用于航天器微振动分析的扰源解耦加载方法

发布时间：2018-04-14 16:32

本文选题：航天器 + 微振动　；参考：《航天器工程》2016年04期

【摘要】：微振动源与航天器主结构之间存在耦合作用,其建模与加载方法直接影响系统级微振动分析结果。文章通过理论推导和证明,提出了一种新的微振动源精确解耦加载方法,使扰源的加载处理不受微振动源与航天器主结构耦合作用的影响,实现了扰动外载荷与航天器结构的解耦,所获取的微振动响应与系统级耦合分析结果完全相同。理论研究和数值算例表明:此方法避免了微振动源与航天器主结构的耦合分析,结果准确可靠,适用于动量轮、控制力矩陀螺等常见的扰源加载,且易于工程实施。
[Abstract]:There is a coupling between the micro vibration source and the main structure of the spacecraft, and the modeling and loading methods directly affect the results of the system level micro vibration analysis.In this paper, a new exact decoupling loading method for micro-vibration source is proposed by theoretical derivation and proof, so that the loading process of the disturbance source is not affected by the coupling effect between the micro-vibration source and the main structure of the spacecraft.The decoupling of the disturbance external load and the structure of the spacecraft is realized. The obtained micro-vibration response is identical to the results of the system-level coupling analysis.The theoretical research and numerical examples show that the method avoids the coupling analysis between the micro vibration source and the main structure of the spacecraft, and the results are accurate and reliable. The method is suitable for loading common disturbance sources such as momentum wheels and control moment gyroscopes, and is easy to be implemented in engineering.
【作者单位】：北京空间飞行器总体设计部;
【基金】：国家重大科技专项工程
【分类号】：V414

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