Abstract: 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/-45S 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.