US 11,724,421 B2
Demolding of large composite parts for aircraft
Darrell D. Jones, Mill Creek, WA (US); Daniel R. Smith, Woodinville, WA (US); Patrick B. Stone, Monroe, WA (US); David Raines, Huntsville, AL (US); Byron James Autry, Charleston, SC (US); and Matthew B. Moore, Edmonds, WA (US)
Assigned to The Boeing Company, Chicago, IL (US)
Filed by The Boeing Company, Chicago, IL (US)
Filed on Nov. 10, 2021, as Appl. No. 17/454,273.
Claims priority of provisional application 63/115,043, filed on Nov. 18, 2020.
Prior Publication US 2022/0152880 A1, May 19, 2022
Int. Cl. B29C 33/44 (2006.01); B29C 33/50 (2006.01); B64F 5/50 (2017.01); B64F 5/10 (2017.01); B29C 70/54 (2006.01); B29C 70/34 (2006.01); B64C 1/12 (2006.01); B64C 1/00 (2006.01)
CPC B29C 33/50 (2013.01) [B29C 70/342 (2013.01); B29C 70/54 (2013.01); B64F 5/10 (2017.01); B64F 5/50 (2017.01); B64C 1/12 (2013.01); B64C 2001/0072 (2013.01)] 26 Claims
OG exemplary drawing
 
1. A method for demolding a composite part from a mandrel, the method comprising:
mechanically coupling a first arm of an extraction tool to a first arcuate portion of a composite part that has been hardened onto a mandrel;
mechanically coupling a second arm of an extraction tool to a second arcuate portion of the composite part; and
separating the composite part from the mandrel by iteratively performing the following operations until the composite part no longer contacts the mandrel;
elastically straining the first arcuate portion of the composite part via the first arm;
elastically straining the second arcuate portion of the composite part via the second arm; and
iteratively alternately increasing an elastic strain applied to the first arcuate portion and an elastic strain applied to the second arcuate portion.