US 11,718,047 B2
Flyaway stringer end caps
Mary LeAnn Parker, Snohomish, WA (US); Khanh Mai Pham, Renton, WA (US); Lisa Christina Carlson, Auburn, WA (US); and Garrett Charles Hanson, Everett, WA (US)
Assigned to The Boeing Company, Chicago, IL (US)
Filed by The Boeing Company, Chicago, IL (US)
Filed on Dec. 12, 2019, as Appl. No. 16/712,154.
Prior Publication US 2021/0178706 A1, Jun. 17, 2021
Int. Cl. B29C 65/00 (2006.01); B29C 70/00 (2006.01); B29C 70/38 (2006.01); B29C 65/78 (2006.01); B29L 31/30 (2006.01); B32B 5/24 (2006.01)
CPC B29C 70/38 (2013.01) [B29C 65/7814 (2013.01); B29C 65/7847 (2013.01); B29L 2031/3085 (2013.01); B32B 5/24 (2013.01); B32B 2250/02 (2013.01); B32B 2262/106 (2013.01); B32B 2605/18 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A method for fabricating a composite part, the method comprising:
forming a skin panel preform comprising fiber reinforced material;
disposing rigid end caps at the skin panel preform at end locations of stringer preforms that will be placed at the skin panel preform;
locating the stringer preforms at the skin panel preform via the rigid end caps disposed at the skin panel preform; and
anchoring the stringer preforms to the skin panel preform between the rigid end caps.