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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
    Abstract3122)   HTML512)    PDF(pc) (26942KB)(2303)       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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    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
    Abstract2362)   HTML114)    PDF(pc) (3131KB)(1168)       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.

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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
    Abstract2330)   HTML285)    PDF(pc) (5160KB)(1358)       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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    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
    Abstract2186)   HTML154)    PDF(pc) (4778KB)(1411)       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.

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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
    Abstract2107)   HTML17)    PDF(pc) (4502KB)(523)       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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    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
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    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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    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
    Abstract1746)   HTML107)    PDF(pc) (7660KB)(1063)       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.
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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
    Abstract1727)   HTML93)    PDF(pc) (14513KB)(1069)       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.
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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
    Abstract1493)   HTML65)    PDF(pc) (9686KB)(690)       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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    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
    Abstract1448)   HTML52)    PDF(pc) (5498KB)(414)       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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    Current status, challenges and opportunities of civil aero-engine diagnostics & health management Ⅱ: Comprehensive off-board diagnosis, life management and intelligent condition based MRO
    CAO Ming, WANG Peng, ZUO Hongfu, ZENG Haijun, SUN Jianzhong, YANG Weidong, WEI Fang, CHEN Xuefeng
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (9): 625574-625574.   DOI: 10.7527/S1000-6893.2021.25574
    Abstract1339)   HTML135)    PDF(pc) (21809KB)(842)       Save
    Based on a comprehensive coverage of the civil aero-Engine Health Management (EHM) needs and goals, this research and development review first analyzes the current status quo & industry trends from the perspectives of the full blown Condition Based Maintenance Plus (CBM+) process, then addresses the challenges and gaps, and points out the critical paths for the future EHM research and development. Furthermore, this research and development review provides in-depth discussions on needs, gaps, and potential EHM solutions/future developments of the three "down-stream" EHM development modules: off-board comprehensive diagnostics, engine life management, intelligent condition based mro (maintenance, repair, overhaul).
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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
    Abstract1317)   HTML104)    PDF(pc) (9132KB)(1145)       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.

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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
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    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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    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
    Abstract1248)   HTML100)    PDF(pc) (12633KB)(955)       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.

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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
    Abstract1095)   HTML86)    PDF(pc) (4874KB)(941)       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.

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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
    Abstract1076)   HTML57)    PDF(pc) (7472KB)(461)       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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    Development and prospect of metal spinning: Additive hybrid manufacturing technology for complex thin⁃walled component with high ribs
    Zhongqin LIN, Zhongqi YU, Donghua DAI, Xiaoguang FAN, Shengfu YU, Dongdong GU, Shuhui LI, Yusheng SHI
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2023, 44 (9): 627493-627493.   DOI: 10.7527/S1000-6893.2022.27493
    Abstract1059)   HTML100)    PDF(pc) (11399KB)(655)       Save

    Complex thin-walled component with high ribs has wide application prospect in aerospace vehicles. Integral forming is an important technology to realize the lightweight component processing, and is also one of the engineering challenges in current manufacturing field. In integral manufacturing processes, metal spinning-additive hybrid manufacturing represents the academic frontier and development trend of the integral forming of complex thin-walled component with high ribs. In recent years, the research teams of the authors work on the spinning-additive hybrid manufacturing of complex aerospace thin-wall cylinder. This paper reviews the research status of spinning of stiffened cylinder and transformative-additive hybrid manufacturing, respectively, and systematically introduces the preliminary achievements of our teams, including the fracture mechanism and microstructure evolution of aluminum alloy stiffened cylinder during the flow spinning, the thermodynamic behavior and microstructure control during additive manufacturing based on the inner wall of spun cylinder, and spinning-additive hybrid manufacturing process; and prospects the development of spinning-additive hybrid manufacturing as well. Furthermore, this paper presents the technology status and trend of the hybrid manufacturing of complex thin-walled cylinder with high ribs, which provides a guide for developing integral forming technology of complex thin-walled components.

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    Progress in hypersonic boundary layer transition delay control
    LIU Qiang, TU Guohua, LUO Zhenbing, CHEN Jianqiang, ZHAO Rui, YUAN Xianxu
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (7): 25357-025357.   DOI: 10.7527/S1000-6893.2021.25357
    Abstract1056)   HTML39)    PDF(pc) (5986KB)(453)       Save
    Due to the large difference between laminar flow and turbulent flow in wall friction and wall heat flow, the transition control of the hypersonic boundary layer is of vital importance to the aerodynamic performance and thermal protection system of vehicles. This paper first summarizes the main instability mechanisms of hypersonic boundary layers, followed by a review of the latest progress in the hypersonic boundary layer transition delay control technology from two aspects, namely, passive control and active control technologies. Passive control methods such as roughness elements, wavy wall, and porous coating are then introduced in detail, the active control measures such as wall heating/cooling and heavy gas injection described, the physical mechanism behind the control analyzed, and the advantages and disadvantages of various control technologies discussed. Finally, suggestions and prospects for further research on transition delay control are presented.
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    A review of online blade tip clearance measurement technologies for aeroengines
    DUAN Fajie, NIU Guangyue, ZHOU Qi, FU Xiao, JIANG Jiajia
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (9): 626014-626014.   DOI: 10.7527/S1000-6893.2021.26014
    Abstract951)   HTML43)    PDF(pc) (9945KB)(542)       Save
    Blade tip clearance is a key parameter in the process of aeroengines design and test, which directly affects the efficiency and safety. Real-time online monitoring of blade tip clearance for aeroengines has become an essential item in the test program. With the development of new aeroengines, blade tip clearance measurement technologies become more mature and in-depth. This paper introduces the basic measurement principle of blade tip clearance, describes the typical structure and common measurement process of the system, and summarizes six key technologies of the online blade tip clearance measurement. Measurement methods including the discharge probe method, the optical fiber method, the capacitance method, the eddy current method and the microwave method are analyzed in details to introduce their working principles, characteristics, research progress and future research directions. Research results and the latest products of various measurement methods are compared and summarized. The development trend and prospect for blade tip clearance measurement are put forward. Key research directions of the blade tip clearance measurement are summarized from six aspects, which provide references for the follow-up research.
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    Multi-ducted twin-turbines ejector-ramjet/scramjet combined cycle engine for hypersonic civil vehicles
    Zeyong YIN, Yancheng YOU, Chengxiang ZHU, Jianfeng ZHU, Liaoni WU, Yue HUANG
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2023, 44 (2): 627181-627181.   DOI: 10.7527/S1000-6893.2022.27181
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    The reusable turbine-based combined cycle engine for wide-space/speed range aircraft is a revolutionary technology attracting global attention. Firstly, this paper briefly describes the state-of-the-art of turbine-based combined cycle engines, and then focusing on the technical characteristics and research progress of the presented Multi-ducted Twin-Turbines Ejector-Ramjet/scramjet (MUTTER) combined cycle engine for hypersonic civil aircraft. Different from conventional turbine-based combined cycle engines,MUTTER uses the distinctive symmetrical configuration of four engine ducts. An ejector engine is placed in the ramjet duct to bridge the thrust gap between the twin turbine engines and the ramjet/scramjet engine. A scaled and staged research and verification plan is introduced, and the study on the core sub-systems shows that the inlet and nozzle sub-systems can work stably and efficiently in the wide-space/speed range, and the ejector ramjet engine sub-system can effectively match with other sub-systems. In addition, the aircraft/engine integration features of the present combine cycle engine are discussed. Finally, some conclusions are drawn from our previous work.

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