Design and Verification of Thermal Deformation Control for Spacecraft
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.