Power system
A power system for an aircraft comprises: a motor-generator component; a shaft, wherein the motor-generator component is connectable to the shaft, the shaft connectable to an additional component of the aircraft to for torque transfer with the additional component; and a de-coupler operable to disconnect the motor-generator component from the shaft, wherein the motor-generator component is located between the de-coupler and the additional component in use.
1. A power system for an aircraft, the power system comprising:
a motor-generator component;
a shaft that defines an axis of rotation, wherein the motor-generator component is connectable to the shaft, and wherein the shaft is connectable to an additional component of the aircraft for torque transfer with the additional component; and
a de-coupler configured to disconnect the motor-generator component from the shaft, wherein the motor-generator component is located axially between the de-coupler and the additional component in use such that the de-coupler is positioned on an opposite side of the motor-generator component relative to the additional component.
2. The power system according to claim 1 , wherein the shaft extends through the motor-generator component, including through a same side of the motor-generator component relative to the additional component, and through the opposite side of the motor-generator component.
3. The power system according to claim 1 , wherein the motor-generator component comprises a second shaft configured to nest with the shaft.
4. The power system according to claim 3 , wherein the second shaft surrounds the shaft.
5. The power system according to claim 1 , wherein:
the de-coupler comprises a connector element; and
the connector element is movable into a disconnected position to disconnect the motor-generator component from the shaft.
6. The power system according to claim 5 , wherein the connector element is slidable into the disconnected position.
7. The power system according to claim 5 , further comprising an actuator configured to move the connector element into the disconnected position.
8. The power system according to claim 7 , wherein the actuator is a solenoid.
9. The power system according to claim 5 , wherein:
the motor-generator component comprises a second shaft configured to nest with the shaft;
the connector element comprises a torque coupler for connecting to the second shaft; and
the torque coupler comprises connector element teeth configured to engage with second shaft teeth on the second shaft.
10. The power system according to claim 9 , wherein the torque coupler is disconnected when the connector element is in the disconnected position.
11. The power system according to claim 10 , wherein the connector element teeth are out of contact with first shaft teeth when the connector element is in the disconnected position.
12. The power system according to claim 5 , further comprising a bias element configured to bias the connector element away from the disconnected position.
13. The power system according to claim 5 , further comprising a latch configured to maintain the connector element in the disconnected position.
14. The power system according to claim 13 , wherein the latch is a centrifugal latch configured to open to release the connector element from the disconnected position when a rotational speed is below a threshold.
15. An aircraft comprising:
a power system comprising:
a motor-generator component;
a shaft that defines an axis of rotation, wherein the motor-generator component is connectable to the shaft, and wherein the shaft is connectable to an additional component of the aircraft for torque transfer with the additional component; and
a de-coupler configured to disconnect the motor-generator component from the shaft, wherein the motor-generator component is located axially between the de-coupler and the additional component in use such that the de-coupler is positioned on an opposite side of the motor-generator component relative to the additional component.
16. The aircraft of claim 15 , wherein:
the de-coupler comprises a connector element; and
the connector element is movable into a disconnected position to disconnect the motor-generator component from the shaft.
17. The aircraft of claim 16 , wherein:
the motor-generator component comprises a second shaft configured to nest with the shaft;
the connector element comprises a torque coupler for connecting to the second shaft; and
the torque coupler comprises connector element teeth configured to engage with second shaft teeth on the second shaft.
18. The aircraft of claim 17 , wherein the torque coupler is disconnected when the connector element is in the disconnected position.
19. The aircraft of claim 16 , wherein the power system further comprises a bias element configured to bias the connector element away from the disconnected position.
20. The aircraft of claim 19 , wherein the power system further comprises a latch configured to maintain the connector element in the disconnected position.