Volume 39 Issue 8
Aug.  2013
Turn off MathJax
Article Contents
Lü Jing, Zhang Mingming, Zhang Yongweiet al. Transfer trajectory design between L2 in Sun-Earth system and L1 in Sun-Mars system[J]. Journal of Beijing University of Aeronautics and Astronautics, 2013, 39(8): 1031-1036. (in Chinese)
Citation: Lü Jing, Zhang Mingming, Zhang Yongweiet al. Transfer trajectory design between L2 in Sun-Earth system and L1 in Sun-Mars system[J]. Journal of Beijing University of Aeronautics and Astronautics, 2013, 39(8): 1031-1036. (in Chinese)

Transfer trajectory design between L2 in Sun-Earth system and L1 in Sun-Mars system

  • Received Date: 17 Aug 2012
  • Rev Recd Date: 25 Dec 2012
  • Publish Date: 30 Aug 2013
  • The transfer trajectory bwtween L2 in the sun-earth system and L1 in the sun-mars system design using invariant manifold of the restricted three body problem is studied. Considering mars,earth and sun in the same plane, the four body problem of sun-mars-earth-spacecraft was divided into two three body problems, that were the three body problems of sun-earth-spacecraft and sun-mars-spacecraft. A Lyapunov orbit of Lagrange liberation point was designed with different correction method and Richardson three-order approximation solution as initial conditions. The transfer trajectory between Lyapunov orbit's invariant manifold of the two different restricted three body problems was designed with different correction method and the results was compared with the transfer trajectory between Halo orbit's invariant manifold of the two different restricted three body problems.The simulation shows that transfer trajectory design using the invariant manifold of Lyapunov orbit cost lower energy and shorter time of flight.

     

  • loading
  • [1] Lo M W.The interplanetary superhighway and the origins program[C]//IEEE Space 2002 Conference.Big Sky,MT:[s.n.],2002:7-3543-7-3562 [2] Koon W S,Martin W,Lo M W,et al.Shoot the moon[R].AAS 00-166,2000 [3] Koon W S,Lo M W,Marsden J E,et al.Low energy transfer to the moon[J].Celestial Mechanics and Dynamical Astronomy,2001,81(1/2):63-73 [4] Gomez G,Koon W S,Lo M W,et al.Connecting orbits and invariantmanifold in the spatial restricted three-body problem[J].Nonlinearity,2004,17(5):1571-1606 [5] 龚胜平.太阳帆航天器动力学与控制研究[D].北京:清华大学航天航空学院,2009 Gong Shengping.Study ondynamics and control of sail-craft[D].Beijing:School of Aerospace,Tsinghua University,2009(in Chinese) [6] Howell K C,Mains D L,Barden B T.Transfer trajectories from Earth parking orbits to Sun-Earth Halo orbits[C]//AIAA Spaceight Mechanics Meeting.Cocoa Beach,Florida:AIAA,1994:94-160 [7] Belbruno E A,Miller J K.Sun-peturbed earth-to-moon transfers with ballistic capture[J].Journal of Guidance,Control,and Dynamics,1993,16 (4):770-775 [8] German.The design of system-system transfer arcs using invariant manifolds in the multi-body problem[D].West Lafayette of Indiana:Graduate School,Purdue University,2006 [9] Francesco Topputo,Massinmiliano Vasile ,Amalia Ercoli Finzi.Combining two and three-body dynamics for low energy transfer trajectories Of Practical Interest[R].IAC-04-A.7.02,2011 [10] 龚胜平,李俊峰,宝音贺西,等.基于不变流形的登月轨道设计[J].应用数学与力学,2007,28(2):183-190 Gong Shengping,Li Junfeng,Baoyin Hexi,et al.Lunar landing trajectory design based on invariant manifold[J].Applied Mathematics and Mechanics,2007,28(2):183-190(in Chinese) [11] 李明涛,郑建华,于锡峥,等.基于流形插入的日地系Halo轨道转移轨道设计[J].吉林大学学报,2011,41(2):585-589 Li Mingtao,Zheng Jianhua,Yu Xizheng,et al.Transfer trajectory design for Sun-Earth Halo orbit based on manifold insertion[J].Journal of Jinlin University,2011,41(2):585-589(in Chinese) [12] 李明涛,郑建华,于锡峥,等.约束条件下的Halo轨道转移轨道设计[J].宇航学报,2009,30(2):437-441 Li Mingtao,Zheng Jianhua,Yu Xizheng,et al.Transfer trajectory design for Halo orbit with multiple constraints[J].Journal of Astronautics,2009,30(2):437-441(in Chinese) [13] 刘建中.日-地系拉格朗日点任务及其转移轨道设计方法[J].导弹与航天运载技术,2009,1(7):7-10 Liu Jianzhong.Missions of Sun-Earth lagrange points and design method of transfer trajectory[J].Missile and Space Vehcile,2009,1(7):7-10(in Chinese) [14] 徐明.平动点轨道的动力学与控制研究综述[J].宇航学报,2009,30(4):1299-1313 Xu Ming.Overview of orbit dynamics and control for libration point orbits[J].Journal of Astronautics,2009,30(4):1299-1313(in Chinese) [15] 徐明.基于平动点理论的航天器轨道动力学与控制研究[D].北京:北京航空航天大学宇航学院,2008 Xu Ming.Spacecraft orbital dynamics and control based on libration point theories[D].Beijing:School of Astronautics,Beijing University of Aeronautics and Astronautics,2008(in Chinese) [16] Mondelo J M.The phase space around the lagrange points of RTBP[J].Physics D,2001,157(4):283-321 [17] Siegel C L,Moser J K.Lectures on mechanics[M].Berlin:Springer-Verlag,1971 [18] Richardson D L.Periodic orbits about the L1 and L2 collinear points in the circular-restricted problem[R].CSC/-TR-78/-6002,1978
  • 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

    Article Metrics

    Article views(1964) PDF downloads(674) Cited by()
    Proportional views
    Related

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return