Design And Research On Minitype Reflector Assemblies In Space Optical Remote Sensor

Optical element is a big part of the space optical remote sensor, the surface figureaccuracy of optical element has an important influence on the imaging quality of thespace optical remote sensor. Optical elements are processed, tested and aligned undergravity load case, they works under the microgravity environment, the supportstructure must have large static stiffness. On the other hand, all kinds of dynamicsconditions have an effect on the remote sensor when it was transported and launched,the support structure must have large dynamic stiffness. Moreover, the supportstructure must be better suitable for the assembly stress and thermal stress.A kind of circumjacent support structure design of minitype reflector in spaceoptical remote sensor was discussed in the dissertation which included followingcontents:1. Choosing materials of the reflector and the support structure, and consideringphysical properties of materials such as density, elastic modulus, thermal conductivityand expansion coefficient, under the precondition of satisfying utility requirements.2. According to the figure and size of the reflector and utility requirements, thestructural form of the reflector was determined.3. Choosing support style of the reflector. According to the structuralcharacteristics of the reflector and the space optical remote sensor, circumjacentsupport style was chosen.4. A flexible support structure was proposed to keep the higher surface accuracyof the reflector under gravity and uniform temperature change load cases.5. The finite element model of the reflector subassembly was established. Thesupport structure of the reflector was analyzed and pivotal part of which wasoptimized.6. Dynamic experiment and vacuum thermal cycle experiment of the reflectorsubassembly had been done so as to test influence of experiments to surface contourprecision, and to the availability of support structure.After above analysis and design, a kind of circumjacent support structure was designed. The analysis under the condition of different gravity orientation andtemperature, made results that the change quantity of surface contour of reflector wasRMS≤λ/50(λ=632.8nm), and that the test measurement of surface contour was notchanged after dynamic experiment and vacuum thermal cycle experiment. Analysisand experimental results demonstrate that designs of reflector and its support structureare effective, which can meet the requirements of space applications.