Volume 39 Issue 8
Aug.  2013
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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.

     

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