Taking a spacecraft composite material integrated rocker arm as an example， the molding process plan is studied for its fully enclosed， nonlinear， variable cross-section， variable wall thickness and slender hollow thin-walled structure. By using the soluble mandrel as the layering mandrel， the problems of layering and demoulding are solved. The airbag pressurizing method is selected to solve the problems of pressurizing and forming. The results show that after 4 high and low temperature cycle tests between -65 ℃ and 60 ℃， there are no defects such as delamination or cracks in the rocker structure. The prepared composite rocker successfully passes the appraisal level mechanical test， and the mechanical properties meet the design requirements. The combination of airbag pressurization and soluble mandrel technology has achieved the goal of low-cost and short-period preparation of the main bearing components of spacecraft composite materials， which has certain reference significance for the development of similar fully enclosed special-shaped composite material structures.