高轨星载GNSS天线与平台结构一体化热耦合设计方法

Integrated Thermal Coupling Design Method of GNSS Antenna on High Orbit Satellite and Platform Structure

为解决星外天线在轨较大温差所产生的热变形过大,以及热控为减小温差所产生的整星资源消耗等一系列问题,提出了一种高轨卫星星载全球导航卫星系统(GNSS)天线热设计方法。通过将天线"镶嵌"在卫星对地板里,使天线与整星机热一体化耦合,利用整星内部的辐射热环境减小天线高低温差,降低主动控温加热器占空比,从而为整星节省能源消耗。通过热仿真分析验证,与传统的隔热设计对比,寿命末期冬至最高温降低6.7℃,加热器占空比减小35.8%,每个轨道周期能源消耗减小928 kJ。通过在轨验证,该方法可供同类高轨卫星天线热设计借鉴。

In order to solve a series of problems, such as the large thermal deformation caused by the large temperature difference in orbit, and the whole satellite resource consumption caused by the thermal control to reduce the temperature difference, a thermal design method of GNSS antenna on high orbit satellite is proposed. By embedding the antenna in the satellite’s panel facing the earth, the antenna and the satellite are mechanical and thermal integration coupling. Using the radiation thermal environment inside the whole satellite, the high and low temperature difference of the antenna and the duty cycle of the active temperature control heater are reduced, so as to save energy consumption for the whole satellite. Verified by thermal simulation analysis and compared with the traditional thermal insulation design, the maximum temperature of winter solstice at the end of its life is reduced by 6.7℃, the duty cycle of heater is reduced by 35.8%, and the energy consumption per track cycle is reduced by 928 kJ. Through on orbit verification, this method can be used for reference in the thermal design of similar high orbit satellite antennas.