大型GEO通信卫星平台转移轨道段热分析

为了增强大型高价值卫星的抗风险能力，针对极端温度环境以及相较一般发射工作程序有所偏离的情况，进行转移轨道卫星平台的热性能分析。对抛整流罩、星箭分离、出地影、南板受照、北板受照5个典型状态下的卫星平台进行热分析，结果显示:卫星平台本体的温度包络为51.68～-16.35 ℃，未超出一般要求，表明卫星平台的热性能有一定保持能力，但平台本体温度与热控要求间的裕度仅3.3～3.6 ℃，须予以关注；同时，采用3D舱板的有限元分析方法揭示出服务舱板厚度方向热梯度在出地影时刻最大值达5 ℃，对结构精度和机构运动性能或带来潜在风险。

Thermal analysis of large communication satellite platform in geostationary transfer orbit

To enhance the anti-risk capability of the high-value large communications satellite under extreme thermal conditions, and with some deviation from the selected working procedure, this paper analyze the platform temperature distributions in the geostationary transfer orbit(GTO) in five typical states, namely, the fairing jettisoning, the SC/LV separation, the exiting from the Earth’s shadow, the +y board under illumination, and the -y board under illumination. The thermal analysis result shows that the temperature of the platform is from 51.68 ℃ to-16.35 ℃, well within the required temperature limit, which demonstrates that the platform has an adequate ability to keep its temperature condition, but the margin between the temperature of the platform body and the thermal control requirements is only between 3.3 ℃ and 3.6 ℃, which should be paid attention to. At the same time, the finite element analysis method with 3D cabin reveals that the maximum thermal gradient in the direction of the thickness of the service cabin is 5 ℃at the time of exit from the ground shadow, which may bring potential risks with regard to the structural accuracy and the kinematic performance of the mechanism.