Helicopter anti-torque system using fuselage strakes

• US 4,708,305 A
• Filed: 01/30/1987
• Issued: 11/24/1987
• Est. Priority Date: 01/30/1987
• Status: Expired due to Term

• Current Assignee: The United States of America As Represented By The Secretary of Agriculture
• Original Assignee: United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration
• Inventors: Wilson, John C., Kelley, Henry L.
• Primary Examiner(s): BAREFOOT, GALEN L
• Application Number:
  US07/008,895
• Time in Patent Office: 298 Days
• Field of Search: 244/91, 244/17.11, 244/17.21, 244/17.19
• US Class Current: 244/17.19
• CPC Class Codes: B64C 2027/8245 using air jets
• CPC Class Codes: B64C 23/00 Influencing air flow over aircraft surfaces, not otherwise provided for
• CPC Class Codes: B64C 27/82 characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft

Abstract

A helicopter 10 with a system for controlling mainrotor torque which reduces the power and size requirements of conventional anti-torque means. The torque countering forces are generated by disrupting the main rotor downwash flowing around the fuselage. The downward flow is separated from the fuselage surface 11 by strakes 16 and 17 positioned at specified locations on the fuselage 11. These locations are determined by the particular helicopter wash pattern and fuselage configuration, generally being located 30° before top dead center 21 and 30° from bottom dead center 22 on the fuselage side to which the main rotor blade 12 approaches during rotation. The strakes 16 and 17 extend along the fuselage 11 from the cabin section 18 to the aft end and can be continuous or separated for aerodynamic surfaces such as a horizontal stabilizer 15.

Claims

1. A helicopter torque control system comprising:

a helicopter;

said helicopter having a main rotor attached thereto;

said helicopter having a fuselage extending rearward through rotor downwash;

helicopter torque control means consisting of a combination of two strake devices, the upper strake being located above the lower strake and both strake devices located only along the side of said fuselage which faces the approaching main rotor blade, for altering rotor downwash, thereby altering lateral aerodynamic force of the fuselage so as to counter main rotor torque; and

supplemental control means to assist in controlling main rotor torque.

2. A helicopter torque control system as in claim 1 wherein the upper strake is located 30°

before top dead center of the fuselage and the lower strake is located 30°

after bottom dead center of the fuselage.

3. A helicopter torque control system as in claim 1 wherein the supplemental torque control means is a small tail rotor.

4. A helicopter torque control system as in claim 3 wherein the tail rotor disc area is 60% -80% of prior art devices.

5. A helicopter torque control system as in claim 1 wherein the supplemental torquel control means is a reaction device.

6. A helicopter torque control system as in claim 5 wherein the reaction device is jet pressurized by the main engine system.

7. A helicopter torque control system as in claim 1 wherein said helicopter has a horizontal stabilizer located between said upper and lower strakes.

8. A helicopter torque control system as in claim 1 wherein the means of altering downwash over the fuselage is a strake having means for positioning which allows configuring for different flight conditions.

9. A helicopter torque control system as in claim 8 wherein the means of positioning said strake is a hydraulic actuator.

10. A helicopter torque control system as in claim 8 wherein the means of positioning said strake is an electrical actuator.

11. A helicopter torque control system as in claim 8 wherein the means of positioning said strake is a pneumatic actuator.

12. A helicopter torque control system as in claim 8 wherein the means of positioning said strake is a mechanical actuator.

13. A helicopter torque control system comprising a helicopter;

said helicopter having a main rotor blade attached thereto;

said helicopter having a fuselage extending rearward through rotor downwash;

said helicopter having a horizontal stabilizer;

helicopter torque control means consisting of a combination of two strake devices, the upper strake being located above the lower strake and both strake devices located only along the side of said fuselage which faces the approaching main rotor blade, said upper and lower strakes being individually segmented into parts with one part extending from the cabin area of the fuselage to the horizontal stabilizer and the other part extending from the horizontal stabilizer to the aft end of the fuselage boom, thereby altering rotor downwash and altering lateral aerodynamic force on the fuselage so as to counter main rotor torque; and

supplemental control means to assist in controlling main rotor torque.

14. A helicopter torque control system as in claim 13 wherein the means of altering downwash over the fuselage is a strake having means for positioning which allows configuring for different flight conditions.

15. A helicopter torque control system as in claim 14 wherein the means of positioning said strake is a hydraulic actuator.

16. A helicopter torque control system as in claim 14 wherein the means of positioning said strake is an electrical actuator.

17. A helicopter torque control system as in claim 14 wherein the means of positioning said strake is a pneumatic actuator.

18. A helicopter torque control system as in claim 14 wherein the means of positioning said strake is a mechanical actuator.

19. A helicopter torque control system as in claim 13 wherein the supplemental torque control means is a small tail rotor.