Orbit determination for Nozomi

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

Research output: Contribution to journalConference articlepeer-review

1 Citation (Scopus)

Abstract

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.

Original languageEnglish
Pages (from-to)55-65
Number of pages11
JournalAdvances in the Astronautical Sciences
Volume108 I
Publication statusPublished - 2001
Externally publishedYes
EventProceedings of the AAS/AIAA Space Flight Mechanics Meeting - Santa Barbara, CA, United States
Duration: 2001 Feb 112001 Feb 15

ASJC Scopus subject areas

  • Aerospace Engineering
  • Space and Planetary Science

Fingerprint Dive into the research topics of 'Orbit determination for Nozomi'. Together they form a unique fingerprint.

Cite this