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

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振动与冲击 ›› 2016, Vol. 35 ›› Issue (6) : 187-191.

论文

郭其威1,2，吴松1,2，刘芳1,2，唐国安3

作者信息 +

Analysis of the affect and change rule of spacecraft flexible annex on system natural vibration characteristics

GUO Qi-wei1,2，WU Song1,2，LIU Fang1,2，TANG Guo-an3

Author information +

文章历史 +

摘要

介绍快速求解含大型柔性附件航天器系统模态的结构动力学方法，通过对多个柔性结构模型缩聚大幅度缩减自由度，集成MATLAB与NASTRAN进行联合仿真分析。遍历附件所有可能工作姿态的系统模态，大幅提高系统模态计算效率。通过该快速求解方法进行仿真实例分析，阐明航天飞行器的系统构型、柔性附件转动角度、本体与柔性附件质量惯量比三方面对柔性附件约束模态与系统模态影响规律。

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.

导出引用

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[J]. Journal of Vibration and Shock, 2016, 35(6): 187-191

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