支撑结构是连接卫星与相机的关键部件, 在发射和在轨环绕阶段对相机提供保护和空间应用需求。深空探测器发射阶段的振动载荷高达13 g甚至更高(地球探测为8~9 g), 支撑结构既要克服剧烈振动可能造成的相机结构破坏还要保证光学系统的热稳定, 具有较高的设计难度。通过分析不同支座形式的结构特点设计了刚性支座、平动支座两种不同的支座形式, 从刚度和热稳定的均衡性出发将两种支座形式进行了组合设计, 提出了“一个刚性支座+两个平动支座”的设计方案。理论分析与实验验证得到: 该支撑结构的一阶频率为58 Hz, 远高于整星基础频率, 温降15 ℃仿真分析结果显示主镜偏转角为3.66″, 次镜及三镜相对主镜最大偏转角为7.85″, 均满足设计要求。振动及热平衡试验表明: 相机各项指标正常。

The support structure is a key component for connecting satellites and cameras to provide protection and space application requirements for cameras during launch and on-orbit surround stages. The vibration load of the deep space probe is 13 g(that of the earth exploration satellite is 8-9 g). The supporting structure should overcome the damage of the camera structure caused by the violent vibration and the thermal stability of the optical system, which has high design difficulty. In this paper, two different support forms of rigid foot and slider foot were designed by analyzing the structural characteristics of different support forms. The two kinds of support forms were designed from the balance of stiffness and thermal stability. The "A rigid foot+two flat foot" program was eventually adopted. The first-order frequency of the support structure is 58 Hz, which is much higher than that of the satellite base frequency. The simulation results show that the deflection angle of the primary mirror is 3.66″, the maximum angle change of second mirror and third mirror relative to primary mirror is 7.85″. They all meet the design requirements. Vibration and imaging tests show that the camera is working properly.