GONG Sheng-ping, LI Jun-feng, BAOYIN He-xi, GAO Yun-feng. Lunar Landing Trajectory Design Based on Invariant Manifold[J]. Applied Mathematics and Mechanics, 2007, 28(2): 183-190.
Citation: GONG Sheng-ping, LI Jun-feng, BAOYIN He-xi, GAO Yun-feng. Lunar Landing Trajectory Design Based on Invariant Manifold[J]. Applied Mathematics and Mechanics, 2007, 28(2): 183-190.

Lunar Landing Trajectory Design Based on Invariant Manifold

  • Received Date: 2005-09-20
  • Rev Recd Date: 2006-10-30
  • Publish Date: 2007-02-15
  • The low-energy lunar landing trajectory design using the invariant manifolds of restricted three body problem is studied.Considering angle between the ecliptic plane and lunar orbit plane,the four body problem of Sun-Earth-Moon-spacecraft was divided into two three body problems,the Sun-Earth-spacecraft in the ecliptic plane and the Earth-Moon-spacecraft in the lunar orbit plane.Using the orbit maneuver at the place where the two planes and the invariant manifolds intersect,a general method to design low energy lunar landing trajectory was given.It is found that this method can save the energy by 20% compared with the traditional Hohmann transfer trajectory.The mechanism of the method that can save energy was investigated in the point of view of energy and the expression of the amount of energy saved is given.In addition,some rules of selecting parameters with respect to orbit design were provided.The method of energy analysis can be extended to energy analysis in deep space orbit design.
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