Aiming at the process characteristics of integral forming and cementing connection of light composite material aircraft, the overall design of the process scheme was carried out. It included the determination of assembly order, the choice of assembly tooling benchmarks. Then, the integration of the tooling structure is designed, refinement of the mold forming and positioning and clamping of the structural parts are also studied. Finallly, small parts like tail, drag plate are manufactured again. The practical use of integrated tooling is verified, meanwhile the feasibility and advancement of integrated tooling design on light composite material aircraft fuselage is verified by analogy analysis. The study can provide reference for design of composite material aircraft.