Abstract: An essentially cylindrical, light weight, composite fastener formed of an interior cylindrical core member, a cone-shaped molded insert plug member in the first or head end of the core, and an exterior cup-shaped overwrap member. Threads are formed at the second or threaded end of the fastener. All of the components are fabricated of an organic resin material with high-modulus fibers embedded therein. The fibers of the exterior member are long and continuous while the fibers of the other members are short and chopped. All the fibers are essentially parallel with the axis of the fastener. The resin material is preferably polyetheretherketone and the fibers are preferably graphite. Also disclosed is the method of manufacturing the above described fastener.

Abstract: A lightweight composite structure including a continuous filament member laced through the structure to provide a plurality of tension members integral with the structure. The preferred method of manufacture is to layup and cure two or more composite structural members, such as "I" beams, with each cured "I" beam having a plurality of holes extended through its upstanding leg, its top and bottom T-cap portions. Next, an uncured composite skin panel is laced to the top T-cap portion of the "I" beams, utilizing the holes provided through the upstanding legs of the "I" beams. The laced composite structure is then cured using pressures and temperatures well known to those skilled in the art.

Abstract: A method and means for strengthening joints in bonded structural assemblies formed of two or more components fabricated of non-metallic composite materials, by using high strength strands or threads inserted through the joints by loop-stitching.

Abstract: A composite structure capable of withstanding multidirectional stress loads in general and in particular high tension and compression loads transmitted to an aircraft center fuselage by wing loading. The structure is essentially a beam formed by inserting two stepped metal end caps into the ends of a graphite/epoxy B-staged tubular strut and subsequently laying-up multidirectional and unidirectional fibers to provide a structure which is in turn cocured and results in a unitized composite wing trunnion structure.