›› 2012, Vol. 32 ›› Issue (1): 1-7.doi: 10.3780/j.issn.1000-758X.2012.01.001

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 ZHAO  Guo-Qiang, BAO  Yin-He-Xi, LI  Jun-Feng   

  1. (SchoolofAerospaceEngineering,Tsinghua University,Beijing100084)
  • Received:2011-05-05 Revised:2012-02-25 Online:2012-02-25 Published:2012-02-25

Abstract: The trajectory design problem was transformed into two point boundary value problem (TPBVP) of ordinary differential equation and solved by differential correction. The  concept of B-plane was used nea earth and Mars. The boundary condition of the TPBVP can be analytically determined by the geometrical characteristics between B-plane and its associatedhyperbolic orbit, and the reason that four kinds of trajectories can be obtained was explained. An accurate mathematical formulation describing the closest approach time to Marswas also proposed. An illustrative example was presented and the results were coincided with satellite tool kit.

Key words: Mars exploration, Trajectory design, Differential correction, B-plane parameters