A method for the synthesis of modal damping factors and other modal data for a spacecraft in orbit is demonstrated. It is based on input information at the component/substructure level. Also, the use of the method and the level of accuracy obtained is illustrated in a case study of the Hermes spacecraft. The synthesis procedure is demonstrated for a spacecraft configuration consisting of a central rigid body, solar array substructures, a momentum wheel and a liquid mercury damping device. The synthesized spacecraft modal data is obtained by eigenproblem analysis of a system model that is constructed from submodels of the components. The system modes are the natural (unconstrained) modes with damping and gyroscopic stiffness accounted for. Numerical experiments show that the procedure is not sensitive to errors in or to omission of damping factors of the higher order substructure modes. Damping factors for the nutational mode are confirmed by an independent analysis.
Damping Synthesis for a Spacecraft Using Substructure and Component Data
1984
88 pages
Report
No indication
English
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