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  • Summary and Future Development of On board Information Fusion for Multi satellite Collaborative Observation
  • HE You, YAO Li bo, LI Gang, LIU Yu, YANG Dong, LI Wen feng
  • 2021, 42 (1): 1-10. doi: 10.3873/j.issn.1000-1328.2021.01.001
  • Abstract ( 1543 ) PDF (3941KB)( 1228 )
    On board information fusion for multi satellite which is based on spatial computing mode can improve the satellitescapability such as the accuracy of detection, the confidence of recognition, the precision of position and the coverage of spatial temporal for disaster monitoring, maritime surveillance and other emergent or continuous persistent observing situations. Firstly, the necessity of on board information fusion is analyzed. Secondly, the on board processing developments are summarized and the existing problems are discussed. And thirdly, the key technology and concepts of on board information fusion are studied in the fields of target feature representation, target association, feature level fusion, autonomous mission planning and other issues. Finally the future developments of on board information fusion are studied and discussed.
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  • Summary of Key Technologies for Heterogeneous Unmanned System Cooperative Operations
  • GUO Ji feng, ZHENG Hong xing, JIA Tao, YAN Peng
  • 2020, 41 (6): 686-696. doi: 10.3873/j.issn.1000-1328.2020.06.006
  • Abstract ( 178 ) PDF (1757KB)( 919 )
    Based on the scale and heterogeneity of the heterogeneous unmanned systems, this paper classifies the heterogeneous unmanned systems, proposes the composition and application assumptions of the cooperative combat teams of the heterogeneous unmanned systems. Based on the problem of the coordinated operations of the heterogeneous unmanned systems in urban environments, the challenges and solutions for the coordinated operations of the heterogeneous unmanned systems are proposed. Based on this, the key technologies of the heterogeneous unmanned system cooperative operations are analyzed from the main aspects of coordinated control architecture, coordinated task planning, intelligent interaction, target perception, and environmental awareness of the heterogeneous unmanned systems. Finally, the current research progress and challenges of the heterogeneous unmanned system cooperative operations are summarized.
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  • Dynamic Analysis of Spinning Deployment of Space Web
  • QIN Zhi wei, LIU Zhen, SUN Guo peng, QI Yu feng
  • 2021, 42 (1): 41-49. doi: 10.3873/j.issn.1000-1328.2021.01.005
  • Abstract ( 300 ) PDF (5459KB)( 840 )
    In the launching scheme of using a pyrotechnic device to project a space web, there are some problems such as the large shock between the space web system and the satellite platform, the short maintenance time of the web configuration after deployed, etc. This paper presents a scheme for unfolding a space web through four controllable rotary tubes to overcome the above problems. An analytical model based on the Lagrange dynamics equation and finite element (FE) models using the central difference algorithm are developed and compared together. The results of the angular velocity of the rotary tubes and the length of the web arms are very consistent when the web arms are analyzed with the analytical model and the FE model, which proves that the simulation model construction method is effective. The topology and control strategy of the space webs are optimized under the FE web model, so that the state after deployment of the space webs can be maintained for a long time.
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  • Review and Prospects of Development of Space On orbit  Manufacturing Technology
  • YANG Xing wen, HAN Jing tao, LIU Jing, ZHANG Cong fa, LIANG Jin chao
  • 2021, 42 (11): 1343-1354. doi: 10.3873/j.issn.1000-1328.2021.11.001
  • Abstract ( 522 ) PDF (8140KB)( 830 )
    In this paper mainly starting from the development background and practical significance of space on orbit manufacturing technology, the development of on orbit manufacturing technology is classified, summarized and commented from the four aspects of on orbit 3D printing, on orbit welding, on orbit strip based plastic forming, and on orbit in situ manufacturing. A series of bottleneck problems encountered in the current development process are pointed out, and the future development trends are predicted. Combining with the successful experiences of foreign on orbit manufacturing technology, this article finally gives out the areas that need to be paid attention and the direction of efforts in the development of China’s on orbit manufacturing technology. It is expected to provide a useful reference for the layout of China’s space on orbit manufacturing technology.

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  • Flight Mission Planning for Solar System Boundary Exploration

  • TIAN Bai yi, WANG Da yi, ZHANG Xiang yu, ZHOU Wen yan, ZHU An wen, HUANG Mei li, WANG Ying
  • 2021, 42 (3): 284-294. doi: 10.3873/j.issn.1000-1328.2021.03.003
  • Abstract ( 394 ) PDF (5888KB)( 801 )
    Mission planning of interplanetary multi objective flyby is carried out for solar system boundary exploration, and the optimization of low thrust interplanetary transfer orbit combined with planet gravity assistance is completed. Based on the above research, the interplanetary flight schemes for the exploration of the tip and tail of the heliosphere are given. The results show that a probe launched during 2024-2025 and 2027-2030 can arrive at about 100 AU from the solar center before 2049, and touch the nasal tip and tail of the heliosphere. Among them, the tip explorer is located in the central region of the nose tip when it flies to the distance of 100 AU, which can effectively complement the Voyager 1 and Voyager 2. The mission planning method used in this paper can provide the basis for the autonomous mission planning technology of solar system boundary exploration, and the relevant research results can provide valuable reference for the implementation of the first solar system boundary exploration mission in China in the future.
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  • Development of Flight Control Technology of Long March Launch Vehicles
  • SONG Zheng yu, PAN Hao, WANG Cong, GONG Qing hai
  • 2020, 41 (7): 868-879. doi: 10.3873/j.issn.1000-1328.2020.07.005
  • Abstract ( 381 ) PDF (4834KB)( 791 )
    This paper firstly introduces the family of the new-generation Long March launch vehicles (LMLVs), and then reviews the evolution of their control systems from four aspects. The guidance method has developed from open-loop guidance, to iterative guidance, raising a variety of algorithms satisfying the large thrust direct injection and/or terminal attitude constraints, and greatly reducing the orbit injection errors. Based on the PID technology, the space modal and equivalent swing angle modeling are adopted in the attitude control method, to solve the problems of joint swing with side and core boosters’ engines; and an active load relief proposal is presented by combining with active-disturbance-rejection controller (ARDC). China’s Manned Space Program promotes the study on systematic reliability design, and a technical system has been formed gradually with the features of redundant devices, fault-tolerant algorithms, and onboard system reconfiguration, thus boosting the overall reliability improvement on the control system. The avionics system develops from the discrete, centralized architecture, to the integrated, distributed digital system. Finally, according to the current research focus in the aerospace control technologies, the latest practices and the prospects of LMLV’s flight control technology are summarized.
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  • Review and Prospect of Missile/Launch Vehicle Guidance, Navigation and Control Technologies
  • MA Wei hua
  • 2020, 41 (7): 860-867. doi: 10.3873/j.issn.1000-1328.2020.07.004
  • Abstract ( 433 ) PDF (1418KB)( 698 )
    This paper reviews the development and achievements of the guidance, navigation and control (GNC) technologies for missiles/launch vehicles. Some important breakthroughs and leapfrogs of GNC key technologies in different stages are summarized. Then, the article mainly focuses on the summary and applications of the inertial navigation, integrated navigation, perturbation guidance, close-loop guidance, iterative guidance, digital design, redundant control, adaptive control and other technologies. This paper considers and prospects the future development direction of China’s GNC technologies, and puts forward seven key technologies. At last, in order to meet the needs of “more intelligent and more autonomous” of the future missiles/launch vehicles, this paper proposes a new concept of launch vehicle named “Self-learning” missile/launch vehicle, and analyses the features of its GNC technologies.
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  • Technological Innovation and Development Prospect of Aerospace Vehicle
  • WANG Chang qing
  • 2021, 42 (7): 807-819. doi: 10.3873/j.issn.1000-1328.2021.07.001
  • Abstract ( 416 ) PDF (22394KB)( 667 )
    Firstly this paper introduces the development history and current situation of foreign aerospace vehicle technology. According to the world development experiences and the aerospace vehicle’s flight features, we raise the basic science problems of aerospace vehicle technology, and propose the solutions of aerospace vehicle technology based on current technological level. In conclusion, the development direction of aerospace vehicle technology is elucidated. It is generally known that the long term future of mankind must be in outer space. Developing a new generation of space transportation system is not only the requirement of large scale exploitation and utilization of outer space, but also will open up a new era of outer space. 

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  • Some Achievements on Interception of Near Space Hypersonic Vehicles

  • ZHAO Liang yu , YONG En mi , WANG Bo lan
  • 2020, 41 (10): 1239-1250. doi: 10.3873/j.issn.1000-1328.2020.10.001
  • Abstract ( 505 ) PDF (958KB)( 663 )
    In order to support the fundamental research and engineering development on interception of near space hypersonic vehicles in China, following the introduction of the flight characteristics and mission profiles of the typical near space hypersonic targets, the research achievements including target early warning and detection, trajectory tracking and prediction, guidance and control methods, and interception strategies are reviewed. Some key technical issues and feasible solutions in each aspect are discussed. It is suggested that the research should focus on early warning with space/near space/air/ground/sea system, infrared multimode seeker, direct/aerodynamic force control, collaborative interception and defense and so on.
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  • PM2.5 in Space: Trend of Research on Dust Dynamics in Solar System
  • JIANG Yu
  • 2020, 41 (7): 889-900. doi: 10.3873/j.issn.1000-1328.2020.07.007
  • Abstract ( 407 ) PDF (1542KB)( 608 )
    This paper provides an overview of the basics involved in the dust dynamics in the solar system, including the classification, composition, size, density, shape, and life cycle of the dust grains. Furthermore, the mechanical processes, theories, models and methods in the mechanism of source and generation of the dust grains have been investigated, including dust ejection, surface spraying, weathering, regolith landslides, mass shedding, and rotational breakup. The charging process and the environment of the magnetic field of the dust grains are described. The results of the dust detection of space missions are briefly summarized. The recent progress on the dynamic model and motion of the dust grains, the distribution characteristics, the dynamic behavior and mechanism of a large number of dust grains have been investigated. Finally, the future trend of dust dynamics in the solar system has been prospected.
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  • Research on Application of Earth Moon NRHO and DRO for Lunar Exploration
  • ZENG Hao, LI Zhao yu, PENG Kun, WANG Ping, HUANG Zhen
  • 2020, 41 (7): 910-919. doi: 10.3873/j.issn.1000-1328.2020.07.009
  • Abstract ( 1054 ) PDF (6544KB)( 581 )
    Researching on the application of NRHO and DRO in the Earth-Moon system on low-energy round-trip transfer for Moon exploration, the paper combines the flyby technique and hybrid optimization technology, analyzes systematically the influence of different target orbits and different flyby azimuth on the key parameters such as flight time and fuel consumption, and provides the selection strategy for the initial value of round-trip orbit design. For the problem of initial value guess, the genetic algorithm and Lambert transfer are used to determine quickly the initial value that satisfies the constraints. Considering multiple constraints at perilune and perigee simultaneously, the fuel optimal round-trip orbit from the Earth is studied further based on the sequential quadratic programming algorithm and multiple shooting method, and the constraint equation analytic gradient is derived to improve the design efficiency. Finally, the variation characteristic of perilune attitude, transfer time and fuel consumption of different target orbits are analyzed, which is of great reference value for round-trip transfer design and parameter selection considering lunar flyby.
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  • The Application of Aerodynamic Coefficients Prediction Technique via Artificial Intelligence Method to Rocket First Stage Landing Area Control Project
  • DU Tao, XU Chen zhou, WANG Guo hui, GONG Yu kun, HE Wei, MOU Yu, LI Zhou yang, SHEN Dan, CHENG Xing, GAO Jia yi, HAN Zhong hua
  • 2021, 42 (1): 61-73. doi: 10.3873/j.issn.1000-1328.2021.01.007
  • Abstract ( 641 ) PDF (5877KB)( 552 )
    A novel approach of predicting aerodynamic data via artificial intelligence technique is proposed in this article. Based on wind tunnel tests of partial test states, combined with several CFD results, machine learning via Kriging model is used to predict the whole aerodynamic characteristics to shorten the development cycle and reduce the expensive wind tunnel tests as many as possible. After solving several key technical problems such as the selection of correlation functions, hyper parameters training, data verification and application of man in loop technique, the complete set of aerodynamic data was obtained successfully and used to the control law design in the rocket first stage landing area control project with grid fins. The correctness of the proposed method was validated by a flight test on 26th July, 2019, which was carried out successfully for the first time in China. At the end, the grading of technology maturity degree for the artificial intelligence technique is presented to evaluate application to aerodynamic engineering design problems.
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  • Investigation on Ascent Guidance Law for Air Breathing Combined Cycle Hypersonic Vehicle
  • LIU Kai, GUO Jian, ZHOU Wen ya, SHE Zhi yong
  • 2020, 41 (8): 1023-1031. doi: 10.3873/j.issn.1000-1328.2020.08.005
  • Abstract ( 196 ) PDF (4597KB)( 502 )
    The ascent trajectory design problem of air-breathing combined-cycle hypersonic vehicle is studied in this paper. By considering the different characteristics of the combined-cycle engine and aerodynamics within the flight envelope, the flight strategy for turbo mode, ejecting mode, scram mode and scram-rocket mode is proposed respectively. Then, by constructing the proper attack angle profile and rocket flow profile, the infinity dimension optimization problem is simplified as the finite dimension parameters optimization problem, which can be solved effectively via the sequence quadratic program algorithm. Moreover, by using the trajectory linearization control approach, the tracking guidance law for the combined-cycle ascent phase is designed, and the principle for choosing the controller parameters to guarantee the stability and performance is also provided. In the end, the simulation is carried out and the results demonstrate the efficacy of the proposed design approach.
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