US 12,404,000 B2
Raised decorative laminate panel and method
Lon Eric Switzer, Seattle, WA (US); Gregory William Nelson, Everett, WA (US); Frank H. Fash, Lynnwood, WA (US); Carolina Aranda, Snohomish, WA (US); and Eric Eagon, Seattle, WA (US)
Assigned to THE BOEING COMPANY, Arlington, VA (US)
Filed by The Boeing Company, Arlington, VA (US)
Filed on Sep. 22, 2023, as Appl. No. 18/472,598.
Prior Publication US 2025/0100668 A1, Mar. 27, 2025
Int. Cl. B64C 1/06 (2006.01)
CPC B64C 1/066 (2013.01) 14 Claims
OG exemplary drawing
 
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.