Flexible Spacecraft Three Axis Attitude Maneuver by Active Vibration Control
In this paper, equation of motion of three axis attitude dynamic of flexible spacecraft is derived using combination of finite element method and Euler equation. Flexible appendafes are modeled by beam elements. Goal of control is target attitude of spacecraft from initial state to desired attitude...
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| Autors principals: | , , |
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| Format: | Artigo |
| Idioma: | Persa |
| Publicat: |
Aerospace Research Institute
2009-03-01
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| Col·lecció: | فصلنامه علوم و فناوری فضایی |
| Matèries: | |
| Accés en línia: | https://jsst.ias.ir/article_14376_62c655280030ff63d32997ab7ffb525c.pdf |
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