Abstract:

Technology for the design and manufacture of main loadcarrying composite joints will widen the application of composite materials in airplane structure, and make it possible to further lighten the structural weight of the airplane, improve its fatigue property as well as reduce manufacture cost. This paper focuses on the design, analysis and experiment of an inplane rounding type laminated composite joint. The engineering design plan and the theoretical analysis are presented and the strength prediction expression at dangerous spots of the joint is derived.

Key words: composites,  , main , load-carrying , joint,  , in-plane , rounding , type , laminated , scheme,  , theoretical , strength , prediction,  , static , experiment