Composite skin panel opening edge and method for manufacture

Details Composite skin panel opening edge and method for manufacture Composite skin panel opening edge and method for manufacture

B - Operations, Transporting

64

C

B64C 1/00 (2006.01)

Patent

CA 2423665

The present invention disclosed herein provides a component frame (18) for supporting a component (28) in a vehicle. The component (28) may be a door, a window or another piece of equipment on an aircraft that requires a flush- fitting interface with the aircraft. The component frame (18) comprises an outer skin (20) having a recessed edge (16) disposed generally around the perimeter of the component frame (18). An inner skin (24) is disposed within the aircraft and serves to sandwich a honeycomb core (22) between itself and the outer skin (20).

L'invention concerne un châssis de composant (18) destiné à supporter un composant (28) dans un véhicule. Ledit composant (28) peut être une porte, une fenêtre, ou une pièce d'aéronef nécessitant une interface encastrée dans l'aéronef. Le châssis de composant (18) comprend revêtement extérieur (20) doté d'un bord évidé (16) disposé généralement autour du périmètre du châssis de composant (18). Un revêtement intérieur (24) est placé dans l'aéronef et une âme en nids d'abeilles (22) est prise en sandwich entre ledit revêtement intérieur et le revêtement extérieur (20).

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