Optimum speed tilt rotor

• US 6,641,365 B2
• Filed: 10/24/2001
• Issued: 11/04/2003
• Est. Priority Date: 02/20/1998
• Status: Expired due to Term

• Current Assignee: Abraham E. Karem
• Original Assignee: Abraham E. Karem
• Inventors: Karem, Abraham E.
• Primary Examiner(s): Nguyen, Ninh H.
• Application Number:
  US10/029,597
• Publication Number:
  US 20020154996A1
• Time in Patent Office: 741 Days
• Field of Search: 416/1, 416/36, 416/44, 416/131, 416/241.R, 244/7.R, 244/12.4
• US Class Current: 416/1
• CPC Class Codes: B64C 27/33 having flexing arms
• CPC Class Codes: B64C 27/467 Aerodynamic features
• CPC Class Codes: B64C 27/473 Constructional features
• CPC Class Codes: B64C 29/0033 the propellers being tiltable relative to the fuselage

Abstract

A variable speed helicopter tilt rotor system and method for operating such a system are provided which allow the helicopter rotor to be operated at an optimal angular velocity in revolutions per minute (RPM) minimizing the power required to turn the rotor thereby resulting in helicopter performance efficiency improvements, reduction in noise, and improvements in rotor, helicopter transmission and engine life. The system and method provide for an increase in helicopter endurance and range. The system and method also provide a substantial improvement in helicopter performance during take-off, hover and maneuver. All such improvements are valid in helicopter mode when the helicopter is supported by rotor vertical lift, in airplane mode when the helicopter is supported by wing lift and the rotor is tilted forward to provide propulsive thrust and in conversion from helicopter mode to airplane mode.

Claims

1. A method for improving the efficiency of a rotorcraft for a specific flight condition, the rotorcraft comprising a rotor having radially extending blades and an engine for providing power to rotate the rotor, wherein the rotor operates at an RPM level between and including a maximum rotor RPM level and a minimum rotor RPM level, the method comprising:

ascertaining an RPM level for improving efficiency for the specific flight condition; and

adjusting the RPM of the rotor to the ascertained RPM level wherein said ascertained RPM level is less than 94% of maximum RPM.

2. A method as recited in claim 1 wherein the ascertained RPM level is less than 80% of the rotor maximum RPM level.

3. A method as recited in claim 1 wherein the ascertained RPM level is less than 70% of the rotor maximum RPM level.

4. A method as recited in claim 1 wherein the ascertained RPM level is less than 60% of the rotor maximum RPM level.

5. A method as recited in claim 1 wherein the step of ascertaining an RPM level comprises determining a blade loading as a function of RPM level and ascertaining an RPM level for achieving the determined blade loading.

6. A method as recited in claim 5 wherein the step of determining comprises the step of determining a range of blade loadings for improved efficiency for the flight condition, and wherein the step of ascertaining an RPM level for achieving the determined blade loading comprises the step of ascertaining an RPM range for achieving a blade loading within the determined range of blade loadings.

7. A method as recited in claim 1 wherein the rotorcraft is a tilt rotor rotorcraft, and the rotor is a tilt rotor and wherein the specific flight condition is a condition of flight occurring during a mode of flight selected from the group of airplane, helicopter and conversion modes, wherein in helicopter mode the ascertained rotor RPM level is less than 94% of the maximum RPM level.

8. A method as recited in claim 7 wherein during helicopter mode the ascertained rotor RPM level is less than 80% of the maximum RPM level.

9. A method as recited in claim 7 wherein during helicopter mode the ascertained rotor RPM level is less than 70% the maximum RPM level.

10. A method for improving the efficiency of a tilt rotor rotorcraft comprising a tilt rotor, the tilt rotor being capable of tilting to and operating in a helicopter mode, a conversion mode, and an airplane mode, and having radially extending blades and an engine for providing power to rotate the rotor at various RPM levels, the tilt rotor being capable of operation at a maximum RPM level in helicopter mode, the method comprising the steps of:

operating the rotor at an RPM level in helicopter mode; and

operating the rotor in airplane mode at an RPM level less than 80% of the maximum RPM level in helicopter mode.

11. A method as recited in claim 10 wherein operating the rotor in airplane mode comprises operating the rotor in airplane mode at an RPM level less than 70% of the maximum RPM level in helicopter mode.

12. A method as recited in claim 10 wherein operating the rotor in airplane mode comprises operating the rotor in airplane mode at an RPM level less than 60% of the maximum RPM level in helicopter mode.

13. A method as recited in claim 10 wherein the operating the rotor at an RPM level in helicopter mode comprises operating the rotor at an RPM level less than 94% of the maximum rotor RPM level in helicopter mode.

14. A method as recited in claim 10 wherein the operating the rotor at an RPM level in helicopter mode comprises operating the rotor at an RPM level less than 80% of the maximum rotor RPM level in helicopter mode.

15. A method as recited in claim 10 wherein the operating the rotor at an RPM level in helicopter mode comprises operating the rotor at an RPM level less than 70% of the maximum rotor RPM level in helicopter mode.

16. A variable speed tilt rotor, wherein the tilt rotor tilts from a helicopter mode position to an airplane mode position, wherein when in helicopter mode the tilt rotor provides lift to a rotorcraft and when in airplane mode the tilt rotor provides thrust to the rotorcraft, the rotor having a radius measured from a center of rotor rotation and a diameter and comprising:

a rotor hub; and

at least two blades radially coupled to the hub, each blade having a root proximal the hub and a tip distal to the hub, wherein each blade weight in lbs. does not exceed the product of 0.004 times the diameter of the rotor in feet cubed.

17. A tilt rotor as recited in claim 16 wherein each blade weight in lbs does not exceed the product of 0.0025 times the diameter of the rotor in feet cubed.

18. A tilt rotor as recited in claim 17 wherein the flap stiffness of each blade in lbs-in² at 30% of the rotor radius as measured from a center of rotor rotation is not less than the product of 100 times the rotor diameter in feet to the fourth power.

19. A tilt rotor as recited in claim 17 wherein the flap stiffness of each blade in lbs-in² at 30% of the rotor radius as measured from a center of rotor rotation is not less than the product of 200 times the rotor diameter in feet to the fourth power.

20. A tilt rotor as recited in claim 17 wherein the weight of each blade per unit length continuously decreases from the blade root to the blade tip.

21. A tilt rotor as recited in claim 17 wherein the flap, lag and torsional stiffness of each blade continuously decrease from the blade root to the blade tip.

22. A tilt rotor as recited in claim 17 wherein the hub is non-gimbaled and hingeless.

23. A variable speed tilt rotor, wherein the tilt rotor tilts from a helicopter mode position to an airplane mode position, wherein when in helicopter mode the tilt rotor provides lift to a rotorcraft and when in airplane mode the tilt rotor provides thrust to the rotorcraft, the rotor having a radius measured from a center of rotor rotation and a diameter and comprising:

a rotor hub; and

at least two blades radially coupled to the hub, each blade having a root proximal the hub and a tip distal to the hub, wherein the flap stiffness of each blade in lbs-in² at 30% of the rotor radius is not less than the product of 100 times the rotor diameter in feet to the fourth power.

24. A tilt rotor as recited in claim 23 wherein the flap stiffness of each blade in lbs-in² at 30% of the rotor radius as measured from a center of rotor rotation is not less than the product of 200 times the rotor diameter in feet to the fourth power.

25. A tilt rotor as recited in claim 23 wherein the weight of each blade per unit length continuously decreases from the blade root to the blade tip.

26. A tilt rotor as recited in claim 23 wherein the flap, lag and torsional stiffness of each blade continuously decrease from the blade root to the blade tip.

27. A rotor for a rotorcraft comprising:

a rotor hub; and

at least two blades radially coupled to the hub, wherein each blade weight in lbs. does not exceed the product of 0.003 times the diameter of the rotor in feet cubed.

28. A rotor as recited in claim 27 wherein each blade weight in lbs. does not exceed the product of 0.002 times the diameter of the rotor in feet cubed.

29. A rotor as recited in claim 27 wherein each blade weight in lbs. does not exceed the product of 0.001 times the diameter of the rotor in feet cubed.