光学小卫星主载荷承力结构的多工况优化设计

为了降低光学小卫星相机次镜上的随机响应，提出了一种蜂窝夹层板结构的优化设计方法，对小卫星光学载荷的蜂窝安装板进行结构参数的优化设计。首先，以整星一阶频率不低于40 Hz为优化目标，对蜂窝芯子密度进行优化，根据三明治夹心理论，推导计算了蜂窝芯子等效力学参数。然后，以次镜的随机响应为优化目标，对蜂窝夹层板的碳纤维面板进行铺层优化设计，得到最优铺层顺序为0/45/90/-45]S，总厚度为0.8 mm。根据以上计算得出蜂窝芯子及碳纤面板等效参数，对整星进行分析。最后，开展了整星振动试验，测量了整星模态和响应，对试验数据进行采集。结果表明:整星模态为42.2 Hz，次镜最大随机响应为11.1g，均在合理范围之内，满足了组件力学要求。

Multi-condition optimization design of main load bearing structure of optical small satellite

In order to reduce the random vibration response of the secondary mirror of the optical camera, a new method was presented to optimize the honeycomb sandwich plate. With this method, the structure parameters on the honeycomb core and the panels of bearing honeycomb plate of the optical payload of the satellite were optimized. Firstly, the satellite's fundamental frequency was greater than 40 Hz as the optimization goal, optimization design of the honeycomb core density was carried out. Besides, the equivalent mechanical parameters of the honeycomb core were calculated based on the sandwich plate theory. Secondly, taking the random response of the secondary mirror as the goal, the design of laminate of carbon fiber panel honeycomb sandwich plate was optimized, optimum laminate sequency was0/45/90/-45]S with the total thickness of 0.8 mm. Based on the equivalent mechanical parameters of the honeycomb core and panel, the finite element model of the entire satellite was analyzed. Finally, the vibration test was carried out, in which the fundamental frequency and random response were collected. The test results shows that the fundamental frequency is 42.2 Hz and the RMS of the secondary mirror is 11.1g, which are both within a reasonable range and can meet the design requirements.