Centrifugal de-clutch
View Patent ↗A mechanical mechanism is used to prevent a rotor of an aircraft from rotating when the rotor is not in use. The mechanical mechanism disengages when the speed of the rotor exceeds a speed threshold and the mechanism reengages when the speed of the rotor is below the speed threshold.
1. A rotor assembly comprising:
a rotor;
a motor comprising a stationary part and a rotating part, the rotating part coupled to the rotor; and
a centrifugal de-clutch coupled to the rotating part of the motor, the centrifugal de-clutch comprising a plurality of friction pads and a monolithic ring including an inner circumference and an outer circumference, the monolithic ring formed to include a plurality of flexures extending circumferentially from the inner circumference in a same direction along the inner circumference of the monolithic ring;
wherein the plurality of flexures are configured to preload the plurality of friction pads against the stationary part of the motor to resist rotation of the rotor below a speed threshold of the rotor to engage the centrifugal de-clutch; and
wherein the plurality of flexures are configured to disengage the plurality of friction pads from the stationary part of the motor to allow the rotor to freely rotate above the speed threshold to disengage the centrifugal de-clutch.
2. The rotor assembly of claim 1 , wherein the rotor comprises a plurality of blades and a hub, the plurality of blades coupled to the hub.
3. The rotor assembly of claim 1 , wherein the rotor is made from carbon fiber.
4. The rotor assembly of claim 1 , wherein the rotor is made from composite material.
5. The rotor assembly of claim 2 , wherein the hub is made from aluminum.
6. The rotor assembly of claim 1 , wherein the monolithic ring is formed to further include a plurality of stop tabs protruding from the inner circumference towards the center of the monolithic ring, each stop tab configured to prevent one of the plurality of flexures from bending beyond a position of the stop tab.
7. The rotor assembly of claim 1 , wherein the centrifugal de-clutch is made from a metal selected from a group of metals consisting of aluminum, steel, and titanium.
8. The rotor assembly of claim 1 , wherein the centrifugal de-clutch is made from a composite material.
9. The rotor assembly of claim 8 , wherein the composite material comprises carbon fiber.
10. The rotor assembly of claim 1 , wherein each flexure comprises a first end and a second end, the first end formed to extend circumferentially from the inner circumference of the monolithic ring.
11. The rotor assembly of claim 10 , wherein each of the plurality of friction pads is attached to a second end of one of the plurality of flexures.
12. The rotor assembly of claim 1 , wherein the plurality of friction pads is made of brake pad material.
13. The rotor assembly of claim 1 , wherein the rotor assembly is coupled to an aircraft.
14. The rotor assembly of claim 1 , wherein the plurality of flexures are configured to reengage the plurality of friction pads to the stationary part of the motor when a speed of the rotor decreases below the speed threshold.
15. The rotor assembly of claim 1 , wherein the plurality of flexures are configured to disengage the plurality of friction pads from the stationary part of the motor due to centrifugal force applied by a mass of each of the plurality of flexures.
16. The rotor assembly of claim 1 , wherein the centrifugal de-clutch further comprises a plurality of proof masses, each proof mass coupled to a flexure.
17. The rotor assembly of claim 16 , wherein the plurality of flexures are configured to disengage the plurality of friction pads from the stationary portion of the motor due to centrifugal force applied by the plurality of proof masses.