PANEL FOR AIRCRAFT APPLICATIONS AND THE METHOD FOR MANUFACTURING THE PANEL

摘要

An aircraft trim panel structure includes a thermoplastic resinated quadraxial fiberglass lay-up prepreg first open structure skin layer having at least a 28 % open area. A thermoplastic resinated quadraxial fiberglass lay-up prepreg second open structure skin layer has at least a 28 % open area. An open structure core layer having at least a 28 % open area is sandwiched between the first open structure skin layer and the second open structure skin layer. The first open structure skin layer, the second open structure skin layer and the open structure core layer are formed into a three dimensional shape corresponding to the aircraft trim panel.