The mechanically fastened joint of composite structure that resists with special force can induce a high load out of plane. A typical c omposite structure is selected from a certain type of helicopter fuselage. An ap propriate joint style is established by finite element analysis, the local lay up of carbon fiber reinforced plastic(CFRP) fuselage is optimized, and then mech anical tests are carried out for the compositemetal joint structure. The resul ts show that analysis data agrees well with test results, and the mechanically f astened joint of composite structure has enough strength and satisfies design re quests at given loads.