日—地系拉格朗日L1点太阳望远镜热控技术研究

发布时间：2018-01-30 13:45

  本文关键词： 太阳望远镜 深空探测 热设计 热分析 热光学分析 日冕仪 空间光学遥感器　出处：《中国科学院研究生院(长春光学精密机械与物理研究所)》2013年硕士论文　论文类型：学位论文

【摘要】：为实现对空间环境的监测，提出了太阳观测计划，该计划拟将太阳观测望远镜发射到离地球150万公里的日-地系拉格朗日L1点附近的halo轨道。该相机属于深空探测任务，搭载了日冕仪（LACI）和成像仪（LADI）两台设备，由于长期对日定向观测，且轨道外热流密度大，，对于热控设计来说是个挑战。 1.本文对国外同类型产品的热设计方案进行了研究，通过对比各个热设计方案，分析了该轨道太阳观测望远镜热设计的特点； 2.介绍该太阳观测望远镜的组成和结构特点，并分析了轨道热环境，计算该轨道的太阳外热流密度； 3.结合望远镜自身的特点制定滤光片组件、电箱组件、CCD组件、LACI反射镜M2光阱组件和整机的热设计方案，通过在向阳面布置集热板，将主动加热功耗降低73%，通过多套方案的对比，最终选择较为合理的热设计方案； 4.通过I-DEAS/TMG软件对三维模型进行网格划分、仿真分析，计算出各个工况下相机温度的分布情况，验证表明各组件均符合温度指标要求。该热设计方案以较低的加热功耗，解决了太阳观测器在轨工作阶段的散热、轨道转移阶段的保温、工作状态下CCD组件与探测器主体间不小于70℃温差的保障等问题； 5.基于上述方案对相机进行优化热设计，得到最合理的热控措施。给出集热板表面属性的选择建议、控温点的设置依据、热管的安装方式，对于航天器热控制技术提有一定的指导意义。 6.基于PATRAN对该太阳望远镜进行热弹性计算，对反射镜镜面各节点拟合计算，得到6面反射镜各自的面形结果，将面形结果与光学设计要求进行对比，表明该热设计方案满足光学指标，验证了热控分系统的可行性；最后计算系统的动态刚度得到一阶固有频率为73.3Hz，满足发射和在轨要求。
[Abstract]:In order to realize the monitoring of the space environment, a solar observation plan was put forward. The plan is to launch the Solar Telescope into halo orbit 1.5 million kilometers from Earth near the Lagrangian L1 point. The camera is a deep space exploration mission. It is a challenge to the design of thermal control because of the long term directional observation of the sun and the high heat flux outside the orbit. 1. The thermal design schemes of the same type of products abroad are studied in this paper. The characteristics of the thermal design of the orbiting solar observation telescope are analyzed by comparing the various thermal design schemes; 2. The composition and structural characteristics of the solar telescope are introduced. The thermal environment of the orbit is analyzed and the heat flux outside the orbit is calculated. 3. According to the characteristics of the telescope, the thermal design scheme of the filter assembly, the CCD component of the electric box and the M2 optical trap assembly of the LACI reflector and the whole machine are made, and the collection plates are arranged on the positive side. The power consumption of active heating is reduced by 73, and through the comparison of multiple schemes, a more reasonable thermal design scheme is finally selected. 4. The 3D model is meshed by I-DEAS-TMG software, and the temperature distribution of the camera is calculated by simulation and analysis. The verification shows that all the components meet the requirements of the temperature index. The thermal design scheme solves the heat dissipation of the solar observer in orbit operation phase and the thermal insulation in the orbit transfer phase with lower heating power consumption. The protection of temperature difference between the CCD module and the detector body is not less than 70 鈩

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