Design and Guidance for Robust Orbit Raising Trajectory of All-Electric Propulsion Geostationary Satellites

• NISHI Kentaro

  Research and Development Directorate, JAXA

• OZAWA Satoru

  Research and Development Directorate, JAXA

• MATUNAGA Saburo

  Department of Mechanical Engineering, Tokyo Institute of Technology

抄録

This paper describes a robust trajectory design and guidance method to GEO for all-electric propulsion satellites. The method splits the transfer time into multiple steps. The length of the steps is in multiples of the orbital period. Each step optimizes gains that generate steering directions of a thrust vector to minimize the weighted sum of residual errors between the orbital elements at the end of the step and those of the specified target orbit. The method extends the transfer with additional steps until the satellite reaches the target orbit. Guidance is based on this multistep optimization. Because the optimizer handles a few variables and no constraints, this method provides the quasi-optimal trajectory acquired with low computational cost. The method is robust to disturbances because it sequentially calculates the gains considering any disturbances. Numerical examples for the GEO orbit-raising transfer problem show that trajectory is appropriately generated to reach GEO by optimized gains against disturbances.

収録刊行物

• TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN

  TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 19 (4), 553-561, 2021

  一般社団法人 日本航空宇宙学会

キーワード

• All-Electric Propulsion Satellites
• Trajectory Design
• Guidance

詳細情報

• CRID: 1390007128168787712
• NII論文ID: 130008062302
• DOI: 10.2322/tastj.19.553
• ISSN: 18840485
• Web Site: https://www.jstage.jst.go.jp/article/tastj/19/4/19_19.553/_pdf
• 本文言語コード: en
• データソース種別:
  • JaLC
  • Crossref
  • CiNii Articles
• 抄録ライセンスフラグ: 使用不可