Lunar landing trajectory design based on invariant manifold

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Lunar landing trajectory design based on invariant manifold

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 is divided into two three-body problems, the sun-earth-spacecraft in the ecliptic plane and the earthmoon-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 is given. It is found that this method can save the energy about 20% compared to the traditional Hohmann transfer trajectory. The mechanism that the method can save energy is 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 are provided. The method of energy analysis in the paper can be extended to energy analysis in deep space orbit design.水利论文P@i&Gd

作 者: GONG Sheng-ping LI Jun-feng BAOYIN He-xi GAO Yun-feng  
作者单位:School of Aerospace, Tsinghua University, Beijing 100084, P. R. China 
刊 名:应用数学和力学(英文版)  EI SCI
英文刊名:APPLIED MATHEMATICS AND MECHANICS 
年,卷(期):2007 28(2) 
分类号:V4 
关键词:three-body problem   Lagrange point   Halo orbit   invariant manifold   lunar landing trajectory  
机标关键词:invariant manifoldenergy analysistrajectory designsave energymethod ofrules of 
基金项目:国家自然科学基金 
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