JAXA Repository / AIREX 未来へ続く、宙(そら)への英知

There are no files associated with this item.

title太陽発電衛星の展開シーケンス最適化
Other TitleOptimization of the deployment sequence of solar power satellite
Author(jpn)石村 康生; 高井 伸明
Author(eng)Ishimura, Kosei; Takai, Nobuaki
Author Affiliation(jpn)北海道大学 大学院工学研究科; 北海道大学 大学院工学研究科
Author Affiliation(eng)Hokkaido University Graduate School of Engineering; Hokkaido University Graduate School of Engineering
Issue Date2005-06
PublisherInstitute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS)
宇宙航空研究開発機構宇宙科学研究本部
Publication title第24回宇宙エネルギーシンポジウム 平成16年度
The Twenty-fourth Space Energy Symposium March 7, 2005
Start page47
End page51
Publication date2005-06
Languagejpn
AbstractFor the demonstration and verification of solar power satellite's functions, a small demonstration solar power satellite has been examined by USEF and ISAS/JAXA. Structural characteristics and attitude motion in steady operation have already been studied. In this paper, deployment sequence for the stable and fast deployment is investigated. The deployment sequence consists of two-stage truss extension and two-stage panel deployment. At first, attitude motion in the deployment is analyzed through numerical simulations. From the result, it is shown that nonlinear effect can not be negligible when pitch angle exceeds about 0.6 rad. In such a case, because independency of the pitch angle does not hold true for the nonlinearity, pitch motion leads to the large roll and yaw motions. Next, to realize stable and fast deployment, optimization of the deployment is carried out by changing each deployment time, interval and acceleration of the deployment. As an objective function, weighted sum of deployment times, maximum amplitudes of attitude angles and residual amplitudes of attitude angles is used. The optimization is carried out by Powell's method. From the result it is shown that maximum amplitudes of attitude angles are kept within 0.08 rad, and residual amplitudes of attitude angles are kept within 0.01 rad without any active control if about five orbital periods (about eight hours) can be spent for the total deployment.
Keywordssolar power satellite; deployment sequence; optimization; attitude stability; spacecraft stability; nonlinear system; moment of inertia; acceleration; 太陽発電衛星; 展開シーケンス; 最適化; 姿勢安定性; 宇宙機安定性; 非線形システム; 慣性モーメント; 加速度
Document TypeConference Paper
JAXA Categoryシンポジウム・研究会
SHI-NOAA0049120010
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/26364


Items in DSpace are protected by copyright, with all rights reserved, unless otherwise indicated.