Abstract

The core optical component of a composite IRST system is a scanning space mirror component, which is the mirror which shape of optical reflector possessing large flakiness ratio, which always effected by the wide-range temperature and harsh environment (especially in – 45°C）in optical system. To suppress the deformation, a flexible support structure for the reflector is designed in this paper. Based on the flexible support principle and thermodynamics theory, a new flexible support structure is designed for small-light-strip space reflector. A flexible support structure was proposed to keep the surface figure accuracy under temperature change load and 0.06mm installation error cases. By adopting finite element analysis software, the mirror component was analyzed. And some experiments are carried on the optical reflector system in-45°C and 0.06mm forced linear displacement. The result shows that the accuracy of reflector surface remains 0.2λPV（λ＝632.8nm, peak-to-valley. These results demonstrate that the novel flexible supporting structure design satisfies the application environment and space requirements.

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