Electric Motor Powered Rotor Drive for Slowed Rotor Winged Aircraft

• US 20130134264A1
• Filed: 04/12/2012
• Published: 05/30/2013
• Est. Priority Date: 11/28/2011
• Status: Abandoned Application

• Current Assignee: Carter Aviation Technologies, LLC
• Original Assignee: Carter Aviation Technologies, LLC
• Inventors: Carter, Jay W. Jr., Lewis, Jeffrey R.
• Application Number:
  US13/445,594
• Publication Number:
  US 20130134264A1
• Time in Patent Office: Days
• US Class Current: 244/7.A
• CPC Class Codes: B64C 27/025 Rotor drives, in particular for taking off; Combination of autorotation rotors and driven rotors
• CPC Class Codes: B64D 27/026 comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine Hybrid electric aircraft B64D27/33

Abstract

A rotor aircraft has an engine, a propeller, wings, and a rotor. An electric motor is coupled to the rotor drive shaft for applying torque to the rotor drive shaft. The electric motor is sized to supply all of the torque to pre-rotate the rotor to a selected speed prior to liftoff of the aircraft. The wings are capable of providing substantially all of the lift required during forward flight at a cruise speed. The rotor being is capable of being trimmed to provide substantially zero lift and auto-rotate at cruise speed. Sensors sense flight conditions of the aircraft and provide signals to a controller that selectively causes the electric motor to cease applying torque to the rotor drive shaft during autorotation at cruise speed. The controller also causes the electric motor to apply torque to the rotor drive shaft if the sensors indicate additional rotor speed is needed.

Claims

1. A rotor aircraft, comprising:

an engine;

a propeller driven by the engine to provide forward thrust to the aircraft;

wings for providing lift while in forward flight;

a rotor having a rotor drive shaft and mounted for selectively providing lift; and

an electric motor for selectively applying torque to the rotor drive shaft.

2. The rotor aircraft according to claim 1, wherein the electric motor comprises the sole source for applying torque to the rotor drive shaft.

3. The rotor aircraft according to claim 1, further comprising:

a clutch connected between the engine and the rotor drive shaft, for selectively engaging and disengaging the engine from the rotor drive shaft; and

wherein the clutch is located such that the electric motor is able to supply torque to the rotor drive shaft while the clutch is disengaged.

4. The rotor aircraft according to claim 1, wherein the electric motor is sized to supply all of the torque to pre-rotate the rotor to a selected liftoff rotational speed prior to liftoff of the aircraft.

5. The rotor aircraft according to claim 1, wherein the aircraft further comprises:

at least one rudder positioned within a prop blast region of the propeller; and

wherein the rudder is sized to counter torque applied by the electric motor to the rotor drive shaft while the aircraft is airborne.

6. The rotor aircraft according to claim 1, further comprising:

sensors for sensing flight conditions of the aircraft; and

a controller that controls the electric motor while the aircraft is airborne in response to input from the sensors.

7. The rotor aircraft according to claim 1, wherein:

the wings are capable of providing substantially all of the lift required during forward flight at a cruise speed;

the rotor is capable of being positioned to provide substantially zero lift and auto-rotate due to air flowing through the rotor at the cruise speed; and

wherein the aircraft further comprises;

sensors for sensing flight conditions of the aircraft; and

a controller that selectively causes the electric motor to cease applying torque to the rotor drive shaft during autorotation at cruise speed and causes the electric motor to apply torque to the rotor drive shaft during flight if the sensors indicate additional rotor speed is needed.

8. The rotor aircraft according to claim 1, further comprising:

a controller that selectively causes the electric motor to cease applying torque to the rotor drive shaft once the forward airspeed is sufficient for the wings to provide substantially all of the lift required.

9. The rotor aircraft according to claim 1, further comprising:

a clutch connected between the engine and the rotor drive shaft for selectively engaging and disengaging the engine from providing torque to the rotor drive shaft;

wherein

the clutch is located such that the electric motor is able to supply torque to the rotor drive shaft while the clutch is disengaged;

the electric motor is sized to pre-rotate the rotor prior to lift off to a selected fraction of a pre-rotation liftoff speed while the clutch is disengaged; and

when reaching the selected fraction, the clutch is engageable to enable the engine to apply torque to the rotor drive shaft to reach the pre-rotation liftoff speed.

10. A rotor aircraft, comprising:

an engine having an output shaft;

a propeller driven by the engine to provide forward thrust to the aircraft;

wings for providing lift while in forward flight,

a rotor having a rotor drive shaft and mounted for selectively providing lift;

an electric motor coupled to the rotor drive shaft for applying torque to the rotor drive shaft;

the electric motor being sized to supply all of the torque to pre-rotate the rotor to a selected speed prior to lift off of the aircraft;

the wings being capable of providing substantially all of the lift required during forward flight at a cruise speed;

the rotor being capable of being trimmed to provide substantially zero lift and auto-rotate due to air flowing through the rotor at the cruise speed;

sensors for sensing flight conditions of the aircraft; and

a controller that selectively causes the electric motor to cease applying torque to the rotor drive shaft during autorotation at cruise speed and causes the electric motor to apply torque to the rotor drive shaft if the sensors indicate additional rotor speed is needed.

11. The rotor aircraft according to claim 10, wherein the electric motor comprises the sole source for applying torque to the rotor drive shaft.

12. The rotor aircraft according to claim 10, further comprising:

a clutch between the output shaft of the engine and the rotor drive shaft, for selectively engaging and disengaging the engine from providing torque to the rotor drive shaft; and

wherein the clutch is located such that the electric motor is able to supply torque to the rotor drive shaft while the clutch is disengaged.

13. The rotor aircraft according to claim 12, wherein:

the electric motor is sized to supply all of the torque to pre-rotate the rotor to a selected fraction of a pre-rotation liftoff speed prior to liftoff of the aircraft; and

the clutch being engageable while at the selected fraction to cause the engine to pre-rotate the rotor to the pre-rotation liftoff speed.

14. The rotor aircraft according to claim 10, wherein the aircraft further comprises:

at least one rudder positioned within a prop blast region of the propeller; and

wherein the rudder is sized to counter torque applied by the electric motor to the rotor drive shaft while the aircraft is airborne.

15. A method of flying a rotor aircraft having an engine, a propeller driven by the engine, wings, and a rotor having a rotor drive shaft, comprising:

(a) coupling an electric motor to the rotor drive shaft;

(b) applying torque from the electric motor to the rotor drive shaft to pre-rotate the rotor to a selected speed prior to liftoff of the aircraft;

(c) rotating the propeller with the engine while the rotor is pre-rotating to cause liftoff of the aircraft; and

(d) once a selected airborne speed is reached, ceasing to applying torque from the electric motor to the rotor drive shaft.

16. The method according to claim 15, wherein step (d) further comprises:

causing the rotor to auto-rotate due to air flow through the rotor before ceasing to apply torque from the electric motor to the rotor drive shaft.

17. The method according to claim 15, wherein step (d) further comprises:

at a selected cruise speed, positioning the rotor to cause the rotor to auto-rotate at a minimum rotational speed with no torque being applied by the electric motor; and

if flight conditions warrant a higher rotor speed than the minimum rotational speed, again causing the electric motor to apply torque to the rotor drive shaft.

18. The method according to claim 15, wherein:

the aircraft has a rudder positioned within a prop blast region; and

step (d) further comprises positioning the rudder after the liftoff to counter the torque applied by the electric motor.

19. The method according to claim 15, wherein step (b) comprises supplying from the electric motor all of the torque required to reach a selected liftoff rotational speed.

20. The method according to claim 15, wherein:

step (a) further comprises connecting the engine to the rotor drive shaft via a clutch;

step (b) comprises while the clutch is disengaged, rotating the rotor with the electric motor up to a selected fraction of a liftoff rotational speed;

then

engaging the clutch and applying torque from the engine to the rotor drive shaft to rotate the rotor up to the liftoff rotational speed.