Advanced Search
Volume 42 Issue 4
Apr.  2016
Turn off MathJax
Article Contents
Journal of Beijing University of Aeronautics and Astronautics  > 2016  >  42(4): 694-702.
ZHAO Guowei, ZHANG Xingmin, TANG Bin, et al. Properties of pendulum motion of tether tugging system and its stable control[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(4): 694-702. doi: 10.13700/j.bh.1001-5965.2015.0286(in Chinese)
Citation: ZHAO Guowei, ZHANG Xingmin, TANG Bin, et al. Properties of pendulum motion of tether tugging system and its stable control[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(4): 694-702. doi: 10.13700/j.bh.1001-5965.2015.0286(in Chinese)
shu

Properties of pendulum motion of tether tugging system and its stable control

doi: 10.13700/j.bh.1001-5965.2015.0286

  • School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

Funds:  National Natural Science Foundation of China (11572016)
  • Received Date: 06 May 2015
  • Rev Recd Date: 11 Sep 2015
  • Publish Date: 20 Apr 2016
    Abstract
  • Taking account of the attitude motion of tethered system, mission satellite and abandoned satellite, dynamics and control models of tethered system are established. According to the flight process under a constant thrust in the tangential direction, an attitude control of mission satellite is adopted on the basis of thrusters and momentum wheels; then, the characteristics of the oscillation of abandoned satellite, the pendulum motion of tethered system and the attitude motion of mission satellite are studied and effects among each other are analyzed. In order to ensure the flight safety of tethered system, the tether tension control which includes damp control law and position-keeping control law, and mission satellite attitude control are adopted. Numerical simulation results indicate that the regular oscillation of abandoned satellite at a specific angular frequency which caused by the offset of hanging position may arouse high order pendulum motion of tethered system during deorbiting under a constant thrust. Furthermore, the attitude motions of satellites are the main factors which bring disturbance torque to mission satellite. In addition, the oscillation of abandoned satellite is damped out and the distance between satellites is maintained by the adopted tension controller, which guarantees the flight safety and stability of tethered system combining with mission satellite attitude control and also reduces energy consuming of mission satellite.

     

    • FullText(HTML)
  • loading
    • References(17)
  • [1]
    邴启军,冯书兴. 基于卫星相撞事件的空间安全新思考[J].装备指挥技术学院学报,2009,20(5):63-67. BING Q J,FENG S X.Reflection on space security concerning the satellites collision[J].Journal of the Academy of Equipment Command & Technology,2009,20(5):63-67(in Chinese).
    [2]
    XU W F, LIANG B,GAO D,et al.A space robotic system used for on-orbit servicing in the geostationary orbit[C]//2010 IEEE/RSJ International Conference on Intelligent Robots and Systems (IROS).Piscataway,NJ:IEEE Press,2010:4089- 4094.
    [3]
    MANKALA K K, AGRAWAL S K.Dynamic modeling and simulation of impact in tether net/gripper systems[J].Multibody System Dynamics,2004,11(3):235-250.
    [4]
    朱仁璋,林华宝. 论绳系卫星系统的运动中心[J].中国空间科学技术,1998,18(5):7-12. ZHU R Z,LIN H B.The motion center of tethered satellite systems[J].Chinese Space Science and Technology,1998,18(5): 7-12(in Chinese).
    [5]
    PELAEZ J, LORENZINI E C,LOPEZ-REBOLLAL O,et al.A new kind of dynamic instability in electrodynamic tethers[C]//Advances in the Astronautical Sciences.San Diego:AAS,2000,105:1367-1386.
    [6]
    王东科,黄攀峰, 孟中杰,等.空间绳系机器人抓捕后复合体姿态协调控制[J].航空学报,2013,34(8):1998-2006. WANG D K,HUANG P F,MENG Z J,et al.Coordinate attitude of the combination system after target capture by a tethered space robot[J].Acta Aeronautica et Astronautica Sinica,2013,34(8):1998-2006(in Chinese).
    [7]
    刘海涛,杨乐平, 张青斌,等.地球静止轨道废弃卫星绳系拖曳离轨研究[J].中国科学:技术科学,2012,42(7):780-787. LIU H T,YANG L P,ZHANG Q B,et al.An investigation on tether-tugging de-orbit of defunct geostationary satellites[J].Science China Technological Sciences,2012,42(7):780-787(in Chinese).
    [8]
    CHO S, MCCLAMROCH N H.Optimal orbit transfer of a spacecraft with fixed length tether[J].The Journal of the Astronautical Sciences,2003,51(2):195-204.
    [9]
    ZHAO G W, SUN L,TAN S P,et al.Librational characteristics of a dumbbell modeled tethered satellite under small,continuous,constant thrust[J].Proceedings of the Institution of Mechanical Engineers,Part G:Journal of Aerospace Engineering,2013,227(5):857-872.
    [10]
    孙亮,赵国伟,黄海,等. 面内轨道转移过程中的绳系系统摆振特性研究[J].航空学报,2012,33(7):1245-1254. SUN L,ZHAO G W,HUANG H,et al.Analysis of librational and vibrational characteristics for tethered systems during orbital transfer in plane[J].Acta Aeronautica et Astronautica Sinica,2012,33(7):1245-1254(in Chinese).
    [11]
    SUN L,ZHAO G W, HUANG H.Stability and control of tethered satellite with chemical propulsion in orbital plane[J].Nonlinear Dynamics,2013,74(4):1113-1131.
    [12]
    SANTANGELO A. Optimal attitude control of a tethered end mass in the earth's upper atmosphere:AIAA-1997-0533[R].Reston:AIAA,1997.
    [13]
    王晓宇,金栋平. 计入姿态的绳系卫星概周期振动[J].振动工程学报,2010,23(4):361-365. WANG X Y,JIN D P.Quasi-periodic oscillation of a tethered subsatellite with attitude[J].Journal of Vibration Engineering,2010,23(4):361-365(in Chinese).
    [14]
    ZHAO G W, TANG B,SUN L,et al.Effect and control of pendular motion of abandoned satellite on tether drag system[J].Applied Mechanics and Materials,2014,513:3900-3906.
    [15]
    钟睿,徐世杰. 基于直接配点法的绳系卫星系统变轨控制[J].航空学报,2010,31(3):572-578. ZHONG R,XU S J.Orbit-transfer control for TSS using direct collocation method[J].Acta Aeronautica et Astronautica Sinica,2010,31(3):572-578(in Chinese).
    [16]
    刘海颖. 微小卫星姿态控制系统关键技术研究[D].南京:南京航空航天大学,2008:23-30. LIU H Y.Research on attitude control system key technologies for micro-satellite[D].Najing:Nanjing University of Aeronautics and Astronautics,2008:23-30(in Chinese).
    [17]
    MENON C, KRUIJFF M,VAVOULIOTIS A.Design and testing of a space mechanism for tether deployment[J].Journal of Spacecraft & Rockets,2007,44(4):927-939.
    • Relative Articles
    • Supplements(0)
    • Cited By
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索
    Get Citation
    PDF
    XML

    Article Metrics

    Article views(932) PDF downloads(503) Cited by()
    Proportional views
    Related

    Copyright © Journal of Beijing University of Aeronautics and Astronautics

    Address: Editorial Department of Journal of Beijing University of Aeronautics and Astronautics, 37 Xueyuan Road, Haidian District, Beijing Post Code: 100191 Email: jbuaa@buaa.edu.cn

    Supported by: Beijing Renhe Information Technology Co., Ltd.    

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return