US 12,005,686 B2
Core material for composite structures
Thomas A. Carstensen, Shelton, CT (US); and Jonathan K. Garhart, Seymour, CT (US)
Assigned to SIKORSKY AIRCRAFT CORPORATION, Stratford, CT (US)
Filed by Sikorsky Aircraft Corporation, Stratford, CT (US)
Filed on Nov. 2, 2020, as Appl. No. 17/086,687.
Application 17/086,687 is a division of application No. 15/580,197, granted, now 10,843,434, previously published as PCT/US2016/038654, filed on Jun. 22, 2016.
Claims priority of provisional application 62/182,954, filed on Jun. 22, 2015.
Prior Publication US 2021/0046725 A1, Feb. 18, 2021
Int. Cl. B32B 3/12 (2006.01); B29D 24/00 (2006.01); B33Y 80/00 (2015.01); F16B 5/01 (2006.01)
CPC B32B 3/12 (2013.01) [B29D 24/005 (2013.01); B32B 2250/03 (2013.01); B32B 2250/04 (2013.01); B32B 2262/101 (2013.01); B32B 2262/103 (2013.01); B32B 2262/106 (2013.01); B32B 2305/024 (2013.01); B33Y 80/00 (2014.12); F16B 5/01 (2013.01)] 19 Claims
OG exemplary drawing
 
1. A composite sandwich structure, comprising:
a skin;
a core panel adhered to the skin, the core panel including a plurality of cell walls defining a plurality of core cells, the plurality of cell walls extending across a thickness of the core panel, the plurality of core cells including one or more defined structural nonuniformities resulting in nonuniform properties of the core panel; and
one or more end flanges disposed at a cell wall of the plurality of cell walls, the one or more end flanges oriented towards an opening of at least one of the plurality of core cells disposed adjacent to the cell wall,
wherein a first portion of the core panel comprises a first material having a first conductivity;
wherein a second portion of the core panel comprises a second material different from the first material, the second material having a second conductivity; and
wherein the second portion of the core panel extends from the first portion of the core panel.