US 11,878,792 B2
Stiffened composite panel with integrated shim
Gregory A. Cass, Seattle, WA (US); Ian E. Schroeder, Seattle, WA (US); and Khanh M. Pham, Tukwila, WA (US)
Assigned to The Boeing Company, Chicago, IL (US)
Filed by The Boeing Company, Chicago, IL (US)
Filed on Nov. 9, 2021, as Appl. No. 17/522,759.
Claims priority of provisional application 63/119,885, filed on Dec. 1, 2020.
Prior Publication US 2022/0169364 A1, Jun. 2, 2022
Int. Cl. B64C 3/18 (2006.01); B32B 3/08 (2006.01); B32B 5/26 (2006.01); B32B 5/10 (2006.01); B29C 65/00 (2006.01); B32B 38/00 (2006.01); B32B 3/10 (2006.01); B32B 38/10 (2006.01)
CPC B64C 3/182 (2013.01) [B29C 66/0326 (2013.01); B32B 3/085 (2013.01); B32B 5/10 (2013.01); B32B 5/26 (2013.01); B32B 38/0004 (2013.01); B32B 38/10 (2013.01); B32B 2038/0076 (2013.01); B32B 2260/023 (2013.01); B32B 2605/18 (2013.01)] 9 Claims
OG exemplary drawing
 
1. A method comprising:
providing a skin member having an inner surface;
positioning a stringer onto the inner surface of the skin member, the stringer comprising a first flange portion and a second flange portion, the first flange portion and the second flange portion contacting the inner surface;
positioning an integrated shim on the first flange portion;
joining the integrated shim, the stringer, and the skin member; and
after the joining step, trimming the integrated shim to fit a gap, wherein the gap is between a surface of the stringer and a surface of another part that is to be joined with the stringer.