| Article ID | Journal | Published Year | Pages | File Type |
|---|---|---|---|---|
| 1714175 | Acta Astronautica | 2016 | 6 Pages |
Abstract
•Equations of motions are derived for a satellite with flexible hinged panel.•Normal modes determine flexible panel motion.•Computation-efficient method provides modes for different panel rotation angles.•Intuitive 3/2DOF example is discussed.
Non-linear mathematical model for the satellite with hinged flexible solar panel is presented. Normal modes of flexible elements are used for motion description. Motion equations are derived using virtual work principle. A comparison of normal modes calculation between finite element method and developed model is presented.
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Authors
M.Yu. Ovchinnikov, S.S. Tkachev, D.S. Roldugin, A.B. Nuralieva, Y.V. Mashtakov,