US 11,679,860 B2
Acoustic abatement panel fabrication
Timothy Dustin Penn, Tulsa, OK (US); Matthew Shaun Fritz, Bixby, OK (US); and Jane Alice Benbenek, Owasso, OK (US)
Assigned to The NORDAM Group LLC, Tulsa, OK (US)
Filed by The NORDAM Group LLC, Tulsa, OK (US)
Filed on Oct. 6, 2021, as Appl. No. 17/494,994.
Application 17/494,994 is a division of application No. 16/108,494, filed on Aug. 22, 2018, granted, now 11,180,237.
Claims priority of provisional application 62/555,320, filed on Sep. 7, 2017.
Prior Publication US 2022/0024555 A1, Jan. 27, 2022
Int. Cl. B64C 1/40 (2006.01); B32B 7/12 (2006.01); B32B 5/18 (2006.01); B32B 5/12 (2006.01); B32B 15/04 (2006.01); B32B 15/14 (2006.01); B32B 15/20 (2006.01); G10K 11/168 (2006.01); B32B 3/12 (2006.01); B32B 37/12 (2006.01); B29C 65/00 (2006.01); B32B 37/14 (2006.01); B32B 38/00 (2006.01); B64C 1/00 (2006.01); B29C 44/18 (2006.01)
CPC B64C 1/40 (2013.01) [B29C 66/727 (2013.01); B29C 66/72525 (2013.01); B32B 3/12 (2013.01); B32B 5/12 (2013.01); B32B 5/18 (2013.01); B32B 7/12 (2013.01); B32B 15/046 (2013.01); B32B 15/14 (2013.01); B32B 15/20 (2013.01); B32B 37/12 (2013.01); B32B 37/146 (2013.01); B32B 38/0004 (2013.01); G10K 11/168 (2013.01); B29C 44/186 (2013.01); B29C 66/72523 (2013.01); B32B 2260/023 (2013.01); B32B 2260/046 (2013.01); B32B 2262/106 (2013.01); B32B 2266/0214 (2013.01); B32B 2305/022 (2013.01); B32B 2305/024 (2013.01); B32B 2307/102 (2013.01); B32B 2307/50 (2013.01); B32B 2605/18 (2013.01); B64C 2001/0072 (2013.01)] 20 Claims
OG exemplary drawing
 
1. An aircraft acoustic structural panel (10) made by the method comprising:
compressing together under pressure and heat a stack including a preformed uniform foam layer (3), a layer of adhesive (2), and a core honeycomb (1) having a plurality of honeycomb cells (14) and thereby pressing said preformed uniform foam layer (3) substantially flush atop said core honeycomb (1) to form corresponding foam plugs from said preformed uniform foam layer (3) being thermally bonded inside said honeycomb cells (14) by said adhesive (2), with said preformed uniform foam layer (3) being initially thicker than said core honeycomb (1) and fully compressed into said honeycomb cells (14) to preform a core honeycomb laminate (12);
stacking said preformed core honeycomb laminate (12) between opposite top and bottom structural outer laminates (16, 18) having corresponding outer skins (20, 22); and
compressing together under heat and pressure said stacked preformed core honeycomb laminate (12) and said structural outer laminates (16, 18) into a unitary structural panel (10) defining said aircraft acoustic structural panel having said preformed core honeycomb laminate (12) integrally bonded between said outer skins (20, 22).