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    A TDOA/FDOA cooperative localization method for multiple disjoint sources based on weighted multidimensional scaling analysis
    Ding WANG, Jiexin YIN, Xinguang ZHANG, Na’e ZHENG
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2023, 44 (7): 327105-327105.   DOI: 10.7527/S1000-6893.2022.27105
    Abstract2096)   HTML17)    PDF(pc) (4502KB)(520)       Save

    TDOA/FDOA localization is an important wireless positioning mechanism for moving emitters, and its location accuracy is greatly affected by measurement errors of TDOA/FDOA and prior measurement errors of sensor models (including sensor position and velocity). To improve the localization performance under the condition of high-level measurement errors, a TDOA/FDOA cooperative localization method for multiple disjoint sources is proposed based on weighted multidimensional scaling analysis in this paper. The proposed method consists of two calculation stages: Stage-a and Stage-b. Specifically, in Stage-a, two groups of scalar product matrices in multidimensional scaling analysis are employed to form the positioning relationship, which is further used to yield the solutions for the locations of multiple disjoint sources and sensors by constructing a weighting matrix. In Stage-b, a constrained minimization model is established based on the intermediate variables introduced in multidimensional scaling analysis to determine the estimation errors in Stage-a. By solving this optimization problem, the expression for the localization errors in Stage-a are obtained, so as to refine the position and velocity estimates of the multiple disjoint sources as well as the sensors. In addition, the first-order error analysis is employed to prove that the proposed method can asymptotically reach the Cramér-Rao Bound (CRB) accuracy. Simulation results show that the new method outperforms the existing TDOA/FDOA positioning methods.

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    Real⁃time dense small object detection algorithm for UAV based on improved YOLOv5
    Zhiqiang FENG, Zhijun XIE, Zhengwei BAO, Kewei CHEN
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2023, 44 (7): 327106-327106.   DOI: 10.7527/S1000-6893.2022.27106
    Abstract1369)   HTML51)    PDF(pc) (5498KB)(378)       Save

    UAV aerial images have more complex backgrounds and a large number of dense small targets compared with natural scene images, which impose higher requirements on the detection network. On the premise of ensuring real-time object detection, a YOLOv5-based UAV real-time dense small object detection algorithm is proposed for the problem of low accuracy of dense small object detection in UAV view. First, combining Spatial Attention Module (SAM) with Channel Attention Module (CAM), the fully connected layer after feature compression in CAM is improved to reduce the computational effort. In addition, the connection structure of CAM and SAM is changed to improve the spatial dimensional feature capture capability. In summary, a Spatial-Channel Attention Module (SCAM) is proposed to improve the model's attention to the aggregated regions of small targets in the feature map; secondly, an SCAM- based Attentional Feature Fusion module (SC-AFF) is proposed to enhance the feature fusion efficiency of small targets by adaptively assigning attentional weights according to feature maps of different scales; finally, a backbone network is introduced in the Transformer in the backbone network, and use the SC-AFF to improve the feature fusion at the original residual connections to better capture global information and rich contextual information, and improve the feature extraction capability of dense small targets in complex backgrounds. Experiments are conducted on the VisDrone2021 dataset. The effects of different network scale parameters and different input resolutions on the detection accuracy and speed of YOLOv5 are first investigated. The analysis concludes that YOLOv5s is more suitable to be used as a benchmark model for UAV real-time object detection. Under the benchmark of YOLOv5s, the improved model improves mAP50 by 6.4% and mAP75 by 5.8%, and the FPS for high-resolution images can reach 46. The mAP50 of the model trained at an input resolution of 1504×1504 can reach 54.5%, which is 11.5% better than that of YOLOv4. The accuracy is improved while the detection speed FPS remains at 46, which is more suitable for real-time UAV object detection in dense small target scenarios.

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    Technology development of high temperature superconducting machine for electric aviation
    Dongbin SONG, Juzhuang YAN, Wenjiang YANG, Mingliang BAI, Rujing LIU, Shaopeng WANG, Yu LIU, Aimei TIAN
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2023, 44 (9): 27469-027469.   DOI: 10.7527/S1000-6893.2022.27469
    Abstract1255)   HTML51)    PDF(pc) (9270KB)(354)       Save

    The superconducting machine has prospects of a wide range of applications in aviation electric propulsion due to its advantages such as small size, high power density, and high efficiency. The characteristics and current situation of the superconducting pure/hybrid electric drive systems are compared, showing the importance of the superconducting machine for high power aviation electric propulsion. In view of different requirements for motors and generators for the superconducting electric drive system for high power aviation electric propulsion, the operating principles and structural topologies of those prototypes of High Temperature Superconducting (HTS) machines studied in the past are reviewed and classified, and the advantages and disadvantages are summarized and analyzed. On this basis, the key technologies of superconducting machine are outlined in terms of superconducting technology, AC superconducting armature, rotor technology, cryogenic technology and insulation technology. Under the background of aviation electrification, the progress in the application of superconducting electric drive system in aviation electric propulsion is outlined, and future development of superconducting electric aviation is also discussed.

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    First flight of SpaceX heavy-lift starship: Enlightenment for aerospace industry in China
    Guang MENG, Chang LIU, Dongchun YANG, Chenghong ZHOU, Hua ZHOU
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2023, 44 (10): 28914-028914.   DOI: 10.7527/S1000-6893.2023.28914
    Abstract1031)   HTML54)    PDF(pc) (7472KB)(437)       Save

    The development of reusable launch vehicles is the persistent pursuit of aerospace industry. Although the first flight of the fully reusable SpaceX two-stage heavy-lift starship was successfully launched, the starship was ultimately self-destructed due to the loss of control in the subsequent flight. After reviewing evolutionary design and the first flight experience of the heavy-lift starship, this paper analyzed the application modes of the heavy-lift starship based on the overall scheme, identified the key technologies involved, and summarized its impact on aerospace industry. Finally, the enlightenment and suggestions of the heavy-lift starship’s achievements to China’s aerospace industry are provided.

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    Research on All-Domain Fire Field in Future Air Combat
    Acta Aeronautica et Astronautica Sinica    DOI: 10.7527/S1000-6893.2023.29699
    Accepted: 13 October 2023

    Technology development in high pressure compressor of civil high bypass-ratio turbofan engine
    Chuanjun CAO, Tianyi LIU, Wei ZHU, Jinchun WANG
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2023, 44 (12): 27824-027824.   DOI: 10.7527/S1000-6893.2022.27824
    Abstract784)   HTML77)    PDF(pc) (6001KB)(571)       Save

    The high bypass-ratio turbofan engines are chosen invariably to provide power and thrust for large passenger aircraft. The vigorous development of the international civil aviation market has promoted the rapid improvement of civil high bypass-ratio turbofan engine technology. As the core component of aero-engines, the high-pressure compressor has the “three highs” characteristics, high efficiency, high pressure ratio, and high mass flow. The American General Electric (GE) Company, Pratt & Whitney (PW) Company and the British Rolls-Royce (RR) Company remain international leading level in the high-pressure compressor design technology. In recent years, research and development concerning civil high bypass-ratio turbofan engine have been carried out based on two National Science and Technology Major Projects, i.e., the Large Airplane Major Project and the Aircraft Engine and Gas Turbine Major Project. Thus, some progress has been achieved in the area of high-pressure compressor design technology. In this paper, the technical features of the high-pressure compressor of civil high bypass-ratio turbofan engine were analyzed. And then, the research status and development trend of it at home and abroad were reviewed. Finally, the domestic technology difficulties and challenges were pointed out objectively. It is expected that learning from the characteristics of the international advanced design could enlighten the technology development of the high-pressure compressor of civil high bypass-ratio turbofan engine in China.

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    Target round-up control for multi-agent systems based on reinforcement learning
    Zhilin FAN, Hongyong YANG, Yilin HAN
    Acta Aeronautica et Astronautica Sinica    2023, 44 (S1): 727487-727487.   DOI: 10.7527/S1000-6893.2022.27487
    Abstract777)   HTML17)    PDF(pc) (2067KB)(279)       Save

    A target round-up control method for multi-agent systems is proposed based on reinforcement learning. Firstly, Markov game modeling for multi-agent systems is carried out. The potential energy function which meets the requirements of arriving at the desired state and avoiding obstacles is designed according to the task of rounding up, and reinforcement learning principles are combined with the model control. The round-up is performed using multi-agent reinforcement learning guided by the potential energy model. Secondly, based on the existing potential energy model, two surrounding strategies are established: tracking round-up and circumnavigation round-up. With the first strategy, consistent tracking of multiple agents is achieved by designing the potential energy function of velocity. In the second strategy, virtual circumnavigation points are added to design potential energy functions, achieving desired circumnavigation. Finally, the effectiveness of the round-up control based on multi-agent reinforcement learning is verified by simulation.

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    Key structural dynamic design technologies in liquid rocket engines: Review
    Dahua DU, Bin LI
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2023, 44 (10): 27554-027554.   DOI: 10.7527/S1000-6893.2022.27554
    Abstract773)   HTML84)    PDF(pc) (4813KB)(546)       Save

    With the development of liquid rocket engine technologies, structural dynamic problems become one of the key factors affecting the life and reliability of engines. In the past decades, the design concepts and methods of the engine gradually developed from the initial static strength and safety life design to the combination of dynamic and static strength, and economic life design, which were widely used in engines, significantly improving the working reliability of the engine structures. However, the increasing size and complex structure and the extreme harshness of the working environment for the new rocket engines require urgent solution to the technical problems of engine structural dynamic design to meet the needs of high performance, high reliability, light weight and reusability. This paper reviews the key technologies such as load prediction, dynamic modeling and model updating, dynamic strength assessment and life prediction, and anti-fatigue design on account of dynamics optimization, based on the analysis of typical dynamic problems in engine structures. The research summary and prospect are also presented. This review will provide guidance for the development of structural dynamic design technology of liquid rocket engines.

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    Review of key technologies for fault diagnosis and accommodation for multi⁃electric distributed engine control system
    Wanli ZHAO, Yingqing GUO, Kejie XU, Cansen WANG, Haojie YING, Xinxin TAO
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2023, 44 (10): 27519-027519.   DOI: 10.7527/S1000-6893.2022.27519
    Abstract740)   HTML42)    PDF(pc) (4677KB)(428)       Save

    In view of the demand for future aero-engines,combined with the characteristics and advantages of multi electric distributed control,the key technologies of fault diagnosis and accommodation of multi-electric distributed engine control system are studied based on advanced algorithms. Firstly,this paper summarizes the fault diagnosis and accommodation technology of multi-electric distributed engine control system at home and abroad from four aspects:distributed engine control system,more electric engine,fault diagnosis and fault-tolerant control methods and hardware in the loop simulation platform,and points out the key problems of fault diagnosis and accommodation of multi-electric distributed engine control system at present. Then the key technologies are proposed,which are the design of fault diagnosis and accommodation architecture of multi-electric distributed engine control system,the model-based fault diagnosis and fault-tolerant control method,the fault diagnosis and accommodation scheme of dual active redundant motor control system,the electro-mechanical actuator fault diagnosis and accommodation scheme based on deep learning,and the construction of hardware in the loop simulation platform. Finally,the future development trend of fault diagnosis and fault tolerance of aeroengine multi electric distributed control system is prospected.

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    Uncertainty⁃based design system for aeroengines
    Xinqian ZHENG, Junying WANG, Weina HUANG, Yu FU, Ronghui CHENG, Hongyang XIONG
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2023, 44 (7): 27099-027099.   DOI: 10.7527/S1000-6893.2022.27099
    Abstract725)   HTML45)    PDF(pc) (3949KB)(415)       Save

    A significant number of random and epistemic uncertainties exist in the whole life cycle of an aeroengine, causing problems such as a long design iteration cycle, low manufacturing qualification rate, and difficulties in maintenance. Recent years have witnessed a series of research on uncertainty analysis at home and abroad; however, the uncertainty design system of aeroengines has not been proposed systematically at the theoretical level. Based on the current deterministic design system and the results of uncertainty research, this paper discusses the construction of the uncertainty-based design system and realization of the design system reform for aeroengines. The uncertainty factors and their influence on aeroengines are first summarized, followed by discussion of the definition and necessity of the uncertainty-based design system. The ultimate goal of the uncertainty-based design system is to achieve successful research and development with a single iteration. The performance distribution is quantitatively evaluated and controlled at each design stage to produce a comprehensive optimal design scheme in terms of performance, reliability, robustness, and costs in the whole life cycle. Based on this definition, the basic elements of the uncertainty-based design system are analyzed, including the process, method, platform, specification, and organization. Finally, the periodic prospects, expected benefits, and challenges of the uncertainty-based design system are presented.

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    Mechanisms, algorithms, implementation and perspectives of brain⁃inspired navigation
    Xiangwei ZHU, Dan SHEN, Kai XIAO, Yuexin MA, Xiang LIAO, Fuqiang GU, Fangwen YU, Kefu GAO, Jingnan LIU
    Acta Aeronautica et Astronautica Sinica    2023, 44 (19): 28569-028569.   DOI: 10.7527/S1000-6893.2023.28569
    Abstract717)   HTML43)    PDF(pc) (9701KB)(573)       Save

    The rapid development of brain and neuroscience in recent decades has initially revealed the neural mechanism of animal navigation. Drawing on the brain neural structures and information processing mechanisms, the study of brain-inspired intelligent navigation systems provides new inspiration for low-power, highly robust autonomous intelligent navigation in complex environments. Based on a detailed review of the neural mechanisms of animal spatial navigation, this paper then outlines and discusses current intelligent algorithms for robotic bionic brain-inspired navigation, which can be categorized into three types according to the three types of neural networks used to process navigation information for intelligent navigation: attractor neural networks, deep reinforcement learning, and spiking neural networks. Then, the ways for implementing brain-inspired navigation, including bionic intelligent sensors and neuromorphic processor platforms, are sorted out. Finally, the development trend of brain-inspired navigation is discussed, including further exploration of the brain neural mechanism of navigation in the biological world and its information processing process with low energy consumption and high robustness mechanism, subcategorization of the conceptual connotation of brain-inspired navigation, and the ways to improve the evaluation index and the unified implementation framework.

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    Maneuvering decision-making of multi-UAV attack-defence confrontation based on PER-MATD3
    Xiaowei FU, Zhe XU, Jindong ZHU, Nan WANG
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2023, 44 (7): 327083-327083.   DOI: 10.7527/S1000-6893.2022.27083
    Abstract703)   HTML20)    PDF(pc) (2920KB)(408)       Save

    This paper explores multi-UAVs attack-defence confrontation maneuvering decision-making in a complex environment with random distribution of obstacles. A motion model and a radar detection model for both attack and defence sides are constructed. the Twin Delayed Deep Deterministic policy gradient (TD3) algorithm is extended to the multi-agent field to solve the problem of overestimation of the value function in the Multi-Agent Deep Deterministic Policy Gradient (MADDPG) algorithm. To improve the learning efficiency of the algorithm, a Prioritized Experience Replay Multi-Agent Twin Delayed Deep Deterministic policy gradient (PER-MATD3) algorithm is proposed based on the priority experience playback mechanism. The simulation experiments show that the method proposed in this paper has a good confrontation effect in multi-UAV attack-defence confrontation maneuvering decision making, and the advantages of the PER-MATD3 algorithm over other algorithms in terms of convergence speed and stability are verified by comparison.

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    A review of topology optimization design methods for multi-scale structures
    Xiaoqian CHEN, Yong ZHAO, Senlin HUO, Zeyu ZHANG, Bingxiao DU
    Acta Aeronautica et Astronautica Sinica    2023, 44 (15): 528863-528863.   DOI: 10.7527/S1000-6893.2023.28863
    Abstract682)   HTML66)    PDF(pc) (22843KB)(577)       Save

    Multi-scale structure is one of the important directions of next-generation structural lightweighting and has great potential and strategic value for application in the aerospace field. Topology optimization techniques for multi-scale structures have also been extensively researched, leading to great progress and achievements. However, many challenges and difficulties remain before realizing actual engineering practice. This paper firstly introduces the mainstream methods and characteristics of single-scale structural topology optimization, the basic idea and special position of homogenization methods, as well as the relationship between topology optimization methods for multi-scale structures and topology optimization methods for single-scale structures. Then, using the structural distribution characteristics as the classification criteria, this paper systematically sorted out the topology optimization design methods for three distribution forms of multi-scale structures: periodic, functional gradient and heterogeneous. For the important issues, including structural connectivity, applicability of multi-scale methods, and application of machine learning technology in multi-scale structural topology optimization, relevant research progresses are reviewed and discussed. Finally, pressing challenges and important research directions in the field are summarized and prospected.

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    Research progress of UAV aerial video multi⁃object detection and tracking based on deep learning
    Yubin YUAN, Yiquan WU, Langyue ZHAO, Jinlin CHEN, Qichang ZHAO
    Acta Aeronautica et Astronautica Sinica    2023, 44 (18): 28334-028334.   DOI: 10.7527/S1000-6893.2023.28334
    Abstract680)   HTML29)    PDF(pc) (2634KB)(399)       Save

    With the increasing convenience of data acquisition for aerial photography of Unmanned Aerial Vehicle (UAV), the multi-target detection and tracking technology based on the UAV platform has developed rapidly and has broad prospects for applications in civil and military fields. In recent years, the rapid progress of in-depth learning has also provided a variety of more effective solutions. However, the challenging problems such as sudden changes in the appearance of the target, serious occlusion of the target area, and disappearance and reappearance of the target from the perspective of UAV have not been completely solved. In this paper, we summarize the algorithms for multi-target detection and tracking in UAV aerial video based on deep learning, and summarize the latest progress in this field, including multi-target detection and multi-object tracking. The multi-object detection module is divided into two parts: two-stage and one-stage detection. For the multi-object tracking module, according to the two classical frameworks of tracking-based detection and joint-detection tracking, the principles of the two algorithms are described and their advantages and disadvantages are analyzed. Then, the existing public data sets are statistically analyzed, and the optimal schemes of the benchmark challenge VisDrone Challenge in the field of multi-target detection and tracking based on UAV aerial video in recent years are compared and analyzed. Finally, the paper discusses the urgent problems of multi-object detection and tracking from the perspective of UAV and the possible research directions in the future, providing a reference for the follow-up researchers.

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    Development needs and difficulty analysis for smart morphing aircraft
    Xuhui ZHANG, Chunlei XIE, Sijia LIU, Ming YAN, Siyuan XING
    Acta Aeronautica et Astronautica Sinica    2023, 44 (21): 529302-529302.   DOI: 10.7527/S1000-6893.2023.29302
    Abstract671)   HTML92)    PDF(pc) (11391KB)(1035)       Save

    With the development and application of artificial intelligent technologies in the military field, future intelligent warfare is to demonstrate the following traits: more complex cognition and decision making, more rapid changes and evolution, and access and denial in the whole warfare. The next-generation flight vehicles will be flight-demand oriented, artificial-intelligence centered, and changing flexible. Smart morphing aircraft, obviously characterized by intelligent technology and deformation technology, can have dual advantages of fast algorithm upgrades and extremely flexible hardware. It introduces new flight modes and combat capabilities, and will therefore become an important trend. However, smart morphing aircraft design requires complicated technologies. The costs of deformation, such as the increased complexity of the machine system, pose challenges to aerodynamic design, flight control, and structural implementation. The challenges include the full-profile optimization, structural application, and performance prediction and validation in the deformation process, where the core problem is to achieve the optimal design in each shape in the context of multidisciplinary engineering.

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    Research progress and engineering application of flow control technology for drag and heat reduction of high-speed vehicles
    Guangsheng ZHU, Shiyong YAO, Yi DUAN
    Acta Aeronautica et Astronautica Sinica    2023, 44 (15): 529049-529049.   DOI: 10.7527/S1000-6893.2023.29049
    Abstract659)   HTML98)    PDF(pc) (4577KB)(791)       Save

    Drag and heat reductions are two core issues in the design of high-speed flight vehicles. Drag reduction can enhance the lift-drag ratio of vehicles and decrease the fuel consumption, while heat reduction can reduce the weight of thermal protection system and promote the effective load of flight vehicles. Drag and heat reductions are the key technologies to improve the fine design and enhance the flight performance. This paper mainly reviews the research status of flow control technology for drag and heat reductions of shock wave and boundary layer, from the perspective of the engineering requirements for drag and heat reductions of high-speed flight vehicles. This paper also points out the existing problems in engineering application and the direction that should be paid close attention to in the future, to realize the engineering application of active flow control of flight vehicles and improve the flight performance.

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    General planning method for energy optimal flight path of solar⁃powered aircraft in near space
    Xianzhong GAO, Xiaolong DENG, Yujie WANG, Zheng GUO, Zhongxi HOU
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2023, 44 (8): 27265-027265.   DOI: 10.7527/S1000-6893.2022.27265
    Abstract652)   HTML40)    PDF(pc) (8136KB)(328)       Save

    Solar-powered aircraft is one of the most promising technical route for the development of low-speed aerial vehicle in near space, and is expected to be an ideal platform for regional communication, relay and transportation.N×24-hour energy closed loop is the crucial problem for the development of near space solar-powered aircraft,and is also a key technology for aircraft to have the ability of “regional maintenance & time sustainability”. The energy optimal flight path planning method is an effective technical route to solve the problem of day-night energy closed-loop of solar-powered aircraft in near space. Currently, there are two methods for energy optimal flight path planning: one is the method without considering the change of wind field, and the other is the method without considering the change of large-scale altitude. Analysis and comment are given to the research results of these two methods. In order to conquer the difficulties and challenges brought by these two different processing frameworks in practical engineering application, suggestion is proposed to build a uniform framework based on reinforcement learning to form a “general” flight path planning method. This framework should consider the changes of solar radiation, space altitude and wind field, and also the effects of energy stored by gravity potential and energy harvested from wind shear. The key technologies to achieve this aim are analyzed: The environmental characterization and reconstruction of wind field; the impact of near space gradient wind field on the energy of solar aircraft glide trajectory; The generation and classification of optimal flight path demonstration trajectory; the construction of solar aircraft reinforcement learning framework based on demonstration trajectory. This paper provides theoretical support for the design method of energy optimal flight path planning, and technical support for realization of high-altitude long-endurance flight.

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    Integrated aerodynamic and stealth optimization of aircraft based on NS/CFIE adjoint equations
    Jiangtao HUANG, Lin ZHOU, Xian CHEN, Chuang MA, Gang LIU, Zhenghong GAO
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2023, 44 (12): 127757-127757.   DOI: 10.7527/S1000-6893.2022.27757
    Abstract645)   HTML9)    PDF(pc) (5034KB)(274)       Save

    Advanced integrated aerodynamic and stealth design technology is the key link to realize the technical indexes of future combat aircraft, such as high stealth, high maneuverability, wide speed range and long range. This study derives the “coupled” adjoint equation of aerodynamic stealth based on the idea of interdisciplinary coupling adjoint. First, the adjoint equation of the flow field is constructed based on the Navier-Stokes equation. Through the variational processing of near-field vector multiplication, far-field vector multiplication, and the radar scattering area, the adjoint equation based on MLFMA is then developed. The electromagnetic adjoint equation of the algorithm, combined with the independently developed XSQP optimization framework and parametric modeling technology, constructs a highly reliable aerodynamic stealth comprehensive optimization technology platform. Taking a certain flying wing layout as the research object, we conduct the aerodynamic stealth integration test. The test results show that both the gradient calculation accuracy of the established accompanying platform and the optimization design efficiency are high, providing strong technical support for the aerodynamic stealth integration design of combat aircraft.

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    A survey of computational methods for spacecraft orbit ropagation and Lambert problems
    Haoyang FENG, Xuechuan WANG, Xiaokui YUE, Changtao WANG
    Acta Aeronautica et Astronautica Sinica    2023, 44 (13): 28027-028027.   DOI: 10.7527/S1000-6893.2022.28027
    Abstract638)   HTML48)    PDF(pc) (1027KB)(369)       Save

    Spacecraft orbit computation is a fundamental problem in the field of aerospace dynamics and control. Future space missions put forward higher demands for more accurate and real-time orbit computational methods. The research on new orbit computational methods with higher performances has significant application value for future aerospace engineering of China. This paper summarizes the research background of space orbit computation and then gives a systematic review of various types of computational methods for solving orbit propagation and Lambert problems. The advantages and disadvantages of these methods, as well as the development tendency of orbit computational methods are discussed. This paper can provide references for choosing suitable computational methods in specific aerospace tasks, as well as inspirations for designing novel and high-performance orbit computational methods.

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    An improved conflict⁃based search algorithm for multi⁃agent path planning
    Lianbo YU, Pinzhao CAO, Liang SHI, Jie LIAN, Dong WANG
    Acta Aeronautica et Astronautica Sinica    2023, 44 (S1): 727648-727648.   DOI: 10.7527/S1000-6893.2022.27648
    Abstract620)   HTML10)    PDF(pc) (4231KB)(271)       Save

    The multi-agent path planning problem is widely used in multi-machine tasks in the aerospace field, but it is difficult to solve the problem. The improved conflict-based search algorithm is designed to quickly solve the multi-agent path planning problem. In terms of global path planning, a multi-objective cost function is designed to give a comprehensive consideration of the sum of path costs and the make span, and a conflict classification and resolution scheme based on the unique shortest path is then proposed to reduce the computational cost of multi-agent path planning. In terms of online conflict resolution, the velocity obstacle method is used to detect and resolve the sudden conflict between agents and dynamic obstacles. Simulation results show that the algorithm proposed retains the optimality of the conflict-based search algorithm in global path planning and reduces the amount of calculation. Thus, this algorithm can effectively realize online conflict detection and resolution.

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