초록 ▼

A layered material includes a ply material and a backing film to support the ply material. The backing film includes a polyester film. The layered material is generated by disposing the backing film upon the ply material. A composite layup is generated by tacking the layered material to a tool, disp

A layered material includes a ply material and a backing film to support the ply material. The backing film includes a polyester film. The layered material is generated by disposing the backing film upon the ply material. A composite layup is generated by tacking the layered material to a tool, disposing the layered material upon the tool along a path, and removing the backing film.

대표청구항 ▼

1. A method of fabricating an aircraft component, the method comprising the sequential steps of: supplying a backed ply material comprising an epoxy resin coated metal foil and a substantially transparent polyester backing film;supporting the metal foil on the backing film during the handling of the

1. A method of fabricating an aircraft component, the method comprising the sequential steps of: supplying a backed ply material comprising an epoxy resin coated metal foil and a substantially transparent polyester backing film;supporting the metal foil on the backing film during the handling of the metal foil;tacking the metal foil having the backing film to a tool that corresponds to the aircraft component;disposing the metal foil upon the tool along a path;inspecting seams between abutting plies of the metal foil after disposing the metal foil upon the tool and prior to removing the backing ply, the metal foil being visible through the polyester backing film; andremoving the backing film. 2. The method according to claim 1, further comprising: cutting the metal foil in response to disposing the metal foil at an end of the path. 3. The method according to claim 1, further comprising: recycling the backing film in response to the removing step. 4. The method according to claim 1, wherein the aircraft component comprises a fuselage section. 5. The method according to claim 1, wherein the aircraft component comprises a wing section. 6. The method according to claim 1, wherein the backing film comprises polyethylene terephthalate. 7. The method according to claim 1, wherein the metal foil is titanium foil. 8. The method according to claim 1, further comprising: directing heated air onto the metal foil when disposing the metal foil upon the tool. 9. The method according to claim 1, wherein the backing film includes a release agent to facilitate removal of the backing film after the metal foil is disposed upon the tool. 10. A method of generating a composite layup, the method comprising the sequential steps of: supplying a backed ply material comprising an epoxy resin coated titanium foil and a substantially transparent polyester backing film;supporting the titanium foil on the backing film during the handling of the titanium foil;tacking the titanium foil having the backing film to a tool;disposing the titanium foil upon the tool along a path;inspecting seams between abutting plies of the titanium foil after disposing the titanium foil upon the tool and prior to removing the backing ply, the titanium foil being visible through the polyester backing film; andremoving the backing film after the titanium foil is disposed upon the tool. 11. The method according to claim 10, further comprising: cutting the titanium foil in response to disposing the titanium foil at an end of the path. 12. The method according to claim 10, further comprising: recycling the backing film in response to the removing step. 13. The method according to claim 10, wherein the composite layup corresponds to an aircraft component.