Patent ID: 7966711
Filing Date: 2011-06-28
Classification: B29C,B29K,B29L,B64F,F16B,Y10T

Abstract:
1. A method for assembling a non-metallic composite structure for an aircraft, the method comprising: positioning a non-metallic composite male fastener component through a pair of aircraft parts, the non-metallic composite male fastener component having a shaft and a mechanical locking feature, wherein the mechanical locking feature is one of a threaded portion of the shaft and a plurality of concentric grooves, and wherein the composite male fastener comprises a carbon fiber and resin without any woven, braided, or circumferentially directed fibers disposed about chopped fibers; positioning a non-metallic composite female fastener component around the shaft and adjacent to the threaded portion of the shaft while the non-metallic composite male fastener component is positioned through the pair of aircraft parts, wherein the non-metallic composite female fastener component comprises carbon fiber and resin without any woven, braided, or circumferentially directed fibers disposed about chopped fibers, and has a cylindrical shape; applying heat and force to the non-metallic composite female fastener component to cause a portion of the non-metallic composite female fastener component to melt and flow into the threaded portion of the shaft; and removing the heat and force such that the portion of the non-metallic composite female fastener component that melted re-solidifies, wherein the non-metallic composite female fastener component is attached to the non-metallic composite male fastener component and the pair of mating aircraft parts are mechanically joined to each other.