US 12,391,367 B2
Drive assembly for driving a movable flow body of an aircraft
Jan Haserodt, Hamburg (DE); and Sarah Dehnbostel, Hamburg (DE)
Assigned to Airbus Operations GmbH, Hamburg (DE)
Filed by Airbus Operations GmbH, Hamburg (DE)
Filed on Jan. 12, 2024, as Appl. No. 18/411,179.
Claims priority of application No. 23151786 (EP), filed on Jan. 16, 2023.
Prior Publication US 2024/0239476 A1, Jul. 18, 2024
Int. Cl. B64C 13/50 (2006.01); B64C 13/30 (2006.01); B64C 13/32 (2006.01); B64C 13/34 (2006.01)
CPC B64C 13/50 (2013.01) [B64C 13/30 (2013.01); B64C 13/32 (2013.01); B64C 13/34 (2013.01)] 17 Claims
OG exemplary drawing
 
1. A drive assembly for driving a movable flow body of an aircraft, the drive assembly comprising:
an electric motor having a first set of windings and a second set of windings, wherein the first set of windings and the second set of windings are independent from each other,
a first motor control electronics unit coupled with the first set of windings and a control computer,
a second motor control electronics unit coupled with the second set of windings and the control computer,
a first actuator configured to be coupled with a first section of the movable flow body,
a second actuator configured to be coupled with a second section of the same movable flow body,
a first transmission shaft, and
a second transmission shaft,
wherein the first and second transmission shafts each have a first end and a second end,
wherein the electric motor is coupled with the first end of the first transmission shaft and the first end of the second transmission shaft to rotate both transmission shafts synchronously,
wherein the second end of the first transmission shaft is coupled with the first actuator,
wherein the second end of the second transmission shaft is coupled with the second actuator,
wherein at least one position pickup unit is coupled with, and located within, at least one of the first and second actuators,
wherein the at least one position pickup unit is coupled with the control computer, and
wherein the drive assembly is configured to selectively move and hold the movable flow body into a plurality of extended positions and a retracted position relative to a fixed structural component of the aircraft by selectively moving and holding the first actuator and the second actuator.