The scan mirror is an very important part of a space remote sensor. This paper discusses the material development and the manufacture method of the big lightened scan mirrors.
扫描镜是光机扫描型空间遥感器的重要组成元件。文章针对目前空间遥感器上应用的大口径轻量化扫描镜，从材料和制作方法方面进行了一定的技术研究。
In order to make reflectors of the space remote sensor keep both high rigidity of structure and fine stability of thermal dimension, a kind of flexible cone-shaped sheath is designed.
针对空间光学遥感器反射镜结构刚度高、热尺寸稳定性差的状况，设计了一种柔性锥套结构，它在保持结构刚度满足力学要求的同时，使反射镜具有良好的热尺寸稳定性。
The space optics remote sensor, being a subsystem for executing significant task, has special requirements for its structure, behavior, operating precision, seal, reliability and so on.
空间光学系统是执行重要任务的子系统，在结构及其性能、工作精度要求、密封性、可靠性等方面均有比较特殊的要求。
The structure scheme of baffle for space optical remote sensor is selected by means of finite element method.
利用有限元工程分析技术对空间光学遥感器的遮光罩结构方案进行了选择。
Dynamic environment in launching and thermal environment on orbit affect dimension stability of space optical remote sensor, thus declining its imaging quality.
发射过程中的力学环境和在轨运行时的热环境，影响航天光学遥感器的尺寸稳定性，进而影响成像质量。
The cylindrical electronic control box for the space optical remote sensor could work normally in the complex environment of space, meet the operation requirements.
设计的空间相机圆柱形电控箱能在复杂的空间环境下正常工作，满足航天使用要求。
With the development of the space optical remote sensor resolution and the primary mirror diameter, the lightweight design is becoming the key technology of the large aperture mirror.
空间光学遥感器分辨率要求的不断提高使其主镜口径也在不断增大，从而对主镜进行轻量化设计就成为空间大口径反射镜工程的关键技术。
The space optical remote sensor is influenced by the solar radiation, albedo, earth emitted infrared and other heat sources as flying in the heat dreariness astrospace.
空间光学遥感器在轨运行过程中要承受太阳辐射和空间冷热沉、黑热沉等恶劣温度环境的影响。
The space optical remote sensor is influenced by the solar radiation, albedo, earth emitted infrared and other heat sources as flying in the heat dreariness astrospace.
空间光学遥感器在轨运行过程中要承受太阳辐射和空间冷热沉、黑热沉等恶劣温度环境的影响。
应用推荐