US 11,981,431 B2
Wing flap deflection control removal
Jan A. Kordel, Redmond, WA (US); Jacob Daniel Virnig, Woodinville, WA (US); Michael Albert Balzer, Bellevue, WA (US); Bruce Detert, Seattle, WA (US); and Emanuel Rizal Setiawan, Kent, 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. 16/712,901.
Application 16/712,901 is a division of application No. 15/386,211, filed on Dec. 21, 2016, granted, now 10,538,306.
Prior Publication US 2020/0115032 A1, Apr. 16, 2020
This patent is subject to a terminal disclaimer.
Int. Cl. B64C 9/18 (2006.01); B64C 9/02 (2006.01); B64F 5/00 (2017.01); B64C 3/44 (2006.01)
CPC B64C 9/18 (2013.01) [B64C 9/02 (2013.01); B64F 5/00 (2013.01); B64C 2003/445 (2013.01); Y02T 50/30 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A method comprising:
entering one or more flight conditions;
receiving aerodynamic forces at a wing, the wing comprising a fixed portion coupled to a seal and extending from the fixed portion of the wing, and wherein the seal is partially contacted prior to flight by a high-lift device surface having an as-built shape determined based on an anticipated deformation during flight; and
deforming the high-lift device surface based, at least in part, on the received aerodynamic forces,
wherein the deforming causes the high-lift device to deform from the as-built shape to a second shape to fully contact the seal to prevent air flow between the seal and the high-lift device surface due to the received aerodynamic forces.