Attitude Determination and Control System for the PROCYON Micro-Spacecraft
-
- IKARI Satoshi
- Department of Aeronautics and Astronautics, The University of Tokyo
-
- INAMORI Takaya
- Department of Aerospace Engineering, Nagoya University
-
- ITO Takahiro
- Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency
-
- ARIU Kaito
- Department of Aeronautics and Astronautics, The University of Tokyo
-
- OGURI Kenshiro
- Department of Aeronautics and Astronautics, The University of Tokyo
-
- FUJIMOTO Masataka
- Department of Aeronautics and Astronautics, The University of Tokyo
-
- SAKAI Shinichiro
- Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency
-
- KAWAKATSU Yasuhiro
- Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency
-
- FUNASE Ryu
- Department of Aeronautics and Astronautics, The University of Tokyo
抄録
This paper describes development strategies and on-orbit results of the attitude determination and control system (ADCS) for the world's first interplanetary micro-spacecraft, PROCYON, whose advanced mission objectives are optical navigation or an asteroid close flyby. Although earth-orbiting micro-satellites already have ADCSs for practical missions, these ADCSs cannot be used for interplanetary micro-spacecraft due to differences in the space environments of their orbits. To develop a new practical ADCS, four issues for practical interplanetary micro-spacecraft are discussed: initial Sun acquisition without magnetic components, angular momentum management using a new propulsion system, the robustness realized using a fault detection, isolation, and recovery (FDIR) system, and precise attitude control. These issues have not been demonstrated on orbit by interplanetary micro-spacecraft. In order to overcome these issues, the authors developed a reliable and precise ADCS, a FDIR system without magnetic components, and ground-based evaluation systems. The four issues were evaluated before launch using the developed ground-based evaluation systems. Furthermore, they were successfully demonstrated on orbit. The architectures and simulation and on-orbit results for the developed attitude control system are proposed in this paper.
収録刊行物
-
- TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
-
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 60 (3), 181-191, 2017
一般社団法人 日本航空宇宙学会
- Tweet
詳細情報 詳細情報について
-
- CRID
- 1390001204079865600
-
- NII論文ID
- 130005635913
-
- ISSN
- 21894205
- 05493811
-
- 本文言語コード
- en
-
- データソース種別
-
- JaLC
- Crossref
- CiNii Articles
- KAKEN
-
- 抄録ライセンスフラグ
- 使用不可