Power Rotor Drive for Slowed Rotor Winged Aircraft

• US 20130134253A1
• Filed: 11/28/2011
• 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.
• Application Number:
  US13/305,441
• Publication Number:
  US 20130134253A1
• Time in Patent Office: Days
• US Class Current: 244/17.11
• CPC Class Codes: B64C 27/12 Rotor drives
• CPC Class Codes: B64C 27/26 characterised by provision of fixed wings

Abstract

A rotor aircraft has an engine having an output shaft. At least one propeller is driven by the engine to provide forward thrust to the aircraft. Wings provide lift while in forward flight. A rotor is driven by rotor drive mechanism, which selectively provides torque to the rotor drive shaft from the engine while in a first mode. The rotor drive mechanism selectively provides torque to the rotor drive shaft to rotate at a speed independent of a speed of the output shaft of the engine while in a second mode. In one embodiment, the rotor drive mechanism is a variable speed transmission powered by the engine. In another embodiment, the rotor drive mechanism is an electric motor.

Claims

1. A rotor aircraft, comprising:

an engine having an output shaft;

at least one forward thrust device 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

rotor drive means for selectively providing torque to the rotor drive shaft from the output shaft of the engine at a speed proportional to a speed of the output shaft of the engine while in a first mode and for selectively providing torque to the rotor drive shaft to rotate at a speed independent of a speed of the output shaft of the engine while in a second mode.

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

sensors for sensing flight conditions of the aircraft; and

a controller that controls the rotary drive means while in the second mode in response to input from the sensors.

3. The rotor aircraft according to claim 1, wherein while in the second mode:

the wings are capable of providing substantially all of the lift required during forward flight;

the rotor is capable of being trimmed to provide substantially zero lift; and

the rotor drive means continues to provide torque to the rotor drive shaft to maintain a desired minimum rotational speed of the rotor.

4. The rotor aircraft according to claim 1, wherein the rotor drive means comprises an electric motor coupled to the rotor drive shaft.

5. The rotor aircraft according to claim 4, further comprising:

a clutch between the output shaft of the engine and the rotor drive shaft, the clutch being released while the rotary drive means is in the second mode, thereby 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 released.

6. The rotor aircraft according to claim 5, wherein while the rotary drive means is in the first mode, the clutch is engaged, thereby causing the output shaft of the engine to apply torque to the rotor drive shaft.

7. The rotor aircraft according to claim 1, wherein the rotary drive means comprises a transmission having an input driven by the output shaft of the engine and an output that is variable in rotational speed relative to the input shaft of the engine.

8. The rotor aircraft according to claim 7, wherein the output of-the transmission is infinitely variable in speed relative to the output shaft of the engine.

9. The rotor aircraft according to claim 7, wherein the transmission has multiple gear ratios of input speed to output speed.

10. A rotor aircraft, comprising:

an engine having an output shaft;

at least one forward thrust device driven by the engine to provide forward thrust to the aircraft;

wings for providing lift during forward flight;

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

a clutch located between the output shaft of the engine and the rotor drive shaft, having an engaged position for causing the engine to provide torque to the rotor drive shaft and a disengaged position releasing the output shaft of the engine from driving engagement with the rotor drive shaft; and

an electric motor coupled to the rotor drive shaft for selectively providing torque to the rotor drive shaft while the clutch is in the disengaged position.

11. The rotor aircraft according to claim 10, wherein the electric motor remains coupled to the rotor drive shaft while the clutch is in engaged position and being driven by the engine.

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

sensors for sensing flight conditions of the aircraft; and

a controller that controls the electric motor in response to input from the sensors while the clutch is in the disengaged position.

13. The rotor aircraft according to claim 10, wherein while the clutch is in the disengaged position:

the wings are capable of providing substantially all of the lift required due to forward airspeed;

the rotor is capable of being trimmed to provide substantially zero lift; and

the electric motor provides torque to the rotor drive shaft to maintain a desired minimum rotational speed of the rotor.

14. A rotor aircraft, comprising:

an engine having an output shaft;

at least one forward thrust device driven by the output shaft of the engine to provide forward thrust to the aircraft;

wings for providing lift during forward flight;

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

a transmission having an input-driven by the output shaft of the engine and an output coupled to the rotor drive shaft, the output of the transmission being selectively variable in rotational speed relative to the input shaft of the engine.

15. The rotor aircraft according to claim 14, further comprising:

sensors for sensing flight conditions of the aircraft; and

a controller that controls the output speed of the transmission in response to input from the sensors.

16. The rotor aircraft according to claim 14, wherein:

the rotor aircraft has a forward flight mode wherein the wings provide substantially all the lift;

the rotor may be trimmed to provide substantially zero lift; and

the transmission provides an output speed to the rotor drive shaft to rotate the rotor at a minimum desired speed.