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Review of laser-metal additive manufacturing + X hybrid technology Acta Aeronautica et Astronautica Sinica    DOI: 10.7527/S1000-6893.2023.29349 Accepted: 13 December 2023

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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 Abstract （3155）   HTML （513）    PDF（pc） （26942KB）（2309）       Knowledge map    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. Reference | Related Articles | Metrics

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Thermal flutter ground simulation test Haoyu CHEN, Binwen WANG, Qiaozhi SONG, Xiaodong LI ACTA AERONAUTICAET ASTRONAUTICA SINICA    2023, 44 (8): 227295-227295.   DOI: 10.7527/S1000-6893.2022.27295 Abstract （424）   HTML （59）    PDF（pc） （4290KB）（1964）       Knowledge map    Save Ground flutter simulation test is a flutter verification experiment technology for real aircraft structures， which uses exciters to simulate unsteady aerodynamic force. In this paper， the thermal environment simulation scheme is used in this technology to establish the thermal flutter ground simulation system. An aerodynamic interpolation point optimization algorithm is proposed based on the weighting of modal shapes. An unsteady aerodynamic reduced-order model for time-varying structure is constructed by using the Kriging surrogate model. After the simulation scheme of aerodynamic thermal environment and the measurement method of high-temperature structure’s response signal are designed， the experiment system based on the titanium alloy wing model is completed. Finally， time-varying thermal flutter boundary tracking and testing is carried out. The testing results show that the testing accuracy is acceptable when the controller is within the preset frequency range， but the narrow control bandwidth of robust controller limits the application of the thermal flutter ground simulation test. Table and Figures | Reference | Related Articles | Metrics

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Current status and prospect of overseas research on aeronautical fatigue SUN Xiasheng, SU Shaopu, SUN Hanbin, DONG Dengke ACTA AERONAUTICAET ASTRONAUTICA SINICA    2021, 42 (5): 524791-524791.   DOI: 10.7527/S1000-6893.2020.24791 Abstract （2008）   HTML （102）    PDF（pc） （17003KB）（1519）       Knowledge map    Save Fatigue is one of the key factors affecting the performance of aircraft in research or service. In this article, firstly, the aeronautical accidents caused by fatigue were quoted as clues to state the evolution of structural strength design concept and research situation at each specific period. Meanwhile, international aeronautical fatigue research and their significant development as well as the future developing directions in areas since 21 century has been reviewed and evaluated in the aspects of structural long-life design, fatigue analysis approaches and tools, full-scale structural fatigue testing technology, structural health monitoring and life extension of aging aircraft. Conclusively, considering the current problems and potential development directions, the challenges resisting the realization of high requirement on the long life, lightweight and high reliability of future aircraft design were pointed out on four topics:aeronautical fatigue on evaluation basic research, design and application research, testing evaluation and digital technology, which provides technical materials for the development of aeronautical fatigue. Reference | Related Articles | Metrics

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Technical development of variable camber wing: Review WANG Binwen, YANG Yu, QIAN Zhansen, WANG Zhigang, LYU Shuaishuai, SUN Xiasheng ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (1): 24943-024943.   DOI: 10.7527/S1000-6893.2020.24943 Abstract （1975）   HTML （119）    PDF（pc） （36682KB）（1501）       Knowledge map    Save The Variable Camber Wing(VCW) remains a research hot-spot as it aims to ensure that aircraft acquire optimal aerodynamic efficiency in various flight conditions. The benefits brought by VCWs are firstly presented, and the demands of VCWs from different types of aircraft are classified and thoroughly described. The developing process of VCWs in the past decades are then reviewed in terms of the leading edge and the trailing edge, respectively, and the current major obstacles in application are listed. Further research directions are finally suggested. Reference | Related Articles | Metrics

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Material⁃structure integrated design for high⁃performance aerospace thin⁃walled component Weihong ZHANG, Han ZHOU, Shaoying LI, Jihong ZHU, Lu ZHOU ACTA AERONAUTICAET ASTRONAUTICA SINICA    2023, 44 (9): 627428-627428.   DOI: 10.7527/S1000-6893.2022.27428 Abstract （2218）   HTML （154）    PDF（pc） （4778KB）（1428）       Knowledge map    Save The rapid development of the next generation of aerospace technology has imposed more and more stringent requirements for such structural performance as the ultra-strong load-bearing， extreme heat-proof， ultra-precision and ultra-lightweight. Therefore， how to design and fabricate high-performance， lightweight， and ultra-precise aerospace thin-walled structures has become a common concern in the field of advanced material and structural design and manufacturing. This paper reviews the main achievements of high-performance design and manufacture of thin-walled components and their aerospace applications in recent years， focusing on the scientific issues including the mapping law between multi-scale structures and structural performance， the composed manufacturing principle of multi-material and multi-scale structures， and the interaction mechanism between material organization evolution and structural deformation. Moreover， the manufacturing process constraints in structural optimization， the influence of additive manufacturing process parameters on the structural optimization， the material-structure integrated design method of high-performance structures and its application in aerospace structures are discussed. The development prospects and applications of the material-structure integrated design and manufacturing methods of typical aerospace thin-walled structures in the future are also prospected， which can provide references for future related research and aerospace applications. Table and Figures | Reference | Related Articles | Metrics

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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 Abstract （2392）   HTML （290）    PDF（pc） （5160KB）（1367）       Knowledge map    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. Reference | Related Articles | Metrics

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Research progress and prospect of fatigue and structural integrity for aeronautical industry in China WANG Binwen, CHEN Xianmin, SU Yunlai, SUN Hanbin, YANG Yu, FAN Junling ACTA AERONAUTICAET ASTRONAUTICA SINICA    2021, 42 (5): 524651-524651.   DOI: 10.7527/S1000-6893.2020.24651 Abstract （1517）   HTML （94）    PDF（pc） （27012KB）（1348）       Knowledge map    Save In China, as the improvement of aeronautical industry, fatigue and structural integrity become one of the key problems that affect the life, safety and reliability of aircraft structures. After years of hard-working, aircraft design philosophy evolved gradually from static strength to safe-life, and now to fatigue and structural integrity as a guide. Aircraft structural integrity program has been implemented successfully into structural development for several new types. The service life, reliability and economy of the new generation aircraft structure have been improved significantly. However, with the improvement of aeronautical technology and the development requirements for new aircrafts, many new problems emerged in this area. From the perspective of aeronautical industry, this paper combs the progress and main achievements of aeronautical fatigue research in China, and focuses on the research status and engineering applications in the aspects of material/structure/process, analysis and evaluation method, fatigue test technology and service life management since 2000. Finally, some aeronautical fatigue research directions need to be focused on were proposed in order to provide reference for the further development of domestic aeronautical structures. Reference | Related Articles | Metrics

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Research progress of corrosion simulation of aircraft structures HUANG Hailiang, CHEN Yueliang, ZHANG Zhuzhu, ZHANG Yong, BIAN Guixue, WANG Chenguang ACTA AERONAUTICAET ASTRONAUTICA SINICA    2021, 42 (5): 524026-524026.   DOI: 10.7527/S1000-6893.2020.24026 Abstract （1060）   HTML （16）    PDF（pc） （8386KB）（1232）       Knowledge map    Save Current environmental adaptability assessment of military aircraft is usually carried out by means of outdoor exposure and laboratory acceleration. However, changes in structure design often necessitate reexamination test, which is both time and labor consuming. Corrosion simulation uses the finite element method or boundary element method to accurately predict the corrosion results in a relatively short time with basic electrochemistry theories, gaining favors from scholars home and abroad and finding applications in some fields in the US and European countries. This paper first focuses on the analysis of the current situation of simulation research on the common corrosion forms of aircraft at home and abroad, including galvanic corrosion, pitting corrosion, crevice corrosion and stress corrosion. The basic theories of corrosion simulation are then summarized, with the advantages and disadvantages of the mature commercial software of corrosion simulation compared. Finally, we point out four research difficulties of corrosion simulation, including dynamic interface tracing, multi-scale and multi-physical field corrosion simulation, corrosion simulation standardization, and engineering application in the field of aviation, hoping to provide a directional reference for further exploration of corrosion simulation. Reference | Related Articles | Metrics

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SST turbulence model improvements: Review Yu ZENG, Hongbo WANG, Mingbo SUN, Chao WANG, Xu LIU ACTA AERONAUTICAET ASTRONAUTICA SINICA    2023, 44 (9): 27411-027411.   DOI: 10.7527/S1000-6893.2022.27411 Abstract （2403）   HTML （114）    PDF（pc） （3131KB）（1177）       Knowledge map    Save The k-ω Shear Stress Transport （SST） turbulence model， one of the best eddy viscosity models with comprehensive performance， has been widely used in recent years. However， with the increase of problem complexity and simulation accuracy requirements， the standard SST turbulence model shows clear limitations in certain aspects， eliciting extensive improvement research. This paper reviews the improvement research of the SST model from six aspects： rotation/curvature effect， compressibility effect， shock wave unsteadiness effect， effect of anisotropy Reynolds stress， effect of stress-strain deviation， and laminar/turbulent transition effect. Meanwhile， it also briefly introduces the model improvement based on the data-driven technology in recent years， sorts out the ideas and development trends of various improvement research， expounds their applicability and limitations， and analyzes the reasons and problems affecting the improvement effect. Finally， some suggestions for future work are given. Table and Figures | Reference | Related Articles | Metrics

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Research progress in key technologies for conceptual-aerodynamic configuration design of supersonic transport aircraft Yulin DING, Zhonghua HAN, Jianling QIAO, Han NIE, Wenping SONG, Bifeng SONG ACTA AERONAUTICAET ASTRONAUTICA SINICA    2023, 44 (2): 626310-626310.   DOI: 10.7527/S1000-6893.2021.26310 Abstract （1325）   HTML （104）    PDF（pc） （9132KB）（1156）       Knowledge map    Save Next-generation Supersonic Transport Aircraft （STA） has become one of the main future directions for civil aviation transport. Compared with subsonic civil aircraft， STA involves a series of technical problems such as sonic boom and is confronted with more strict performance indexes， imposing higher requirements for the conceptual aerodynamic configuration design. This paper classifies the existing supersonic civil aircraft configurations in the world into three generations according to the design strategy and the main technical features. The first-generation configurations mainly adopt a delta wing/ double-delta wing platform to achieve supersonic civil flight and balance both high and low speed performance. The second-generation configurations take the low-boom and low-drag performance into consideration and employ the highly-swept arrow-wing tailless layout， while the third-generation focuses more on the multi-disciplinary comprehensive performance and the technical feasibility. Almost all these configurations adopt the T-tail or V-tail layout and the engine nacelle knapsack or tail crane layout. The technical bottlenecks and difficulties of the new generation STA conceptual-aerodynamic configuration design are then presented. The progress and state of the art of the conceptual design technology， low-boom design technology， supersonic drag reduction technology， and airframe-propulsion integrated design technology are reviewed. Finally， the development trend of a new-generation STA configuration is discussed， stressing some of the key scientific and technical issues to be broken through. Supersonic business jets or small and medium class STA will be the priority in the near future， with technical features approximating those of the third-generation configurations. Comprehensive performance and engineering realizability of factors such as sonic boom， drag reduction， airframe-propulsion integration， aeroelasticity， and man-machine efficacy should be the mainly concern in future research. Table and Figures | Reference | Related Articles | Metrics

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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 Abstract （734）   HTML （94）    PDF（pc） （11391KB）（1104）       Knowledge map    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. Table and Figures | Reference | Related Articles | Metrics

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Intelligent air combat decision making and simulation based on deep reinforcement learning Pan ZHOU, Jiangtao HUANG, Sheng ZHANG, Gang LIU, Bowen SHU, Jigang TANG ACTA AERONAUTICAET ASTRONAUTICA SINICA    2023, 44 (4): 126731-126731.   DOI: 10.7527/S1000-6893.2022.26731 Abstract （1721）   HTML （129）    PDF（pc） （4846KB）（1091）       Knowledge map    Save Intelligent decision-making for aircraft air combat is a research hotspot of military powers in the world today. To solve the problem of Unmanned Aerial Vehicle （UAV） maneuvering decision-making in the close-range air combat game， an autonomous decision-making model based on deep reinforcement learning is proposed， where a reward function comprehensively considering the attack angle advantage， speed advantage， altitude advantage and distance advantage is adopted and improved. The improved reward function avoids the problem that the agent is induced to fall to the ground by the enemy aircraft， and can effectively guide the agent to converge to the optimal solution. Aiming at the problem of slow convergence caused by random sampling in reinforcement learning， we design a value-based prioritization method for experience pool samples. Under the premise of ensuring the algorithm convergence， the convergence speed of the algorithm is significantly accelerated. The decision-making model is verified based on the human-machine confrontation simulation platform， and the results show that the model can suppress the expert system and the driver in the process of close air combat. Table and Figures | Reference | Related Articles | Metrics

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Lightweighting of aerospace and aeronautical equipment: Challenges and perspectives Weihong ZHANG, Changhong TANG Acta Aeronautica et Astronautica Sinica    2024, 45 (5): 529965-529965.   DOI: 10.7527/S1000-6893.2023.29965 Abstract （958）   HTML （156）    PDF（pc） （2009KB）（1076）       Knowledge map    Save Lightweight is a substantial theme in the research and development of aerospace and aeronautical equipment due to its decisive impact on the comprehensive performance and operational efficiency of the equipment. Over the past decades， a handful of innovative optimization design approaches， emerging high-performance materials， and revolutionary manufacturing technologies have been uninterruptedly developed， and the level of lightweighting in aerospace and aeronautical equipment has been significantly advanced. However， the increasing demands for comprehensive performance and multifunctionality of the next generation of equipment present serious challenges to existing lightweight design and manufacturing technologies. Therefore， with a particular emphasis on the layout design， electromechanical system design， materials and structures， high-performance manufacturing and assembly， this paper analyzes the posed challenges and future perspectives. Table and Figures | Reference | Related Articles | Metrics

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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 Abstract （1742）   HTML （93）    PDF（pc） （14513KB）（1070）       Knowledge map    Save 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. Reference | Related Articles | Metrics

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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 Abstract （1782）   HTML （108）    PDF（pc） （7660KB）（1067）       Knowledge map    Save 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. Reference | Related Articles | Metrics

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Progress and application of key technologies of SensorCraft Shuai HAO, Tielin MA, Yi WANG, Jinwu XIANG, Hongzhong MA, Baifeng JIANG, Jun CAO ACTA AERONAUTICAET ASTRONAUTICA SINICA    2023, 44 (6): 27034-027034.   DOI: 10.7527/S1000-6893.2022.27034 Abstract （1278）   HTML （100）    PDF（pc） （12633KB）（960）       Knowledge map    Save SensorCraft is an early warning and surveillance and information synthesis aircraft proposed by the Air Force Research Laboratory， with high ceiling and long endurance. It adopts the platform-payload integration technology， with the dual features of the aircraft and sensor. Coupling of multiple elements between platform and payload means that the overall layout design is different from that of the traditional Intelligence， Surveillance and Reconnaissance （ISR） vehicle. Flight conditions and performance indexes bring new challenges to the aerodynamic design. Aeroelastic problem of large aspect ratio flexible wing not only worsens flight performance， but also leads to loss of electromagnetic performance of wing conformal antenna. This paper summarizes the technical characteristics of SensorCraft， expounds the development history of the United States SensorCraft system from two aspects of the flight platform and conformal antenna. From the perspective of technical characteristics， key technologies supporting SensorCraft are sorted out， such as integrated layout design， laminar drag reduction， gust alleviation， conformal antenna design， deformation measurement & reconstruction， and electromagnetic performance compensation. Relevant applications are introduced. The development trend of this aircraft is also discussed in terms of the flight ability， stealth ability， perception ability and coordination ability of the aircraft， so as to provide reference for the new ISR aircraft. Table and Figures | Reference | Related Articles | Metrics

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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 Abstract （1856）   HTML （106）    PDF（pc） （74835KB）（952）       Knowledge map    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. Reference | Related Articles | Metrics

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A tutorial and review on robot motion planning Yongxing TANG, Zhanxia ZHU, Hongwen ZHANG, Jianjun LUO, Jianping YUAN ACTA AERONAUTICAET ASTRONAUTICA SINICA    2023, 44 (2): 26495-026495.   DOI: 10.7527/S1000-6893.2021.26495 Abstract （1112）   HTML （86）    PDF（pc） （4874KB）（948）       Knowledge map    Save As application scenarios become more complex， the need for autonomous motion planning techniques which aims at generating collision-free path （trajectory） becomes more urgent. Although a large number of planning algorithms adapted to different scenarios have been proposed already， how to properly classify the existing results and analyze the advantages and disadvantages of different methods is still a problem that needs in-depth consideration. In this paper， the basic connotation of motion planning and the key steps of classical algorithms are explained. Secondly， aiming at the contradiction between real-time performance and the quality of solution path （trajectory）， the existing algorithm acceleration strategies are analyzed and summarized hierarchically based on whether differential constraint is considered. Finally， facing the new requirements of planning under uncertainty （i.e.， sensor uncertainty， future state uncertainty and environmental uncertainty） and intelligent planning， the latest achievements and development direction in the field of motion planning are reviewed. It is expected that the review can provide ideas for future research. Table and Figures | Reference | Related Articles | Metrics

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Parallel HVDC electric power system for more-electric-aircraft: State of the art and key technologies ZHANG Zhuoran, XU Yanwu, YU Li, LI Jincai, XIA Yiwen ACTA AERONAUTICAET ASTRONAUTICA SINICA    2021, 42 (6): 624069-624069.   DOI: 10.7527/S1000-6893.2020.24069 Abstract （1784）   HTML （47）    PDF（pc） （17725KB）（942）       Knowledge map    Save The integration of onboard secondary energy is gradually realized by the More Electric Aircraft (MEA), improving the efficiency, reliability, and safety of energy utilization. The High-Voltage DC (HVDC) power supply system with outstanding advantages such as lightweight, low loss, and high reliability can, in principle, realize easier parallel operation of the Electric Power System (EPS), enabling the expansion of the power supply capacity in a multi-engine/multi-generator layout, and hence uninterrupted power supply. In addition, both the electric power quality and reliability of the EPS are improved. The characteristics and advantages of the HVDC EPS are analyzed in this paper, followed by a summary of the research status and the key technical issues of the HVDC parallel EPS. A dual-channel HVDC parallel EPS based on novel doubly salient brushless DC generators is proposed and implemented to achieve current sharing control of the system, and the dynamic responses during sudden load changes, paralleling in, and splitting out are examined. The research has proved that the HVDC parallel EPS provides good steady-state accuracy and dynamic performance, exhibiting important value in the MEA or All Electric Aircraft (AEA) applications. The dynamic behaviors, the modeling method, and the protection logic of the HVDC parallel EPS still require further research. Reference | Related Articles | Metrics