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.