Abstract：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.
郭其威1,2，吴松1,2，刘芳1,2，唐国安3. 航天器柔性附件对整器固有振动特性影响因素及规律分析[J]. 振动与冲击, 2016, 35(6): 187-191.
GUO Qi-wei1,2，WU Song1,2，LIU Fang1,2，TANG Guo-an3. Analysis of the affect and change rule of spacecraft flexible annex on system natural vibration characteristics. JOURNAL OF VIBRATION AND SHOCK, 2016, 35(6): 187-191.
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