The invention provides a telescope thermal control method for an aircraft adaptive to a sun-earth Lagrange point L2, and the method is characterized in that the method comprises the following steps: S1, shielding the direct irradiation of the sun of an L2 orbit through a satellite sailboard, and coating the outer surface of a space telescope light shield and the outer surface of a main body with a plurality of layers of thermal insulation assemblies; s2, designing a load temperature control cabin for the space telescope, and installing the telescope main body in the load temperature control cabin; s3, performing active temperature control on a cabin plate at the bottom of the telescope by adopting a PID (Proportion Integration Differentiation) high-precision temperature control algorithm based on pulse width modulation; s4, compensating radiation heat leakage of the primary mirror and the secondary mirror through the light inlet and the cold black background through two types of heaters of coarse control and fine control; and S5, solving the problem of temperature uniformity for the secondary mirror support truss of the telescope by adopting a variable heat flux density heater.
本发明提供了一种适应日地拉格朗日点L2飞行器的望远镜热控方法,其特征在于,包括如下步骤:S1、采用卫星帆板遮挡L2轨道的太阳直接照射,在空间望远镜遮光罩和主体外表面包覆多层隔热组件;S2、为空间望远镜设计载荷控温舱,望远镜主体安装于载荷控温舱内;S3、对望远镜底部舱板采用基于脉冲宽度调制的PID高精度控温算法进行主动温控;S4、通过粗控和精控两种类型的加热器补偿主、次镜通过入光口与冷黑背景的辐射漏热;S5、对望远镜次镜支撑桁架采用变热流密度加热器解决温度均匀性问题。
Telescope thermal control method suitable for sun-earth Lagrange point L2 aircraft
一种适应日地拉格朗日点L2飞行器的望远镜热控方法
2023-09-01
Patent
Electronic Resource
Chinese
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