Abstract
The SiC scanning reflective mirror with a dimension of 460 mm×290 mm used in a spaceborne optical remote sensor is studied.The composite form of triangle and quadrangle and the combination of open and closed back are explored for the design of lightweight scanning mirror.A new kinematic mount and a flexible structure in axis is taken to hold the mirror around the lateral surface.The flexible structure in axis is used as an interface to the kinematic mount to support the mirror,which can eliminate the impact of thermal stress induced by the mismatch of thermal expansion coefficient among the materials on the mirror surfaces.Optical performance of the mirror is analyzed by using Finite Element Method(FEM).Results indicate that the surface figure errors are 4.5 nm and 20.3 nm under a gravity load of 1 g and the temperature load change of 8 ℃ in different directions.The results show that the lightweight designing and supporting structure of this scanning reflective mirror meet the requirements of optical imaging,and can improve the stability of structure effectively.It can be an important reference for the design of big size scanning reflective mirror components.
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