Method and apparatus for fastening components using a composite two-piece fastening system

A composite aircraft structure comprising:

• a first composite aircraft part;
• a second composite aircraft part;
• a composite male fastener component placed through the first composite aircraft part and the second composite aircraft part, wherein the composite male fastener component comprises carbon fiber and resin without any woven, braided, or circumferentially directed fibers disposed about chopped fibers and has a mechanical locking feature;
• and
• a composite female fastener component attached to the composite male fastener component wherein the composite female faster component comprises carbon fiber and resin without any woven, braided, or circumferential directed fibers disposed about chopped fibers and a portion of the composite female fastener component engages the mechanical locking feature of the composite male fastener component when an application of heat and force causes the portion to flow around the mechanical locking feature and to re-solidify around the mechanical locking feature of the composite male fastener component to join the composite female fastener component to the composite male fastener component.