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首页> 外文会议>American Society of Mechanical Engineers(ASME) Summer Heat Transfer Conference(HT2005); 20050717-22; San Francisco,CA(UA) >INTEGRATED THERMAL DEFORMATION MODELING AND MEASUREMENT OF SPACE OPTICAL SYSTEMS
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INTEGRATED THERMAL DEFORMATION MODELING AND MEASUREMENT OF SPACE OPTICAL SYSTEMS

机译：空间光学系统的热变形综合建模与测量

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摘要

A computational and experimental study of the thermal, response and thermally induced deformation of a circular piano mirror (101.6 mm in diameter) undergoing mW heat loading was performed to verify the capability to model the response of a representative imaging optic on the Space Interferometry Mission (SIM) spacecraft. Novel state of the art experimental and computational techniques provided milliKelvin and picometer precision in temperature and deformation prediction and experimental measurement. Mirrors of two different substrates, initially at ambient temperature, were subjected to nominal thermal loading profiles of three 5 hour steps of 12 mW, 54 mW, and 295 mW respectively, representing flight-like and overdrive thermal disturbance conditions. The experimental setup measured milliKelvin level temperature changes using the mKTMS (milliKelvin Temperature Measurement System) instrument and picometer level deformation responses using the CoPHI (Common Path Heterodyne Interferometer) instrument. I-deas/TMG was used to generate an integrated model to predict milliKelvin level temperature changes of the mirror and picometer level deformation responses of the mirror surface. This paper focuses on the thermal modeling and correlation to thermal experimental data of the optical system. Comparison between experimental results and computational models for the thermal aspects of the test show good agreement for the two test mirror materials, fused silica and Zerodur. In particular for the flight-like regime of primary interest, agreement between the experimental temperatures and computational thermal results was within 14%.
机译：对经受mW热负荷的圆形钢琴镜（直径为101.6 mm）的热，响应和热致变形进行了计算和实验研究，以验证能够对空间干涉测量任务中代表性成像光学器件的响应建模的能力（ SIM）航天器。最新的实验和计算技术为温度和变形预测以及实验测量提供了毫开尔文和皮米级的精度。最初处于环境温度下的两种不同基板的反射镜分别经历了三个5小时步长的标称热负荷曲线，分别为12 mW，54 mW和295 mW，这代表了飞行和超速驱动的热干扰条件。实验装置使用mKTMS（milliKelvin温度测量系统）仪器测量了毫开氏温度变化，并使用CoPHI（共通外差干涉仪）仪器测量了皮米级变形响应。 I-deas / TMG用于生成一个集成模型，以预测反射镜的毫开氏温度变化和反射镜表面的皮米级变形响应。本文重点研究光学系统的热建模及其与热实验数据的相关性。在测试的热学方面，实验结果与计算模型之间的比较表明，两种测试镜面材料（熔融石英和Zerodur）具有良好的一致性。特别是对于主要感兴趣的类飞行状态，实验温度与计算热结果之间的一致性在14％以内。

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