Locking assembly for a propeller rotor of an aircraft, a rotor assembly for the aircraft, and a method

A rotor assembly for an aircraft, the rotor assembly comprising:

• a propeller rotor selectively rotatable about a longitudinal axis;
• a locking assembly coupled to the propeller rotor and configured to selectively lock the propeller rotor in a stationary position, the locking assembly including:
• an electric machine coupled to the propeller rotor and having a first mode to energize the electric machine to produce torque to drive rotation of the propeller rotor and a second mode to deenergize the electric machine to stop production of the torque which causes rotation of the propeller rotor to stop;
• wherein the electric machine includes a first wall coupled to the propeller rotor such that the first wall and the propeller rotor are rotatable together about the longitudinal axis when the electric machine is in the first mode, and wherein the first wall and the propeller rotor become stationary relative to the longitudinal axis when the electric machine is in the second mode;
• wherein the electric machine includes a second wall spaced apart from the first wall and the second wall is stationary relative to the first wall regardless of the electric machine being in the first mode or the second mode;
• a magnetic assembly including a first component coupled to the first wall via a pivot point, and including a second component attached to the second wall;
• wherein the first component is movable relative to the pivot point to a locked position and an unlocked position;
• and
• wherein the first component and the second component align proximal to each other when the first component is in the locked position such that the first component and the second component create a magnetic attraction therebetween to lock the first wall and the propeller rotor in the stationary position when the electric machine is in the second mode, and wherein the first component moves away from the second component to the unlocked position due to rotation of the first wall when the electric machine is in the first mode.

A method of controlling a propeller rotor of an aircraft, the method comprising:

• signaling, via a controller, an electric machine to operate in a first mode to produce torque to drive rotation of the propeller rotor, wherein the electric machine includes a first wall coupled to the propeller rotor such that the first wall and the propeller rotor are rotatable together about a longitudinal axis when the electric machine is in the first mode;
• signaling, via the controller, the electric machine to operate in a second mode to deenergize the electric machine to stop production of the torque which causes rotation of the propeller rotor to stop, wherein the first wall and the propeller rotor become stationary relative to the longitudinal axis when the electric machine is in the second mode, and wherein the electric machine includes a second wall spaced apart from the first wall and the second wall is stationary relative to the first wall regardless of the electric machine being in the first mode or the second mode;
• and
• operating a locking assembly to selectively lock the propeller rotor in a stationary position such that a first component of a magnetic assembly and a second component of the magnetic assembly align proximal to each other when the first component is in a locked position in which the first component and the second component create a magnetic attraction therebetween to lock the first wall and the propeller rotor in the stationary position when the electric machine is in the second mode, and wherein the first component moves away from the second component to an unlocked position due to rotation of the first wall when the electric machine is in the first mode, wherein the first component is coupled to the first wall via a pivot point and movable relative to the pivot point to the locked position and the unlocked position, and the second component is attached to the second wall.