Spinning solar sail orbit steering via spin rate control

被引：21

作者：

Mimasu, Yuya ^{[1
]}

Yamaguchi, Tomohiro ^{[2
]}

Matsumoto, Michihiro ^{[1
]}

Nakamiya, Masaki ^{[1
]}

Funase, Ryu ^{[1
]}

Kawaguchi, Jun'ichiro ^{[1
]}

机构：

[1] Japan Aerosp Explorat Agcy, Chuo Ku, Kanagawa 2525210, Japan

[2] Grad Univ Adv Studies, Dept Space & Astronaut Sci, Chuo Ku, Kanagawa 2525210, Japan

来源：

ADVANCES IN SPACE RESEARCH | 2011年 / 48卷 / 11期

关键词：

Attitude drift motion; Spin control; Orbit control;

D O I：

10.1016/j.asr.2011.08.030

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

The orbit of a solar sail can be controlled by changing the attitude of the spacecraft. In this study, we consider the spinning solar power sail IKAROS (Interplanetary Kite-craft Accelerated by Radiation of the Sun), which is managed by Japan Aerospace Exploration Agency (JAXA). The IKAROS attitude, i.e., the direction of its spin-axis, is nominally controlled by the rhumb-line control method. By utilizing the solar radiation torque, however, we are able to change the direction of the spin-axis by only controlling its spin rate. With this spin rate control, we can also control indirectly the solar sail's trajectory. The main objective of this study is to construct the orbit control strategy of the solar sail via the spin-rate control method. We evaluate this strategy in terms of its propellant consumption compared to the rhumb-line control method. Finally, we present the actual flight attitude data of IKAROS and the change of its trajectory. (C) 2011 COSPAR. Published by Elsevier Ltd. All rights reserved.

引用

页码：1810 / 1821

页数：12

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