Stability Analysis Of Structure Dimension Of Optical Reflector Subassembly

Space optical remote sensor is a kind of space precision optical instrument to perfect the earth observation. It benefits the social and economy and is valued by governments, public and the community of space technology. It calls much strict on relative position between optical components and their surface shape. High quality of image demands for good dimensional stability of optical remote sensor system structure, which will be usually changed in the mechanical environment as the sensor is set off and carried.The mechanical environment as the sensor is set off and carried, which include mainly impact, vibration and overload, as well as statics and thermal environment, directly influence the dimensional stability of the sensor, then influence whether the sensor can make accurate imaging.This paper deals with how to lighten the structure of the space optical mirror to maximize, as the same time, to make sure the system rigidity and stiffness are good. Focusing on the design of the space optical remote sensor, we mainly work on the following topics:1. Based on comparative analysis of the performance, we chose a proper material for the mirror. Then we fixed the form of the lightweight hole after a series of design and analysis. All of these lay the foundation for the implementation of the lightweight design.2. Based on rational supporting structure design and according to equivalent principle, we built the geometrical model of the space optical remote sensor, then the finite element model is also built on the basis of it.3. Based on analysis of statics and thermo elasticity, we adopted well designed flexible hinge supporting structure in the respect of structural parameter, which has good rigidity and stiffness, to make the system structure meet the requirements of imaging.4. Based on analysis of the mirror and its units, we can make sure that the structure stiffness is good enough to avoid the vibration, which is caused by moving component of the sensor, thereby to guarantee the surface precision of the mirror and finally guarantee the quality of the imaging of the camera.5. Based on analysis of the low frequency sin vibration response of the mirror and its units, we got the position where the maximum stress of the response curve and the maximum acceleration happened.6. Based on analysis of the random vibration response of the mirror and its units, we got the position where the response curve is. It indicated that, the design of the mirror and its units meet the design requirement and can guarantee the stability of the optical components and the quality of the imaging of the space optical remote sensor in an adverse mechanical environment.