Optimal Research On800mm Reflect Mirror And It’s Support Structure Of Space Camera

With the rapid development of science and technology, people put forwardincreasingly demanding about space camera.The reflect mirror assembly is one ofmost important component of space camera, whose diameter keeps increasingbringing about some new problems, for example, gravity and changes of temperaturemay affect the surface figure sensitively. From the above all, it is needed tolightweight design large diameter reflect mirror reasonably and effectively. The businterface bears the total weight of reflect mirror, it must satisfy the stiffnessrequirement with lightest weight. This paper gave out some research and design aboutan800mm diameter reflect mirror, including the support structure and bus interface.The paper presents the investigation about different features of commonly usedmaterials. SiC is a kind of composite material with well specific stiffness and thermalconductivity. Considered the situation in the mission, SiC was chosen to make themirror at last. The mirror was designed in two ways of basic shape and lightweight,and finally the mirror was designed as back-closed with triangular lightweight holes.The positions of9points in back of the mirror were optimal designed then, makingeach point got approximately equal stress when the optical axis vertical.The mirror assembly will be undergo complex mechanical environment, so thesupport structure must be reasonable designed with flexible hinge. By comparing theclassical and modified flexible hinges, the back support was designed as thin rod.Combined sensitivity analysis and parameter optimization, adjusting the parameterbased on the sensitivity analysis. This method is more efficient than the traditional,and the result can be excellent. Finally designed9supports in the back of mirror and6lateral, which reached well mirror figure.The paper firstly designed9supports in the back of mirror, but it was approvedthat cannot get the requirement, therefore6lateral support was designed.Carbon fiber composite material was used to process the bus interface.Considering the characteristic of carbon fiber composite material, the bus interface was design as flanged beam to some extent. This form of structure can get excellentspecific stiffness and high rate of lightweight. Then the mirror assembly wassimulated in the way of finite element method, including gravity and temperatureimpact analysis, modal analysis, overload analysis and random vibration analysis. Allthe above analysis demonstrates that the mirror assembly took perfect characteristic,which fully satisfy the requirements. There are some deficiencies in the paper, futureplan was presented at the end, so that the continued job can be proceed reasonably.