To meet design requirements of the small off-axis space camera with compact structure and light weight, a highly lightweight integral carbon fiber main frame is designed. First, according to the design indicators and the optical system of the specific functions of the space camera, the material and structure of the main frame are determined. And the basic configuration of the carbon fiber monolithic main frame is designed. Then, the layup thickness is parameterized and optimized. The manufacturing constraints of carbon fiber composite materials are considered. The thickness and proportion of the main frame carbon fiber layup are determined. The results of parametric optimization are discretized, the stacking sequence of carbon fiber is optimized, the optimal stacking sequence is determined, the optimization design of carbon fiber is achieved, the lightweight design of the main frame is realized, and the optimization problem of complex carbon fiber parts is solved. Next, the designed carbon fiber main frame structure is substituted into the finite element model of the whole machine, and the finite element simulation analysis is implemented to verify the performance index of the main frame. Finally, the whole machine is assembled for dynamic test, and compared with the finite element analysis results. After optimization, the mass of the carbon fiber main frame is 4. 5 kg, the first-order frequency of the camera is 81 Hz, the first-order frequency of the camera obtained through the dynamic test is 78 Hz, and the simulation error is 3. 7% , which is in line with simulation results. Results further explain the rationality and correctness of the design. The design method of carbon fiber integral main frame of space camera proposed in this article has a certain reference significance for the structural design of micro off-axis three trans space camera and the lightweight optimization design of carbon fiber parts.