| The deeper development of space optics technology, the greater diameter of the mirror for a space optics remote sensor is required. The weight deformation of the mirror becomes bigger as long as the increased diameter, which also makes greater mirror deformation arise from temperature variation. In order to screw down the launch costs of space optics remote sensor and reduce figure error of the mirror caused by bad working conditions, it is necessary to optimize analysis the mirror and its components, at mean while to make the structure lighter and stronger.The development history of space optics remote sensor and the basic theory for the further design is introduced. Several optimization design approaches of the mirror are conducted with different finite element software. A1-meter-aperture reflector is optimized. Firstly, the optimum position of support points of the mirror is conducted and the general rules of design are found out. Secondly, parameter optimization of the mirror structure is done. The mass of the mirror is reduced and the surface figure is improved effectively. Thirdly, topological optimization is conducted, which determines the final morphology of the mirror.2-meter aperture spherical mirror and its components is studied. The optimization analysis of the mirror and its support components is conducted, which makes the result consistent with the whole structure. The installation position of supports has great influence on the mirror’s surface flatness, which was found in the optimization process. A new flexible supporting structure is designed, which could save design space effectively and improve the surface figure. A truss structure is adopted for the supporting rear panel of the mirror, which could improve the structural stiffness effectively. |
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