Abstract: A composite brace, strut, or link for any application requiring the transfer of a concentrated load uses a stepped insert at the lug end to distribute the applied loads into a composite structure formed of a stacked arrangement of internal and external plies of composite material. The manufacture of the brace, strut, or link is performed in a cost effective manner. The composite lay-up is done so that many individual parts can be cut from the initial multi-part assembly, allowing the economy of scale to lower fabrication costs of the individual manufactured parts. The structure provides a system whereby the concentrated load applied at the stepped inserts can be distributed into the composite material without any gapping or separation as would occur in a traditionally configured end fitting joint between a circular metallic bushing and the adjacent composite material interface.

Abstract: Thin perforated sheets of titanium are interleaved between adjacently situated graphite/epoxy plies--in the area where metal fittings are to be installed. Epoxy flows through these perforations so as to achieve a gripping mechanism between the titanium sheet and the graphite/epoxy plies. The result is efficient transfer of load in the titanium to the composite fiber materials without suffering the cost penalty of extensive graphite/epoxy buildups (without interleaved titanium sheets). Epoxy plugs within the titanium sheet perforations bond to confronting surfaces of the graphite/epoxy plies and provide a fail safe gripping mechanism between the titanium sheet and adjacent graphite/epoxy plies to allow for the load transfer between the titanium sheet and the graphite/epoxy plies in the unlikely event that the shear bond between the faces of the titanium sheet and the graphite/epoxy plies becomes completely disbonded.

Abstract: An isolator assembly for use in minimizing mechanical thermal and/or vibrationary strains between two structures is disclosed. The isolator assebly generally includes two spaced base members which are interconnected by a plurality of equally spaced rods. The length, diameter and material of the rods are determined based on the particular environment within which the isolator assembly is utilized. The invention has particular application in supporting a hot air blower tube within a cowling of a jet engine unit.

Abstract: A graphite epoxy spoiler for an aircraft wing is manufactured by estimating the shear force to which the spoiler will be subject, and forming a fitting attachment surface and fitting designed to eliminate a separate shear attachment between the spoiler structure and the center attachment/drive fitting. This permits use of a one piece co-cured honeycomb sandwich construction for the spoiler.