Low Energy Transfer Trajectories of a Spacecraft from the Earth to the Moon

Bibliographic Information

Other Title
  • 421 宇宙ロケットの地球から月への低エネルギー遷移軌道

Search this article

Description

We consider a problem of constructing a spacecraft transfer trajectory with low cost and moderate flight time from the Earth to the Moon. We adopt as the spacecraft model the planar circular restricted three-body problem or its perturbation due to the solar gravitation, and reduce computation of optimal transfers to a nonlinear boundary value problem. Using a computer software called AUTO, we solve it and continue its solutions numerically to obtain the optimal transfers. Especially, we find a transfer trajectory having about 15% lower cost, compared to the traditional Hohmann transfer.

Journal

Keywords

Details 詳細情報について

  • CRID
    1571417127143710848
  • NII Article ID
    110002483300
  • NII Book ID
    AA11901770
  • ISSN
    13480235
  • Text Lang
    ja
  • Data Source
    • CiNii Articles

Report a problem

Back to top