星载预应力可展开结构收拢状态的确定、分析与试验

Determination,analysis and test on the prestressed folded state of spaceborne deployable structures

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。

Due to the lack of specific criteria for the prestressed folded state of spaceborne deployable structures, and the difficulty in meeting the mechanical environmental requirements in the phase of rocket active flight,a kind of criteria was put forward to determine the entire star “stable”folded state.Finite element analyses and related experiments were carried out for understanding the structural strength and stiffness at the “stable”folded state to give a reference to the following study.Based on this spaceborne prestressed developable structure,tests were conducted to study the relationship of the cord pretension wiht the structural natural frequency in folded locking state and the average locking operation time. Then the pretension was determined.The intensity and modes of the entire structure in “stable”state were analysed by ANSYS software.The rationality of the finite element analysis results was verified by comparing the shaking-table test results with the fundamental frequency measurements by using the hammering method.