Attitude Control of IKAROS Solar Sail Spacecraft and Its Flight Results
- Paper number
IAC-10.C1.4.3
- Author
Dr. Ryu Funase, Japan Aerospace Exploration Agency (JAXA), Japan
- Coauthor
Dr. Osamu Mori, Japan Aerospace Exploration Agency (JAXA), Japan
- Coauthor
Dr. Yuichi Tsuda, Japan Aerospace Exploration Agency (JAXA), Japan
- Coauthor
Dr. Yoji Shirasawa, Japan Aerospace Exploration Agency (JAXA), Japan
- Coauthor
Dr. Takanao Saiki, Japan Aerospace Exploration Agency (JAXA), Japan
- Coauthor
Dr. Yuya Mimasu, Japan Aerospace Exploration Agency (JAXA), Japan
- Coauthor
Dr. Junichiro Kawaguchi, Japan Aerospace Exploration Agency (JAXA), Japan
- Year
2010
- Abstract
JAXA has been proposing a concept of “Solar Power Sail" for future deep space exploration. It combines the concept of solar sail (photon propulsion) with a larger power generation by flexible solar cells attached on the sail membrane. An interplanetary solar sail demonstration spacecraft is planned to be launched by JAXA in the summer of 2010, which is named “IKAROS” (\underline{I}nterplanetary \underline{K}ite-craft \underline{A}ccelerated by the \underline{R}adiation \underline{O}f the \underline{S}un). IKAROS is the precursor mission to demonstrate the key technologies for the solar power sail concept, which are (1) deployment of large sail in space, (2) solar power generation by means of thin film solar cells attached on the sail, (3) confirming the acceleration by solar radiation pressure attracted on the sail and (4) demonstration of the interplanetary guidance and navigation of the solar sail spacecraft. IKAROS will deploy a 20m-span sail within one month after the launch, and performs interplanetary solar-sailing from the Earth to Venus. This paper focuses on the 4th mission, or attitude control of flexible spinning solar sail for the guidance and control of the solar photon sail. This paper first introduces and verifies two attitude dynamics model of spinning solar sail. The first one is a simplified analytical model which is to be used for the attitude controller design. The other one is a precise numerical model incorporating the flexibility of the membrane and is to be used for performance verification of the controller. Then, several attitude controllers are designed using the analytical model which takes into consideration the flexibility of the large membrane, and the performance of the controllers is verified by numerical simulations using the precise numerical model. The controllers are implemented on the IKAROS spacecraft and finally the paper will discuss the up-to-date flight results.- Abstract document
- Manuscript document
IAC-10.C1.4.3.pdf (🔒 authorized access only).
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