US 12,304,624 B2
Hybrid aircraft and landing launch/recovery system
Gordon L. Harris, Vista, CA (US); and Stephen L. Harris, Vista, CA (US)
Assigned to Leigh Aerosystems Corporation, Vista, CA (US)
Filed by Leigh Aerosystems Corporation, Vista, CA (US)
Filed on Jul. 10, 2023, as Appl. No. 18/349,822.
Application 18/349,822 is a continuation in part of application No. 18/321,992, filed on May 23, 2023, abandoned.
Application 18/349,822 is a continuation in part of application No. 16/995,534, filed on Aug. 17, 2020, granted, now 11,697,508.
Claims priority of provisional application 63/508,657, filed on Jun. 16, 2023.
Claims priority of provisional application 63/479,500, filed on Jan. 11, 2023.
Claims priority of provisional application 62/887,210, filed on Aug. 15, 2019.
Prior Publication US 2023/0406489 A1, Dec. 21, 2023
Int. Cl. B64U 10/20 (2023.01); B64C 3/56 (2006.01); B64C 27/26 (2006.01); B64D 27/02 (2006.01); B64D 27/10 (2006.01); B64D 27/24 (2006.01); B64U 70/93 (2023.01)
CPC B64C 27/26 (2013.01) [B64C 3/56 (2013.01); B64D 27/10 (2013.01); B64D 27/24 (2013.01); B64D 27/026 (2024.01); B64U 10/20 (2023.01); B64U 70/93 (2023.01)] 8 Claims
OG exemplary drawing
 
1. An aircraft, comprising:
a fuselage extending along a first x-axis;
a wing assembly including a first wing and a second wing;
a first power assembly that includes a first propulsion element and a first electric motor coupled to the first propulsion element;
a second power assembly that includes a second propulsion element and a second electric motor coupled to the second propulsion element;
a third power assembly positioned along the first axis aft of the first power assembly and the second power assembly, wherein the third power assembly includes a third propulsion element and an internal combustion engine coupled to the third propulsion element, wherein the entire internal combustion engine rotates about at least one axis;
wherein the entire first power assembly and the entire second power assembly can rotate about respective x-axes to provide yaw control and side force control of the aircraft; and
wherein the entire third power assembly rotates to provide pitch and yaw control and forward propulsion for the aircraft.