Aircraft electric motor
Aircraft electric motors include a rotor comprising a plurality of magnet segments arranged on a frame of the rotor, the rotor defining an internal cavity radially inward from the plurality of magnet segments, an output shaft operably coupled to the rotor, a stator comprising at least one winding wrapped about a support structure, the stator arranged within the internal cavity of the rotor, and a stator support configured to supply at least a current into the at least one winding, wherein the support structure is structurally supported on the stator support. The magnet segments are symmetrically arranged about the stator to balance axial forces applied to the rotor when a current is induced within the at least one winding and maintain a gap between the plurality of magnet segments and the at least one winding.
1. An aircraft electric motor comprising:
a rotor comprising a plurality of magnet segments arranged on a frame of the rotor, the rotor being an annular structure defining an internal cavity within the plurality of magnet segments;
an output shaft arranged radially inward from the rotor and operably coupled to the rotor, the output shaft defining a motor axis;
a stator comprising at least one winding wrapped about a support structure, the stator arranged within the internal cavity of the rotor; and
a stator support comprising a portion extending radially inward from the support structure and a portion extending parallel with the output shaft, the stator support configured to supply at least a current into the at least one winding, wherein the support structure of the stator is structurally supported on the stator support;
wherein the magnet segments are symmetrically arranged about the stator to balance axial forces applied to the rotor when a current is induced within the at least one winding and maintain a gap between the plurality of magnet segments and the at least one winding,
wherein the at least one winding defines a longitudinal axis that is parallel to the motor axis and a radial axis that is normal to the longitudinal axis and parallel with an axis or line extending radially through the stator support,
wherein the symmetrical arrangement of the magnet segments creates a symmetric magnetic field about the at least one winding, and
the output shaft is supported on the stator support at one or more bearings.
2. The aircraft electric motor of claim 1 , wherein the frame of the rotor comprises a first rotor shell and a second rotor shell coupled to each other, wherein the plurality of magnet segments are supported on the first and second rotor shells.
3. The aircraft electric motor of claim 2 , further comprising a fastener configured to join the first rotor shell to the second rotor shell.
4. The aircraft electric motor of claim 1 , wherein the frame comprises an opening on a radially interior side and the stator support extends radially inward from the stator.
5. The aircraft electric motor of claim 1 , wherein the frame is supported on one side in a cantilevered arrangement to the output shaft.
6. The aircraft electric motor of claim 1 , wherein the stator support comprises one or more stator connections.
7. The aircraft electric motor of claim 6 , wherein the one or more stator connections include an electrical connection and a cooling fluid connection.
8. The aircraft electric motor of claim 1 , wherein the at least one winding and the plurality of magnet segments are arranged to have a dominant axial flux.
9. The aircraft electric motor of claim 1 , further comprising a cooling system comprising an annular heat exchanger arranged about the rotor.
10. The aircraft electric motor of claim 9 , further comprising a motor housing arranged radially inward from the heat exchanger, the motor housing defining a rotor- stator cavity with the rotor and stator arranged therein.
11. The aircraft electric motor of claim 1 , further comprising a gear assembly arranged to operably couple the rotor to the output shaft.
12. The aircraft electric motor of claim 1 , further comprising at least one power module system configured to control operation of the aircraft electric motor.
13. The aircraft electric motor of claim 1 , further comprising a cooling system comprising a header configured to direct cooling fluid to the one or more windings of the stator from a heat exchanger.
14. The aircraft electric motor of claim 13 , further comprising a pump configured to circulate the cooling fluid through the header and the heat exchanger.
15. An aircraft comprising:
at least one engine; and
at least one electric motor configured to rotationally drive a component of the aircraft, the at least one electric motor comprising:
a rotor comprising a plurality of magnet segments arranged on an interior surface of a frame of the rotor, the rotor being an annular structure defining an internal cavity within the plurality of magnet segments;
an output shaft arranged radially inward from the rotor and operably coupled to the rotor and configured to be rotationally driven by rotation of the rotor, the output shaft defining a motor axis;
a stator comprising at least one winding wrapped about a support structure, the winding arranged within the rotor; and
a stator support comprising a portion extending radially inward from the support structure and a portion extending parallel with the output shaft, the stator support configured to supply at least a current into the at least one winding, wherein the support structure of the stator is structurally supported on the stator support;
wherein the magnet segments are symmetrically arranged about the stator to balance axial forces applied to the rotor when a current is induced within the at least one winding and maintain a gap between the plurality of magnet segments and the at least one winding,
wherein the at least one winding defines a longitudinal axis that is parallel to the motor axis and a radial axis that is normal to the longitudinal axis and parallel with an axis or line extending radially through the stator support,
wherein the symmetrical arrangement of the magnet segments creates a symmetric magnetic field about the at least one winding, and
the output shaft is supported on the stator support at one or more bearings.
16. The aircraft of claim 15 , wherein the frame of the rotor comprises a first rotor shell and a second rotor shell coupled to each other, wherein the plurality of magnet segments are supported on the first and second rotor shells.
17. The aircraft of claim 15 , wherein the frame comprises an opening on a radially interior side and the stator support extends radially inward from the stator.
18. The aircraft of claim 15 , wherein the frame comprises an opening on a radially exterior side and the stator support extends radially outward from the stator.
19. The aircraft of claim 15 , wherein the at least one winding and the plurality of magnet segments are arranged to have a dominant axial flux.