摘要
为提高遥感相机主反射镜的在轨面形和结构稳定度,文章对φ650 mm主反射镜组件进行了特殊结构设计,采用传统的装框式支撑结构,通过设计使胶斑切向受力,以有效解决镜子和支撑结构材料热失调问题。力学和热特性计算表明:主反射镜面形在y向(地面装调方向)1g重力作用下的峰谷值(PV)变化为2.30 nm,均方根值(RMS)变化为0.42 nm,镜子顶点位置变化为0.8μm,光轴变化为0.01″;在相机温控指标(20±2)℃环境下,反射镜的PV变化为3.02 nm,RMS变化为0.56 nm;主反射镜的计算仿真基频为164.3 Hz。主反射镜组件振动试验结果显示组件的实际基频为158.0 Hz,与仿真计算结果基本一致。经过振动和真空放气试验,组件的结构接口稳定性均为平移不大于3μm,角度变化不大于3″。以上全部满足设计指标要求。
To improve the in-orbit surface and structural stabilities of the primary mirror for the remote sensing camera, a special design of a 650 mm primary mirror assembly is presented in this paper. The traditional frame support structure is used for the mirror subassembly, and the glue spot is subjected to shear loads in this structure to make a uniform distribution of the thermal expansion of the materials of the mirror with the support structure. The structural analysis of the mirror assembly shows that the optical surface error is 2.30 nm（PV） and0.42 nm（RMS）; the displacement of the mirror vertex is 0.8 μm, and the light axis deviation of the mirror is 0.01″under 1 g gravity in the y direction, on which the mirror subassembly is tested. And the optical surface error is3.02 nm（PV） and 0.56 nm（RMS）, respectively under a（20±2） ℃ thermal environment, as complied with the camera thermal requirement on obrit. The simulated natural frequency of the mirror assembly is 164.3 Hz,basically in accordance with the experimental result of 158.0 Hz. After a routine vibration and vaccum outgassing test, the structural displacement is measured to be less than 3 μm and the degree deviation is less than 3″. It is shown that all concerned properties of this large-aperture space mirror meet the design requirements.
作者
史姣红
罗世魁
唐璐
罗廷云
SHI Jiaohong;LUO Shikui;TANG Lu;LUO Tingyun(Beijing Institute of Space Mechanics ＆ Electricity,Beijing 100190,China)
出处
《航天器环境工程》
2018年第3期258-262,共5页
Spacecraft Environment Engineering
关键词
主反射镜组件
结构设计
仿真计算
地面环境试验
primary mirror assembly
structural design
simulation calculation
ground environmental test
