Beijing Jinkun Technology Co., Ltdwww.jonkon.com.cn

Tan Jinguo1，2He Xin1Pay Liangliang1
（1.Changchun Institute of Optics, Precision Mechanics and Physics, Chinese Academy of Sciences, Changchun, Jilin130033；
2. Graduate School of the Chinese Academy of Sciences, Beijing100039）
Abstract: The space remote sensorreflectorThe working temperature is18±15℃, RequestreflectorMeet the design requirements under these complex operating conditions. introducedreflectorSelection of materials and supporting structural materials; toreflectorAnalyzed and discussed the support methods, lightweighting, and other aspects; according toreflectorThe design principle of flexible support structure adoptsCAD/CAEThe engineering software was analyzed and optimized, and a flexible structure supported by the center of the reflector was designed through finite element method. Within this temperature range,reflectorChange in surface shape errorPVValue less thanλ/10TheRMSValue less thanλ /40（λ=632.8 nm）Afterwards, the mechanical environment experiment was conducted to test the shape change of the reflector surface and the dynamic characteristics of the simulated reflector component, proving that the structure meets the design requirements.
Keywords Central support; Small reflector mirror； flexible structure
Classification number:TH122Document identifier code:AArticle Number:1007-2276（2010）06-1070-05
Support technique in centre of minitype reflector
TAN Jin-guo1,2, HE Xin1, FU Liang-liang1
（1. Changchun Institute of Optics, Fine Mechanics and Physics, Chinese Academy of Sciences, Changchun 130033, China；
2. Graduate School of the Chinese Academy of Sciences, Beijing 100039, China）
Abstract: The working temperature of space remote sensor reflector is 18 ±15 ℃in this article, and
the reflector in the complex working condition needs to meet the design requirements. The choices of the reflector materials and the supporting structure materials were introduced. The supporting way and the lightweight structure of the reflector and so on were discussed. According to the design principles of the flexible supporting structure of the reflector and using CAD/CAE engineering software for analysis and optimization, a kind of reflector flexible structure of centre support was designed by means of finite element method （FEM）. Surface deformation less than λ /10 （PV） and λ /40 （RMS） （λ =632.8 nm）in this temperature range. Finally, the changes of reflector surface deformation and the dynamic characteristic of reflector component simulators were tested by the mechanical environment test. The conclusion is proved that the structure of the reflector meets the demand of the optical design.
Key words: Centre Support;Minitype reflector; Flexible structure

0 Introduction
With the development of space remote sensing industry, the application of space remote sensors is becoming more and more widespread, which also puts forward higher requirements for the imaging quality of remote sensors
Please. due toreflectorEven small deformations can affect the imaging quality of remote sensors. Therefore,reflectorThe supporting technology has become one of the key technologies for developing space optical remote sensors. Due to the fact that mirrors are critical components of imaging systems, their accuracy and stability directly affect the quality of imaging. Therefore,reflectorThe supporting technology has become one of the key technologies for engineering applications. The mirror studied in this article is the main mirror of a certain type of small space remote sensor. Its external dimensions are184 mm×153 mm×30 mm， The precision of the mirror surface shape has reachedPV≤λ/10，RMS≤λ/40(λ=632.8 nm)The ambient temperature is18 ±15℃.reflectorThe support should ensure the stability of the position and surface accuracy of the reflector in the same state, while effectively reducing the impact of deformation of the connected components due to external environmental changes on the mirror surface accuracy. In addition, it is also necessary toreflectorHas good dynamic performance and can withstand the impact and vibration generated during the launch phase.

Beijing Jinkun Technology Co., Ltdwww.jonkon.com.cn