US 11,926,077 B2
Composite sandwich panels with over-crushed edge regions
Jason Turner, Marysville, IL (US); Mitchell Zachary Kotlik, Everett, WA (US); Christopher Robert Schwartz, Snohomish, WA (US); and Michael B. Black, Seattle, WA (US)
Assigned to The Boeing Company, Chicago, IL (US)
Filed by The Boeing Company, Chicago, IL (US)
Filed on Aug. 3, 2022, as Appl. No. 17/817,064.
Application 17/817,064 is a division of application No. 15/887,839, filed on Feb. 2, 2018, granted, now 11,440,283.
Prior Publication US 2022/0371234 A1, Nov. 24, 2022
Int. Cl. B32B 3/12 (2006.01); B29C 43/02 (2006.01); B29C 43/20 (2006.01); B29C 43/36 (2006.01); B29C 43/40 (2006.01); B29C 70/02 (2006.01); B29C 70/46 (2006.01); B29C 70/54 (2006.01); B29C 70/76 (2006.01); B29D 99/00 (2010.01); B32B 3/02 (2006.01); B32B 3/30 (2006.01); B29C 70/68 (2006.01); B29C 70/72 (2006.01); B29L 31/00 (2006.01); B29L 31/30 (2006.01); B29L 31/60 (2006.01)
CPC B29C 43/02 (2013.01) [B29C 43/203 (2013.01); B29C 43/36 (2013.01); B29C 43/40 (2013.01); B29C 70/026 (2013.01); B29C 70/46 (2013.01); B29C 70/545 (2013.01); B29C 70/763 (2013.01); B29D 99/0089 (2013.01); B32B 3/02 (2013.01); B32B 3/12 (2013.01); B32B 3/30 (2013.01); B29C 2043/403 (2013.01); B29C 70/685 (2013.01); B29C 70/72 (2013.01); B29C 2793/0027 (2013.01); B29C 2793/009 (2013.01); B29L 2031/3076 (2013.01); B29L 2031/608 (2013.01); B29L 2031/72 (2013.01); B32B 2250/40 (2013.01); B32B 2605/18 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A composite sandwich panel comprising:
a first composite skin;
a second composite skin;
a hollow cell core between the first composite skin and the second composite skin, wherein the first composite skin and the second composite skin and the hollow cell core are consolidated resulting in a 5% to 10% reduction in thickness of the entire composite panel to a nominal thickness;
a first edge comprising a first over-crush edge region, the first over-crush edge region having a first thickness at least 40% less than the nominal thickness of the composite sandwich panel, wherein the first over-crush edge region has a length of at least 0.25 inches over which a thickness of the composite sandwich panel decreases; and
an open edge, wherein the open edge is the nominal thickness of the composite sandwich panel.