Drive assembly for driving a movable flow body of an aircraft
A drive assembly for driving a movable flow body of an aircraft comprises an electric motor having a two sets of independent windings, two motor control electronics units coupled with the windings and a control computer, two actuators couplable with a first or second section of the flow body, a first and a second transmission shaft, wherein the transmission shafts each have a first and a second end, wherein the electric motor is coupled with the first ends of the transmission shafts, wherein the second ends of the transmission shafts are coupled with the respective actuator, and wherein the drive assembly is designed 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.
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.
2. The drive assembly of claim 1 , wherein the first transmission shaft and the second transmission shaft are designed as flexible shafts.
3. The drive assembly of claim 1 , wherein one of the at least one position pickup unit is coupled with at least one of the first and second transmission shafts, or the electric motor, or both, and
wherein the at least one position pickup unit is coupled with the control computer.
4. The drive assembly of claim 1 , wherein the at least one position pickup unit is a single position sensor.
5. The drive assembly of claim 1 , wherein the at least one position pickup unit is a redundant position sensor.
6. The drive assembly of claim 1 , wherein the first actuator, or the second actuator, or both comprise a linear ball screw actuator.
7. The drive assembly of claim 1 , wherein the first actuator, or the second actuator, or both comprise a geared rotary actuator.
8. The drive assembly of claim 1 , wherein the first actuator, or the second actuator or both comprises a no-back device, or a power-off brake adapted to prevent the movable flow body from moving when the electric motor is stopped, or both.
9. The drive assembly of claim 1 , wherein the electric motor comprises a power-off brake to arrest the drive assembly before and after a drive sequence.
10. The drive assembly of claim 1 , wherein the first and second actuators comprise a rotary input having a rotational axis transverse to a rotational axis of the electric motor; and
wherein the rotational axis of the rotary input and the rotational axis of the electric motor enclose an angle in a range of 45° to 135°.
11. A drive system comprising:
a plurality of the drive assembly according to claim 1 ,
wherein the drive assemblies are independent from each other, such that individual flow bodies are movable independently from each other.
12. A high lift system comprising:
at least one drive system according to claim 11 , and
at least one movable flow body coupled with the at least one drive system,
wherein the high lift system is a trailing-edge flap high lift system.
13. A wing comprising:
at least one high lift system of claim 12 .
14. An aircraft comprising:
at least one wing of claim 13 .
15. The drive assembly of claim 1 , wherein the electric motor comprises a rotational axis, which is aligned parallel to a spanwise axis of a respective wing of the aircraft.
16. The drive assembly of claim 1 , wherein the first actuator, or the second actuator or both include an integrated load sensor which measures the loads on the first actuator, or the second actuator or both.
17. The drive assembly of claim 1 , further comprising a first electrical power supply coupled to the first motor control electronics unit and a second electrical power supply coupled to the second motor control electronics unit, the first and second electrical power supplies being redundant power supplies.