针对星载预应力可展开结构收拢状态缺乏明确的判定标准，且需满足运载火箭主动飞行段力学环境要求的难点，提出了整星“稳定”收拢状态的确定标准，并对其“稳定”收拢状态下结构的强度、刚度进行有限元分析和相关试验验证，为后续预应力可展开结构收拢状态的研究提供了借鉴。基于星载预应力可展开结构，通过试验研究了捆绳预紧力与收拢状态结构基频及平均熔断时间的关系并确定了捆绳预紧力；利用ANSYS对整星“稳定”收拢状态进行了有限元建模及强度、模态分析；通过振动台试验和锤击法测基频试验对比验证了有限元分析结果的合理性。
Abstract
Due to the lack of specific criteria for the spaceborne deployable structure in prestressed folded state, and the difficulty of meeting mechanical environmental requirements in rocket active flight segment, a kind of criteria was put forward to determine the entire star "stable" folded state. The finite element analyses and related experiments were carried out for structural strength and stiffness of this "stable" folded state as a kind of reference for the following study. Based on this spaceborne prestressed developable structure, the tests were conducted to study the relationship be-tween cord pretension and structural natural frequency in folded locking state and the average locking operation time. Then the value of this pretension was determined. The intensity and modals of the entire structure in "stable" state were computed by ANSYS software. The rationality of the finite element analysis results was verified by comparing the shak-ing-table test with hammering method of fundamental frequency measurement.
关键词
预应力可展开机构 /
收拢状态 /
力学分析 /
基频模态 /
振动台试验 /
锤击法
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Key words
prestressed deployable structure /
folded state /
mechanical analysis /
fundamental mode /
shaking-table test
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