Raised decorative laminate panel and method

1. An aircraft cabin panel comprising:

a panel substrate, said panel substrate comprising a panel substrate first side and a panel substrate second side;

a panel insert, said panel insert comprising a panel insert first side and a panel insert second side, said panel insert second side positioned adjacent the panel substrate first side, said panel insert further comprising a panel insert dimensional characteristic, said panel insert comprising a panel insert thickness ranging from about 2 mils to about 4 mils;

a deformable outer panel layer, said deformable outer panel layer comprising a deformable outer panel layer first side and a deformable outer panel layer second side, said deformable outer panel layer further comprising a deformable outer panel layer average thickness, said deformable outer panel layer first side further comprising a raised relief area, said raised relief area substantially matching the panel insert dimensional characteristic said deformable outer panel layer comprising a deformable outer panel layer thickness ranging from about 2 mils to about 4 mils;

an insert positioning layer consisting of at least one of an adhesive layer and a tackifier layer, said insert positioning layer configured to maintain the panel insert in a selected position between the panel substrate first side and the deformable outer panel layer second side during assembly of the aircraft cabin panel;

wherein the deformable outer panel layer dimensional characteristic is visually detectable and tactilely detectable at an aircraft cabin panel exterior surface;

wherein the panel insert thickness is substantially equivalent to the deformable outer panel layer thickness; and

wherein the dimensional characteristic in the panel insert and transfer of the dimensional characteristic from the panel insert to the deformable outer panel layer does not require individual machining.

2. The aircraft cabin panel of claim 1 , wherein the deformable outer panel layer first side is the aircraft cabin panel exterior surface.

3. The aircraft cabin panel of claim 2 , wherein the aircraft cabin panel exterior surface comprises an aircraft cabin panel exterior surface raised area, and wherein said raised relief area is out-of-plane with respect to the aircraft cabin panel exterior surface.

4. The aircraft cabin panel of claim 1 , wherein the raised relief area is visually detectable and tactilely detectable.

5. The aircraft cabin panel of claim 1 , wherein the panel substrate comprises a sandwich panel construction.

6. The aircraft cabin panel of claim 1 , wherein the deformable outer panel layer comprises a decorative laminate material.

7. The aircraft cabin panel of claim 1 , further comprising an adhesive layer, said adhesive layer positioned between the panel substrate first side and the deformable outer panel layer second side.

8. The aircraft cabin panel of claim 1 , wherein the panel insert further comprises an adhesive layer on at least one of the panel insert first side and the panel insert second side.

9. An aircraft cabin comprising the aircraft cabin panel of claim 1 .

10. An aircraft comprising the aircraft cabin panel of claim 1 .

11. A method for forming a raised relief area on an aircraft cabin panel assembly exterior surface, the method comprising:

disposing a panel insert between a panel substrate exterior side of a deformable outer panel layer and a deformable outer panel layer interior side of the deformable outer panel layer to form an aircraft cabin panel pre-assembly, said panel insert comprising a panel insert dimensional characteristic, said panel insert further comprising a panel insert first side and a panel insert second side, said panel insert comprising a panel insert thickness ranging from about 2 mils to about 4 mils, said deformable outer panel layer comprising a deformable outer panel layer thickness ranging from about 2 mils to about 4 mils, said panel insert thickness substantially equivalent to the deformable outer panel layer thickness;

forming the aircraft cabin panel pre-assembly, said aircraft cabin panel pre-assembly comprising an aircraft cabin panel pre-assembly exterior surface;

applying a force of about 14 psi to the aircraft cabin panel pre-assembly;

deforming the deformable outer panel layer; and

forming an aircraft cabin panel assembly comprising the aircraft cabin panel assembly exterior surface, said aircraft panel assembly exterior surface comprising an area of exterior surface raised relief, said area of exterior surface raised relief substantially matching the panel insert dimensional characteristic; and

wherein the dimensional characteristic in the panel insert and transfer of the dimensional characteristic from the panel insert to the deformable outer panel layer does not require individual machining.

12. The method of claim 11 , further comprising:

applying an adhesive layer on at least one of the panel insert first side and the panel insert second side prior to disposing the panel insert between the panel substrate exterior side and the deformable outer panel layer interior side to form the aircraft cabin panel pre-assembly.

13. The method of claim 11 , further comprising:

applying an adhesive layer to at least one of the panel substrate exterior side and the deformable outer panel layer interior side prior to disposing the panel insert between the panel substrate exterior side and the deformable outer panel layer interior side to form the aircraft cabin panel pre-assembly.

14. The method of claim 11 , wherein the aircraft panel assembly exterior surface comprising the area of exterior surface raised relief is visually detectable and is further tactilely detectable.