Orbit determination for Nozomi

Takafumi Ohnishi, Shiro Ishibashi, Makoto Yoshikawa, Takaji Kato, Tsutomu Ichikawa, Hiroshi Yamakawa, Jun'ichiro Kawaguchi

研究成果: Conference article査読

2 被引用数 (Scopus)

抄録

Nozomi is the first Japanese spacecraft to explore the planet Mars. It was launched in July, 1998, and put into interplanetary trajectory by multiple lunar gravity assists and a powered Earth swing-by. This paper describes the analysis of orbit determination in each phase of Nozomi trajectory. Non-conservative force which is caused by solar radiation pressure and unexpected small maneuvers at reorientations has a significant influence on orbit determination for Nozomi. We improved the modeling of the non-conservative force. The accuracy of orbit determination is 1km in position and 1 cm/s in velocity in well determined period for cislunar orbit.

本文言語English
ページ(範囲)55-65
ページ数11
ジャーナルAdvances in the Astronautical Sciences
108 I
出版ステータスPublished - 2001
外部発表はい
イベントProceedings of the AAS/AIAA Space Flight Mechanics Meeting - Santa Barbara, CA, United States
継続期間: 2001 2 112001 2 15

ASJC Scopus subject areas

  • 航空宇宙工学
  • 宇宙惑星科学

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