論文

2016年

Attitude Estimation of Nano-satellite with Deployable Aeroshell during Orbital Decay

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN
  • WATANABE Yasumasa
  • ,
  • SUZUKI Kojiro
  • ,
  • IMAMURA Osamu
  • ,
  • YAMADA Kazuhiko

14
30
開始ページ
Pf_1
終了ページ
Pf_5
記述言語
英語
掲載種別
DOI
10.2322/tastj.14.Pf_1
出版者・発行元
一般社団法人 日本航空宇宙学会

As a part of the "Membrane Aeroshell for Atmospheric-entry Capsule" (MAAC) project pursued by the University of Tokyo, JAXA and several other universities, a demonstration is planned to deploy an atmospheric-entry nano-satellite from International Space Station (ISS). The effect of aeroshell deployment timing on the orbital decay was evaluated and it was clarified that the orbital decay is significantly accelerated after aeroshell deployment due to the change in its ballistic coefficient. In order to keep the forward surface of the aeroshell in the direction of motion at the moment of aeroshell deployment, it is necessary to obtain the attitude of satellite with reference to the orbital direction. The applicability of the Faraday cup as an ion detector is discussed through experimental results at Inductively Coupled Plasma (ICP) wind tunnel and it was revealed to be promising for the estimation of the satellite direction.

リンク情報
DOI
https://doi.org/10.2322/tastj.14.Pf_1
CiNii Articles
http://ci.nii.ac.jp/naid/130005126068
URL
https://jlc.jst.go.jp/DN/JLC/20020536273?from=CiNii
ID情報
  • DOI : 10.2322/tastj.14.Pf_1
  • ISSN : 1884-0485
  • CiNii Articles ID : 130005126068

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