Research On Circumjacent Support Structure Of Minitype Relfector In Space Camera

The space camera is the important effective payload of remote satellite. It is a basic conditionof satisfying imaging quality requirement of the optical system, to make each optical componentof the optical system archive precision index, in status of ground test, launch and orbital flight.Changes of external environment factors such as gravity, temperature and pressure etc, causedistortion of reflector, and the change of position and angle between optical components,furthermore influence imaging quality of the optical system, because of high precisionrequirements of the optical system. Therefore, the support structure of the reflector must ensurethat reflector could satisfy index requirements in each load case, and have good static anddynamic properties at the same time. Akind of circumjacent support structure design of minitypereflector in the space camera was discussed in the dissertation which included followingcontents:1. Choosing materials of the reflector and the support structure, and considering physicalproperties of materials such as density, elastic modulus and expansion coefficient, under theprecondition of satisfying utility requirements.2. Choosing support style of the reflector. According to figure and measurement characterof the reflector and utility requirements, circumjacent support style was chosen. According tosemi-kinematics localization theory, restriction of six degrees of freedom was realized.3. The flexible lamina theory of installation frame and the parametric design method offlexible gemel were adopted to design support structure of the reflector. 4. The finite element model of the reflector subassembly was established. Then supportstructure of the reflector was analyzed and pivotal part of which was optimized.5. Dynamic experiment and vacuum thermal cycle experiment of the reflector subassemblyhad been done so as to test influence of experiments to surface contour precision, and to validatethe 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 and temperature, made resultsthat the change quantity of surface contour of reflector was PV≤λ/10, RMS≤λ/50, that thechange quantity of position and angle were both in allowed range, and that the test measurementof surface contour was not changed after dynamic experiment and vacuum thermal cycleexperiment. The conclusion was validated that the support structure of the reflector could ensureits surface contour precision and position precision, which had good static and dynamicproperties at the same time, and could satisfy design and utility requirement. The supportstructure was benefit to other similar measurement minitype reflector of reference.