Abstract: For reducing the weight of a satellite and enhancing its mechanical transfer performance, the carbon fiber T800H resin matrix composite material is used for the conical-columned integrated structural design of the stringer stiffened cylinder according to the actual demands of developing the satellite, the size of the cylinder is optimized, the thickness of the envelope and the stacking sequences are defined, the integrated joint frames are designed, and the adhesive technique is adopted in jointing parts of the cylinder. After the structural optimization design, the mass of the cylinder is reduced by about 52.4%. Meanwhile, the corresponding mechanical analysis is performed for the full satellite. The static test of the cylinder and the vibration test of the full satellite are carried out. It is shown that the cylinder can satisfy the technical requirements.