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Study on the support technology of the light-weighted mirror

机译：轻型镜支撑技术研究

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To reduce the surface deformation of a space remote sensor mirror in space environments, a flexible supporting structure of space mirror is designed to improve the surface accuracy of mirror under operating conditions, making the mirror in good thermal dimensional stability and the structure stiffness meet the requirements of mechanics at the same time. Using the finite element method to do simulation analysis about the surface accuracy and structural strength and dynamic stiffness of the mirror assembly under the force-heat coupling state. Simulation results show that the first-order natural frequency of the mirror component is 393.73Hz, and the RMS values of 1g gravity respectively reach 8.920nm, 1.856nm, 4.516nm; under lg gravity and 4 degrees centigrade rising coupling state in three directions, the RMS values respectively reach 10.02nm, 3.312nm, 5.718nm, the results meet the design specifications requirement that the RMS value less than λ/50 (λ=632.8nm). Finally, the analysis of the random vibration was carried out on the mirror components, results show that the mirror and its supporting structure was designed reasonable which can meet the requirements of space applications.
机译：为了减少空间遥感器在空间环境中的表面变形，设计了一种柔性的空间镜支撑结构，以提高工作条件下反射镜的表面精度，使反射镜具有良好的热尺寸稳定性和结构刚度满足要求。在同一时间的力学。利用有限元方法对力-热耦合状态下后视镜组件的表面精度，结构强度和动态刚度进行了仿真分析。仿真结果表明，镜面分量的一阶固有频率为393.73Hz，1g重力的RMS值分别达到8.920nm，1.856nm，4.516nm。在lg重力和4摄氏度三个方向上的上升耦合状态下，RMS值分别达到10.02nm，3.312nm，5.718nm，结果满足RMS值小于λ/ 50（λ= 632.8nm）的设计规格要求。 。最后，对后视镜部件进行了随机振动分析，结果表明，后视镜及其支撑结构设计合理，可以满足空间应用的要求。

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