US 12,312,083 B2
Systems and methods for aerodynamic deployment of wing structures
Christopher Noskowicz, San Clemente, CA (US)
Assigned to SWIFT ENGINEERING, INC., San Clemente, CA (US)
Filed by SWIFT ENGINEERING, INC., San Clemente, CA (US)
Filed on Oct. 10, 2023, as Appl. No. 18/484,394.
Application 17/111,259 is a division of application No. 16/128,432, filed on Sep. 11, 2018, abandoned.
Application 18/484,394 is a continuation of application No. 17/111,259, filed on Dec. 3, 2020, granted, now 11,814,165.
Prior Publication US 2024/0116624 A1, Apr. 11, 2024
Int. Cl. B64C 9/00 (2006.01); B64U 10/25 (2023.01); B64U 20/50 (2023.01); B64U 30/10 (2023.01); B64U 70/50 (2023.01); B64U 80/70 (2023.01); B64U 50/13 (2023.01); B64U 101/31 (2023.01)
CPC B64C 9/00 (2013.01) [B64U 10/25 (2023.01); B64U 20/50 (2023.01); B64U 70/50 (2023.01); B64C 2009/005 (2013.01); B64U 30/10 (2023.01); B64U 50/13 (2023.01); B64U 80/70 (2023.01); B64U 2101/31 (2023.01)] 20 Claims
OG exemplary drawing
 
1. An aircraft comprising:
a fuselage;
a wing carried by the fuselage, wherein the wing comprises an inboard portion and an outboard portion, and wherein the outboard portion comprises a movable aerodynamic control surface; and
a deployment system for deploying the wing from a folded configuration to an unfolded configuration, wherein in the folded configuration, the outboard portion overlaps the inboard portion, and in the unfolded configuration, the outboard portion and the inboard portion together extend away from the fuselage and form a lifting surface for providing aerodynamic lift to the aircraft;
wherein the movable aerodynamic control surface is configured to deflect toward the inboard portion to provide an aerodynamic force to cause the outboard portion to rotate relative to the inboard portion toward the unfolded configuration; and
wherein the deployment system comprises:
a first hinge arm connected to the inboard portion;
a second hinge arm connected to the outboard portion, wherein the second hinge arm is rotatably connected to the first hinge arm at a hinge axis; and
a latching mechanism, wherein the latching mechanism is positioned to releasably lock the wing in the unfolded configuration.