Aircraft stabilization systems and methods of modifying an aircraft with the same

• US 8,985,503 B2
• Filed: 03/27/2014
• Issued: 03/24/2015
• Est. Priority Date: 04/26/2013
• Status: Active Grant

• Current Assignee: BLR Aerospace, LLC
• Original Assignee: BLR Aerospace, LLC
• Inventors: Desroche, Robert J.
• Primary Examiner(s): Bonzell, Philip J
• Application Number:
  US14/228,120
• Publication Number:
  US 20140317900A1
• Time in Patent Office: 362 Days
• Field of Search: 244/17.11, 244/17.19, 244/17.21, 298/972, 294/020.3, 294/020.8
• US Class Current: 244/17.19
• CPC Class Codes: B64C 2027/8263 comprising in addition rudders, tails, fins, or the like
• CPC Class Codes: B64C 23/06 by generating vortices
• CPC Class Codes: B64C 27/04 Helicopters
• CPC Class Codes: Y02T 50/10 Drag reduction
• CPC Class Codes: Y10T 29/49716 Converting

Abstract

A method of modifying a helicopter includes providing a tail boom of the helicopter. The tail boom includes a first side located on an opposite side of the tail boom from a second side of the tail boom. A main rotor blade of the helicopter approaches the second side of the tail boom during rotation. The first side and the second side of the tail boom include asymmetrical surface profiles about a vertical plane of the tail boom. The method further includes securing a plurality of vortex generators to the first side of the tail boom.

Claims

1. A method for modifying a helicopter, comprising:

physically coupling a tail boom modification structure to at least an exiting side of a tail boom fuselage that is opposite an approaching side of the tail boom fuselage, the tail boom modification structure having a first convex exterior surface that extends from a vertical apex of the tail boom modification structure to a vertical nadir of the tail boom modification structure, a first concave exterior surface that extends from the vertical apex to a transition point and is shaped to fittingly receive an exiting side of a tail rotor drive shaft cover that is opposite an approaching side of the tail rotor drive shaft cover, a second concave exterior surface that extends from the transition point to the vertical nadir of the tail boom modification structure and is shaped to fittingly receive at least a portion of the exiting side of the tail boom fuselage, and a plurality of vortex generators physically coupled to the first convex exterior surface.

2. The method of claim 1 wherein physically coupling a tail boom modification structure to at least an exiting side of a tail boom fuselage comprises physically coupling the tail boom modification structure to at least the exiting side of the tail boom fuselage to eliminate a shoulder formed by the exiting side of the tail rotor drive shaft cover and the exiting side of the tail boom fuselage.

3. The method of claim 1 wherein physically coupling a tail boom modification structure to at least an exiting side of a tail boom fuselage comprises physically coupling the tail boom modification structure to at least the exiting side of the tail boom fuselage, the tail boom modification structure having the first convex exterior surface that forms a single continuous curve between the vertical apex and the vertical nadir of the tail boom modification structure.

4. The method of claim 1 wherein physically coupling a tail boom modification structure to at least an exiting side of a tail boom fuselage comprises physically coupling the tail boom modification structure to at least the exiting side of the tail boom fuselage, the tail boom modification structure having the plurality of vortex generators which are respectively spaced from each other a distance that is between 3 inches and 6 inches.

5. The method of claim 1 wherein physically coupling a tail boom modification structure to at least an exiting side of a tail boom fuselage comprises physically coupling the tail boom modification structure to at least the exiting side of the tail boom fuselage, the tail boom modification structure having the plurality of vortex generators that are each canted at an angle between 10 degrees and 30 degrees off a vertical axis.

6. The method of claim 1 wherein physically coupling a tail boom modification structure to at least an exiting side of a tail boom fuselage comprises physically coupling the tail boom modification structure to at least the exiting side of the tail boom fuselage, the tail boom modification structure having the plurality of vortex generators physically coupled to the first convex exterior surface so as to be located at between 5 percent and 20 percent of a chord length associated with the tail boom fuselage.

7. A tail boom modification structure, comprising:

a first convex exterior surface that extends from a vertical apex of the tail boom modification structure to a vertical nadir of the tail boom modification structure;

a first concave exterior surface that extends from the vertical apex to a transition point and is shaped to fittingly receive an exiting side of a tail rotor drive shaft cover, the exiting side of the tail rotor drive shaft cover opposite an approaching side of the tail rotor drive shaft cover;

a second concave exterior surface that extends from the transition point to the vertical nadir of the tail boom modification structure and is shaped to fittingly receive at least a portion of an exiting side of a tail boom fuselage, the exiting side of the tail boom fuselage opposite an approaching side of the tail boom fuselage; and

a plurality of vortex generators physically coupled to the first convex exterior surface.

8. The tail boom modification structure of claim 7 wherein the first convex exterior surface forms a single continuous curve between the vertical apex and the vertical nadir of the tail boom modification structure.

9. The tail boom modification structure of claim 7 wherein each of the plurality of vortex generators comprises a leading edge, a trailing edge, a top edge, and a bottom.

10. The tail boom modification structure of claim 7 wherein the leading edge of each of the plurality of vortex generators is tapered.

11. The tail boom modification structure of claim 7 wherein each of the plurality of vortex generators has a length that ranges from 1 inch to 2 inches.

12. The tail boom modification structure of claim 7 wherein each of the plurality of vortex generators has a width that ranges from 0.25 inches to 0.50 inches.

13. The tail boom modification structure of claim 7 wherein the plurality of vortex generators are respectively individually physically coupled to the first convex exterior surface.

14. The tail boom modification structure of claim 7 wherein the plurality of vortex generators are physically coupled to the first convex exterior surface as a single assembly.

15. The tail boom modification structure of claim 7 wherein the plurality of vortex generators are respectively spaced from each other a distance that is between 3 inches and 6 inches.

16. The tail boom modification structure of claim 7 wherein each of the plurality of vortex generators is canted at an angle between 10 degrees and 30 degrees off a vertical axis.

17. The tail boom modification structure of claim 7 wherein the plurality of vortex generators are physically coupled to the first convex exterior surface so as to be located at between 5 percent and 20 percent of a chord length associated with the tail boom fuselage when the when the tail boom modification is physically coupled to the tail boom fuselage.

18. The tail boom modification structure of claim 7 wherein each of the plurality of vortex generators is canted in a forward direction or canted in an aft direction.

19. The tail boom modification structure of claim 18 wherein the plurality of vortex generators are all canted in the same direction.

20. The tail boom modification structure of claim 18 wherein the plurality of vortex generators are respectively canted in alternating directions.

21. A helicopter tail boom, comprising:

a tail boom fuselage that has an approaching side and an exiting side opposite the approaching side, the tail boom fuselage symmetrical about a vertical plane;

a tail rotor drive shaft cover that has an approaching side and an exiting side opposite the approaching side, the tail rotor drive shaft cover symmetrical about the vertical plane; and

a tail boom profile modification structure, comprising;

a first convex exterior surface that extends from a vertical apex of the tail boom modification structure to a vertical nadir of the tail boom modification structure;

a first concave exterior surface that extends from the vertical apex to a transition point between the tail rotor drive shaft cover and the tail boom fuselage and is shaped to fittingly receive the exiting side of a tail rotor drive shaft cover; and

a second concave exterior surface that extends from the transition point between the tail rotor drive shaft cover and the tail boom fuselage to the vertical nadir of the tail boom modification structure and is shaped to fittingly receive at least a portion of the exiting side of a tail boom fuselage;

wherein the tail boom fuselage, the tail rotor drive shaft cover, and the tail boom profile modification structure collectively form a modified external profile that is asymmetrical about the vertical plane.

22. The helicopter tail boom of claim 21 wherein the first convex exterior surface forms a single continuous curve between the vertical apex and the vertical nadir of the tail boom modification structure.

23. The helicopter tail boom of claim 21 wherein the vertical nadir of the tail boom modification structure is located at a horizontal apex of the exiting side of the tail boom fuselage.

24. The helicopter tail boom of claim 21 wherein the vertical apex of the tail boom modification structure is located at a vertical apex of the tail rotor drive shaft cover.

25. The helicopter tail boom of claim 21 wherein the tail rotor drive shaft cover is integral to the tail boom fuselage.

26. The helicopter tail boom of claim 21 wherein at least a portion of the approaching side of the tail boom fuselage and the approaching side of the tail rotor drive shaft cover are uncovered and form a shoulder.

27. The helicopter tail boom of claim 26 wherein the modified external profile comprises the single continuous curve and the shoulder.

28. The helicopter tail boom of claim 21 wherein the tail boom profile modification structure further comprises a plurality of vortex generators physically coupled to the first convex exterior surface.

29. The helicopter tail boom of claim 28 wherein each of the plurality of vortex generators is canted in a forward direction or canted in an aft direction.

30. The helicopter tail boom of claim 28 wherein the plurality of vortex generators are physically coupled to the first convex exterior surface so as to be located at between 5 percent and 20 percent of a chord length associated with the tail boom fuselage.