航天器热变形控制设计及验证

Design and Verification of Thermal Deformation Control for Spacecraft

随着载荷高精度探测能力的提升,对航天器安装精度控制及保持要求越来越高,由太空复杂热环境引起的结构变形成为精度尺寸链上必须考虑的技术难题。本文基于某型号研制过程,为实现对飞行器指向的高精度控制,对航天器系统级热变形控制进行设计,模拟在轨典型外热流工况设计工况完成全系统热变形试验,使用数字摄影和经纬仪获取试验数据,并通过仿真对在轨状态进行评估,分析验证了航天器热变形控制设计的有效性,对评估航天器在轨运行期间的热变形具有参考意义。

With the improvement of the ability of high-precision detection of payloads,the requirements for the control and maintenance of spacecraft installation accuracy are becoming higher and higher.Thermal deformation of structure caused by thermal environment changes has become a technicl probelm that must be considered in the precision dimension chain.This paper is based on the development process of a certain type,in order to realize the high-precision control of pointing aircraft,the spacecraft system-level thermal deformation control is designed.The simulation of typical in-orbit external heat flow conditions is designed to complete the system-wide thermal deformation test.The test data is obtained by digital photography and theodolite,and the in-orbit stata is evaluated by simulation.The analysis verifies the effectiveness of the thermal deformation control design of spacecraft,which has reference significance for evaluating the thermal deformation of spacecraft during orbit operation.