Cylinder is the main bearing component of a satellite

which plays a major role in the load-bearing performance of the whole structure. Due to lightweight and high strength

Kagome grid satellite cylinder made by filament winding is commonly used in satellite cylinder. However

the structural parameters are coupled with each other in the design of the grid structure

and the effect of the parameters on the load-bearing performance of the cylinder is unclear. In this paper

the structure optimization of the Kagome grid satellite cylinder is studied. The finite element method is used to analyze the load-bearing performance of the cylinder under the working conditions for the satellite. Furthermore

the relative independence design conception regarding spiral rib and ring rib is put forward. Combining the parametric modeling strategy

the effect of each structural parameter on the load-bearing performance is obtained. With the loadbearing performance and mass as the main optimization objectives

the structural parameters of the cylinder are optimized using the multi-objective genetic algorithm. Also

the strength and buckling performance of the optimal structure are analyzed. The results show that the mass of the optimal structural is reduced by 21.2%

and the mechanical properties meet the specific working conditions of the satellite. Finally

the self-developed desktop winding machine is used to wind the cylinder.