Formulation Methods of Rigid Multibody Systems for Large Space Structures and Some Results of Computer Simulation

Material type: 文書・図像類

Author: 狼, 嘉彰ほか

Publisher: 航空宇宙技術研究所

Publication date: 1987-08

Material Format: Digital

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Note (General)：: In this paper we describe a comparative study of the simulation algorithms for dynamics of large space structures modeled as a collection of rigid mul...

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Material Type: 文書・図像類
Title: Formulation Methods of Rigid Multibody Systems for Large Space Structures and Some Results of Computer Simulation
Author/Editor: 狼, 嘉彰
岡本, 修
木田, 隆
山口, 功
山田, 克彦
土屋, 和雄
OOKAMI, Yoshiaki
OKAMOTO, Osamu
KIDA, Takashi
YAMAGUCHI, Isao
YAMADA, Katsuhiko
TSUCHIYA, Kazuo
Author Heading: 狼, 嘉彰
岡本, 修
木田, 隆
山口, 功
山田, 克彦
土屋, 和雄
OOKAMI, Yoshiaki
OKAMOTO, Osamu
KIDA, Takashi
YAMAGUCHI, Isao
YAMADA, Katsuhiko
TSUCHIYA, Kazuo
Publication, Distribution, etc.: 航空宇宙技術研究所
Publication Date: 1987-08
Publication Date (W3CDTF): 1987-08
Alternative Title: 多剛体宇宙構造物のモデリング手法とシミュレーション結果
Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-942
No. or year of volume/issue: 942
Volume: 942
Pages: 17-
ISSN (Periodical Title): ISSN : 0389-4010
Text Language Code: eng
Target Audience: 一般
Note (General): In this paper we describe a comparative study of the simulation algorithms for dynamics of large space structures modeled as a collection of rigid multibodies connected by hinges. Two different algorithms have been independently developed at two different research institutes. One method is basically based upon the well-known Euler Newton formulation and the unified matrix approach. The unified matrix approach solves the dynamical equation for the derivatives of the non-holonomic velocities and the internal torques and forces simultaneously, hence permitting us to deal with an aribitrary LSS configuration. The other method provides for an efficient and fast algorithm based on Kane’s method with modification in the inertia dyadic and other quantities. Both methods have been applied to two typical examples: the first one is a satellite with a four-link manipulator as a model of a chain structure, and the second is a satellite with a closed loop deployment mechanism. The results coincide satisfactorily and the validity of the two methods has been proven perfectly. The numerical values given in this report will be useful as a reference in other simulations.
資料番号: NALTR0942000
レポート番号: NAL TR-942
Access Restrictions: 限定公開
Data Provider (Database): 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
https://irdb.nii.ac.jp
Original Data Provider (Database): 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ