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

• YAGASAKI Kazuyuki

  Gifu University

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

Abstract

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

• Dynamics and Design Conference : 機械力学・計測制御講演論文集 : D & D

  Dynamics and Design Conference : 機械力学・計測制御講演論文集 : D & D 2003 (0), 201-, 2003-09-15

  The Japan Society of Mechanical Engineers

Keywords

• Space Engineering
• Rocket
• Earth-to-Moon Transfer
• Space Mission Design
• Restricted Three-Body Problem
• Nonlinear Boundary Value Problem
• Numerical Continuation

Details

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