US 12,441,456 B2
Wing module for air vehicle with non-zero angular displacement pivot axes for first wing and second wing elements
Shai Alexandroni, Lod (IL); Gaby Vaisman, Lod (IL); and Ofek Ohana, Lod (IL)
Assigned to ISRAEL AEROSPACE INDUSTRIES LTD., Lod (IL)
Appl. No. 18/000,976
Filed by ISRAEL AEROSPACE INDUSTRIES LTD., Lod (IL)
PCT Filed Jun. 21, 2021, PCT No. PCT/IL2021/050753
§ 371(c)(1), (2) Date Dec. 7, 2022,
PCT Pub. No. WO2021/260688, PCT Pub. Date Dec. 30, 2021.
Claims priority of application No. 275576 (IL), filed on Jun. 22, 2020.
Prior Publication US 2023/0174218 A1, Jun. 8, 2023
Int. Cl. B64C 5/12 (2006.01); B64C 5/02 (2006.01); B64U 10/25 (2023.01); B64U 30/40 (2023.01)
CPC B64C 5/12 (2013.01) [B64C 5/02 (2013.01); B64U 10/25 (2023.01); B64U 30/40 (2023.01)] 29 Claims
OG exemplary drawing
 
1. A wing system for an air vehicle, the air vehicle having a fuselage including a fuselage section and a fuselage longitudinal axis, the wing system comprising at least one wing deployment module, each wing deployment module comprising:
a set of wing elements, including at least a first said wing element having a first wing element longitudinal axis, and a second said wing element having a second wing element longitudinal axis;
each said wing deployment module configured for selectively transitioning between a respective stowed configuration and a respective deployed configuration;
wherein in the stowed configuration, the first wing element and the second wing element are in overlying relationship such that the first wing element longitudinal axis and the second wing element longitudinal axis are nominally parallel with one another; and
wherein in the deployed configuration, the first wing element is oriented with respect to the second wing element such that the first wing element longitudinal axis is non-parallel with respect to the second wing element longitudinal axis
and wherein for each said wing deployment module:
each said first wing element is configured for being transitioned between the stowed configuration and the deployed configuration by:
pivoting said first wing element about a first module pivot axis by a non-zero first module angular displacement, and
pivoting said first wing element about a first wing element pivot axis by a non-zero first wing element angular displacement;
and
each said second wing element is configured for being transitioned between the stowed configuration and the deployed configuration by:
pivoting said second wing element about a second module pivot axis by a non-zero second module angular displacement.