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Thermally-induced structural motions of satellite solar arrays.

机译：卫星太阳能电池阵列的热诱导结构运动。

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Satellites have experienced attitude disturbances resulting from thermally. induced structural motions of flexible appendages since the early days of the space program. Thermally-induced structural motions are typically initiated during orbital eclipse transitions when a satellite exits from or enters into the Earth's shadow. The accompanying rapid changes in thermal loading may lead to time-varying temperature differences through the cross-section of appendages resulting in differential thermal expansion and corresponding structural deformations. Since the total angular momentum of the system must be conserved, motions of flexible appendages such as booms and solar arrays result in rigid body rotations of the entire satellite. These potentially large attitude disturbances may violate satellite pointing and jitter requirements. This research investigates thermally-induced structural motions of rigid panel solar arrays (solar panels) through analytical and experimental studies. Orbital eclipse transition heating and thermal analyses were completed to study solar panel thermal behavior and provide results for input to dynamics analyses. A hybrid coordinate dynamical model was utilized to study the planar dynamics of a simple satellite consisting of a rigid hub with a cantilevered flexible solar panel undergoing thermally-induced structural motions. Laboratory experimental studies were carried out to gain new insight into thermal-structural behavior and to validate analytical models. The experimental studies investigated the thermal-structural performance of honeycomb sandwich panels and satellite solar panel hardware subject to simulated eclipse transition heating. Results from the analytical and experimental studies illustrate the importance of the through-the-thickness temperature difference and its time derivatives as well as the ratio of the characteristic thermal and structural response times in solar panel thermally-induced structural motions. The thermal-structural tests demonstrated quasi-static thermally-induced bending deformations of solar panels in the laboratory. During heat-up and cool-down the solar panels exhibited short duration acceleration transients with characteristic thermal snap disturbance histories. Thermal-structural models were validated through comparison of test results and predictions from finite element analyses. Overall, results for the measured and predicted responses of the solar panels showed good agreement. Importantly, the analyses correctly predicted all of the key features of the solar panel thermal-structural response.
机译：卫星经历了由热引起的姿态扰动。自太空计划初期以来就引起了柔性附件的结构运动。当卫星从地球阴影中出来或进入地球阴影时，通常会在轨道月食过渡期间引发热引起的结构运动。伴随的热负荷快速变化可能导致通过附件横截面的时变温度差异，从而导致差异的热膨胀和相应的结构变形。由于必须保持系统的总角动量，因此柔性附件（例如吊杆和太阳能电池阵列）的运动会导致整个卫星发生刚体旋转。这些潜在的大姿态干扰可能会违反卫星指向和抖动的要求。这项研究通过分析和实验研究来研究热致刚性面板太阳能电池阵列（太阳能电池板）的结构运动。完成了日食过渡加热和热分析，以研究太阳能电池板的热行为，并为动力学分析提供输入结果。利用混合坐标动力学模型研究了一个简单的卫星的平面动力学，该卫星由一个刚性毂和一个悬臂式柔性太阳能板组成，这些板经历了热诱导的结构运动。进行了实验室实验研究，以获取对热结构行为的新见解并验证分析模型。实验研究了蜂窝夹心板和人造日光板硬件在模拟月食过渡加热条件下的热结构性能。分析和实验研究的结果说明了整个厚度的温差及其时间导数的重要性，以及太阳能电池板热致结构运动中特征热响应时间和结构响应时间之比。热结构测试表明，在实验室中准静态热诱导的太阳能电池板弯曲变形。在加热和冷却过程中，太阳能电池板的短时加速瞬变具有特征性的热瞬态扰动历史。通过比较测试结果和有限元分析预测，验证了热结构模型。总体而言，太阳能电池板测量和预测响应的结果显示出良好的一致性。重要的是，分析正确地预测了太阳能电池板热结构响应的所有关键特征。

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