on statistics and terminology dictionaries for the field of validation experiments: first, the conditional random fields (CRF) model is used to achieve text initial segmentation; Then, based on the domain files, a terminology dictionary is constructed, and combined with the Reverse Maximum Matching (RMM) algorithm on the basis of the terminology dictionary and the initial segmented text to achieve professional segmentation of the text; Finally, based on the professional segmentation results, the unstructured files are divided and indexed to support data retrieval based on file content. To verify the correctness of the proposed method, a case segmentation was conducted using the text content of a certain experimental outline, and compared with traditional statistical segmentation methods such as CRF, N-gram, and Hidden Markov Model (HMM). The result shows that the proposed method exhibited the best accuracy in professional segmentation. The segmentation retrieval method proposed in this article can help build a civil aircraft validation test database and achieve rapid retrieval of unstructured files in the database.
    “民用飞机飞行技术”专栏
    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
    2025,16(5):164-170. DOI: 10.16615/j.cnki.1674-8190.2025.05.18
    [Abstract] (13) [HTML] (29) [PDF 2.03 M] (22)
    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 Quantitative Evaluation Method of Flight Technology Combining Artificial and Data
    Liu Wei, LIU YUYAN, YANG YONG
    2025,16(5):171-182. DOI: 10.16615/j.cnki.1674-8190.2025.05.19
    [Abstract] (11) [HTML] (18) [PDF 1.48 M] (12)
    Abstract:
    The evaluation of flight technology runs through the whole flight process, and the objective and fair evaluation is of great significance to the improvement of pilot technology, which is of great significance to the flight safety of China"s civil aviation. At present, the evaluation of flight technology is subjective and arbitrary, and the evaluation method is not comprehensive, which is difficult to meet the needs of the Professionalism Lifecycle Management System in the new era. This paper summarizes the current flight technology evaluation methods and their shortcomings, proposes to quantitatively evaluate flight technology by combining artificial and data with complementary advantages, and creatively introduces the evaluation dimensions and implementation methods of maneuvering quality and weather influence in the evaluation, so that the flight technology evaluation can be upgraded from a single dimension of completion to a three-dimensional evaluation of completion, maneuvering completion and weather impact. Through practical cases, it is proved that this method can more objectively and comprehensively reflect the flight skill level of pilots, and is ready to fully pass the data evaluation after the data accuracy meets the requirements.
    Competency Assessment and Management Method in Commercial Pilot License Stage Based on CatBoost Multiclass Algorithm
    Sun Hong, zhangzhaoyang, LAN Jian, MENG Xiaoya
    2025,16(5):183-189. DOI: 10.16615/j.cnki.1674-8190.2025.05.20
    [Abstract] (19) [HTML] (4) [PDF 795.01 K] (16)
    Abstract:
    Scientific quantification of flight training is a prerequisite for optimizing pilot skills training and improving training efficiency. In response to the characteristics of flight training at the commercial pilot license (CPL) stage, We devised a competency evaluation framework using a mature matrix to manage and select students. Then We designed a training assessment sheet based on typical subjects.,we mapped observations to observable behaviors(OB), deriving formulas for their quantity and frequency. Threshold values were determined using a random forest algorithm. Finally, a competency rating model was built, validated empirically.
    Research on Correction Principle of Assumed Temperature under ARJ21 Aircraft Non-standard Conditions
    WANGKE, HUANGYUXUAN, XIAJUN
    2025,16(5):190-198. DOI: 10.16615/j.cnki.1674-8190.2025.05.21
    [Abstract] (13) [HTML] (16) [PDF 2.98 M] (14)
    Abstract:
    At present, the assumed temperature thrust reduction takeoff has been widely used in the operation of domestic civil aircraft. In order to assist flight crew in understanding the principle of rapid correction under non-standard conditions and to recognize its rationality and safety, the "weight-assumed temperature" relationship of ARJ21 aircraft is taken as the analysis object, and three typical non-standard conditions such as anti-ice, runway state and air pressure state are respectively investigated. Carry out the ARJ21 aircraft assumed temperature change characteristics analysis, correction principle research and correction results of the rationality verification. It is revealed that the essence of the assumed temperature correction principle under non-standard conditions is to match the actual takeoff weight with the thrust corresponding to a "sub-high-temperature weight" point, and the difference between this thrust and the minimum thrust required by the actual takeoff weight is greater than zero. And demonstrating the variation law of V_R and V_2 in the high temperature and small weight area corresponding to different airfield elevations. The results show that it is reasonable and safe to use the modified column of takeoff analysis table constructed according to this method to modify the assumed temperature under non-standard conditions.
    AHP-FCEM based core competency assessment for flight trainees
    XU Haiwen, KONG Yifan, HUANG Hong, LIANG Aimin, ZHAO Yunxiang
    2025,16(5):199-206. DOI: 10.16615/j.cnki.1674-8190.2025.05.22
    [Abstract] (16) [HTML] (20) [PDF 1.35 M] (9)
    Abstract:
    Flight training for flight trainees is an important method to ensure civil aviation safety.The core competency assessment of flight trainees is a crucial part of the construction of a pilot lifecycle management system. A multi-level evaluation framework for assessing the core competencies of flight trainees was established by combining Analytic Hierarchy Process (AHP) and Fuzzy Comprehensive Evaluation Method (FEM). Firstly, based on relevant research into the competencies of civil aviation practitioners, and taking into account the unique characteristics of flight trainees, a comprehensive core competency index system specifically for flight trainees has been formulated. Secondly, AHP is employed to determine the relative weights of each core competency indicator, while fuzzy rules are incorporated to devise evaluation sheets tailored to various behavioral indicators. Subsequently, by integrating these weights with the fuzzy membership degrees assigned to each indicator, a multi-level fuzzy comprehensive evaluation of the flight trainees" core competencies is undertaken. Finally, utilizing flight data sourced from a particular division of our school, the validity of the proposed evaluation method is verified by comparing the outcomes of the multi-level fuzzy comprehensive evaluation against both existing evaluation methodologies and the assessment results obtained by the flight squadron.
    Fuel Flow Prediction of Domestic Civil Aircraft Based on LSTM-XGBoost
    yangjunli, lilikun, qianyu, tangshengxiang, yangpeida
    2025,16(5):207-214. DOI: 10.16615/j.cnki.1674-8190.2025.05.23
    [Abstract] (14) [HTML] (23) [PDF 1.18 M] (18)
    Abstract:
    In order to improve the fuel flow prediction accuracy of domestic civil aircraft, a combination method based on LSTM (Long Short-Term Memory) and XGBoost (Extreme Gradient Boosting) algorithms was proposed to predict the fuel flow of domestic civil aircraft in the whole flight stage. Nine parameters affecting fuel flow were selected for grey correlation analysis, and eight parameters with correlation degree greater than 0.7 were obtained as the influencing parameters of fuel flow. The QAR (Quick Access Recorder) data of domestic civil aircraft were denoised by wavelet transform, and the flight data needed for research were obtained. LSTM prediction model and XGBoost prediction model were established for this data, and the error reciprocal method was used to combine the two models for prediction. The results show that the accuracy of LSTM-XGBoost combined prediction is 96.53%, which is higher than the 90.2% predicted by a single LSTM model, the 88.47% predicted by the XGBoost model and the 91.23% predicted by the PSO-BP model, and the prediction accuracy is high. The prediction of fuel flow rate by the combined model can provide a basis for fuel saving research of domestic civil aircraft.
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    Aeroservoelastic Analysis Method for Flight Control System Mixed-Command Fault
    Ding Luning, Yang Fei, Li Peng
    Available online:October 21, 2025, DOI:
    [Abstract] (23) [HTML] (0) [PDF 792.42 K] (5)
    Abstract:
    Large civil aircraft fly-by-wire flight control systems may experience a fault condition where both normal mode and direct mode control commands are output simultaneously. It is necessary to propose a method to demonstrate the airworthiness compliance of the aircraft"s aeroservoelasticity under this fault condition. Current research on the airworthiness compliance of system structural coupling under fault conditions primarily focuses on verification concepts and does not provide specific verification methods for particular faults. This paper proposes an aeroservoelastic analysis method for the mixed command fault in flight control systems. First, an equivalent assumption for the mixed control commands from the normal and direct modes is proposed, and an equivalent method is provided. Based on this assumption, the principle for aeroservoelastic analysis under mixed commands is presented. Second, an iron bird test was designed to verify the equivalent assumption for the mixed control commands. Finally, an aeroservoelastic analysis of the fault state was conducted. The study shows that, compared to the normal mode, the aeroservoelastic stability of the aircraft improves under the mixed command fault, meeting the design requirements. This analysis method can be used for the design and verification of aeroservoelasticity in aircraft fault states.
    Layered Optimization Design of Dual Three-Phase Drive Motor for eVTOL Aircraft Based on NSGA-Ⅲ
    Wang Haoyu, Li Qin, Xu Zehua, Li Kangshuai, Fu Boyu, He Jiaqi, He Qiang
    Available online:October 21, 2025, DOI:
    [Abstract] (28) [HTML] (0) [PDF 2.61 M] (9)
    Abstract:
    By optimizing the design of electric motors for electric vertical take-off and landing (eVTOL) aircraft, significant improvements can be achieved in torque density and efficiency while reducing torque ripple, thereby enhancing the application potential of eVTOL vehicles in urban air mobility and improving their performance in noise control, payload capacity, and flight safety. This paper proposes an NSGA-III-based hierarchical optimization method for a dual three-phase drive motor used in an eVTOL aircraft, focusing on six stator structural parameters. After optimization, the motor achieves a torque density of 55.5 N·m/kg and efficiency of 93.55%, representing improvements of 6.05 N·m/kg and 1.35% respectively compared to the pre-optimized design, while reducing torque ripple from 3.96% to 2.54%. The reliability of the optimized solution is verified through both simulation and experimental results.
    Experiment and simulation research on the effect of aircraft flexibility on landing load
    LIUSUIBUFU, LIUXIAOCHUAN, HUIXULONG, BAICHUNYU, LIXIAOCHENG, ZHOURUIPENG
    Available online:October 21, 2025, DOI:
    [Abstract] (28) [HTML] (0) [PDF 1.66 M] (7)
    Abstract:
    In order to research the influence of aircraft flexibility on landing load, an experiment piece of full scale aircraft simplified structure with landing gears has been designed. Meanwhile, a rigid-flex coupling full aircraft landing dynamics simulation model was established based on the theory of mode superposition.Otherwise, landing gear drop experiment and full scale aircraft drop experiment were carried out respectively. The influence of aircraft flexibility on landing load was further studied through the simulation model, which was verified through the experiment data, and the results show that the experimental method can effectively obtain a series of data such as landing gear vertical load, buffer stroke, and acceleration at the center of gravity. The landing gear dynamics model and full scale aircraft landing dynamics model have an error of less than 5% compared to the experiment, the reliability of the simulation model was verified. The influence of aircraft flexibility on landing dynamic response cannot be ignored. Considering the flexibility of the aircraft, the peak vertical ground load and acceleration at the center of gravity of the landing gear will decrease, the pulse-width of the vertical ground load and the acceleration will increase, and the landing power absorbing and buffering efficiency of the landing gear will decrease. The results provide reference for aircraft weight reduction and landing gear design.
    Numerical simulation of aerodynamic/flow field of carrier-based UAV landing in sea wind field
    GENG Yansheng, XU Xiaoping, ZHOU ZHou
    Available online:October 21, 2025, DOI:
    [Abstract] (33) [HTML] (0) [PDF 4.86 M] (5)
    Abstract:
    During the landing phase of a carrier-based fixed-wing unmanned aerial vehicle (UAV), the aircraft must traverse a highly complex aerodynamic environment characterized by the intricate wind field over the sea surface and the turbulent flow field at the ship"s stern, the latter being significantly affected by the superposition of the ship"s multi-degree-of-freedom motion. A comprehensive evaluation of these aerodynamic and flow field characteristics is essential for the development and implementation of robust control strategies to ensure the safe and precise landing of carrier-based aircraft. In this paper, the complex ship/deck flow field and unsteady aerodynamic characteristics of carrier-based unmanned aerial vehicle (UAV) landing process under sea wind field are numerically simulated. A high-fidelity simulation model of the flow field/aerodynamic during the landing process of carrier-based UAV is established, which includes sea wind field, ship motion mode, landing trajectory of carrier-based UAV and dynamic overset grid technology. The dynamic flow field of ship/deck and unsteady aerodynamic characteristics of carrier-based UAV in stationary and moving state are analyzed. The results show that: The velocity distribution in the W direction on the landing trajectory of the carrier-based aircraft is typical "Rooster Wake", and the vertical cutting velocity is very obvious; the maximum vertical velocity variation of the flow field is close to 12m/s due to the coupled motion of ship pitch/heave mode; The aerodynamic characteristics of UAV in the process of landing are strongly unsteady, and the lift coefficient shows a trend of first increasing and then decreasing.
    Structure Reliability analysis of civil aircraft based on improved Kriging based on classification enhancement strategy
    Xu Guiqiang, FENG Yunwen, CHEN Junyu, ren qizhen
    Available online:October 21, 2025, DOI:
    [Abstract] (22) [HTML] (0) [PDF 3.98 M] (5)
    Abstract:
    The reliability analysis performance of civil aircraft structures directly affects whether the corresponding functions can be realized normally. To improve the accuracy and efficiency of reliability analysis of nose wheel steering gear, an improved Kriging based on classification enhancement strategy (IK-CES) is proposed. The classification enhancement strategy aims to achieve global optimization of the design point for the failure domain through population classification and individual incentives. Improving Kriging by incorporating the indicative impact of samples on the overall functional function into the Kriging modeling mechanism, which adaptively simulates the functional relationship between input variables and output response. Taking the bending stress of the nose wheel steering gear of civil aircraft as a case study, the effectiveness of the proposed method in functional function modeling and failure probability estimation is verified by combining finite element analysis data. The case results show that the proposed IK-CES method can capture the optimal design point and minimize the indication error, improve the reliability analysis performance of the bending stress of the nose wheel steering gear of civil aircraft, and ensure the functional realization of the nose wheel steering gear of civil aircraft.
    Status of airworthiness requirements, risks and challenges for obtaining TC of person-carrying eVTOL aircraft
    Zhang Miaochan, LI Lei, SUN Zhongkei, LIANG Wei
    Available online:October 13, 2025, DOI:
    [Abstract] (64) [HTML] (0) [PDF 2.11 M] (12)
    Abstract:
    Obtaining a type certificate (TC) is a necessary prerequisite for the commercial operation of person-carrying electric vertical take-off and landing (eVTOL) aircraft, it is necessary to conduct the relevant airworthiness research for TC certification. Based on the current development status of eVTOL aircraft, this paper analyzes the applicability and key points of airworthiness requirements related to person-carrying eVTOL aircraft that have been issued by the International Civil Aviation Organization (ICAO), the European Aviation Safety Agency (EASA), the Federal Aviation Administration (FAA) of the United States, and China. The shortcomings of the existing airworthiness requirements are summarized, and suggestions for establishing and improving the airworthiness requirements are put forward. Focused on currently domestic person-carrying eVTOL aircraft’s TC certification, six aspects of risks and challenges are analyzed and countermeasures are given, with the aim of providing reference for the establishment and improvement of airworthiness requirements, and the smooth progress of TC certification for domestic eVTOL aircraft.
    Key technology and application prospects of low altitude UAV system
    li jing yao, wang bao jun, li xuan, wang zhan xi, luo zi yan
    Available online:October 13, 2025, DOI:
    [Abstract] (45) [HTML] (0) [PDF 3.15 M] (14)
    Abstract:
    UAV is the core carrier and key driving force in the low altitude economy. The UAV industry has gradually become a strategic emerging industry that takes into account the coordinated development of new productivity and industrial innovation. Based on the development status of low altitude UAV in China, this paper analyzes the current industrial scale and management classification of low altitude UAV. The main technical bottlenecks of large-scale commercial application of low altitude UAVs are analyzed. It is concluded that the industry development in the future needs to focus on three strategic technical fields, namely, UAV power energy, 5g satellite integrated communication and airspace intelligent management. Discussions are carried out around aircraft power solutions in low altitude economic environment, UAV communication and data processing technology, and low altitude airspace management and safety technology. It is proposed that these technological breakthroughs and industrial upgrading have significant synergistic effects, which can effectively enable the construction of intelligent and efficient low altitude economy industry, and is the key to unlock the huge potential of low altitude economy and ensure its safe and reliable operation.
    Research on the Influence of Assembly Gap on the Connection Strength of Composite Overlap Structures Caused by Curing Deformation
    zhuxiaolong, zhaoyumeng, wangguoyue, yanwei, wangle, songluyang, zhengxitao
    Available online:October 13, 2025, DOI:
    [Abstract] (26) [HTML] (0) [PDF 1.79 M] (16)
    Abstract:
    The assembly structure of aircraft has a large number of components, large dimensions, high precision requirements, and complex coordination processes. The solidification deformation of composite materials greatly affects the forming accuracy of structural components, resulting in assembly gaps during subsequent assembly processes, leading to significant assembly stresses and even inability to assemble properly, thereby affecting the overall structural strength and aerodynamic efficiency of the aircraft. This article proposes a "thermal coupling pre-treatment method" to study the effect of assembly gaps caused by solidification deformation on the connection strength of composite lap structures. For composite single lap structures, a porous laminated plate model is established for thermal mechanical coupling analysis, and a porous laminated plate model with solidification deformation is obtained. Based on this model, a composite single lap structure model with assembly gaps is established, and numerical simulation of tensile tests is carried out to obtain the tensile strength of composite single lap structures. The tensile strength of composite single lap structures is compared with that of composite single lap structures without solidification deformation, and the influence of solidification deformation on the mechanical connection strength of composite materials is analyzed.
    Vibration reduction of bending-torsion coupling dry friction oscillator based on two-dimensional normal load distribution
    huyanhua, tangxianju, huzhian, hanbing, zhaoxiong
    Available online:October 13, 2025, DOI:
    [Abstract] (31) [HTML] (0) [PDF 2.08 M] (11)
    Abstract:
    Attaching dry friction dampers to turbine blades can effectively reduce vibration and suppress high-cycle fatigue failure. As the design speed of engines continues to increase, dry friction damping blades may excite torsional vibration modes during service. Considering the micro-slip characteristics of interface and bending-torsional coupling vibration, in this paper, a bending-torsional coupling dry friction oscillator with a mass of finite dimensions is introduced. By modeling distributed friction force through multiple contact points and discretizing the two-dimensional dry friction interface, the dry friction contact element for analyzing the bending-torsion coupling vibration and the discrete numerical calculation method are established. Three typical normal load distributions (uniform, convex, and concave) are designed, and the steady-state vibration energy reduction rate and displacement amplitude reduction rates are introduced as evaluation criteria for overall and all directions vibration reduction effects, respectively. Combined with micro-slip contact analysis of interface, the fourth-order Runge-Kutta method is applied to solve the dynamic response of the bending-torsion coupling dry friction oscillator. The influence of key parameters on the vibration reduction characteristics of bending-torsion coupling vibration under different normal load distributions is deeply researched. Simulation results demonstrate that the proposed numerical method for the bending-torsion coupling dry friction oscillator has high computational efficiency. Among the different normal load distributions, the concave and uniform distributions have better vibration reduction effects than convex distribution. Furthermore, the vibration reduction effect of the system is significantly improved through the design of normal load distributions. The conclusions provide valuable insights for the engineering design of bending-torsion coupling dry friction damping systems.
    Data Fusion-Based Method for Reconstruction of Aerodynamic Thermal Sparse Wind Tunnel Test Data
    Wang Ze, Li Yang, Cheng Siye, Liao Menghao, Song Shufang
    Available online:October 13, 2025, DOI:
    [Abstract] (29) [HTML] (0) [PDF 3.29 M] (12)
    Abstract:
    Data-driven modeling methods have become one of the main techniques for predicting aerodynamic thermal behavior in hypersonic applications. However, due to the limitations of wind tunnel experimental conditions, the spatial distribution of aerodynamic thermal wind tunnel experiment data is often sparse, and the sample size is relatively small. This poses challenges in constructing high-performance data-driven aerodynamic thermal prediction models. To address these issues, this paper proposes a reconstruction method for sparse aerodynamic thermal wind tunnel experiment data, integrating a multi-fidelity data fusion modeling approach. First, low-fidelity simulation data for aerodynamic thermal calculations are introduced based on the sparse aerodynamic thermal wind tunnel experiment data to construct a training set for the deep neural network (DNN). Then, a weighted loss function for the DNN is designed. The weighted loss function consists of two components: the loss from the wind tunnel experimental data and the loss from the low-fidelity simulation data. Finally, the DNN is trained to obtain the reconstruction results of the sparse aerodynamic thermal wind tunnel experiment data. Aerodynamic thermal reconstruction is conducted using aerodynamic thermal sparse wind tunnel experiment data from hypersonic wind tunnels for different geometries, including double-ellipsoid, blunt-cone, bicone, and 25°/55° bicone. The results indicate that not only is the normalized root mean square error of the aerodynamic thermal reconstruction results within 9% of the wind tunnel experimental data, but the volume of the reconstructed aerodynamic thermal data is also comparable to that of the low-fidelity numerical simulation results, allowing for a detailed visualization of the aerodynamic thermal distribution in cloud plot form.
    Research on aircraft ground test methods for aircraft lighting system
    Zhang Dongmei, ZOU YUBO, HE BINBO, MA PINGSHE, GONG Liang, GAO XINGSHENG
    Available online:October 13, 2025, DOI:
    [Abstract] (41) [HTML] (0) [PDF 1.91 M] (12)
    Abstract:
    The external lighting system of the aircraft is an important system affecting the safety of the aircraft. In addition to carrying out necessary equipment qualification tests, the aircraft system usually also needs to carry out on-board ground tests of the lighting system, which is a quantitative test of the performance of the lighting lamps. In China, there are some HB and GJB documents that introduce the test content of lighting, but only put forward detailed testing requirements for the quantitative test of lighting, and do not explain the testing methods and equipment, and the actual test cannot be effectively carried out according to the testing requirements. In view of the testing requirements of the standard documents, this paper analyses the detection principle of the in-flight ground test, explains what kind of testing equipment is selected, and finally forms a complete set of in-flight ground test implementation methods and steps for the aircraft external lighting system. Taking the on-board ground test of the lighting system of a typical aircraft as an example, the test criteria and test data processing instructions are listed in detail. This paper can provide guidance for various types of aircraft to carry out on-board ground tests of lighting systems, and provide a reference for airworthiness certification tests.
    Design of Composite Wing-Battery Integrated Structure for VTOL Fixed-Wing UAVs
    Yinghui Zhao¹, Kaomin Zhang¹, Haiting Xia¹, Fenglin Tian¹, Zhenhu Miao¹, Xiaoyu Yang¹
    Available online:September 30, 2025, DOI:
    [Abstract] (35) [HTML] (0) [PDF 2.21 M] (24)
    Abstract:
    This paper focuses on a light vertical takeoff and landing fixed-wing unmanned aerial vehicle (UAV) with a maximum takeoff weight of 30kg. It addresses the layout of batteries in the UAV wings and the integrated design of wing-battery structures. A composite material wing-battery integrated structure was designed, and its load-bearing performance was analyzed through simulation to address key issues such as the transmission of forces in the structural battery in high-altitude flight environments and overall performance optimization. Utilizing ABAQUS finite element analysis software, the structure"s performance is simulated and analyzed. Post-optimization results indicate that under the load limit, the peak values of stress, strain, and deflection reduced by 8.5 MPa, 76.5με, and 0.6 mm, respectively. These represent optimization rates of 4.7%, 29.1%, and 6.3%. Furthermore, post-optimization assessments reveal a more even load distribution across the wing-battery integrated structure. The first six modal frequencies have increased, leading to enhanced overall structural Vibration resistance. Notably, there is a significant improvement in stiffness, bolstering its adaptability to the complex wind conditions encountered at high altitudes.
    Analysis of influence of wingtip spacing variation on aerodynamic of combined solar UAV
    Li Xian, ma xiaoping, Ying Pei
    Available online:September 30, 2025, DOI:
    [Abstract] (74) [HTML] (0) [PDF 3.17 M] (14)
    Abstract:
    To explore the variations of tip vortices and their influences on aerodynamic characteristics and energy consumption during the docking process of a combined solar-powered unmanned aerial vehicle (UAV), a CFD approach employing the RANS control equation and the SST k-ω turbulence model was utilized to conduct research on a type of solar-powered UAV. Through the reduction of the spanwise spacing between two solar-powered UAVs, the situation where two UAVs combine in the air through tip-linked wings was simulated. The results indicate that a pair of vortices with opposite rotational directions on the wing tips of the two solar-powered UAVs start to merge when the tip spacing is reduced to 20% of the average aerodynamic chord length, and changes occur in terms of morphology and characteristic parameters. The combined strategy of tip-linked wings enables the lift-to-drag ratio of the solar-powered UAV to increase by up to 23.5% and the power consumption during flight to decrease by up to 12.2%, demonstrating the potential for reducing the capacity requirement of energy storage batteries and enhancing the overall performance of solar-powered UAVs.
    Numerical study on the aerodynamic performance of ice ridge airfoil with dual synthetic jets actuator
    YANG Shengke, ZUO Chenglin, LIU Senyun, WANG qiao, YI Xian
    Available online:September 30, 2025, DOI:
    [Abstract] (47) [HTML] (0) [PDF 2.21 M] (16)
    Abstract:
    The ice ridge formed during the anti/de-icing or under the condition of supercooled large droplet will seriously damage the aerodynamic performance of the airfoil and affect flight safety. In order to improve the flight performance of ice ridge airfoil, the active flow control method based on dual synthetic jet was adopted. The aerodynamic performance control of NACA0012 ice ridge airfoil based on dual synthetic jet was studied through numerical simulation. The effect and mechanism of dual synthetic jet on improving the aerodynamic performance of ice ridge airfoil, and the influence of parameters such as momentum, frequency, angle and position of dual synthetic jet were explored. The results show that adding dual synthetic jet at appropriate position on the wing surface can effectively improve the lift, reduce the drag and expand the stall angle of attack. The dual synthetic jet control parameters have a significant impact on the control effect. The larger the jet momentum coefficient, the better the control effect, the optimal control effect is achieved when the dimensionless control frequency is around 0.2, the jet angle has a good control effect within the range of 30°-75°, and the control effect is best when the jet outlet is located near 0.2 times the chord length.
    Study on Cooling Performance of Ribbed Flame Tube Walls in Micro Combustor
    FU Yu, YAN Xu, YU Jnnli, LIN Han, ZUO Hongfu
    Available online:September 30, 2025, DOI:
    [Abstract] (49) [HTML] (0) [PDF 2.92 M] (18)
    Abstract:
    Micro-combustor features small size and compact layout, leading to poor heat dissipation. Applying ribbed cooling design to micro-turbojet engine combustion chambers significantly improves heat dissipation performance. A simplified model of the flame tube was established, with ribs added at different positions on flame tube walls. Three groups of ribs were arranged at varying positions to analyze the effects on airflow within combustor across an inlet velocity range of 10 m/s to 100 m/s, as well as the impact of different rib configurations on heat dissipation. Results show that adding ribs compresses airflow channels, causing acceleration in upstream sections. As airflow passes over ribs, compression effect diminishes, leading to reduced velocity. At the same inlet velocity, temperature variation in the third flame tube is greater, as ribs are closer to inlet and less affected by internal environment, providing better cooling. When ribs are positioned farther from airflow inlet, rear wall influence leads to more turbulent airflow and less stable heat dissipation. At lower airflow velocities, between 10 m/s and 60 m/s, rib cooling effect becomes more pronounced, but at higher velocities (60 m/s to 100 m/s), increased flow rate weakens cooling. These findings hold theoretical significance and practical value for ribbed heat dissipation structure design in micro-combustors.
    Study on the Influence of Structural Parameters of Fuel Bend Pipe on Natural Frequency of Aircraft Engine
    Tanghaiping, Liuziguang, Zhuniantao, Yipei
    Available online:September 30, 2025, DOI:
    [Abstract] (56) [HTML] (0) [PDF 1.56 M] (19)
    Abstract:
    In order to investigate the vibration modal characteristics of aviation fuel bend pipes, This article studies the influence of structural parameters of fuel bend pipes on the natural frequency of aircraft engines. Firstly, the modal analysis of a simple fixed support pipeline was conducted through simulation experiments. Secondly, the force hammer method is used for testing to verify the accuracy of the simulated data. Next, finite element modeling was conducted on fuel bend pipes with different external assembly parameters, and the changes in modal shapes and natural frequencies of each order were analyzed. Finally, based on the principles of dynamics, the reasons for the variation of natural frequency with assembly parameters were explained. The research results indicate that the first mode of vibration of the bent pipe is a bending deformation, with a maximum deformation of 96.63 mm, and the main vibration direction is in the Z direction; The second stage is the second bending deformation, with a maximum deformation of 78.20 mm, and the main vibration direction is in the Y direction. Radius, span, and bending radius are the main structural parameters that affect the natural frequency of bent pipes. The natural frequency is positively correlated with the radius of the pipeline and the bending radius. As the radius and bending radius increase, the stiffness of the pipeline also increases; The natural frequency is negatively correlated with the span of the pipeline, as an increase in span leads to an increase in pipeline mass and a decrease in pipeline stiffness.
    Numerical Research on Static Aeroelasticity of Highly Flexible Wing Based on CFD/CSD Coupling
    LIU Zheng, JIANG Panpan, WANG Guoliang, LI Xia
    Available online:September 23, 2025, DOI:
    [Abstract] (22) [HTML] (0) [PDF 1.45 M] (28)
    Abstract:
    High altitude long-endurance UAV uses lightweight wings, which are highly flexible. The wings are significantly different in shape before and after being loaded. It is difficult to generate the meshes and to control the meshes’ quantity. To solve these problems, this paper adopts the unstructured CFD meshes and couples the static mechanics solving program. Just in a few coupling steps, the analysis converged to the stable equilibrium state. The CFD’s meshes used in coupling have high fidelity under the wing’s stall angle, which is verified by fine meshes. When the angle of attack is small, the CFD/CSD coupling results agree with traditional panel method when taking airfoil into account. When the angle of attack increases, the CFD/CSD coupling method can simulate a certain degree of separation. What’s more, this method can count geometric nonlinearity and aerodynamic forces of curved surface. In addition, the CFD/CSD coupling method is efficient and worth promoting.
    Simulation of the Vector Jet Effect on the Aircraft Engine
    zhangjunfeng, wangtao, wangrui, caojiping
    Available online:September 23, 2025, DOI:
    [Abstract] (54) [HTML] (0) [PDF 2.12 M] (31)
    Abstract:
    Based on the NNW-FSI V1.0 software, the flow past Fifth generation fighter configuration is simulated. The flow with and without jet are all studied. Aerodynamic force coefficient, pressure distribution and flow pattern on the surface are analyzed. The deflection of the nozzle, change from the angle of attack and the vector jet effect that influence the aerodynamic characteristics of the Fifth generation fighter configuration standard model are studied. The numerical results agree well with the experimental data. The deflection of the nozzle change the lift character, the jet effect accelerates with the angle of attack.
    Study of vibration and flutter characteristics of sandwich panel with a magnetorheological fluid core in supersonic airflow
    gao ze hao, zhou jian, xu ming long
    Available online:September 23, 2025, DOI:
    [Abstract] (25) [HTML] (0) [PDF 936.41 K] (23)
    Abstract:
    Modern supersonic aircraft employ large-area skin panels to enhance aerodynamic performance and stealth characteristics. However, in complex and harsh mechanical environments, the risk of panel flutter is increasing. This paper aims to improve the flutter stability of the panels by introducing a magnetorheological fluid (MRF) sandwich structure, and to investigate its vibration and flutter characteristics in supersonic airflow. The three-node mindlin plate element (MIN3) and first-order piston theory aerodynamic force with an airflow yawed angle have been employed to establish the aeroelastic equation of three-dimensional MRF sandwich panel. Under the simply supported boundary condition, the influence of parameters such as magnetic field strength, thicknesses of MRF layer and upper and lower surface layers, and airflow yawed angle on the modal frequency and critical flutter dynamic pressure of the sandwich panel is studied by solving the eigenvalue. The results indicate that the modal frequency and flutter critical dynamic pressure of MRF sandwich panel increase with the increase of magnetic field strength. However, when the magnetic field strength increases to a certain value, they will decrease by the increase in magnetic field strength. When the magnetic field strength is constant, the modal frequency decreases with the increase of the MRF layer thickness, and increases with the increase of upper surface layer thickness. The flutter critical dynamic pressure of the panel decreases first and then increases with the increase of the MRF layer thickness, and increases with the increase of the upper surface layer thickness. When other parameters remain unchanged, the flutter critical dynamic pressure of the panel gradually decreases with the increase of the airflow yawed angle.
    Variant design and aerodynamic characteristics analysis of autonomous takeoff and landing various-speed aircraft
    Zhan Xiyu, Wei Wenyu, Li Jiarui, Wang Xinghui, Wang Zikang, Hu Haoyuan, Li Zihao, Ma Yiyuan
    Available online:September 23, 2025, DOI:
    [Abstract] (66) [HTML] (0) [PDF 3.84 M] (28)
    Abstract:
    In response to the current limitations of variable-wing designs in cross-speed regimes, which often suffer from limited aerodynamic efficiency and compromised structural integrity, this work proposes a variable-configuration solution based on an oblique-swept wing configuration with autonomous takeoff and landing capabilities. Using numerical simulation methods, the aerodynamic characteristics of three distinct configurations of the aircraft were analyzed to investigate their performance across different speed ranges. The results demonstrate that the variable-wing design achieves maximum lift-to-drag ratios of 9.1, 5.6, and 1.6 in subsonic, transonic, and hypersonic regimes, respectively, enabling high aerodynamic efficiency across a broad speed spectrum. By integrating an upper oblique-swept wing layout with a waverider-like design, the aircraft leverages shockwave control and optimized pressure distribution during transonic and supersonic phases, simultaneously enhancing lift and reducing drag, leading to significant improvements in aerodynamic performance. This configuration allows the aircraft to efficiently transition between low- and high-speed conditions, thereby meeting diverse mission requirements.
    Energy-Oriented Architecture Optimization Method for Aircraft
    Song Yi-Chuan, Qiao Fu-Xiang, Luo Yi-Ge, Zhang Wen-Qian, Zhou cheng
    Available online:September 23, 2025, DOI:
    [Abstract] (26) [HTML] (0) [PDF 1.13 M] (27)
    Abstract:
    With the emerging trend of multi-electric/ all-electric vehicles, more and more researchers are engaged in this field. However, the coupling complexity, overall energy efficiency and economic balance of multi-electric/ all-electric vehicle systems are becoming more and more important. Traditional design experience is difficult to apply in the context of new technologies, resulting in increased R D costs and extended R D cycles. In order to meet the above challenges, an energy-optimal architecture optimization method for aircraft is proposed in this paper. By defining architecture optimization process and framework, the definition logic and simplification rules of architecture optimization space are defined. Among many parameters, the energy and weight which have the greatest influence on the performance of all-electric multi-electric vehicle are selected as optimization targets, and the optimization evaluation standard system is established. Combined with multi-objective discrete intelligent optimization algorithm, the effective evaluation and optimization of system architecture are realized. Aiming at the multi-electric development of a certain aircraft, the application practice of this optimization method is carried out, which verifies its effectiveness in improving energy and optimizing system configuration, solves the limitation of traditional design concept in complex flight scenarios, and provides a basis for future research and development of multi-electric/ all-electric aircraft. It provides important theoretical support and engineering guidance
    Optimization of aircraft power system architecture and energy management strategy
    Song Xiaohui, Wang Bo, Cao Xin, Liu Feng
    Available online:September 23, 2025, DOI:
    [Abstract] (39) [HTML] (0) [PDF 2.92 M] (27)
    Abstract:
    With the development of fully electric aircraft, especially the technological advances in hybrid-electric and electric propulsion aircraft, the optimization of aircraft power system design and operation has been effectively addressed. This paper analyzes the basic concepts and research progress of aircraft power system optimization, evaluation technologies, and dynamic management control methods. It summarizes engineering design trends for power system architecture optimization, based on multi-objective optimization that considers constraints such as weight, reliability, safety, efficiency, and renewable energy characteristics. Based on cost functions related to energy efficiency and power quality, this paper explores the relationships of power flow in the aircraft. Furthermore, it compares dynamic control strategies for different microgrid architectures in aircraft. With reference to relevant literature, this paper discusses power quality and stability issues in aircraft power systems. Finally, it discusses future energy interaction optimization between aircraft microgrids and electric propulsion aircraft power systems. This paper summarizes the development trends of optimization methods for aircraft power system architecture. Considering the current status of EMS technology development and architecture optimization, it discusses the energy optimization issues of future aircraft microgrids and aircraft power systems. Based on the latest technologies in aircraft power system energy management (EMS) and architecture, it proposes a control strategy that combines EMS and PHM (Energy Management System + Health Management System) in aircraft architecture selection.
    Design and Research of Graphene-Based Rapid Heating Device for High-Pressure Gas Cylinders
    LIU Feng, WANG Bo, li xinying, han xiao, CUI Wenjing
    Available online:September 23, 2025, DOI:
    [Abstract] (43) [HTML] (0) [PDF 1.79 M] (29)
    Abstract:
    In the field of aviation and aerospace, high-altitude low temperature environments have a significant impact on the performance of high-pressure gas cylinders in aircraft-mounted pressure actuation systems. This leads to internal pressure decreases in the gas cylinders, which poses risks to the normal operation of aircraft actuator components. This study presents a novel design of a rapid heating device based on Graphene-skinned Glass Fiber (GSGF). By optimizing the three-electrode layout and innovating the design of a 3-mm aerogel thermal insulation layer, the challenges of heating efficiency and uniformity have been addressed. Based on the heat flux density calculation (power density of 0.8 W/cm2) and temperature field simulation by ANSYS Fluent, combined with the experimental verification under the -55℃ working condition, the results show that the device can heat a single gas cylinder from -55℃ to 25℃ in 6 minutes and 58 seconds, with the electro-thermal conversion efficiency reaching 94.2% and the heat loss reduced to 30 W. This scheme provides an efficient solution for the stable operation of high-pressure gas cylinders in low-temperature environments and has significant application value in aerospace and polar equipment fields.
    Optimization of Aircraft Fuel Thermal Management System Architecture Based on a Double-Layer Genetic Algorithm
    LIU Jing, ZHU Linhai, CHEN Chuang, HE Shiyu, TAN Haotian, LV Hongqing
    Available online:September 23, 2025, DOI:
    [Abstract] (25) [HTML] (0) [PDF 964.03 K] (27)
    Abstract:
    The aircraft fuel thermal management system architectures’ arrangement is complex. Traditional design methods use thermal capacity insufficiently and underutilize fuel heat sinks. This paper conducts research on the optimization of the topological architecture of aircraft fuel thermal management systems. A characterization method for fuel thermal management architectures based on the concept of equipotential points is proposed, and a depth-first search algorithm is employed to generate all possible topological architectures of the fuel thermal management system. To address the issue of excessive architectures and time-consuming exhaustive optimization, a dual-layer genetic algorithm is applied to optimize the topological graphs. Results demonstrate that compared to pure exhaustive search, the dual-layer genetic algorithm achieves an 833-fold speed increase, completing the calculation for 38,703 architectures across 6 subsystems in 1.29×103 seconds. The optimized architectures exhibit minimal average heat dissipation variance and the lowest fuel consumption for heat dissipation while maintaining high total heat absorption. This prove the method"s effectiveness.
    Intelligent flight control test of unmanned aerial vehicle based on deep reinforcement learning
    QUAN Jia-le, ZHANG Sheng, HU Wei-jun, HUANG Jiang-tao, CHENG Gang
    Available online:September 12, 2025, DOI:
    [Abstract] (93) [HTML] (0) [PDF 3.04 M] (95)
    Abstract:
    Deep Reinforcement Learning (DRL) provides a new technological paradigm for the intelligent flight control of unmanned aerial vehicles. However, confidence in the "black box" Artificial Neural Network (ANN) intelligent model is the main obstacle to practical application. To validate the neural network-based intelligent flight control model designed with DRL through flight test, a longitudinal end-to-end intelligent flight control model that maps the flight state to the elevator/thrust commands is developed for a fixed-wing scaled model aircraft, based on the multi-dimensional continuous state input and action output DRL Proximal Policy Optimization (PPO) algorithm. The robustness of ANN control model is validated through the simulation, and its engineering implementation for the sim-to-real transfer is further carried out. A flexible onboard ANN controller is developed and the model flight demonstration is launched. The test results preliminarily verify the applicability and generalization performance of the ANN controller.
    Research on the stability of helicopter ground steering motion based on bifurcation analysis method
    Wang Jiawei, Yin Qiaozhi, Sun Hao, Wang Zhongting, Wei Xiaohui, Nie Hong
    Available online:September 12, 2025, DOI:
    [Abstract] (85) [HTML] (0) [PDF 2.86 M] (93)
    Abstract:
    Due to the lack of rudder, high center of gravity, short wheelbase and other factors, heavy helicopters are prone to accidents that seriously threaten the safety of life and property such as rushing out of the runway or oversteering when taxiing on the ground. In order to obtain the stable parameter area of helicopter taxiing on the ground and improve the stability of helicopter taxiing on the ground, the bifurcation analysis method is proposed to study the stability. In this paper, a six-degree-of-freedom nonlinear dynamic model of helicopter ground taxiing is established in MATLAB/Simulink. The highly nonlinear forces such as tire force and rotor tension are introduced into the model, which can truly simulate the force of the helicopter when it is on the ground taxiing. Based on the bifurcation theory and the numerical continuation tool AUTO, the stability of the helicopter ground steering direction is studied. The single-parameter stability bifurcation analysis with the front wheel angle as the bifurcation parameter is carried out, and the influence of the front wheel angle on the stability of the helicopter ground steering direction is analysed. Combined with the factors such as helicopter tire force and yaw angle, the Hopf bifurcation phenomenon in the unstable state of the system is analysed. The results show that the essence of the helicopter ground steering instability is that the lateral friction of the tire cannot provide the centripetal force required for the helicopter ground steering.
    Prediction Model of landing load on aircraft landing gear based on multi-task learning
    yanguangyun, xuheyong, LIAN Xiaofeng, LI Rongqiang, GE Zihang
    Available online:September 12, 2025, DOI:
    [Abstract] (59) [HTML] (0) [PDF 2.33 M] (101)
    Abstract:
    Building a predictive model between flight parameters and landing load on landing gear is of great significance for the stress analysis and safety life assessment of landing gear structures, as well as predictive maintenance. This paper presents a landing gear landing load prediction model based on multi-task learning framework, using a Multi-gate Mixture of Experts (MMoE). The input features of the MMoE model were determined by Pearson correlation analysis on the flight parameter dataset, achieving accurate prediction of the landing gear landing load and comparing the performance with Single-Task model and Shared-Bottom model. The results show that the framework based on the MMoE model significantly improves the prediction ability of load data. Compared with the other two models, the MMoE model exhibits greater robustness, and the mean square error (MSE) on the test set is reduced by more than 66%.
    Research on the residual fatigue limit of damaged stainless-steel blades
    Yan Cheng, Mao Qianzhu, Tang Xiaotian, tangxianglin, anbo, liushaohua, zhangchao
    Available online:September 12, 2025, DOI:
    [Abstract] (61) [HTML] (0) [PDF 5.99 M] (95)
    Abstract:
    When aero-engine blades are subjected to foreign object impact, the resulting blade damage may lead to fatigue fractures, which pose a serious threat to the reliability and operational safety of the engine. In order to investigate the effect of metallic foreign object damage (FOD) on the fatigue performance of aircraft engine blades, a high-speed light gas gun testing system was used to accelerate 3mm-diameter steel balls to speeds of 290–310 m/s for the pre-damage testing of the blades. Subsequently, a high-cycle vibration fatigue testing system was used to study the impact of metallic foreign object damage on the residual fatigue limit of stainless-steel blades. By analyzing the influence of notch size on the fatigue limit and using the Peterson model, the fatigue limit of the damaged blades was predicted. The results show that the residual fatigue limit of the damaged blades decreases significantly with increasing damage depth and width, with the notch depth having the most pronounced effect on the fatigue limit. According to the predictions from the Peterson model, the residual fatigue limit of the damaged blades falls within 1.5 times the scatter band, and most experimental values are lower than the predicted values.
    High precision fitting method for hyperbolic annular features of intake tracts under realistic assembly
    mazheming, yangyapeng, pengyun, wangshuchun, lishuanggao, houguoyi
    Available online:September 12, 2025, DOI:
    [Abstract] (61) [HTML] (0) [PDF 5.25 M] (85)
    Abstract:
    In the digital transformation of next-generation aircraft assembly, digital-physical assembly plays a critical role. Rapid, high-precision reconstruction of key assembly features is central to accurately predicting on-site assembly outcomes. However, current methods for reconstructing complex hyperbolic ring surfaces face limitations in both accuracy and efficiency. In this study, we focus on point cloud data from the mating surface of an intake duct. First, a radius-based filter is applied to remove obvious noise points, and region-growing techniques are used to determine upper and lower thresholds for passthrough filtering, resulting in the target point cloud for reconstruction. Next, the point cloud is classified by importance, and voxel downsampling based on centroid selection is performed using grids of varying sizes according to priority. Then, segmentation is performed based on direction angle ranges determined through region growing using a normal vector threshold. Subsequently, surface fitting is conducted via rapid NURBS base surface construction and iterative optimization. Finally, the fitted annular mesh surface is merged using a zipper-based stitching approach. To validate the method, a mock intake duct and an annular metal frame were fabricated, and point cloud data of the mating surfaces were collected. Comparative experiments on fitting accuracy and efficiency demonstrated that this method, when compared to approaches in literature and commercial software, effectively reconstructs complex hyperbolic annular surfaces with high efficiency while maintaining fitting accuracy, meeting the high-fidelity requirements for intake duct fitting and assembly simulation.
    Numerical simulation of the receiver aircraft components impacted by the oil joint of the tanker aircraft
    CHEN Feiying, YU Li, CHEN Chi, LIU Lihao, ZHANG Jinhang, WANG Jiangyang, LIU Jun
    Available online:September 02, 2025, DOI:
    [Abstract] (50) [HTML] (0) [PDF 2.58 M] (100)
    Abstract:
    In the process of air refueling, the oil joint of the tanker aircraft may break away from the air refueling hose and collide with the receiver aircraft, which can lead to significant damage to the receiver aircraft components and endanger the safety. In order to ensure the anti-impact ability of the receiver aircraft components, the dynamic simulation of the collision process between different parts of the receiver aircraft and the oil joint was carried out by using a transient nonlinear impact analysis, and the effects of different impact attitudes and different impact velocities of the oil joint on the impact damage of the receiver aircraft components were studied. It was concluded that the higher the impact velocity, the more serious the damage of the receiver aircraft, and the damage degree of that is non-linear with the impact velocity. Besides, the vertical impact of the oil joint head is more destructive than that of the oil joint tail. When the oil joint head impacts the windshield or the upper wall panel vertically, the center of the leading edge is the weakest location for the vertical impact. It was also found that the stiffness matching between the structural components should be considered in the anti-impact design of the receiver aircraft.
    Very-large eddy simulation of blended methane/hydrogen jet flame
    FAN Xiaojing, CHEN Tao, HAN Xingsi, WANG Longfei
    Available online:September 02, 2025, DOI:
    [Abstract] (67) [HTML] (0) [PDF 4.02 M] (99)
    Abstract:
    As a new type of combustion, hydrogen-enriched combustion has high potential for the application of the decarbonization in power equipment. The development and assessment of high-fidelity numerical simulation methods for hydrogen-enriched combustion is of great significance for better understanding of hydrogen-enriched combustion process and the development of engineering technology. In the present study, an adaptive Very-Large Eddy Simulation method (VLES) based on the k-ε model is developed according to the scenario characteristics of methane/hydrogen blended combustion using high-speed jet. On the basis, combining the Eddy Dissipation Concept (EDC), Thickened Flame method (TF), i.e. finite rate combustion model and flamelet tabulated combustion model, a high-fidelity turbulent combustion numerical method for hydrogen-blended combustion is developed and verified in detail. Numerical simulations were carried out for two different types of classical hydrogen-enriched flames, namely the JHC hot coflow jet flame with the low reaction rate MILD combustion, and the Sydney bluff-body stabilized high-speed jet flame HM1 with high reaction rate. The simulation predictions were compared with the available experimental and numerical data. The results show that the developed VLES-EDC method can accurately predict the strong unsteady combustion process of methane/hydrogen blended flames, and the prediction results of velocity, temperature, etc., under the two types of combustion conditions have satisfactory accuracy. For the hydrogen enriched combustion, compared with the finite-rate turbulent combustion model, the prediction accuracy of the flamelet combustion model is reduced, and the prediction accuracy under different combustion scenarios needs to be verified accordingly.
    Numerical Simulation Study on Flow and Heat Transfer Characteristics of RP-3 Aviation Kerosene in a Dimple-type U-tube
    Deng Zhibin, Xu Ziyang, Zhao Liang, Liu Xiang, Zhang Tianlai, Chen Yonggang, Li Shilin
    Available online:September 02, 2025, DOI:
    [Abstract] (37) [HTML] (0) [PDF 4.94 M] (96)
    Abstract:
    To enhance convective heat transfer in the U-tube through surface structure optimization, this study proposes an improved heat transfer design for aviation kerosene air-oil heat exchangers using a dimple-structured U-tube. Numerical simulations were conducted to systematically analyze the coupled flow and heat transfer mechanisms of RP-3 aviation kerosene under high-pressure (3–5 MPa) and high-heat-flux (500–800 kW/m2) conditions. The results demonstrate that the combined effects of dimple structures and centrifugal forces in the bend region induce adverse pressure gradients and promote secondary flows in the boundary layer, significantly amplifying turbulent kinetic energy and generating unique vortex structures distinct from conventional Dean vortices. These dimple-induced vortices propagate toward the tube core, enhancing heat transfer performance. The U-bend section achieves Nusselt numbers 2.4–3.0 times higher than those of straight tubes, with a performance evaluation criterion (PEC) of 1.96–2.71. Notably, increasing operating pressure/heat flux or reducing flow rate further improved PEC values, highlighting the superiority of the dimple-type U-tube in convective heat transfer enhancement through synergistic structural and flow effects.
    Design of a Tethered Balloon Simulation Training System Based on a Spherical Scale Model
    tao wei, JIANG Yanlong, LIU Zongqiang
    Available online:September 02, 2025, DOI:
    [Abstract] (78) [HTML] (0) [PDF 1.63 M] (96)
    Abstract:
    As an emerging complex equipment, tethered balloons feature intricate operation procedures and are highly influenced by environmental factors. Improper operation may affect the safety of products or personnel, and professional trained personnel are required to operate them. Direct training and training of physical equipment will affect the normal use of equipment, shorten the service life of equipment, cost a lot of money and have safety risks. Therefore, it is imperative to employ a simulation training system first, allowing trainees to acquire a solid foundation in theoretical knowledge and operational skills before proceeding to hands-on training with the actual equipment. This paper integrates the operational requirements and functional components of tethered balloons to design and develop a tethered balloon simulation training system. This system adopts a combined approach of scaled-down physical models and software. The scaled-down physical models encompass the balloon structure, telemetry and control subsystem, and launch-and-recovery subsystem. The software component comprises modules for balloon status monitoring, theoretical teaching, and equipment maintenance, supported by computer and network equipment. Through testing and application, the system has achieved simulations of balloon platform operations, launch-and-recovery procedures, status monitoring, and networking-based teaching. It also facilitates effective performance evaluation. The tethered balloon simulation training system, applied to both theoretical and practical training, can conserve training resources, enhance training efficiency, and mitigate training risks.
    Review on Failure Analysis and Reliability Assessment of Aviation Wire and Cable
    Guo Junhui, Zhang Xingyuan, Chen Zhixiong, Zhang Huyi
    Available online:August 22, 2025, DOI:
    [Abstract] (49) [HTML] (0) [PDF 883.93 K] (109)
    Abstract:
    Electrical wires and cables, as critical foundational components of aircraft, are extensively distributed throughout the entire structure of the aircraft. Aviation electrical wires and cables serve as the conduits for energy, data, and signal transmission within aerospace electrical systems. Due to their wide deployment and significant proportion, any failure that occurs can result in substantial losses. Consequently, there are heightened requirements for the reliability of aviation electrical wires and cables. The paper begins by introducing the composition of the Electrical Wiring Interconnection System (EWIS) and analyzing its failure mechanisms. It subsequently discusses the typical failure modes and failure mechanisms of aviation electrical wires and cables during their operational life. Finally, it reviews the research status of reliability assessment for electric wires and cables, and summarizes the commonly used fault detection and life prediction methods for them. By summarizing advancements in the research on electrical wires and cables, this paper aims to provide valuable insights for the development of aviation electrical wires and cables in China.
    Study on Surface Morphology of Light Alloy Based on External Cylindrical Turning Mechanism
    WangFulin, YangXiao, TangNengyi, TangDianya
    Available online:August 22, 2025, DOI:
    [Abstract] (89) [HTML] (0) [PDF 16.82 M] (119)
    Abstract:
    The construction of the prediction model of light alloy turning surface morphology is of great significance for the optimization of turning parameters and the improvement of part surface quality. Based on the mechanism of cylindrical turning, the simulation model of workpiece surface topography is established considering the influence of tool geometry, machine vibration and cutting elastoplastic deformation.Cutting experiments were conducted to verify and compare the surface morphology obtained from simulation and experiments.The trend of peak height variation tended to be consistent under different cutting parameters;Three-dimensional surface roughness arithmetic mean height Sa and root mean square height Sq are used to characterize the surface topography. The average relative error of Sa is 3.95% and the average relative error of Sq is 8.34%,,indicating that the model is accurate and has good prediction effect, and can reflect the surface quality of the workpiece.Finally, with cutting efficiency and surface roughness as optimization objectives,the cutting parameters were optimized using Non-Dominated Sorting Genetic Algorithm II (NSGA-II), and the non-dominated solution set of cutting parameters was obtained for reference by decision makers.
    Analysis and verification of fire resistance of non-metal fuel water drain valve of aircraft
    LvHongzheng, WangYong
    Available online:August 22, 2025, DOI:
    [Abstract] (65) [HTML] (0) [PDF 4.72 M] (101)
    Abstract:
    Non-metal fuel water drain valve installed on the outer surface of the aluminum wing tank near the nacle of the aircraft engine shall meet the fire resistance requirements in accordance with the provisions of the Airworthiness standards. The transient thermal analysis of the valve with different body thicknesses is carried out. The influence of the thickness of the valve body on the combustion heat transfer and fuel seal is analyzed, and the results are verified by experiments. The results show that when the valve body is thickened to at least 13mm, the valve begins to have fire resistance, that is, in the case of high temperature flame combustion, it can neither fuel leakage nor overtemperature in the fuel tank.
    Flight Simulation Assisted Validation Method for Automatic Objective Test of Flight Simulator
    tongyu, wuzhao, guijingran, lubei, xujing
    Available online:August 22, 2025, DOI:
    [Abstract] (60) [HTML] (0) [PDF 2.28 M] (120)
    Abstract:
    After the completion of flight dynamics modeling, due to the impact of flight test data error and modeling error, the comparison results between automatic objective test simulation data and flight test data are often difficult to fully meet the requirements of simulator evaluation regulations. In order to further improve the test and verification results, the subjects in the airworthiness certification regulations are classified into three categories according to the flight dynamics characteristics of maneover and the purpose of the investigation of the subjects. Secondly, for the subjects that need to adopt assisted validation, the assisted validation strategy of test subjects is developed. Then, based on the formed strategy, a P-I-D assisted validation system is established. Finally, a flight simulation assisted validation method for automatic objective test of flight simulator is established. Through a flight simulation example of a civil aircraft, the effectiveness of the assisted validation method is compared and verified. The results show that the assisted validation method can effectively improve the test validation effect of simulation data and flight test data, and help meet the tolerance requirements of airworthiness regulations.
    Study on the Impact of Test Loading on the Sudden Extension Performance of Dual-Chamber Buffers
    cuipanli, Northwestern Polytechnical University, Luxuefeng, yangzhengquan, wangbinwen
    Available online:August 22, 2025, DOI:
    [Abstract] (39) [HTML] (0) [PDF 1.89 M] (111)
    Abstract:
    Carrier-based aircraft usually increase the take-off angle of attack by extending the nose landing gear suddenly at the end of the stroke during catapult take-off. The measurement of the sudden extension performance of landing gear is of great significance for the development of the model. A test scheme for the sudden extension of landing gear with double-chamber cushioning device has been designed. The nose landing gear of a certain type of aircraft has been analyzed and verified. By changing the test loading conditions, the influence of different loading conditions on the sudden extension performance of landing gear has been analyzed. The test results show that for the double-chamber landing gear, the temperature in the high-pressure chamber changes dramatically before and after the sudden extension, while the low-pressure chamber hardly changes. And the holding time after loading has a greater impact on the sudden extension performance of the cushioning device than the loading rate, which should be considered in ground verification tests.
    Review of vibration fatigue life analysis methods with mean stress
    limengnan, Yao Weixing
    Available online:August 08, 2025, DOI:
    [Abstract] (87) [HTML] (0) [PDF 916.69 K] (113)
    Abstract:
    Vibration fatigue with mean stress is widely used in various engineering structures, while researchers have different solving methods. In order to compare and discuss the applicability of these methods, literature on fatigue life evaluation with mean stress was reviewed and summarized in recent decades, and the treatment methods were divided into two categories: (1) The influence of mean stress is considered in the S-N curve of the material; (2) Directly calculate the fatigue damage of different mean stress and vibration load. Discussed the test principle and application of each test method, as well as the model basis and further development of each theory method respectively. Evaluated these methods from the aspects of theoretical basis, calculation effect, engineering application range, etc., then the shortcomings of existing research are pointed out, and the development direction of related research in the future is prospected .
    Wind Tunnel Test Study On The Influence Of Slat End Size Changes In Transport Aircraft
    Yan Wei, Xu Hui Wen, Li jing ye, zhang zi yang, zhangmeihong, zhaokeliang, yangkai, yanwencheng
    Available online:August 08, 2025, DOI:
    [Abstract] (69) [HTML] (0) [PDF 6.01 M] (120)
    Abstract:
    For conventional layout civil transport aircraft in a low-speed and high lift configuration, the advance of the stall angle of attack causes the aircraft"s approach speed to be too high. It is necessary to optimize the low-speed characteristics of the high-lift configuration and control the flow separation in the inner wing area of the aircraft wing. The aerodynamic study on the changes in the end face size of the inner slat was carried out through conventional force measurement wind tunnel tests and fluorescent oil flow wind tunnel tests. Under the conditions of the optimal solution, the lift coefficient has been significantly improved, and the pitching moment coefficient still meets the requirements of the classic criterion after aerodynamic optimization, meanwhile, the flow mechanism of flow separation controlled by the extension of the inner slat end face is explained, that is, the airflow passing between the extension part and the main wing can inject high-energy flow into the main wing surface boundary layer near the root of the downstream wing, enhancing the resistance to the ability to withstand adverse pressure gradients and delays local flow separation.
    The Mechanism and Effect of Pump Case Return Oil on the Temperature of Aircraft Piston Pump
    SHI Hongyu, WANG Xiaowei, KONG Ziqi, YAN Feiyun, WANG Zhanxi
    Available online:August 08, 2025, DOI:
    [Abstract] (68) [HTML] (0) [PDF 930.32 K] (107)
    Abstract:
    Aircraft piston pumps generate a significant amount of heat due to reasons such as leakage flow and mechanical friction, which often leads to overheating failures. The piston pump dissipates heat through the casing return oil, and the flow rate of the casing return oil not only determines the working efficiency of the piston pump but also affects its temperature characteristics. Based on the analysis of the heat generation mechanism and heat transfer process of the piston pump, a temperature characteristic model of a constant pressure variable displacement piston pump is established and simulated using hydraulic simulation analysis software. The temperature variation of piston pump under different volumetric and mechanical efficiencies in typical working conditions are obtained. Analysis of the temperature variation trends reveals that in the early stages of the piston pump"s operation, the lower the volumetric efficiency, the more pronounced the temperature rise of the pump itself and the casing return oil. After the piston pump has been working for a while, the lower the volumetric efficiency, the greater the casing return oil flow, and the more obvious the heat dissipation effect of the casing return oil. It is also found that as the mechanical efficiency of the piston pump decreases, the heat generation of the system increases significantly, leading to a substantial rise in the temperature of the pump casing and the casing return oil. In the actual operation of the aircraft piston pump, it is necessary to consider the issue of overheating failure of the piston pump caused by wear and other reasons leading to a decrease in mechanical efficiency.
    Analysis of Partial Structural Parameters Affecting the Performance of Aviation Priority Valves
    SHI Hongyu, KONG Ziqi, YAN Feiyun, WANG Xiaowei, WANG Zhanxi
    Available online:August 08, 2025, DOI:
    [Abstract] (82) [HTML] (0) [PDF 1.61 M] (110)
    Abstract:
    The aircraft hydraulic system plays a crucial role in controlling the movement and stability of various aircraft components. In actual use, it often encounters complex hydraulic variations. The priority valve, a type of sequential valve widely used in aircraft hydraulic systems, ensures that hydraulic pressure is prioritized for critical flight control systems when a sudden pressure drop occurs due to an increased demand for flow at the load end. The performance of the priority valve in supplementing pressure to downstream systems can be evaluated based on the outlet pressure image and the valve spool displacement vibration image. To ensure the safety and practicality of the priority valve during operation, it is necessary to study the structural parameters that affect its performance.This article first analyzes the working process of a certain type of priority valve and the causes of vibration, identifying the structural parameters that may affect its performance. Next, using hydraulic fluid simulation methods, the existing design of the priority valve is optimized, focusing primarily on the mass of the valve spool and the area of hydraulic force. By altering certain structural parameters affecting these aspects, the study analyzes the dynamic performance under the same operating conditions, examining how these changes influence the dynamic working performance of the priority valve. The results indicate that reducing the main valve spool mass decreases the amplitude of the spool during the pressure compensation phase. A smaller main valve seat orifice diameter leads to higher pressure at the load end, better pressure compensation performance, and reduced vibration amplitude. Additionally, increasing the mass of the main valve seat can reduce the amplitude of the spool during the pressure compensation phase.
    Analysis and Research on Airworthiness Certification Technology for Helicopter Aeromedical Rescue System
    shikaiwen, lixiaoxue
    Available online:August 08, 2025, DOI:
    [Abstract] (56) [HTML] (0) [PDF 733.32 K] (120)
    Abstract:
    The aeromedical rescue system is a necessary equipment for helicopter medical rescue, and retrofitting the medical rescue system will directly affect the safe operation of the aircraft, requiring strict airworthiness certification procedures. Airworthiness is the minimum safety requirement for the development of aeromedical rescue systems. The medical equipment industry generally lacks full process airworthiness experience, which seriously hinders the development of domestic aeromedical equipment industry. Starting from the basic composition and installation requirements of aeromedical rescue systems, this article introduces the classic configuration, functional requirements, and airworthiness test requirements of aeromedical rescue systems. Based on the corresponding provisions of Part 29 R2 "Airworthiness Regulations for Transport Rotorcraft" of the CCAR, the acceptable compliance methods of aeromedical rescue systems and the acceptable criteria in verification tests are analyzed. In addition to passing the medical equipment standard performance test, aeromedical rescue equipment also needs to undergo environmental testing in accordance with requirements, with a focus on testing the electromagnetic compatibility during the charging and discharging process of defibrillation equipment. During airworthiness certification, the Civil Aviation Administration of China should invite medical equipment experts to provide professional advice and judgments to assess whether it meets airworthiness requirements.
    Review of research on the combat operations of airborne laser weapon systems
    LI XIAOCHEN, GE YUXUE, PEI YANG, SHI AIMING, Gu YUNCHEN, CAO LUGUANG
    Available online:July 29, 2025, DOI:
    [Abstract] (82) [HTML] (0) [PDF 6.36 M] (133)
    Abstract:
    Airborne laser weapons, mounted on aircraft, hold significant potential within the military domain. In the context of information warfare, integrating airborne laser weapons into complex combat systems can effectively address the limitations of traditional weaponry, significantly enhancing both the combat capability and survivability of these systems. This paper reviews the historical development and current state of airborne laser weapon research, providing an analysis and summary of key aspects related to the collaborative combat systems in which these weapons operate. Specifically, it focuses on the assessment of damage inflicted by airborne laser weapons, target allocation strategies, combat system modeling, and system effectiveness evaluation techniques. Additionally, considering the systematic and intelligent nature of modern combat environments, this paper outlines future research directions for advancing key technologies in collaborative combat systems involving airborne laser weapons. The goal is to offer insights that may guide the optimization of airborne laser weapon resource allocation and improve the overall effectiveness of combat systems.
    Effect of heat and surface treatment on mechanical properties of 300M steel for civil main landing gear fuse-pin
    fuliang, LI Tiannan, TAN Zihao, HUANG Shaofan, XIAO Xijun, FENG Kangtun, MENG Qinghe
    Available online:July 29, 2025, DOI:
    [Abstract] (96) [HTML] (0) [PDF 5.83 M] (118)
    Abstract:
    The control of accuracy breakaway load for emergency fuse-pin of civil aircraft main landing gear is crucial for mechanical design of fuse-pin. To propose requirements for heat and surface treatment process of fuse-pin and explore the mechanical property design index of fuse-pin material, a series of experiments were conducted to study the influence of tempering temperature (300°C、350°C和400°C) and surface treatments (shot peening, chromium plating and high-velocity oxygen-fuel) on microstructure and mechanical properties of 300M steel. The results reveal that the microstructure of 300M steel mainly consists of tempered martensite and bainite by tempering treatment of 300°C and 350°C, exhibiting the ductile fracture property, which ensuring the comprehensive mechanical properties. Moreover, due to the higher yield ratio(0.87) and better impact strength by 350°C tempering temperature, the breakaway load can be accurately controlled. All surface treatments are not change the microstructure and reduce the structural size of specimens, resulting in lower tensile force. Compared to shot peening and chromium plating, tensile force of specimen with HVOF treatment is the lowest because higher temperature of WC-10Co4Cr power melt the specimen surface and reduced its local size.
    Research on Low Noise Departure Trajectory Planning Based on Improved Dynamic Window Method
    Chengqing, PENG Yuanming
    Available online:July 29, 2025, DOI:
    [Abstract] (43) [HTML] (0) [PDF 884.80 K] (111)
    Abstract:
    With the rapid development of civil aviation industry, green aviation has gradually become the focus of people"s attention. Taking into account factors such as aircraft performance, noise impact, and atmospheric environment in the terminal area, an optimization plan for aircraft departure trajectory has been proposed. Aiming at the problem that traditional Dynamic Window Approach (DWA) cannot effectively solve in aircraft departure trajectory planning, an improved Dynamic Window Approach combined with aircraft performance is proposed. Construct aircraft departure performance constraints based on the requirements of Base of Aircraft Data (BADA) and Continuous Climb Operations (CCO). At the same time, considering the noise impact of aircraft departure, the smaller the noise impact, the better the trajectory. Secondly, under the same research environment, analyze the methods with different index weights based on the duration and area of influence, and select the methods with the smallest comprehensive impact. Finally, based on the selected method, analyze the performance parameters such as thrust, speed, and path angle of the departing aircraft. The simulation experiment results show that the trajectory under the improved dynamic window method can meet the requirements of aircraft departure performance.
    Research on Integrated Calculation of Full-Flight Takeoff Obstacle Clearance Based on Level-Off Strategies
    wangke, qiuyang, xiajun, linxihao
    Available online:July 29, 2025, DOI:
    [Abstract] (39) [HTML] (0) [PDF 1.65 M] (121)
    Abstract:
    Existing aircraft performance software can determine obstacle weight limits when analyzing takeoff clearance. However, when it comes to clearing obstacles during the fourth segment, manual decision-making is required for a reasonable evaluation of the obstacle weight limit. Grounded in a comprehensive analysis of the intentions behind CCAR25 regulatory clauses, this paper proposes a precise simulation algorithm for gross and net takeoff flight paths and establishes a comprehensive model covering key constraints for full-segment obstacle clearance assessment. This model achieves an integrated calculation of obstacle clearance analysis through different level-off height strategies. Compared to traditional obstacle-clearance models, the simulation results demonstrate a possible enhancement of obstacle-limited takeoff weights by up to 24% in this model"s assessments. This research provides more reliable support for the efficient and safe operation of domestic civil aircraft.
    Study of calculating stability derivative
    yizichao, su yan
    Available online:July 29, 2025, DOI:
    [Abstract] (80) [HTML] (0) [PDF 1.31 M] (114)
    Abstract:
    Aviation safety is a global focus, and as the aviation system becomes increasingly complex, it becomes particularly important to conduct systematic risk analysis. This paper combines the HAZOP method with the WSR methodology to comprehensively identify critical risk nodes in aviation safety. By constructing a complex network model based on real-life case studies, the dynamic transmission process of risk elements in the aviation network is simulated. The risk grade and transmission probability were determined according to the difference of risks, and the transmission probability among different risks was differentiated based on the risk grade, so as to improve the susceptible-infection-susceptible (SIS) model and quantify the dynamic characteristics of risk transmission. Finally, through the analysis of 47 aviation cases, taking bird strikes as the scenario, the most likely to cause 10 high-risk nodes and their risk transmission chain are identified. The study shows that, compared with traditional SIS models, the risk quantitative analysis using the improved SIS model can more sensitively identify risks, providing reference for effective management of aviation safety.
    Comprehensive analysis and optimization for conceptual design of hydrogen-powered turbofan aircraft
    CHEN Zichu, YU Xiongqing
    Available online:July 22, 2025, DOI:
    [Abstract] (48) [HTML] (0) [PDF 3.01 M] (117)
    Abstract:
    Hydrogen-powered turbofan aircraft is powered by the direct combustion of hydrogen in the turbofan engine, which is an important development direction of green aviation. Aiming at the concept design of hydrogen-powered turbofan aircraft, a comprehensive analysis and optimization method is studied. According to the characteristics of hydrogen-powered turbofan aircraft, the liquid hydrogen system model is established based on physical principles, and the discipline analysis methods of conventional aircraft are updated and expanded. A multidisciplinary analysis method is developed, which consists of engine, liquid hydrogen system, geometry, weight, aerodynamic, performance, emission and cost modules. Based on the multidisciplinary analysis method, the primary parameters of the 150-class hydrogen turbofan aircraft concept are optimized, and the effects of the parameters of the liquid hydrogen tank on the aircraft weight and cost are investigated. The results show that the operating empty weight of the optimized aircraft is reduced by 1.63% and the direct operating cost is reduced by 1.79%. The shape of the liquid hydrogen storage tank and the characteristics of the insulation material have significant impacts on the aircraft weight and direct operating cost. The method presented in this paper can be effectively applied to the conceptual design of hydrogen-powered turbofan aircraft.
    Landing Response Suppression Technology for Large Flexible Aircraft
    KONG Fanzhuo, ZHANG Ming, RUAN Shuang, TAN Chong, GUI Xiwen
    Available online:July 22, 2025, DOI:
    [Abstract] (75) [HTML] (0) [PDF 1.82 M] (141)
    Abstract:
    Modern large airliners and high-altitude unmanned aerial vehicles predominantly utilize high aspect ratio wings. Aircraft equipped with high aspect ratio wings can effectively reduce energy consumption; however, due to their structural characteristics, they experience considerable deformation under the influence of gravity and aerodynamic force. In order to investigate the landing response characteristics of a large flexible aircraft, a comprehensive landing dynamics model was developed, taking into account the flexibility of the airframe. This model was based on a high aspect ratio UAV as a reference sample and was integrated with a finite element model of the airframe. The analysis focused on the effects of the elastic modes and the initial attitude angle of the airframe on the landing loads and the dynamic response of the wings. Utilizing the response surface method, a surrogate model was created to optimize the parameters of the landing gear buffers. The results indicate that for large flexible aircraft, increasing the design travel of the landing gear buffers is beneficial in reducing both the landing loads and the dynamic response of the wings.
    A smooth algorithm for endomorphic surfaces in thermal protection systems
    wei biao, Wang Zhijin
    Available online:July 22, 2025, DOI:
    [Abstract] (74) [HTML] (0) [PDF 3.45 M] (115)
    Abstract:
    The re-entry vehicle will experience severe heat flow loads during its return to the atmosphere, requiring the design of an insulated tile-type thermal protection system for the vehicle. Due to the differences in the heat flow density distribution on the surface of the vehicle, a step in the thickness of the designed thermal protection system occurs, resulting in a poorly shaped internal surface of the thermal protection system, which is not smooth.The article proposes a smoothing algorithm for the endomorphic surface, which takes the position of the endomorphic surface type value points of the thermal protection system as the optimization object to smoothen the endomorphic surface, and fits the smoothened double-three times B-spline surface according to the coordinates of the processed endomorphic surface type value points, and the folding inflection angle of each node of the endomorphic surface is reduced to less than 10° which solves the thickness step problem of the thermal protection system, and the method is an effective smoothing algorithm.
    Research on the ACMP Starting Problem of RAT for Civil Aircraft
    HONG Ye, Wang Bangting, Ma Ying, Wei Peikun, Pu Chennan, Wang Fei
    Available online:July 22, 2025, DOI:
    [Abstract] (58) [HTML] (0) [PDF 3.39 M] (124)
    Abstract:
    This article studies the AC Motor Pump ACMP Starting Process with Ram Air Turbine RAT. The power generation capacity of RAT is affected by multiple factors such as temperature, airspeed, and altitude, while the ACMP is affected by the input frequency of the motor and the temperature of the hydraulic oil. These multiple factors make the analysis of the starting process very complex, and previous researchers have not conducted direct research on this. This article combines experiments with simulations and uses simulation models to calibrate the test results. During the calibration process, key parameters such as peak current and starting time errors are all within 5%, indicating that the model can demonstrate the starting process of the RAT starting ACMP. This article analyzes the most severe working conditions of the stamping air turbine starting ACMP and simulates the most severe work during the starting process. The simulation accuracy is controlled within 5%. A model for analyzing RAT starting ACMP in harsh scenarios is established, which can be used for subsequent design optimization of aircraft and detailed design of similar models.
    Research on Model-Based Multi-Dimension Aircraft Reliability Requirement Capture and Decomposition
    LUO Tiansu, TIAN Keyuan, LU Yingbo, WANG Min, QIAN Xiaochao
    Available online:July 22, 2025, DOI:
    [Abstract] (52) [HTML] (0) [PDF 2.77 M] (120)
    Abstract:
    In the aircraft design process, requirement capture is a key step to ensure that the product design meets stakeholders" expectations. In order to ensure the completeness of reliability requirements capture and the accuracy of requirements decomposition, firstly, multi-dimensional capture and decomposition of civil aircraft reliability requirements will be carried out from the scenario dimension and the stakeholder dimension. Secondly, combined with the MBSE process, the accuracy and completeness of civil aircraft reliability requirements capture and validation will be realized through the stakeholders identification, reliability requirements capture-validation-modeling, and reliability requirements decomposition- verification-modeling. Finally, using a typical civil aircraft system as a case study, the model-based civil aircraft reliability requirements capture and decomposition technology completes the scenario-based and stakeholder-based reliability requirements capture, modeling and validation. Besides, obtaining a typical system stakeholder reliability requirements MBSE model, which provides the requirements for the whole life cycle of the civil aircraft based on the MBSE reliability design process input. This research provides MBSE methods and solutions for system engineers involved in requirement capture and decomposition of civil aircraft.
    A new type of six-rotor and its attitude active disturbance rejection
    liyaoqiang, xujinfa
    Available online:July 14, 2025, DOI:
    [Abstract] (71) [HTML] (0) [PDF 2.64 M] (137)
    Abstract:
    Based on the traditional four-rotor configuration, the new six-rotor adds two main thrust propellers, which can fly forward quickly without changing the pitch Angle and realize yaw quickly. This paper designs an attitude control system based on a new type of six-rotor. The uncertainty of external interference during UAV flight brings great challenges to the design and verification of flight control system. The flight dynamics model of a new six-rotor UAV is established, the Control strategy is designed, and the attitude controller is designed using the Active Disturbance Rejection Control (ADRC). Through the attitude control simulation, the effect of the active disturbance rejection controller is superior to the PID controller. Particle Swarm Optimization (PSO) was used to optimize some parameters of the active disturbance rejection controller, and the control effect of PSO-ADRC was better than that of ADRC. The results show that the attitude ADRC controller has better anti-interference and robustness, which can ensure the fast and stable flight of the six-rotor UAV. Particle swarm optimization (PSO) further enhances the control effect of ADRC controller.
    Influence of permeability characteristics on the aerodynamic characteristics of airfoils
    lifukun, haolishu, BAO Haiwei, GAO Yongwei
    Available online:July 14, 2025, DOI:
    [Abstract] (59) [HTML] (0) [PDF 1.71 M] (131)
    Abstract:
    Porous media materials, due to their unique pore structure, can be used to simulate the permeability characteristics of bird wing feathers. This article takes the NACA0012 airfoil as the research object, covers the surface of the airfoil with porous materials to simulate bird wing feathers, applies the theory of porous media, and explores the influence of permeability parameters on the aerodynamic characteristics of the airfoil through CFD method.The results show that: 1) The semi covered porous airfoil can significantly improve the aerodynamic performance of the airfoil, especially the stall characteristics of the airfoil. The stall angle of attack increases by 2°, and the maximum lift coefficient increases by 16.2%; 2) The permeability characteristic parameters Darcy""s number and porosity have a significant impact on the aerodynamic characteristics of the airfoil. The aerodynamic performance of the airfoil deteriorates with the increase of Darcy""s number and improves with the increase of porosity; 3) Anisotropy has a significant impact on the aerodynamic characteristics of airfoils, among which the anisotropic porous airfoil with high permeability in the y-direction has the best aerodynamic characteristics, which is consistent with the bird wing feather structure. The surface covered porous medium airfoil scheme and its research conclusions adopted in this article can provide a reference for the design and research of bionic airfoil.
    Analysis of 3-D Conversion Corridor and Establishment of Transition Path for Tilting Quadcopter Aircraft
    ZHOUXianqi, XUJinfa
    Available online:July 14, 2025, DOI:
    [Abstract] (43) [HTML] (0) [PDF 2.95 M] (131)
    Abstract:
    Designing a suitable rotor tilt path in the tilt transition corridor is one of the key steps in the flight dynamics analysis and flight control of tilt rotor aircraft. In response to the above application background,this article establishes a flight dynamics model of a tilting quadcopter aircraft, and determines the 3-D conversion corridor of the forward flight velocity tilt angle acceleration of the tilting quadcopter aircraft through triming calculations. The characteristics of the conversion corridor boundary under different accelerations are analyzed. Comprehensive performance indicators involving flight attitude, total distance, and required power factors have been defined. The A * algorithm was used to search for the optimal conversion path of a tiltrotor quadcopter aircraft with the goal of minimizing the overall performance indicators. The research results indicate that 3-D conversion corridor can provide more information for tilting conversion and provide theoretical basis for determining conversion paths; The A * algorithm optimizes the 3-D conversion path search, which is beneficial for the safe and stable completion of tilt transition flight.
    Calculation Model of Aircraft Attitude Transformation Parameters Based on Multi-objective Optimization
    ZHOU CHAGNCHUN, raoxiaohao, CHEN CHANG
    Available online:July 14, 2025, DOI:
    [Abstract] (51) [HTML] (0) [PDF 917.37 K] (144)
    Abstract:
    In aircraft assembly, due to measurement errors, manufacturing errors,and coordinate conversion errors, the assembly accuracy and quality of components do not meet the requirements, and the assembly gap is unevenly distributed. In order to make the assembly clearance distribution as uniform as possible and the assembly quality meet the requirements, the optimal pose transformation parameters are calculated in advance before the assembly of the components. On the premise of ensuring that all the attitude adjustment datum points meet the tolerance requirements, the coordinate error of the target position of all the attitude adjustment datum points and their theoretical positions, as well as the characteristics of the mating surface (angle and clearance) of the mating plane, are optimized, and the optimal pose transformation parameters are solved by the multi-objective particle swarm optimization algorithm, and finally the virtual assembly is carried out in PolyWorks to complete the verification.
    Development, technical characteristics and market analysis oflarge-scale cargo UAVs in China
    WANG Changzhou, LIU Fuhu
    Available online:July 02, 2025, DOI:
    [Abstract] (116) [HTML] (0) [PDF 4.95 M] (162)
    Abstract:
    Large-scale civilian cargo UAVs refer to transport aircraft which can carry heavier and larger cargo and have longer flight times and ranges. They are usually used in fields such as cargo transportation, and material support, and can provide fast, safe, convenient, low-cost freight transportation services. In this paper, the development of large civilian cargo UAVs which have a payload of more than 100kg in our country are reviewed in the past 10 years, and the technical characteristics of those UAVs that have completed their maiden flights is analyzed. Besides, the scene application and market trend of large-scale cargo UAVs are emphatically analyzed. At the same time, the research and development of large-scale civilian cargo UAV in China requires strengthening infrastructure construction, strengthening ecological construction of the industry system, the continuous breakthroughs of key technologies and providing customized solution.
    Comparative analysis on aerodynamic characteristics of the UAV with different tails under propeller slipstream
    Zhao Caixia, Dong Wenhui, Fan Kejing, Zhao Zhixiao
    Available online:July 02, 2025, DOI:
    [Abstract] (71) [HTML] (0) [PDF 2.12 M] (128)
    Abstract:
    The tails often placed behind the propeller of the long endurance twin-boom UAV. In this case, the propeller slipstream will affect the aerodynamic characteristics. Based on the twin-boom UAV with inverted U-tail and inverted V-tail, Comparative analysis on the lift-drag characteristic and longitudinal static stability of two type UAV under propeller slipstream by numerical calculation method. The results show that when the longitudinal static stability of inverted U-tail/inverted V-tail UAV is similar, the tail capacity of inverted V-tail UAV is larger. The maximum increase of inverted U-tail UAV’s drag coefficient is 36.67%, the maximum increase of inverted V-tail UAV’s drag coefficient is 35.12%, the lift-drag ratio of inverted U-tail UAV is reduced by 4.14, The lift-drag ratio of inverted V-tail UAV is reduced by 4.32 under propeller slipstream, The effect of two type UAV’s lift-drag characteristic under propeller slipstream are basically same. The longitudinal static stability of inverted U-tail UAV is decreases by 2.09%, The inverted V-tail UAV is decreases by 0.99% under propeller slipstream. The longitudinal static stability of two type UAV become worse under propeller slipstream, And the inverted U-tail UAV becomes worse seriously. It provides reference for the design of the long endurance UAV’s tail with two-boom.
    Research on Flight Simulation Repositioning Algorithm and Its Application
    WuYuanhang, ZhangQiang, ShenCe
    Available online:July 02, 2025, DOI:
    [Abstract] (78) [HTML] (0) [PDF 1.85 M] (151)
    Abstract:
    In the application of flight simulator, it is required that the aircraft simulation model quickly relocates to a specific state according to the training subject requirements, so it is crucial to quickly obtain the initial state parameter values of the aircraft. This paper proposes a trimming algorithm based on an improved Powell algorithm and an aircraft flight dynamics model, obtaining state variables and control inputs that enable the aircraft to achieve stable flight, thus realizing the relocation of aircraft motion state parameters. Furthermore, based on the solved motion parameters and aircraft system simulation principles, a repositioning method for aircraft system state parameters is proposed, forming an algorithm architecture for flight simulator repositioning. This algorithm has been applied to a specific model of a flight simulator, ensuring stable flight during the initial phase of simulation, with minimal visual and motion platform disturbances, thereby enhancing the logical consistency and realism of the simulation training, and has a faster solving speed.
    Risk identification of streamed flight data based on deep temporal network
    Zeng Lijun, Ding Songbin, Chen Chen
    Available online:July 02, 2025, DOI:
    [Abstract] (55) [HTML] (0) [PDF 3.09 M] (138)
    Abstract:
    Compared with post-flight operations quality assurance, it is helpful to identify and pre-warn operation risks by monitoring streamed flight data. A risks identification method based on streamed flight data deep learning was studied, and the proposed method was further verified in aircraft approaching flight. A deep temporal network (DTN) was constructed by combining temporal convolutional networks (TCN) with gated recurrent units (GRU). Firstly, the DTN was used to extract the long-term memory and local time-dependent features based on the offline flight dataset. Secondly, the DTN was simplified to the DTN-R network which is suitable for online anomaly monitoring. The anomaly detection tests based on real streamed flight data show that the DTN-R is able to identify typical anomalies including high speed exceedance (HSE), glide slope deviation (GSD) and late flap setting (LFS), thus achieving the online risk monitoring. By studying different risk features, the DTN can be extended to identify other in-flight risks. Providing the score of risk confidence, the DTN-R is helpful to explain the causes of abnormal risks. Furthermore, the proposed methodology provides an effective way of assuring flight safety.
    Prediction of runway excursion landing parameters based on flight data
    gaoyansong, gaozhenxing, zhangrunhao, xiangzhiwei
    Available online:July 02, 2025, DOI:
    [Abstract] (74) [HTML] (0) [PDF 1.05 M] (143)
    Abstract:
    The occurrence of runway excursion is a frequent and dangerous safety issue in civil aviation, and reducing the probability of such incidents is a key focus in aviation operations.?This study first selects positive samples with the risk of runway excursion and negative samples without the risk from real flight data and determines crucial time point based on flight manuals and China Civil Aviation Industry Standard.Subsequently, repeated measure experiments to these samples are conducted to obtain important parameters affecting runway excursion and the temporal characteristics of these parameters.Finally, grey relational analysis is used to select parameters,and LSTM neural networks and these selected parameters are used to train models to predict the important parameters and off runway center line distance of all crucial time points .The experiments show that the MAE of each model is consistently less than or equal to 1.2, indicating high accuracy. In the future, the pre-trained models can be used with real-time approach data to achieve online warning for runway excursion.
    Study on the technical system and key contents of aircraft tire burst design for CS 25.734
    Zhou chang wei, chenyu, wangzhaodong, Jinhui, Zhanglijuan, Zhangchenlizi, wuxihui, wangjiajie, wangpeiyan
    Available online:July 02, 2025, DOI:
    [Abstract] (61) [HTML] (0) [PDF 2.67 M] (144)
    Abstract:
    Tire bursting is a common aviation accident that easily occurs during aircraft take-off and landing, seriously affecting aircraft safety.In order to minimize the harm of tire bursting to aircraft, the aircraft design characteristics were investigated.On the basis of summarizing the engineering practice of domestic civil aircraft on the latest international tire blasting clauses, and based on the civil aircraft system engineering concept, an aircraft tire blasting design technical system for CS25.734 has been established,and aircraft design technology research has been carried out in four typical stages from project establishment to airworthiness verification.The results showed that: Setting fusible plugs is not a perfect measure to prevent tire bursting. Active or passive design measures should be taken in the aircraft wheel cabin for heat sources to prevent aircraft tires from overheating and bursting; there are four failure modes for aviation tire bursting, and the impact area is related to the compression state of the landing gear ,which is affected by all ground conditions(weight and center of gravity envelope, temperature envelope, etc.);a series of design considerations, verification ideas and compliance criteria on system/structure/fuel fire protection have been verified in the airworthiness certification of a domestic large passenger aircraft,which can provide reference for tire burst protection design of large transport aircraft.
    Analysis of Lightning Current in Composite Civil Aircraft Based on EMA3D
    HU Hao, FENG Yunwen, CHEN Junyu
    Available online:June 20, 2025, DOI:
    [Abstract] (68) [HTML] (0) [PDF 5.75 M] (178)
    Abstract:
    The anisotropic low conductivity of composite materials leads to local current concentration and current conduction hysteresis in aircraft after lightning strikes. Currently, most aircraft lightning current simulation methods focus on the study of metal materials, which makes it difficult to effectively characterize the surface current density distribution and transient current conduction of composite aircraft after lightning strikes. To ensure the effectiveness of lightning protection design and analysis for composite civil aircraft, the anisotropic conductivity matrix of composite materials under the influence of various layers and fiber content is introduced into the three-dimensional time-domain finite difference method to analyze the principle of lightning current conduction in composite civil aircraft. EMA3D simulation software is used to analyze the lightning current of composite civil aircraft, which is used to explore the surface current distribution and transient current conduction performance of the composite civil aircraft under multi-channel lightning injection paths. Then, a 3D modeling and simulation of a certain equivalent composite civil aircraft is carried out to analyze the overall current distribution law and transient current change characteristics of civil aircraft under the influence of composite material properties. The results show that: (i) composite civil aircraft may experience current concentration in the local area of the impact point and sharp parts such as the front and rear edges of the wing after being struck by lightning without protective measures, the current density of which is relatively high; (ii) the current preferentially conducts along the axis of the fuselage when composite civil aircraft is struck by lightning at the nose, and the current preferentially conducts along the spanwise direction of the front and rear edges of the wing when lightning strikes from the wing; (iii) the transient current of composite civil aircraft has conduction hysteresis compared to metal civil aircraft.
    Numerical Simulation Study of Bird Strike on Windshield Glass Based on SPH-DEM Coupling
    LIU Zongxing, CAO MIAO, SHENG Jiacheng, ZHANG Chunyang, LIU Jun
    Available online:June 20, 2025, DOI:
    [Abstract] (75) [HTML] (0) [PDF 2.47 M] (153)
    Abstract:
    Glass-type brittle materials are widely used in aircraft windshield structures, located at the front of the aircraft"s windward side, making them susceptible to bird strikes and subsequent fracturing. Testing fracture parameters of brittle windshield glass is challenging. Typically, elastic-plastic constitutive models and failure strains are used to describe the stress deformation and failure of glass. However, using this traditional SPH (Smoothed Particle Hydrodynamics)-FEM (Finite Element Method) coupling method makes it difficult to simulate the propagation of fine cracks in the windshield glass after a bird strike. This paper, based on the numerical calculation of fracture problems using the DEM (Discrete Element Method), calibrated the microscopic parameters of organic glass fracture with experimental data and established a bird-strike numerical simulation model of flat windshield glass based on the SPH-DEM coupling analysis method. The calculation results indicate the fracturing process of the windshield glass under bird strike impacts. The fracture results of the glass show good consistency with the bird strike test results, demonstrating that the SPH-DEM coupling analysis method can more accurately simulate the fracturing of windshield glass under bird strikes. This provides a new research method and approach for the numerical simulation of bird strikes on aircraft windshield glass.
    Study on minimum flight speed airworthiness standard of supersonic civil aircraft
    YangJianzhong, ZhangChenyang, YangShibing
    Available online:June 20, 2025, DOI:
    [Abstract] (104) [HTML] (0) [PDF 3.84 M] (136)
    Abstract:
    Supersonic civil aircraft have significant changes in aerodynamic layout and design compared to subsonic civil aircraft, which will bring new risks and make some provisions of the current regulations inapplicable. By conducting a qualitative analysis of CCAR Part 25 and the special conditions while using computational fluid dynamics (CFD) methods, the aerodynamic characteristics of a small aspect ratio, large sweep angle supersonic civil aircraft in low-speed conditions are analyzed; Finally, the safety intent behind the minimum flight speed mentioned in the supersonic civil aircraft special conditions is revealed through a combination of qualitative and quantitative analysis. The results show that the stall speed reference defined by CCAR Part 25 is not applicable to supersonic civil aircraft. Supersonic civil aircraft adopt the minimum flight speed (Vmin) and zero climb rate speed (Vzrc) as new speed references to ensure stable flight while still having climbing ability.
    Research on the Matching Performance of S-shaped Inlet and Turbojet Engine
    Quan jing ge, Li hong jun, Feng xiao qiang, Zhang wan yi, Gao xin
    Available online:June 20, 2025, DOI:
    [Abstract] (66) [HTML] (0) [PDF 3.84 M] (155)
    Abstract:
    The inlet/engine matching principle of target drone propulsion system is important to evaluate the engine working characteristics. To obtain the inlet/engine matching performance of a target drone, the investigation of the S-shaped inlet and small turbojet engine matching characteristic is carried out in this paper, by combining inlet/engine matching ground test with inlet suction experiment. It concentrates the influence of the S-shaped inlet on the engine characteristics. And an engineering method is produced to evaluate the small engine characteristics on ground running, by building the connections between the inlet/engine matching ground test and inlet suction experiment. It"s shown that the performance of engine in matching ground test is mainly affected by the S-shaped inlet characteristic parameters. When the full scale S-shaped inlet installed, the engine performance is no longer as good as the craft inlet installed, but falls. As the engine rotating speed enhanced, the mass flow increases, and the inlet performance gets worse. The total pressure recovery coefficient at the inlet exit decreases and the distortion index rises, which has a negative effect on the engine performance, resulting in the thrust smaller and the fuel consumption larger. Moreover, the proposed method can reliably evaluate the small engine characteristic parameters under matching ground condition based on the experimental data, so it is effective on engineering application.
    Wind Tunnel Test Research On Optimization Of Low-Speed Characteristics in The Kink Area of Transport Aircraft Wings
    Yan Wei, Huiwen Xu, Jingye Li, Ziyang Zhang, Meihong Zhang, Keliang Zhao, Renshan Jiao, Fei Wang, Wenchen Yan, Weiping Zeng
    Available online:June 20, 2025, DOI:
    [Abstract] (57) [HTML] (0) [PDF 7.34 M] (169)
    Abstract:
    For conventionally laid out civil transport aircraft in low-speed condition and high lift configurations, the advance of the stall angle of attack causes the aircraft"s approach speed to be too high, it is necessary to optimize the low-speed characteristics of the high-lift configuration and improve the landing performance of the aircraft by controlling the flow in the Kink area of the aircraft wing. Wind tunnel tests were used to conduct research on two passive control technologies: nacelle outer strake and slat edge tiny cut, obtained the best combination plan of nacelle outer strake (trailing edge height: H medium) and slat edge tiny cut (medium size cutting), under the best combination conditions, the lift coefficient is significantly improved, and the pitch moment coefficient still meets the requirements of the classic criterion after a slight pitch up. Fluorescent oil flow test reveals flow mechanism of optimized measures, that is, the high-energy vortices generated by nacelle outer strake and slat edge tiny cut are injected into the downstream wing surface, suppressing the separation of the flow on the wing surface.
    Airworthiness study of civil aircraft engine operating characteristics
    DENG Tianze, YANG Fei, ZHU Yan, QIU Jian, ZHONG Weixing
    Available online:June 20, 2025, DOI:
    [Abstract] (72) [HTML] (0) [PDF 1.28 M] (150)
    Abstract:
    Engine operating characteristics of civil aircraft engines are one of the most basic and complex verification subjects in the airworthiness certification process of the part25 "Airworthiness Standard for Transport Aircraft" of China Civil Aviation Regulations. The provisions require that turbine engines should work stably under normal flight conditions without adverse working characteristics. The verification of engine operating characteristics includes the engine performance, the control characteristics, the accessory actuation and other factors. Based on the airworthiness verification of the operating characteristics of a civil aircraft engine and guided by CCAR 25.939 (a) "Turbine Engine operating Characteristics" and AC25.939-1, this paper captures the verification requirements of CCAR25.939 (a), studies the verification methods of factors affecting engine operating characteristics, and analyzes the compliance test verification methods of engine transient performance, combining with a civil aircraft review case is used to illustrate the compliance method. This civil aircraft has successfully obtained part25 type certificate (TC certificate), indicating that the verification method can be effectively applied to the part25 airworthiness certification work of civil aircraft engine operating characteristics, and can provide reference for the subsequent civil aircraft engine airworthiness certification work.
    Head and neck injury analysis of THUMS HBM in brace position
    SHI xiaopeng, CUI shurui, SHI xiaolong, LI peiyao, HUI Xulong, XIE jiang
    Available online:June 11, 2025, DOI:
    [Abstract] (76) [HTML] (0) [PDF 3.73 M] (157)
    Abstract:
    During emergency landing, passengers using different anti-impact postures often produce different protective effects. A seat/passenger restraint system model based on the THUMS biomechanical dummy is established, comparing head and neck injuries in upright sitting posture, head and hand supported sitting posture, and head supported sitting posture under a 16g horizontal impact. A double-handed neck-holding anti-impact posture was proposed. By analyzing cervical axial tensile, compression force, anterior-posterior bending moment of the neck, the dynamic responses were analyzed, and the biomechanical response of the occupants, including vertebral stress, ligament elongation rate, intracranial equivalent stress, intracranial pressure, cranial equivalent stress, were analyzed. The damage assessment was conducted. Finally, the level of muscle activation was taken into consideration to explore the head and neck injuries of passengers in a state of muscle tension or relaxation. The results show that adopting an anti-impact posture can effectively reduce head and neck injuries, with the proposed double-handed neck-holding anti-impact posture reducing cervical axial force, bending moment, vertebral stress, and intracranial equivalent stress, but still carrying risks of neck soft tissue contusion and mild concussion. Tense muscles during impact can effectively reduce cervical axial force, bending moment, ligament elongation rate, intracranial equivalent stress and intracranial pressure.
    Study on the Asymmetric Extension States" Flutter Characteristics of a Telescopic Wing UAV
    yangjian, jiang pan pan, chen li yong, liu xiao chuan, wang wei
    Available online:May 28, 2025, DOI:
    [Abstract] (51) [HTML] (0) [PDF 2.77 M] (173)
    Abstract:
    Telescopic wing UAVs not only exhibit excellent flight performance across a wide speed range but can also utilize asymmetric wing extensions for flight control. This study focuses on a UAV with asymmetrically extendable wings. The extension process is discretized into distinct states, and a dynamic finite element model considering both structural and aerodynamic asymmetries is established to investigate the changes in flutter characteristics under asymmetric extension. The results show that both the flutter speed and flutter frequency in the asymmetric extension states are higher than those in the baseline symmetric state. As the asymmetry degree increases, the form of flutter transitions from body freedom flutter to bending-torsion coupling flutter, resulting in significant increases in both flutter speed and flutter frequency.
    Impedance distribution and electromagnetic coupling characteristics evaluation of aircraft low impedance conductive network
    zhenguoshuai, zangjiazuo, qixuefeng, songguodong, sunhongpeng
    Available online:May 28, 2025, DOI:
    [Abstract] (63) [HTML] (0) [PDF 846.97 K] (138)
    Abstract:
    The impedance distribution of low impedance conductive networks in aircraft has a significant impact on the electromagnetic coupling effect of onboard wiring harnesses. Studying the electromagnetic coupling characteristics of low impedance conductive networks in aircraft can significantly improve the accuracy of aircraft system level electromagnetic compatibility simulation. This article proposes an electromagnetic prototype modeling method for aircraft low impedance conduction networks. Based on the electromagnetic prototype, the impedance distribution characteristics and electromagnetic coupling characteristics of the aircraft low impedance conduction network are simulated and evaluated, and the aircraft actual test verification is completed. The simulation and test results show that the low impedance conductive network of the aircraft exhibits resistive and inductive characteristics in the frequency band below 0.1MHz, and alternating inductive and capacitive electromagnetic resonance characteristics in the frequency band above 0.1MHz.
    Study of Manned Airship Lightning Protection Design and Airworthiness Compliance Validation
    yangjianfneg, YAO Yongjie, PANG Chenglong, PENG Min
    Available online:May 28, 2025, DOI:
    [Abstract] (72) [HTML] (0) [PDF 2.30 M] (134)
    Abstract:
    When a manned airship is struck by lightning, in order to avoid damage to flight safety caused by lightning currents, we need to consider building lightning protection channels in the design of the manned airship and conduct airworthiness compliance verification during the development process. This article studies the lightning protection design and airworthiness compliance verification methods of AS700 manned airships. It simulates the lightning exposure of manned airships in thunderstorm and lightning environments, constructs the lightning current circuit of manned airships, and conducts lightning compliance tests on key components and materials to confirm that the lightning protection design of AS700 manned airships meets airworthiness requirements.
    A decision-making system for air transportation of emergency relief materials based on deep learning
    Xie ziliang, Tu lianghui, Shen jiaqi, Li zhenwen
    Available online:May 28, 2025, DOI:
    [Abstract] (57) [HTML] (0) [PDF 4.73 M] (153)
    Abstract:
    In emergency rescue, the decision of air transportation of relief materials is very important, but the traditional method of relying on experienced experts has some problems such as long time consumption and low efficiency. Therefore, this paper introduces deep learning technology and constructs a decision-making system for air transportation of emergency relief materials. According to the task requirements, the system generates all feasible transportation schemes for different types of aircraft and different modes of transportation, and quantifies all kinds of factors that can affect the air transportation process. By using neural network to calculate and predict the task completion time, the prediction results of the completion time of all schemes are obtained. This paper also verifies the influence of various factors on the prediction accuracy under different conditions, and further improves the prediction accuracy of this system by using the improved neural network. Compared with the traditional empirical expert decision-making method, this system greatly shortens the decision-making time of transportation scheme and improves the emergency rescue efficiency. It solves the limitations of traditional methods and provides more flexibility and reliability for emergency rescue work..
    Analysis of the applicability of operation regulations of large civil aircraft under intelligent assisted flight in the future
    WANG Wenchao, LAI Xin, WANG Jingjing, WANG Lei
    Available online:May 18, 2025, DOI:
    [Abstract] (109) [HTML] (0) [PDF 5.86 M] (161)
    Abstract:
    The deep integration of intelligent technology into the civil aviation industry system is bringing unprecedented changes. This integration is not only leading to innovations at a technical level, but also has far-reaching influence and intense impact on the standardized management of civil aviation. Therefore, how to regulate the operation regulations has become an urgent problem to be solved. In this paper, firstly, on the basis of systematically combing China"s existing laws and regulations related to Intelligent Assisted Flight (IAF), a basic analysis of future-oriented IAF"s operation regulations is carried out; Secondly, Secondly, based on the demand for rational development of intelligent assisted flight, an applicability analysis method based on the Osborne checklist method is proposed and applied in CCAR-91 and CCAR-121; finally, after in-depth discussion on the revision strategies of related regulations, a collaborative revision strategy is given and some referable revision proposals are put forward, which can help to improve the safety index of the flight process, and at the same time promote the improvement and innovation of the operation regulations.
    Research on Aircraft Configuration Management Methods for Frequent Configuration Changes
    LEI Shuai, WANG Hui, GE Lei, SHEN Jiaji, ZHAO Weidong, ZHANG Yingyao
    Available online:May 18, 2025, DOI:
    [Abstract] (80) [HTML] (0) [PDF 1.61 M] (154)
    Abstract:
    Frequent configuration changes during aircraft development process increase the difficulty and challenge of configuration management. In this paper, an aircraft configuration management method for frequent configuration changes is proposed. Firstly, a configuration management framework based on graph database technology is constructed, storing aircraft structures in a graph format within the database to facilitate efficient and intuitive management and tracking of configuration changes. Secondly, a demand-oriented modular product breakdown structure and a staged configuration identification coding method are introduced to address the management issues associated with frequent configuration changes during the aircraft design and manufacturing stages. Finally, a module-oriented engineering change propagation tracking and validity identification method is established to manage the frequent engineering changes encountered during the aircraft manufacturing stage. The results demonstrate that the proposed configuration management method for frequent configuration changes enables the rapid and intuitive identification of affected components and subsystems based on the graph database, and significantly reduces the steps and time required to implement changes, thereby enhancing the efficiency of configuration management.
    Design of Ice-slab Input Device for Aeroengine
    wangdi, JIN Zhengyang, XU Jianlei, LI Meichuan
    Available online:May 07, 2025, DOI:
    [Abstract] (82) [HTML] (0) [PDF 9.86 M] (192)
    Abstract:
    Test of ice ingestion aeroengine is a verification item that must be passed by airworthiness certification. Ice-slab ingestion is an important part of it, which is to verify the strength of aeroengine under the expected ice absorption conditions, and is an important guarantee for the safe operation of aircraft. Based on the requirements and principles of aeroengine ice ingestion test, a rotating ice projection test model is established, and the speed composition of the device is analyzed, and the aeroengine ice-slab input device is developed. The device is of horizontal structure, mainly composed of frame, rotating power system, release power system, rotating arm, protection mechanism, release mechanism, ice-slab box mechanism, guard plate structure, computer control system, operation panel, etc. The rotating arm mechanism provides stable impact velocity for ice-slab; The quick change ice-slab box mechanism realizes the rapid replacement of different specifications of ice-slab, and meets the test of ice ingestion requirements of different types of aeroengine; According to the field test, it is showen the flight attitude of ice-slab is stable, and it can hit the target point with the thickness side; The target impact test proves that the ice-slab projected by the device can impact into the effective calibration area, and the newly developed device can meet the requirements of test of ice ingestion in the airworthiness regulations of aeroengines at home and abroad.
    Study and the selection strategy of quality control system in aviation nondestructive testing
    Xu Guirong, Ning Ning, Guan Xuesong
    Available online:May 07, 2025, DOI:
    [Abstract] (68) [HTML] (0) [PDF 477.96 K] (166)
    Abstract:
    The quality control system applied in the field of domestic aviation non-destructive testing can be divided into three levels according to the size of the application surface: basic general quality management system, non-destructive testing qualification certification management system and non-destructive testing industry standards. At present, the non-destructive testing qualification certification management system is widely used in CMA, CNAS, DIAC, NADCAP, ALAC, ASP, etc., in the face of many systems, many customers have no choice. In order to help more units and suppliers have a deeper understanding of these systems, and can choose suitable NDT quality control systems according to needs, this paper analyzes the similarities and differences of different systems, process element control requirements and typical application cases. Specific suggestions are given to the selection strategies of quality control system for enterprises and suppliers according to different customer requirements.
    Research on Flight Deck Operation Process Optimization Based on Virtual Reality
    Mu Lin, Wu Jiaren, Liu Dong, TIAN Yongliang, Yang Sichao, Liu Hu
    Available online:May 07, 2025, DOI:
    [Abstract] (103) [HTML] (0) [PDF 1.78 M] (171)
    Abstract:
    The flight deck operation process and support time of carrier-based aircraft have an important impact on the overall dispatch capability. Aiming at the optimization of the flight deck operation process of carrier-based aircraft, a method of using heuristic algorithm combined with 3D modeling and virtual simulation is proposed, and the heuristic algorithm considering multiple constraints is used to solve the time-series scheme of flight deck operation for carrier-based aircraft and shorten the surface of the carrier-based aircraft. The support process is time-consuming. Based on the virtual reality platform, the carrier-based aircraft support process simulation environment is built, and the high-precision component 3D modeling of the carrier-based aircraft flight deck operation process is carried out, and the fine-grained visual simulation of the carrier-based aircraft flight deck operation process is carried out. Deduction and space interference detection are used to verify the carrier-based aircraft flight deck operation sequence scheme solved by manual scheduling or algorithm, evaluate its rationality and feasibility, and verify that the evaluation results can support the further optimization of the carrier-based aircraft flight deck operation timing scheme.
    Operational Risk Analysis of Large Unmanned Aerial Vehicles Based on STPA and Fuzzy Bayesian Networks
    zhang zi ang, zhang xiaoquan
    Available online:May 07, 2025, DOI:
    [Abstract] (48) [HTML] (0) [PDF 1.56 M] (173)
    Abstract:
    In order to meet the arrival of large unmanned aerial vehicles and reduce the probability of accidents, the main roles and responsibilities and scenarios in the operation process were analyzed, and the control feedback structure in the operation process was constructed by using the System Theory Process Analysis Method (STPA) to identify the risk factors that lead to accidents. Based on the correlation between factors, the Bayesian network (BN) was constructed, and the GeNIe software was used to carry out forward causal inference on the risk probability, and the key factors were determined through reverse reasoning, sensitivity analysis and impact intensity analysis. The results show that control failure is the most critical factor leading to accidents. Navigation system failure, bad weather, and battery failure are highly sensitive factors, and the analysis results can provide a basis for the prevention and control of large-scale unmanned aircraft operation risks.
    A Review of propel configurations and aerodynamic interaction between propellers and components of UAVs
    Wang Xiaolu, CHEN Changning, LIU Yingyu, ZHAO Ke
    Available online:April 25, 2025, DOI:
    [Abstract] (108) [HTML] (0) [PDF 8.72 M] (225)
    Abstract:
    The propulsive mode of propeller has the characteristics of high efficiency and universal applicability, and is widely utilized in modern UAVs design. The aerodynamic interaction between propellers and UAVs has a great impact on the aerodynamic characteristics, flight stability and controllability of UAVs, and the effect of slipstream is supposed to be considered in the design of UAVs. Firstly, the engineering research of the technical development, the basic theory and the analysis method of propellers are summarized in this paper. Secondly, the propulsive configurations are classified into 4 categories, and the research progress in aerodynamic characteristics of propellers and UAVs is investigated. Finally, the research status of the aerodynamic characteristics on different components is studied, and the future development trend of rotor-propelled UAVs is forecasted, which effected by the propeller slipstream. References for the selection of propulsive configurations and the optimizing design of aerodynamic interaction on can be provided by this paper.
    Research on Multidisciplinary Objective Optimization of Aerodynamic Stealth with Leading Edge Radius Distribution of Flying Wing Layout
    Yu Longzhou, Zhong Shidong, Huang Jiangtao, He Chengjun, Chen Xian, Qu Congcong
    Available online:April 25, 2025, DOI:
    [Abstract] (87) [HTML] (0) [PDF 1.95 M] (185)
    Abstract:
    In order to study the influence of the distribution of leading edge radius along the spanwise direction on the stealth and aerodynamic characteristics of flying wing layout, the spanwise distribution CST airfoil matching method is used to realize the parameterization of leading edge radius, and the multidisciplinary model output method based on mapping linkage is used to calculate and output numerical models with consistent shapes for aerodynamic and stealth disciplines. The experimental design method is used to construct sample points, the Kriging surrogate model is established, and the evolutionary algorithm based on the surrogate model is used to carry out single-objective and multi-objective optimization. Through the multi-objective optimization results of aerodynamic stealth with spanwise distribution of leading edge radius, it is proved that the forward radar cross section of stealth optimized shape can be further reduced by about 2 dB without losing aerodynamic characteristics.
    Experimental study on response of carbon fiber composite with fasteners under lightning strike
    Yao Junjun, Li dan, He zheng, Xiong xiu
    Available online:April 25, 2025, DOI:
    [Abstract] (89) [HTML] (0) [PDF 8.80 M] (223)
    Abstract:
    Composite materials have been widely used in aircraft lightning protection, and their protection methods are becoming increasingly mature, but the research onconducted lightning currentat the joint of metal fasteners and composite materials is stillincomplete. Therefore, for the carbon fiber composite materials used for lightning protection of copper mesh, this paper studied the conducted lightning current capacity of a single fastener and the influence of fastener number and connection method on the conducted lightning current effect through lightning test. The test data shows that a single M4 screw can safely conduct 200kA lightning current, while a single M4 blind rivet can safely conduct 50kA lightning current; When the plate connection form is lap joint, the number of M4 screws shall be at least 7; When the plate connection is butt joint, three M4 screws or rivets can safely conduct 200kA lightning current.
    Research on high precision detection technology of coating thickness based on standard tool
    Jian Gu, Jiyang Zhang, Tao Lei, Dandan Zhang, Jiaojiao Ren, Junwen Xue, Qi Chen, Wentao Yang
    Available online:April 25, 2025, DOI:
    [Abstract] (96) [HTML] (0) [PDF 4.21 M] (194)
    Abstract:
    With the swift advancement of aerospace science and technology, the accurate measurement of coating thickness is particularly important, which is directly related to the performance and safety of aircraft.In this paper, a terahertz nondestructive testing method of coating thickness based on a standard tool was developed for the coating thickness measurement in aerospace field,by using a quartz window,the time-of-flight change caused by material thickness into the refractive index change caused by equivalent air thickness,the total thickness and refractive index of the composite coating can be accurately measured without prior knowledge.The results shows that the thickness measurement accuracy of this method can reach 3μm for single dielectric material and 5μm for coating material,also can accurately obtain the equivalent refractive index of the sample in terahertz band.The aforementioned technology can effectively detect the thickness and refractive index of composite coatings with high precision, making it highly valuable for precise coating thickness control applications such as aerospace.
    Explorations and Practices on the Intelligent Manufacturing of Aeronautical Composite Materials
    HE Liang, GUO Jungang, ZHU Panxing, SU Xia, HU Dabao, WANG Xiaokai, Xu Yingjie
    Available online:April 18, 2025, DOI:
    [Abstract] (62) [HTML] (0) [PDF 1.00 M] (199)
    Abstract:
    The intelligent manufacturing is a key development direction to realize manufacturing upgrading, and also one of the main competitive fields of industrial modernization around the world. However, the intelligent manufacturing of advanced composite materials is still in the exploration stage due to its particularity of manufacturing technology. In the present paper, the ideal of moderate intelligence for composite production line is proposed based on the state-of-the-art technology of intelligent manufacturing and the characteristics of the prepreg-autoclave processing, and explorations and practices on the intelligent manufacturing of composite materials are discussed from the perspectives of the intelligent production line model, the intelligent manufacturing standard system of composite materials, industry 4.0-enabling technologies. The present research can be used as guidance for the application of intelligent manufacturing of composite materials.
    VHC fatigue properties of two SLM manufactured aluminum alloy
    Yin Haibiao, Yao Weixing, Fu Dingkun
    Available online:April 18, 2025, DOI:
    [Abstract] (133) [HTML] (0) [PDF 2.65 M] (207)
    Abstract:
    Aluminum alloy manufactured by SLM (Selective Laser Melting) technology has been widely used in aerospace and other industries, but it has some defects such as gas pore, LOF (Lack of Fusion) and so on, which can seriously affect the fatigue performance, and there are few studies concerning its VHC fatigue properties and S-N curve so far. In this paper, the VHC fatigue properties of SLM manufactured TiB2 high-strength aluminum alloy and AlMgScZr high-strength aluminum alloy were studied, and the fatigue test up to 108 cycles has been completed. The S-N curves of the two materials were obtained, the fracture characteristics were analyzed, and the fatigue properties of the two alloys were compared with those of ordinary aluminum alloys. The results show that the fatigue property of AlMgScZr high strength aluminum alloy is slightly better than that of TiB2 high strength aluminum alloy. At the same time, the static strength and fatigue strength of two kinds of SLM aluminum alloy are higher than that of ordinary aluminum alloy, but the relative fatigue strength is worse than that of ordinary aluminum alloy.
    Research on approach sector dynamic capacity based on machine learning
    CAO Shu-jian, HU Ming-hua, WANG Shu-ce, zhao zheng, YIN Meng-xuan
    Available online:April 18, 2025, DOI:
    [Abstract] (61) [HTML] (0) [PDF 1.16 M] (185)
    Abstract:
    The study of sector complexity can effectively improve the accuracy of sector dynamic capacity assessment and provide reference for air traffic decision-making. This paper firstly establishes the approach and departure procedures’ potential exceeding conflict complexity metrics and key conflict node complexity metrics to quantify the impacts of different dynamic traffic indicators; secondly, using machine learning to train and test the different features and the number of passing aircraft in the sector and get the mapping relationship, the model can be used to predict the sector traffic capacity under different traffic flow configurations; finally, uses the one-week operation data of AP16 from complex terminal for example verification, and the result shows that the machine model can be predicted the sector traffic capacity. The results show different traffic configurations would have an impact on sector capacity, and the dynamic capacity of the sector in the nearly balanced phase of approach and departure reached a maximum of 15 flights/15min. In addition, this paper applies Shapley"s additive interpretation to quantify the contribution of each feature to the predicted sector capacity, which can provide a reference for the subsequent planning and design of the sector.
    Integrated test cases and procedures development method for civil aircraft CNS system
    ZHANG Hui, YAO Yujia
    Available online:April 03, 2025, DOI:
    [Abstract] (76) [HTML] (0) [PDF 736.46 K] (176)
    Abstract:
    The airborne radio communication, navigation and surveillance (CNS) system is an important component of the civil aircraft avionics system. Test procedure is an important technical document in the CNS system verification process, and it is also the basis and foundation for conducting testing and verification work. How to reduce the time of creating and testing the test procedures, and save valuable time resources for testing and verification activities is one of the key issues to consider in the CNS system verification process. Various factors that affect the time of creating and testing the test procedures are analyzed. Targeting at enhancing the similarity of test procedures for different CNS functions, through in-depth analysis of CNS functional integrated features, an integrated test case and procedure development method for CNS systems is proposed. Based on actual engineering data, a comparative analysis is conducted between integrated development method and conventional development method. The results indicate that the integrated development method can effectively reduce the time of creating and testing the test procedures, thus improve verification efficiency, which has a reference significance for the testing and verification of other avionics systems.
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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] (400) [HTML] (238) [PDF 2.60 M] (11997)
    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] (3876) [HTML] (0) [PDF 1.89 M] (9713)
    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] (1364) [HTML] (0) [PDF 833.51 K] (8811)
    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.
    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] (1571) [HTML] (1395) [PDF 3.67 M] (6858)
    Abstract:
    The vertical takeoff and landing (VTOL) fixed wing unmanned aerial vehicle (UAV) has many advantages, such as low requirements for takeoff and landing site, good maneuverability, high cruise speed and long endurance, etc., which is a hot topic in the aviation field. This paper describes the existing VTOL fixed wing UAV development status and their features around the world, and then analyzes the technical problems faced by these different types of VTOL fixed wing UAVs. It indicates that the VTOL fixed wing UAV with higher cruise speed, longer battery life, and stronger ability of task load seems to be the main developing direction and inevitable trend in the future. Although the tilting rotor configuration and tailstock configuration are still the mainstream configuration of the VTOL fixed wing UAV in nowadays, the distributed electric propulsion (DEP) VTOL fixed wing UAV technology will become the hottest issues in the field of aerospace, therefore, it is necessary to enhance the evolutionary research in the new-concept configurations and new principles of the high-performance VTOL fixed wing UAVs.
    Analysis of Development Trend and Design Technology of Refueling Boom
    Wang Xiuxiang, Gao Xu, Gao Yakui
    2020,11(3):302-307. DOI: 10.16615/j.cnki.1674-8190.2020.03.002
    [Abstract] (1388) [HTML] (0) [PDF 1.65 M] (6818)
    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] (872) [HTML] (0) [PDF 8.07 M] (6416)
    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] (1640) [HTML] (0) [PDF 1.21 M] (6314)
    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.
    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] (2792) [HTML] (0) [PDF 1.88 M] (5936)
    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] (2687) [HTML] (0) [PDF 1.77 M] (5462)
    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] (2303) [HTML] (0) [PDF 562.11 K] (5210)
    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.
    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] (1502) [HTML] (0) [PDF 1.19 M] (5131)
    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.
    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] (1165) [HTML] (1426) [PDF 1.07 M] (5074)
    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.
    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] (1490) [HTML] (0) [PDF 1.57 M] (4761)
    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.
    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] (1052) [HTML] (0) [PDF 533.70 K] (4708)
    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.
    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] (4185) [HTML] (0) [PDF 2.89 M] (4264)
    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.
    Analysis on Integrated Design of Military Aircraft PHM System
    jingbo, huangsonglin, wangshenglong, cuizhanbo, shengzengjin
    2022,13(3):64-73. DOI: 10.16615/j.cnki.1674-8190.2022.03.08
    [Abstract] (984) [HTML] (992) [PDF 1.74 M] (4176)
    Abstract:
    Aiming at the problems of lack of design standards, high complexity and low accuracy in the design and engineering application of prognostic and health management (PHM) system for military aircraft, the design requirements of data, structure and function dimensions of PHM system are analyzed. Based on the study of the relations and characteristics of the three dimensions, the three-dimensional multiphase iterative design criteria is proposed. A three-in-one design architecture of real-time health management based on embedded system, knowledge logic visualization based on knowledge graph, and PHM system modeling based on MBSE is proposed. The PHM system design process is constructed by analyzing the PHM system design strategy, which provides a method for the engineering application of military aircraft PHM system.
    Research 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] (1620) [HTML] (0) [PDF 3.91 M] (4121)
    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] (1930) [HTML] (0) [PDF 3.27 M] (4111)
    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] (1569) [HTML] (0) [PDF 1.20 M] (4084)
    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.
    Current situation and trend of air-to-air missile launch technology
    liuhao, zhou jun, zhang shiwei
    2018,9(2):147-158. DOI: 10.16615/j.cnki.1674-8190.2018.02.002
    [Abstract] (1058) [HTML] (0) [PDF 2.04 M] (4066)
    Abstract:
    Air-to-air missile launcher which gives missile good separation attitude is an important mechanism of aircraft weapon system, it has a direct impact on combat capabilities of fighters. This paper summarized development process and present status of air-to-air missile launcher, focused on the theoretical research hotspot of the current mainstream launch mode of air-to-air missile such as guide rail, store ejection and embedded ejection , and pointed out that the high mach number launching, high overload launching, rolling launching, multidisciplinary coupling research of launching, ground ejection experiment technology considering pneumatic are still in initial stages, they are the focus of theoretical research in the future. Compared the two present classical embedded ejection launcher of stealth fighter, analyzed the key technology, technology advantages and disadvantages of them. In the end, technology development directions of air-air missile launcher was pointed out.

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