摘要
主次镜支撑结构设计是航空相机高质量成像的关键技术之一。基于反射镜支撑的刚度和面形精度的分析,对某航空双波段相机主次反射镜柔性结构进行了设计。提出了主镜周边柔性支撑配合胶粘的形式,使得反射镜组件对外部接点可以远离镜面,从而消除了反射镜安装镜框的装配应力对镜面面形的影响。由有限元分析软件,对主次镜的刚度和面形精度进行了分析,结合分析结果实现了对主次镜的优化,并验证分析了2 g^5 g加速度过载工况下的主次镜面形精度。分析结果表明,主次镜在施加重力和5℃均匀温升综合作用下优化后的面形精度达到PV<λ/10,RMS<λ/40(λ=632.8 nm),主镜组件一阶固有频率为241.7 Hz,均满足设计要求。
The support structure design of primary-secondary mirror is one of the key techniques for high quality imaging. Based on the analysis of the mirror support stiffness and the surface shape accuracy, the flexible support structure of the primary-secondary mirror is investigated. The flexible support with adhesive form is provided to the primary mirror, by which the mirror assembly external connection point will be as far as possible from the mirror reflector frame assembly and eliminate the influence of stress on the surface. Using the finite element analysis, the primary and secondary mirror stiffness and surface shape precision are analyzed, and with the analyzed results, the primary and secondary mirror are optimizated. the surface shape accuracy analysis is accompanied on the operating condition of 2G ~ 5g acceleration overload. The analysis results show that, the optimized primary and secondary mirror surface precision on the operating condition of weight and 5 temperature rise is up to℃ PV<λ/10, RMS<λ/40(λ=632.8 nm), and the primary mirror assembly first-order natural frequency is 241.7Hz, which can meet the requirements for the primary mirror.
出处
《仪器仪表学报》
EI
CAS
CSCD
北大核心
2014年第S1期77-81,共5页
Chinese Journal of Scientific Instrument
关键词
空间相机
主镜
支撑结构
柔性铰链
有限元分析
space camera
primary mirror
support structure
flexible hinge
finite element analysis
