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    Development status, challenges and trends of strength technology for hypersonic vehicles
    SUN Cong
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (6): 527590-527590.   DOI: 10.7527/S1000-6893.2022.27590
    Abstract1030)   HTML286)    PDF(pc) (26942KB)(897)       Save
    As a type of hi-tech weapon, hypersonic vehicle plays an important strategic role in national security and benefits. It has now become a research hotspot in the field of aerospace, and the competition is becoming increasingly fierce all over the world. Advanced material and structure design is a basic key technology to support the development of hypersonic vehicle. The strength of materials and structures in extremely severe service environments is still a key issue restricting the development of this type of aircraft. This paper reviews the structure strength problems and evolution characteristics in the field of hypersonic vehicles in the past few decades. Combined with the current vehicle model development demand and technology development trend, this paper analyzes the current situation and shortcomings of structure strength technology in supporting the development of hypersonic vehicles and discusses the new requirements, new characteristics and new methods of strength problems in this field in the future. Finally, the future development direction in the field of hypersonic vehicle structure strength is proposed after summarization.
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    Sonic boom inversion technology based on inverse augmented Burgers equation
    Yiran GU, Jiangtao HUANG, Shusheng CHEN, Deyuan LIU, Zhenghong GAO
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2023, 44 (2): 626258-626258).   DOI: 10.7527/S1000-6893.2021.26258
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    Sonic boom has always been one of the obstacles restricting the development of supersonic airliners. Hence, the low sonic boom design technology is particularly important in the design of supersonic airliners. The inverse augmented Burgers equation can invert the mid-field sound pressure signal to the near-field and provide optimization objectives for the low sonic boom inverse design. This study uses the operator splitting technique and the pseudoparabolic equation method to numerically solve the inverse Burgers equation and calculate the corresponding reversed equivalent-area. With the assistance of the three standard examples, we investigate the convergence of the numerical method, the accuracy of the solution, and the calculation accuracy of the inversion technique at different field heights and different rolling angles. Based on the characteristics of the inverse augmented Burgers equation, the feasibility of setting target waveforms in the mid-field for the inverse design method is discussed, and the propagation characteristics of high-frequency components in the sound pressure signal are studied. The research shows that the above method can accurately complete the inversion calculation of the sound pressure signal from the mid-field to near-field, and that using mid-field target waveforms instead of ground target waveforms can reduce the influence of the inversion distance on the inversion calculation process.

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    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (3): 0-0.  
    Abstract288)      PDF(pc) (50325KB)(714)       Save
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    Technical innovations of the Tianwen-1 Mission
    ZHANG Rongqiao, GENG Yan, SUN Zezhou, LI Dong, ZHONG Wenan, LI Haitao, CUI Xiaofeng, LIU Jianjun
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (3): 626689-626689.   DOI: 10.7527/S1000-6893.2021.26689
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    Tianwen-1 is the first mission in the world to achieve the three goals of Mars orbiting, landing and roving in one mission, and has made some key-technology breakthroughs. The mission objectives and flight progress are introduced, and eight kinds of innovation achievements and the main technical breakthroughs are comprehensively summarized in this paper. Specifically, the key technologies include the overall design of Mars orbiting, landing and roving objectives strongly coupled, multi-trajectory launch of Earth escape orbit, interplanetary flight and Mars capture, Mars enter, descent and landing, solutions adaptive to Martian harsh environment, 400-million-kilometer communication, advanced payloads of remote sensing and patrol detection, and Mars environmental modeling and ground validation. The complete success of the mission has made China become one of the advanced countries in the field of deep space exploration.
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    Review of distributed hybrid electric propulsion aircraft technology
    ZHU Bingjie, YANG Xixiang, ZONG Jian'an, DENG Xiaolong
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (7): 25556-025556.   DOI: 10.7527/S1000-6893.2021.25556
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    Distributed hybrid electric propulsion system has great potential and advantage in development of general electric aviation. By the optimization of secondary power system, hybrid electric technology can not only heighten the utilization efficiency of energy, but also satisfied the distributed arrangement of power system for higher propulsive efficiency. The paper firstly summarized the current major types of electric aircraft, reviewed the history background of distributed electric propulsion aircraft. Then, the research status of distributed hybrid electric propulsion aircraft technology is summarized, this part mainly discussed the distributed layout technology of propulsion system, type-selection design of hybrid electric propulsion system, modeling and energy management of hybrid electric propulsion system, and so on. The key technologies of distributed hybrid electric propulsion at home and abroad are discussed fully. Eventually, combined with the research of the team, the difficult point problems and solutions of distributed hybrid electric propulsion aircraft are discussed in detail, including dynamic management strategy of energy based on complex system optimization control, optimal energy distribution prediction model driven by historical big data, and principle prototype designing of distributed hybrid electric propulsion system. The main content of this paper clarify the design thoughts and analysis method for distributed hybrid electric propulsion system and energy arrangement, which can provide references for the research of electric propulsion aircraft technology.
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    Current status, challenges and opportunities of civil aero-engine diagnostics & health management Ⅰ: Diagnosis and prognosis of engine gas path, mechanical and FADEC
    CAO Ming, HUANG Jinquan, ZHOU Jian, CHEN Xuefeng, LU Feng, WEI Fang
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (9): 625573-625573.   DOI: 10.7527/S1000-6893.2021.25573
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    The engineering advancements during the last two decades have presented opportunities as well as challenges for the Engine Health Management (EHM) system development of civil aero-engines. This R&D review provides an in-depth discussion on EHM needs, gaps and potential solutions/future R&D development directions, focusing on the "up-stream" EHM development modules: Engine gas path diagnostics and prognostics, mechanical diagnostics and prognostics, FADEC diagnostics and prognostics. Results shows the Unscented Kalman Filter (UKF) method and deep-learning neural networks have shown promises on improving the engine gas path diagnostics accuracy; composite fans have found widespread applications in turbo-fan engines; powder metallurgy has seen more and more applications on fabricating aero-engine parts with complex shapes; the accuracies of metal particle sensing technologies have witnessed significant improvements, with technology readiness level matching the aero-engine needs, and paved the way for fusion diagnostics with vibration signal. The result also show that electrification and intelligentization trends of FADEC system presents new challenges for the diagnostics of the traditionally centralized control architecture.
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    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (6): 0-0.  
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    Research status and prospect of fault diagnosis for gas turbine aeroengine
    LIN Jing, ZHANG Boyao, ZHANG Dayi, CHEN Min
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (8): 626565-626565.   DOI: 10.7527/S1000-6893.2021.26565
    Abstract748)   HTML78)    PDF(pc) (5160KB)(515)       Save
    Gas turbine engine is a comprehensive embodiment of the level of national science, technology and industry. Fault diagnosis is an important guarantee for its safe and reliable operation and an essential indicator of engine advancement. However, due to the complicated structure, highly integrated system, harsh service environment, variable mission profiles, the constraints of limited online testing conditions, and the poor supportability of diagnostic information acquisition, the fault diagnosis for aeroengine faces multiple challenges. In this paper, the research status in China and abroad is firstly reviewed and analyzed from three aspects: gas path analysis and performance evaluation, mechanical fault diagnosis and information fusion. Then, the exciting key problems and challenges in the current research are pointed out. Finally, the future development trends are discussed.
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    Plasma synthetic jet actuator for flow control: Review
    ZHOU Yan, LUO Zhenbing, WANG Lin, XIA Zhixun, GAO Tianxiang, XIE Wei, DENG Xiong, PENG Wenqiang, CHENG Pan
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (3): 25027-025027.   DOI: 10.7527/S1000-6893.2020.25027
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    Plasma Synthetic Jet (PSJ) actuators are a type of flow control device which generates high-temperature and high-speed zero-net mass flux jets using gas heating and pressurization of arc discharge in a semi-closed chamber. With advantages of high jet velocity, strong boundary layer penetration ability, fast response, wide actuation bandwidth and no moving parts, this device shows promising applications as a novel active flow control actuator. This paper presents a review of the recent progress in the research on plasma synthetic jet actuators. The optimization designs of plasma synthetic jet actuator systems for improving control authority, increasing energy efficiency and expanding environmental adaptability are summarized, the innovative research methods used in the investigations introduced, and the energy efficiency characteristics and the influence of parameters of the actuator presented. The applications of plasma synthetic jet actuators in various situations such as crossflow interaction, flow separation control, shock control and control of shock wave/turbulent boundary layer interaction are then reviewed. The interaction mechanisms between plasma synthetic jet and crossflow, separation bubbles and shock waves are discussed, followed by the analysis of the effects of momentum injection, blast waves and local heating of plasma synthetic jet in active flow control. The research trends are finally discussed.
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    Multibody separation dynamics: Review
    SONG Wei, AI Bangcheng
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (9): 25950-025950.   DOI: 10.7527/S1000-6893.2021.25950
    Abstract396)   HTML4)    PDF(pc) (12397KB)(482)       Save
    As an important dynamic problem, multibody separation dynamics often exists in the separation system of multibody vehicles in aerospace and weapon fields. Different from multibody system dynamics generally studying the motion law of multiple flexible and rigid bodies connected with each other, multibody separation dynamics is a highly integrated point of aerodynamics and flight dynamics. After unlocking and separation, the multibody vehicles no longer restrain or contact with each other, leading to air medium interaction between the multibody vehicles. The multibody separation process involves both aerodynamic interference (multibody aerodynamics) and relative motion between multiple bodies. This paper summarizes the key scientific problems and related technical difficulties of multibody separation dynamics according to the research requirements of multibody aircraft in the fields of aerospace and weapon systems. Firstly, the problems and main characteristics of several typical multibody vehicles (such as aircraft stores, multistage vehicles, aircraft with fairing, and multimissile vehicles) are presented, followed by a summary of the theoretical and experimental prediction methods of multibody separation dynamics. Then, the advantages and disadvantages of different research methods are analyzed. Finally, some views and future prospects are proposed.
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    Fundamental mechanical problems in high-performance aerospace composite structures: State-of-art review
    ZHAO Tian, LI Ying, ZHANG Chao, YAO Liaojun, HUANG Yixing, HUANG Zhixin, CHEN cheng, WANG Wandong, ZU Lei, ZHOU Huamin, QIU Jinhao, QIU Zhiping, FANG Daining
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (6): 526851-526851.   DOI: 10.7527/S1000-6893.2022.26851
    Abstract511)   HTML24)    PDF(pc) (74835KB)(482)       Save
    Benefitting from the superiorities brought by the organic fusion of different materials, high-performance composites are considered as an effective approach to achieving light-weight design, multi-functionality and intelligentization of aviation aircraft. However, the high anisotropy and multi-scale structural properties of the composites also produce significant problems and challenges for structural design, fabrication and characterization. The application and development of high-performance composite materials in aircraft is a multi-disciplinary problem involving, material science, mechanical engineering and control technology. Focusing on several related fundamental mechanical problems, this paper mainly presents a critical review on the recent research progress in mechanical design and property evaluation, functional design and manufacturing mechanics of aircraft composite structures. An outlook for the research directions in aircraft composite structures is provided in the final part.
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    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (10): 2-0.  
    Abstract175)      PDF(pc) (25160KB)(481)       Save
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    Effects of belly flap on take-off and landing characteristics of a flying-wing vehicle
    CHEN Xian, CHEN Cheng, HUANG Jiangtao, CHEN Qisheng, YU Longzhou, ZHONG Shidong
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (3): 125028-125028.   DOI: 10.7527/S1000-6893.2021.25028
    Abstract776)   HTML31)    PDF(pc) (13700KB)(468)       Save
    Taking a flying wing configuration model as the initial shape of flying wing configuration aircraft, the location and the deflection angle of belly-flaps in the take-off and landing process are studied by the method of numerical simulation, and the influence law of belly-flap deflection on elevator rudder effect and ground effect is obtained.The results show that when the belly-flap is located at 40% mean aerodynamic chord behind the center of gravity, a high lift enhancement efficiency can be maintained at high angles of attack, and there is a small change in the pitching moment.As the deflection angle of the belly-flap increases, the lift and the drag show a quasi linear growth, while the change of the pitching moment is small and can be trimmed by about 1° deflection of the elevator.When the belly-flap is deflected, the rudder efficiency of the elevator decreases by about 6%, and the increment of lift caused by ground effect increases, while the longitudinal static stability is decreased.
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    Development situation and future challenges of CAE software used in aeronautical structural analysis
    WANG Binwen, DUAN Shihui, NIE Xiaohua, GUO Yuchao
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (6): 527272-527272.   DOI: 10.7527/S1000-6893.2022.27272
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    Structural analysis CAE software is an important means of core technology research, a fundamental guarantee for major equipment development and key support for intelligent manufacturing advancement. The high-level autonomous and controllable (aviation) structural analysis CAE software is of great strategic significance to the leading innovation of aviation science and technology, and the integrity and safety of the equipment development system. By deeply combing the development process of domestic and foreign structural analysis CAE software deeply, this paper systematically analyzes the general development law of this software. Moreover, the challenges of this software are also pointed out from four dimensions, i.e. the complexity of the software itself, research and development cycle, the requirements of equipment, and the reliability. Meanwhile, the generalized connotation, overall idea and key technology of autonomous (aviation) structural analysis CAE software development are put forward from such three levels as the general analysis function group, special analysis tool chain and domestic data resource pool. Finally, based on the current world and national condition of industrial software and the law of scientific development, the prospect of autonomous controllable (aviation) structural analysis CAE software is offered.
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    Research progress of vision based aerospace conflict sensing technologies for small unmanned aerial vehicle in low altitude
    ZHANG Zhouyu, CAO Yunfeng, FAN Yanming
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (8): 25645-025645.   DOI: 10.7527/S1000-6893.2021.25645
    Abstract329)   HTML7)    PDF(pc) (13055KB)(410)       Save
    Unmanned Aerial Vehicles (UAV) aerospace conflict sensing is the most challenging key technology in national aerospace integration. Considering the broad application of small sized UAVs in low altitude aerospace, this paper makes a research survey of vision based aerospace conflict sensing technologies. Firstly, the application status of small sized UAVs in low altitude aerospace is briefly introduced, and the typical features of this kind of UAVs is summarized. Secondly, based on the categories of sensing objects, existing aerospace conflict sensing technologies are classified into cooperative sensing method and non-cooperative sensing method. The sensing technology most appropriate for small sized UAVs in low altitude aerospace is concluded. Then, the research progress of three key technologies of vision based aerospace conflict sensing, including visual information pre-processing, vision based intruder detection, vision based collision avoidance trajectory planning, are introduced. Finally, the challenges to be solved in this area are concluded, and several future research trends are introduced.
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    Aerodynamic design of laminar flow wings for jet aircraft: Review
    YANG Tihao, BAI Junqiang, DUAN Zhuoyi, SHI Yayun, DENG Yiju, ZHOU Zhu
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (11): 527016-527016.   DOI: 10.7527/S1000-6893.2022.27016
    Abstract388)   HTML8)    PDF(pc) (3137KB)(382)       Save
    The laminar flow technology is the core technology for the future development of "green aviation", and its huge drag reduction potential makes it a research hotspot in the aviation field. This article starts from the physical characteristics of flow and the nature of transition phenomena of jet airliners, and expounds the realization principle and application scope of the NLF and HLFC technology. The global research status and development trend of the NLF/HLFC technology are reviewed. Focusing on the cutting-edge issues of the CFD-based laminar flow wing design technology, we systematically discuss the laminar flow from multiple levels of engineering application-oriented transition prediction methods, gradient-free/gradient-based optimization methods, uncertainty analysis and the robust optimization method. Meanwhile, the similarities and differences between the laminar flow wing aerodynamic design and full turbulent aerodynamic design are discussed, and the aerodynamic design theories of the NLF and HLFC wing are then sorted out. Finally, based on the development trend of the jet airliner technology, the problems faced by the laminar flow design technology are summarized, and the future development direction and suggestions for the aerodynamic optimization design technology of laminar flow wings are presented.
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    Knowledge graph construction technology and its application in aircraft power system fault diagnosis
    NIE Tongpan, ZENG Jiyan, CHENG Yujie, MA Liang
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (8): 625499-625499.   DOI: 10.7527/S1000-6893.2021.25499
    Abstract635)   HTML14)    PDF(pc) (9686KB)(333)       Save
    The electrification degree of airborne equipment continues to increase with the development of science and technology. Owning to this, failure in aircraft power system is posing an increasing threat to flight safety, which granted necessity to fast and accurate health state assessment. The commonly used data-driven fault diagnosis method cannot make use of expert knowledge. Meanwhile, the result of data-driven method is lack of interpretability, and therefore, limits its application in real practice. Knowledge graph has the ability to normalize the storage of such unstructured data as expert knowledge and use it for diagnosis. Moreover, knowledge graph can utilize the unstructured knowledge and supply a reasonable explanation for the cause of the failure. However, in the field of fault diagnosis, there are still few studies on the application of knowledge graph technology. In this article, a knowledge graph construction and application technology for aircraft power system fault diagnosis is proposed. First, ontology of the knowledge graph, which specifies the entity and relation types in the knowledge graph, is constructed based on the priori expert knowledge. Then, Bi-Directional Long Short-Term Memory (Bi-LSTM) method is trained with BMEO-tagged corpus and utilized to extract entities from the unstructured texts. After that, an attention-based Bi-LSTM algorithm is trained with relation-tagged corpus and then utilized to realize relation extraction. Finally, the knowledge graph for aircraft power system fault diagnosis is constructed based on the extracted entities and relations. A fault isolation manual of aircraft power system is used as raw corpus data in the case study to verify the effectiveness of the proposed method by the indicators of precision and recall. Based on the knowledge graph, intelligent searching, recommending and Q & A are realized, which strongly support the application prospect of knowledge graph in the field of fault diagnosis.
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    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (5): 0-0.  
    Abstract283)      PDF(pc) (57088KB)(323)       Save
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    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (10): 1-0.  
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    Real-time dense small object detection algorithm for UAV based on improved YOLOv5
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    DOI: 10.7527/S1000-6893.2022.27106
    Accepted: 09 May 2022