Helicopter tail boom with venting for alleviation and control of tail boom aerodynamic loads and method thereof

• US 6,352,220 B1
• Filed: 06/02/2000
• Issued: 03/05/2002
• Est. Priority Date: 06/02/2000
• Status: Expired due to Fees

• Current Assignee: National Aeronautics and Space Administration US Government As Represented By The Administrator of The
• Original Assignee: United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration
• Inventors: Kelley, Henry L., Banks, Daniel W.
• Primary Examiner(s): Jordan, Charles T.
• Assistant Examiner(s): Dinh, T.
• Application Number:
  US09/586,603
• Time in Patent Office: 641 Days
• Field of Search: 244/51, 244/17.19, 244/17.11, 244/207, 244/208, 244/52, 244/73.C, 244/12.5, 239/265.27, 239/265.29
• US Class Current: 244/17.19
• CPC Class Codes: B64C 2027/8245 using air jets
• 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

In at least one embodiment, the apparatus of the invention is a flight vehicle tail assembly having an exterior surface, at least one first vent in the exterior surface, at least one second vent in the exterior surface, and an air passage connecting the at least one first vent to the at least one second vent allowing air to flow therebetween. Where the at least one first vent is located near a high air pressure area acting on the exterior surface during a range of predefined flight conditions. Further, the at least one second vent is located near a low air pressure area acting on the exterior surface during the predefined flight conditions. So that at the predefined flight conditions adverse loads on the tail assembly are reduced by venting air from the high pressure area, through the tail assembly, to the low pressure area. The method of the present invention includes the steps of: receiving air through the at least one first vent in the exterior surface, passing the air through the tail assembly from the at least one first vent to at least one second vent in the exterior surface, and ejecting the air out of the tail assembly at the at least one second vent.

Claims

1. A flight vehicle tail assembly comprising:

A. an exterior surface;

B. at least one first vent in the exterior surface;

C. at least one second vent in the exterior surface;

D. an air passage connecting the at least one first vent and at least one second vent allowing air to flow therebetween;

wherein the at least one first vent is-located at least near a high air pressure area acting on the exterior surface during a range of predefined flight conditions, and wherein the at least one second vent is located at least near a low air pressure area acting on the exterior surface during said predefined flight conditions; and

at least one first vent door attached to the tail assembly, wherein the at least one first vent door has a first door closed position, and wherein with the at least one first vent door is the first door closed position the at least one first vent door covers at least a portion of the at least one first vent.

2. The fight vehicle tail assembly of claim 1, wherein the at least one first vent further comprises an air permeable cover positioned to cover at least a portion of the at least one first vent and wherein the at least one second vent further comprises an air permeable cover positioned to cover at least a portion of the at least one second vent.

3. The flight vehicle tail assembly of claim 1, further comprising at least one second vent door attached to the tail assembly, wherein the at least one second vent door has a second door closed position, and wherein with the at least one second vent door in the second door closed position the at least one second vent door covers at least a portion of the second vent.

4. The flight vehicle tail assembly of claim 1, further comprising at least one second vent door attached to the tail assembly, wherein the at least one second vent door has a second door closed position, and wherein with the at least one second vent door in the second door closed position the at least one second vent door covers at least a portion of the second vent.

5. The flight vehicle tail assembly of claim 1, wherein the air passage is a cavity defined within the tail assembly.

6. The flight vehicle tail assembly of claim 1, further comprising at least one strake mounted to the exterior surface and positioned to disrupt airflow along the exterior surface.

7. The flight vehicle tail assembly of claim 1, wherein the tail assembly further comprises a first end and a second end, wherein the tail assembly is mounted to a flight vehicle fuselage at the first end and to a tail at the second end, and wherein said tail further comprises a yaw control apparatus.

8. The flight vehicle tail assembly of claim 1, wherein the air passage is a cavity defined within an external plenum.

9. A helicopter tail boom for reducing adverse loads during a range of predefined flight conditions, the tail boom having a length, a first end and a second end, wherein the boom is mounted between a helicopter fuselage at the first boom end and a tail at the second boom end, said tail further comprising a yaw control apparatus, the boom comprising:

A. an exterior surface;

B. a high pressure vent positioned substantially longitudinally along the length of the boom at least near a high air pressure area acting on the exterior surface during said range of predefined flight conditions;

C. a low pressure vent positioned substantially longitudinally along the length of the tail boom at least near a low air pressure area acting on the exterior surface during said range of predefined flight conditions; and

D. an air passage between said high pressure vent and said low pressure vent allowing air to flow therebetween, so that air can pass through the boom from said high pressure area to said low pressure area to cause a reduction of adverse loads on the tail boom.

10. The helicopter tail boom of claim 9, wherein the high pressure vent further comprises a first air permeable covering over at least a portion of the high pressure vent, and wherein the low pressure vent further comprises a second air permeable covering over at least a portion of the low pressure vent.

11. The helicopter tail boom of claim 9, further comprising at least one high pressure door attached to the tail boom, the at least one high pressure door having a high pressure door closed position, and wherein with the at least one high pressure vent door in the high pressure door closed position the at least one high pressure vent door covers at least a portion of the at least one high pressure vent, and at least one low pressure vent door attached to the tail boom, wherein the at least one low pressure vent door has a low pressure door closed position, and wherein with the at least one low pressure vent door in the low pressure door closed position the at least one low pressure vent door covers at least a portion of the low pressure vent.

12. The helicopter tail boom of claim 9, further comprising at least one strake mounted to the exterior surface and positioned to disrupt airflow along the exterior surface.

13. The helicopter tail boom of claim 9, further comprising a first strake mounted to the exterior surface adjacent to the high pressure vent and positioned to disrupt airflow along the exterior surface and channel air into the high pressure vent.

14. The helicopter tail boom of claim 13, further comprising a second strake mounted to the exterior surface and adjacent the low pressure vent.

15. The helicopter tail boom of claim 9, wherein the air passage is a duct.

16. A method for alleviating adverse loads on a flight vehicle tail assembly having an exterior surface, the method comprising:

A. receiving air through at least one first vent in the exterior surface;

B. passing the air through the tail assembly from the at least one first vent to at least one second vent in the exterior surface;

C. ejecting the air out of the tail assembly at the least one second vent; and

at least one first vent door attached to the tail assembly, the at least one first vent door having a first door closed position, and wherein with the at least one first vent door in the first door closed position the at least one first vent door covers at least a portion of the at least one first vent, and at least one second vent door attached to the tail assembly, wherein the at least one second vent door has a second door closed position, and wherein with the at least one second vent door in the second door closed position the at least one second vent door covers at least a portion of the second vent.

17. The method of claim 16, wherein the at least one first vent further comprises at least one first air permeable covering positioned over at least a portion of the at least one first vent, and wherein the at least one second vent further comprises at least one second air permeable covering positioned over at least a portion of the at least one second vent.

18. The method of claim 16, further comprising at least one strake mounted to the exterior surface and positioned to disrupt airflow along the exterior surface.