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    Equivalent Degradation of Aviation Organic Coating During Indoor Accelerated Testing and Outdoor Exposure
    LUO Chen, CAI Jianping, XU Guangxing, ZHAO Liangliang, LIU Ming, SUN Zhihua, TANG Zhihui, LU Feng
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2014, 35 (6): 1750-1758.   DOI: 10.7527/S1000-6893.2014.0007
    Abstract882)      PDF(pc) (4096KB)(1124)       Save

    The relationship between indoor accelerated testing and outdoor exposure in terms of equivalent degradation in aviation organic coating is studied in order to provide fundamental data for the life prediction of aircraft skin. Long-term outdoor exposure and indoor accelerated testing of the coating are carried out, with surface morphology periodically examined. Electrochemical impedance spectroscopy (EIS) is used to quantitatively analyze the damage of organic coating. Thus, the degradation behavior of the coating in indoor accelerated testing and tropical marine atmosphere for 5 years is investigated. It is found that the central area of organic coating specimen is intact after 7 cycles of indoor accelerated testing and 5 years outdoor exposure, but exhibits significant decrease in electrochemical impedance modulus. The organic coating's correlation coefficient (ρ) between outdoor exposure and indoor accelerated testing is 0.77. The degradation of organic coating after 6 cycles of indoor accelerated testing is equivalent to that after 3 years outdoor exposure in Wanning, Hainan. 3 years outdoor exposure or 5 cycles of indoor accelerated testing led to the fact that the special frequence electrochemical impedance modulus |Z|f=0.1 of organic coating specimen is in the same order with |Z|f=0.1 of alloy substrate. Since then, the organic coating which is comprised of zinc yellow acrylic polypropylene and fluorinated polyurethane fails to protect the alloy any more.

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    Analysis of thermal comfort in aircraft cockpit based on the modified PMV index
    SUN Zhi, SUN Jianhong, ZHAO Ming, CHEN Yue
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2015, 36 (3): 819-826.   DOI: 10.7527/S1000-6893.2014.0135
    Abstract1185)      PDF(pc) (1254KB)(820)       Save

    To measure the thermal comfort of an aircraft cockpit with narrow space and high solar radiation for the pilot in the sky, the predicted mean vote (PMV) index has been studied in this paper. By increasing the effect of solar radiation in the human heat balance equation, an improved evaluation index PMV_F (PMV for Fighter) has been suggested in this paper. Meanwhile, numerical simulations as to an aircraft cockpit's flow field and temperature field have been taken by Reynolds average Navier-Stokes (RANS) method. The numerical simulation results are in a good agreement with the experimental data. The results of the PMV_F fit well with the status of pilot's thermal comfort. It shows that the method of numerical simulation based on the new evaluation index PMV_F can be used to analyze the thermal comfort in aircraft cockpit.

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    Acceleration response prediction for lunar lander using time-domain substructure methods
    DONG Weili, LIU Li, ZHOU Sida
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2015, 36 (3): 848-856.   DOI: 10.7527/S1000-6893.2014.0080
    Abstract2840)      PDF(pc) (1302KB)(667)       Save

    The remarkable increase in the complexity and size of spacecraft has inflicted unprecedented difficulties and challenges on system level dynamics simulation. At present, dynamic substructure method is mainly adopted to improve the solution efficiency and protect the proprietary technologies in model sharing among different project groups. The acceleration shock response spectrum is commonly used to describe the impact dynamic environment during the soft landing phase. It is acknowledged that the effects of high order modes on acceleration responses are more significant than those on displacement responses, so under the condition of small damping, the acceleration prediction accuracy is far lower than the prediction accuracy of displacement obtained by classical substructure methods based on modal with identical cut-off frequency. To solve this problem, a recently proposed novel method called impulse based substructuring (IBS) method is applied and its reduced-order form of iterative solution format used to predict acceleration is presented. Based on the buffer load measured from the soft landing numerical experiment, the acceleration response of the lunar lander is respectively calculated through the Craig-Bampton (CB) method and the IBS method. A numerical example shows that the IBS method has higher accuracy and efficiency than CB method, and it is suitable for rapid prediction for acceleration of the lunar lander with high accuracy.

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    An image autofocus algorithm using blind homomorphic deconvolution for synthetic aperture radar
    SHAO Peng, LI Yachao, LI Xueshi, XING Mengdao
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2015, 36 (5): 1606-1616.   DOI: 10.7527/S1000-6893.2014.0274
    Abstract1483)      PDF(pc) (6256KB)(542)       Save

    Synthetic aperture radar (SAR) image suffers from the deterioration due to the unknown phase error caused by unstable platform and atmosphere perturbation. A novel autofocus algorithm is presented in this paper to obtain phase error. The proposed algorithm is put forward based on the differences of smoothness properties for log-spectrum of motion error and image reflectivity. The differences could be employed to discriminate the motion error and reflectivity function. The log-spectrum of motion error is a slow-varying function, while the log-spectrum of image reflectivity owns some statistical properties which is similar to jagged function distribution. Then, motion error can be separated by applying a proper smoothing filter to the log-spectrum of blurred image. We set up a model that the log-amplitude spectrum and phase of spectrum for blurred image are processed through different smoothing filter functions. The log-spectrum of amplitude is recovered by current de-noising algorithms and phase is restored through phase-unwrapping and smoothing filter. It is demonstrated that the amplitude and phase of motion error can be reliably restored from the blurred SAR image and refiectivity function of image can be accurately reconstructed. In this paper, Riesz basis is constructed by scaling function of Daubechies wavelet function. An orthogonal subspace is built. Finally, a smoothing filter is applied to the derivative of compressed data. Then, motion error can be obtained. In order to demonstrate the performance of the proposed method, simulation data and real data are processed to verify the proposed algorithm. The analysis illustrates that this algorithm could obtain accurate motion error and possesses higher implementation efficiency.

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    Development of future fighters
    YANG Wei
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2020, 41 (6): 524377-524377.   DOI: 10.7527/S1000-6893.2020.24377
    Abstract10969)      PDF(pc) (4047KB)(13438)       Save
    Recent years have witnessed extensive discussions on the change of warfare forms and the development of post-4th generation fighters against the background of great power competition and batches of 4th generation fighters entering service. This paper reviews the origin of fighter generation classification and the driving elements behind each generational leap, outlining the evolution of Observe, Orient, Decision, Act (OODA) loops for air combat and proposing the essence of OODA 3.0. After a summary of the supportive and progressive relations among mechanization, informatization and intelligentization, it explores the dialectical relationship among autonomy and manned/unmanned, as well as that among platform, system of systems, and distributed operation, followed finally by a discussion of an agile and efficient development approach of future fighters.
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    Influencing factors of active cooling at leading edge of hypersonic vehicles
    LUO Shibin, MIAO Zhichao, SONG Jiawen
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (12): 627023-627023.   DOI: 10.7527/S1000-6893.2022.27023
    Abstract287)   HTML5)    PDF(pc) (8522KB)(131)       Save
    The active cooling technology is the key development direction of hypersonic vehicles, and the combination of different active cooling technologies can achieve complementary advantages and provide effective thermal protection for the leading edge of vehicles with high heat flux. This study examines the film-transpiration combined cooling structure on the leading edge of hypersonic vehicles. The CFD numerical calculation model is established to study the influence of angles of attack of 0°, 4°, and 12° on the combined cooling effect, and the combined cooling effect of configurations with different upper wedge angles on the leading edge is analyzed. The results show that the angle of attack increases the temperature difference between the upper and lower halves of the leading edge model. The maximum temperature difference between the upper and lower walls is 639.2 K. The change in the angle of attack affects the flow distribution of the coolant in the structure by influencing the distribution of outside wall pressure. Increasing the upper wedge angle of the leading edge will reduce the distance of the coolant to the downstream of the porous medium. There is an approximate linear growth trend of the outside wall temperature with the increase of the upper wedge angle.
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    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2023, 44 (2): 0-.  
    Abstract50)      PDF(pc) (283520KB)(76)       Save
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    Review of aircraft battle damage assessment and repair estimation and design technology
    ZU Guangran, PEI Yang, HOU Peng
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2020, 41 (6): 523455-523455.   DOI: 10.7527/S1000-6893.2019.23455
    Abstract2053)      PDF(pc) (5134KB)(1163)       Save
    Aircraft Battle Damage and Repair (ABDR) is one of the important means to improve aircraft survivability and combat capability. The research on ABDR technology covers the whole life stage of the aircraft. The research history and current advances are reviewed in this paper. The key points of ABDR system research are summarized from the aircraft battle damage assessment, aircraft design for battle damage repair, and aircraft battlefield rapid maintenance and support. Attentions are paid to the aircraft battle damage and repair pre-assessment technologies, field evaluation techniques of ABDR, the criteria and principles of aircraft design for battle field repair, evaluation method of aircraft design for battlefield damage and repair, aircraft expedient repair technologies, aircraft battle repair support method, etc. Furthermore, considering the system-of-system combat and intelligent combat environment in the future, the problems of aircraft battle damage and repair deserving further investigations are proposed, such as advanced materials structures aircraft battle damage and repair technologies, ABDR technology in helicopter, and the application of artificial intelligence in aircraft battle damage assessment and interdisciplinary technology in ABDR.
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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
    Abstract293)   HTML4)    PDF(pc) (9132KB)(212)       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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    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
    Abstract180)   HTML8)    PDF(pc) (5119KB)(107)       Save

    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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    Rotor-wing aerodynamic interference characteristics in conversion mode
    LIU Jiahao, LI Gaohua, WANG Fuxin
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (12): 126097-126097.   DOI: 10.7527/S1000-6893.2021.26097
    Abstract192)   HTML14)    PDF(pc) (13426KB)(117)       Save
    A high-resolution numerical simulation was carried out for the aerodynamic interference phenomenon between rotor and wing of the tilt-rotor aircraft in the conversion mode. The integral form unsteady Navier-Stokes equations are discretized by the finite volume method, and the relative motion between the rotor blade and the wing is processed by overlapping grids. The Cartesian structured grid based on the octree structure is adopted for background grids, and the grid self-adaptive technology based on the non-dimensional Q criterion is used to obtain high-resolution wake. First, the hover states of the isolated rotor and the rotor-wing combination are calculated. According to the calculation results, the accuracy for rotor aerodynamic prediction and the high-resolution characteristics for rotor wake structure evolution of high-resolution solver are proved. The calculation results of IDDES and RANS in the hovering state of rotor wing assembly are compared. The flow field obtained by IDDES is shown to be more accurate, and the aerodynamic results obtained with IDDES are also different from the RANS results. Subsequently, simulations of the flight states of rotor-wing assembly with different tilt angles in the conversion mode are carried out. Then, the aerodynamic interference flow field between the rotor and the wing is obtained and analyzed. The results show that the induced slipstream produced by the rotor in the middle of the conversion state has a certain lift gain effect on the wing, but there is no obvious lift gain at the beginning and end of tilt-state and there is even negative gain at the beginning. The aerodynamic variation of rotor and wing shows that rotor-wing aerodynamic interference in the conversion mode has an important influence on the aerodynamic performance of tilt-rotor.
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    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (6): 0-0.  
    Abstract311)      PDF(pc) (77175KB)(523)       Save
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    Status and development of laminar flow wing design technology
    DENG Yiju, DUAN Zhuoyi, AI Mengqi
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (11): 526778-526778.   DOI: 10.7527/S1000-6893.2021.26778
    Abstract341)   HTML34)    PDF(pc) (1621KB)(314)       Save
    The importance and necessity of aircraft drag reduction design are emphasized by analyzing the target of aircraft drag reduction proposed by green aviation, and the laminar wing technology is considered an important approach to aircraft drag reduction. After reviewing the development of laminar wing design, research, and verification, this paper identifies the gap and technical problems between the laminar wing technology and the aircraft design industry. The potential and development direction of the laminar wing technology are analyzed, and the feasibility of this technology in future aircraft design evaluated.
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    Recent development of unmanned aerial vehicle swarms
    JIA Yongnan, TIAN Siying, LI Qing
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2020, 41 (S1): 723738-723738.   DOI: 10.7527/S1000-6893.2019.23738
    Abstract2355)      PDF(pc) (4041KB)(1885)       Save
    Swarm as a typical collective behavior is omnipresent in animal kingdom, such as fish schooling, bird flocking, and bee swarming. In a colony, large-scale synchronous behavior emerges by virtue of local sensing and very simple communication rules. Inspired by these collective performances, the swarm of unmanned aerial vehicles is proposed as a new combat pattern. These unmanned aerial vehicles are characterized by large quantity, low cost, high speed, well adaptability, and convenient carried/launched mechanism, contributing to the scale advantage of UAVs and the possession of war initiative In recent years, many military powers, such as China, Russia, United States, have made great effort to the continuous development of swarm-related technology of unmanned aerial vehicles. To resolve the swarming problem of unmanned aerial vehicles, this paper introduces the research motivations of UAVs, summarizing the research approaches from modeling, control protocol, and execution platform. Besides, several classical combat modes and involved key technologies are discussed in detail. Above all, the swarm-related technology has bright application potential in the military area, leading to a brand new combat pattern.
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    Hybrid particle swarm algorithm for multi-UAV cooperative task allocation
    ZHANG Ruipeng, FENG Yanxiang, YANG Yikang
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (12): 326011-326011.   DOI: 10.7527/S1000-6893.2021.26011
    Abstract210)   HTML5)    PDF(pc) (6535KB)(160)       Save
    This paper proposes a hybrid particle swarm optimization algorithm for solving the Multi-UAV Task Allocation Problem (MTAP), which takes flight range, task revenue, and task completion time window into consideration. First, particle positions are encoded as a set of task assignment vectors, and a deadlock detection and repair algorithm based on digraphs of multi-strike tasks is designed for the possible deadlock problem of simultaneous strike scenarios, decoding the corresponding set of feasible task assignment solutions or schemes to realize the discretization of particle swarm algorithm solutions. Then, to overcome the drawback of premature convergence for traditional Particle Swarm Optimization (PSO), a policy of jumping local optimum is proposed based on variable neighborhood search, so that the balance between jumping local convergence and computational cost is achieved. Finally, an Hybrid Partide Swarm Optimization(HPSO) is obtained by embedding the proposed strategy into traditional PSO, which can be used to solve the underlying MTAP. A local task reassignment method based on the matching strategy is also designed for failure of the initial plan caused by new target discovery. Simulation experiments show that the proposed HPSO algorithm can effectively solve the task assignment problem in heterogeneous multi-UAV simultaneous strike scenarios.
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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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    Radar cross-section effect of canard
    GUO Zhanzhi, CHEN Yingwen, MA Lianfeng
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2020, 41 (6): 523485-523485.   DOI: 10.7527/S1000-6893.2019.23485
    Abstract3907)      PDF(pc) (4964KB)(2242)       Save
    This paper studies the Radar Cross-Section (RCS) effect on canard configuration fighter of canard. First, the scattering mechanism of canard is analyzed. And then, the Multi-Level Fast Multipole Method (MLFMM) is used to compute the configuration’s RCS of the given fighter models. And by comparing the computational results of both the canard configuration and the conventional configuration, the RCS effect of canard is analyzed, focusing on the RCS effect on fighter after the canard is rotated. In addition, a full-size parts stealth test is conducted by researching the RCS effect on fighter of both edge scattering and gap scattering and respective inhibition measures. The test results show that, after the scattering of canard is inhibited, the RCS level of canard configuration can be applied to configuration design of stealth fighter. And its stealth capacity is comparable with that of the conventional configuration. Finally, the guiding principles of canard stealth design are postulated.
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    Key technology and future development of regional airliner
    Yong CHEN, Kelin ZHONG, Yue LUO, Miao WANG
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2023, 44 (2): 26697-026697.   DOI: 10.7527/S1000-6893.2022.26697
    Abstract96)   HTML3)    PDF(pc) (7579KB)(97)       Save

    With the surge in market demand and the support of national policies, regional aviation is about to enter a period of rapid development. As a core technology product in the regional aviation market, the regional airliner is not only the key to the global regional market, but also an important business card that reflects the economic and technological strength of the country. Based on the development history of the regional airliner, this paper analyzes the missions of the regional airliner, and elaborates on the three key technologies including overall aerodynamics, powerplant systems, and airborne systems. Then, the technical development direction of regional airliners is discussed in the context of development of commercial aircraft. Finally, according to the future development needs, the concept of regional jet airliner mission system characterized by automation, autonomy and artificial intelligence is proposed.

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    Research progress and perspective of robotic equipment applied in aviation assembly
    WANG Hao, CHEN Genliang
    ACTA AERONAUTICAET ASTRONAUTICA SINICA    2022, 43 (5): 626128-626128.   DOI: 10.7527/S1000-6893.2021.26128
    Abstract361)   HTML176)    PDF(pc) (14672KB)(226)       Save
    Robotic equipment has many advantages, such as high level of automation, good movement flexibility, high positioning accuracy, and flexible production layout. Besides, it has a wide range of applications in the assembly process of aviation products. This paper summarizes the application status of robotic equipment in the automated assembly of aerospace products from the automatic docking equipment for large parts, robot assembly theory, human-machine collaboration technology, aero engine automatic assembly systems, artificial intelligence auxiliary systems and AGV. On this basis, this paper analyzes the evolution process and development trend of mechanism configuration in docking assembly equipment in detail, and systematically compares the technological gap between domestic and foreign aviation industry in the field of automatic assembly from the aspects of application scenarios, technology maturity and equipment performance. Finally, this paper summarizes the technical challenges and development trends of robotic equipment in aviation assembly, as well as the development opportunities that integrate with emerging technologies such as Industry 4.0 and intelligent manufacturing.
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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
    Abstract443)   HTML183)    PDF(pc) (15156KB)(453)       Save
    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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