A structural dynamics method for rapidly solving spacecraft system mode with large flexible appendages was introduced. By scanning the system mode of the appendages in all possible working attitude, the system mode computing efficiency was hugely improved through reducing several flexible appendages in model, largely cutting freedom, and carrying out combined simulation analysis with integrating MATLABand NASTRAN.By simulation analysis example using the rapid solution method, the influence on constrained mode with flexible appendages and system mode was clarified through three aspects: system configuration of spacecraft, rotation angle of flexible appendages, and mass and inertia ratio between spacecraft and flexible appendages.
Key words
spacecraft /
flexible annex /
vibration /
frequency
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References
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