大型高轨通信平台主动段热变形分析

对于大型高轨通信卫星等的高价值卫星，为增强卫星的抗风险能力，对极端温度环境条件和相较一般发射工作程序有所偏离的情况下，进行了卫星平台的热分布情况分析。采用了能够较全面深入反映平台结构热变形的3D舱板模型的有限元分析方法。表明最高温度50.8 ℃，最低温度-11.89 ℃，未超出卫星的极限温度要求，卫星平台的热性能有一定保持能力。舱板厚度方向温差2.5 ℃。对分析的热分布结果与一般条件下的热平衡试验结果进行了分析比较，分析结果较一般条件下的热平衡试验结果温度高出约25 ℃。在热分析结果基础上所做的卫星平台热变形分析，表明舱板的最大变形在抛罩时刻为0.185 mm，在星箭分离时刻为0.506 mm，已经接近结构局部精度的要求量级。在抛罩和星箭分离时的服务舱仪器板的热变形方向相反，预示着这里是热振动的潜在振源。

Thermal Deformation Analysis of Large High Orbit Communications Platform

For enhancing the anti risk capacity of a large high orbit communications satellite with a high value, the thermal distribution is analyzed for the satellite platform under the extreme thermal environmental conditions as well as the situations different from the usual launch procedure. The 3D structural plate finite element analysis method is adopted to comprehensively and deeply reflect the thermal deformation of the platform structure. It indicates that the highest temperature of 50.8 ℃ and the lowest temperature of -11.89 ℃ are all within the extreme temperature limits of the satellite, and the thermal performance of the satellite platform can be kept to a certain degree. The temperature difference through the module plate thickness is 2.5 ℃. Compared with the usual thermal equilibrium test result, the thermal analysis result in this paper is about 25 ℃ higher. The satellite platform thermal deformation analysis based on this thermal analysis result indicates that the biggest module plate thermal deformations are 0.185 mm and 0.506 mm at fairing jettison and SC/LV separation respectively, which are close to the required local structural precision. The thermal deformation directions of the service module instrument plate at fairing jettison and SC/LV separation are contrary to each other, indicating that this is the potential source of thermal vibration.