The main load-bearing structure determines the stability of the space optical remote sensor and is a key structure of the system. It has the characteristics of large structural size, multiple interfaces, high stability and light weight requirements. A main bearing structure composed of aluminum honeycomb composite sandwich panels was designed to meet the high stability requirements of space optical remote sensor. The space optical remote sensor is in an extremely complicated space orbit thermal environment when it works on orbit. In order to solve the problem about the thermal deformation measurement of the main bearing structure of optical remote sensor, a digital photogrammetry system is proposed. The test system is built and the test conditions are designed for test verification. The research results indicate that the stability of the main bearing structure meets the requirements. The accuracy of digital photogrammetry system can reach 0.05mm, which provides a technical basis for the reasonable prediction of optical remote sensor optical structure on-orbit thermal deformation.
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