To satisfy the space position requirement of a space camera to be installed onboard a satellite and avoid the sympathetic vibration between the space camera and the satellite, a cabin structure is designed. The design uses a carbon fiber with good mechanical and technological properties and a truss structure with a reasonable topological structure form. The section sizes of the pole in the cabin structure are optimized by using a computer simulation test method and a cubic spline interpolation. The result shows that both the dynamic features and the total mass of the cabin structure satisfy the design requirements for the section size of 28 mm×28 mm×3 mm.