US 11,945,573 B2
Hybrid electric aircraft with gyroscopic stabilization control
Mehdi Milani Baladi, Turin (IT); and Randy M Vondrell, Cincinnati, OH (US)
Assigned to General Electric Company, Schenectady, NY (US); and GE Avio S.r.l., Rivalta di Torino (IT)
Filed by General Electric Company, Schenectady, NY (US); and GE Avio S.r.l., Rivalta di Torino (IT)
Filed on Nov. 18, 2021, as Appl. No. 17/529,556.
Claims priority of application No. 102021000018170 (IT), filed on Jul. 9, 2021.
Prior Publication US 2023/0051515 A1, Feb. 16, 2023
Int. Cl. B64C 17/06 (2006.01); B64C 29/00 (2006.01); B64D 27/02 (2006.01); B64D 27/14 (2006.01); B64D 27/24 (2006.01); B64D 31/02 (2006.01)
CPC B64C 17/06 (2013.01) [B64C 29/0033 (2013.01); B64D 27/14 (2013.01); B64D 27/24 (2013.01); B64D 31/02 (2013.01); B64D 2027/026 (2013.01)] 9 Claims
OG exemplary drawing
 
1. An aircraft defining a prime stability axis, the aircraft comprising:
a turbo-generator having a gas turbine engine and an electric generator operatively coupled with the gas turbine engine, the turbo-generator defining a rotation axis about which a spool of the gas turbine engine is rotatable;
one or more propulsors, each of the one or more propulsors being electrically-driven;
a pivot mount operatively coupled with the turbo-generator, the pivot mount being operable to adjust the rotation axis of the turbo-generator relative to the prime stability axis of the aircraft; and
a controller configured to perform the following:
receive data indicating an orientation of the rotation axis of the turbo-generator and an orientation of the prime stability axis of the aircraft; and
cause the pivot mount to adjust the rotation axis of the turbo-generator relative to the prime stability axis of the aircraft based at least in part on the orientation of the rotation axis of the turbo-generator relative to the orientation of the prime stability axis of the aircraft.