A system of composite and adhesive materials provides for a high strength, producible closeout joint in the form of tapered tension bond joint for high performance structures. The system includes one skin that is co-bonded to flat panel spars, with the joint being positioned at the opposite side of the spars. The spar includes a female receptacle that receives a male blade from the closeout skin assembly. The blade and receptacle are wedge-shaped woven preforms. The flat panel spars have imbedded nut elements that serve as "internal tooling" to provide a positive stop for locating and clamping the structural members together.

 
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> Method for determination of fuselage shape of supersonic aircraft, and fuselage front section shape

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