| US 11,806,954 B2 | ||
| Wrinkle mitigation in contoured composite stiffeners | ||
| Gagandeep Saini, Snohomish, WA (US); Ian Edward Schroeder, Seattle, WA (US); Kurtis Shuldberg Willden, Kent, WA (US); and Lisa Christina Carlson, Auburn, WA (US) | ||
| Assigned to The Boeing Company, Chicago, IL (US) | ||
| Filed by The Boeing Company, Chicago, IL (US) | ||
| Filed on Dec. 14, 2021, as Appl. No. 17/644,285. | ||
| Prior Publication US 2023/0182417 A1, Jun. 15, 2023 | ||
| Int. Cl. B29C 70/54 (2006.01); B29D 99/00 (2010.01); B29C 70/46 (2006.01); B29L 9/00 (2006.01); B29L 31/00 (2006.01) | ||
| CPC B29C 70/549 (2021.05) [B29C 70/462 (2013.01); B29D 99/0003 (2013.01); B29L 2009/00 (2013.01); B29L 2031/001 (2013.01)] | 20 Claims |
|
1. Apparatus for forming a contoured composite laminate stiffener, comprising:
a first die and a second die between which a multi-ply composite charge may be formed into a stiffener, the first die and the second die being configured to form a contour in the stiffener; and at least a first diffuser positioned between the first die and the second die, and configured to diffuse wrinkles in the stiffener along the contour; wherein the first diffuser includes depressions therein into which the plies of the multi-ply charge may strain in response to compressive stress in the stiffener caused by forming the stiffener to the contour, and wherein the depressions form a plurality of peaks and troughs forming a serpentine pattern or a sine wave pattern. |