Noise-suppressing strut support system for an unmanned aerial vehicle

• US 8,070,092 B2
• Filed: 10/31/2008
• Issued: 12/06/2011
• Est. Priority Date: 10/31/2008
• Status: Expired due to Fees

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Bouldin, Bruce Dan, Burdisso, Ricardo
• Primary Examiner(s): Price, Jr., Richard
• Application Number:
  US12/262,428
• Publication Number:
  US 20100108809A1
• Time in Patent Office: 1,131 Days
• Field of Search: 244/1.N, 244/12.6, 244/34.A, 244/54, 244/53.R, 244/7.B, 244/23.A, 244/23.C
• US Class Current: 244/34.A
• CPC Class Codes: B64D 2033/0206 comprising noise reduction means, e.g. acoustic liners
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 20/10 for stealth, e.g. reduction of cross-section detectable by radars
• CPC Class Codes: B64U 20/20 for noise reduction
• CPC Class Codes: B64U 2101/15 for conventional or electronic warfare
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 30/26 Ducted or shrouded rotors
• CPC Class Codes: B64U 50/14 ducted or shrouded

Abstract

A strut support system for a ducted fan unmanned aerial vehicle to suppress noise comprising: a ducted fan fuselage that defines an opening; an engine that extends longitudinally through the opening in the fuselage; a drive mechanism rotatably mounted to the engine, wherein a fan is mounted on the drive mechanism within a duct defined by the opening; and a plurality of struts extending between the ducted fan fuselage and the engine each comprising a first leg and a second leg joined together by a curvilinear junction, wherein the first leg is attached to the ducted fan fuselage and the second leg is attached to the engine, wherein the plurality of struts are positioned upstream of the fan, wherein the junction between the first leg of each of the plurality of struts and the ducted fan fuselage is outside the highlight of the ducted fan fuselage'"'"'s leading edge.

Claims

1. A strut support system for a ducted fan unmanned aerial vehicle, the strut support system comprising:

a ducted fan fuselage that defines an opening;

a centerbody that extends longitudinally through the opening in the fuselage, wherein the centerbody comprises an engine, a drive mechanism rotatably mounted to the engine, and a fan mounted on the drive mechanism; and

a plurality of struts extending between the ducted fan fuselage and the centerbody, each strut comprising a first leg and a second leg joined together by a curvilinear junction, wherein the first leg is attached to the ducted fan fuselage and the second leg is attached to the engine, wherein the plurality of struts are positioned upstream of the fan, and wherein the junction between the first leg of each strut of the plurality of struts and the ducted fan fuselage is outside a highlight of a leading edge of the ducted fan fuselage.

2. The strut support system of claim 1, wherein a trailing edge along a length of the first leg of each strut of the plurality of struts remains outside a circumference of the highlight of the leading edge of the ducted fan fuselage until a point at which the first leg meets the curvilinear junction.

3. The strut support system of claim 1, wherein the first leg and the second leg are substantially perpendicular to each other.

4. The strut support system of claim 1, wherein a ratio of the length of the first leg to the length of the second leg is approximately 1:

2.

5. The strut support system of claim 1, wherein a profile of each strut of the plurality of struts is aerodynamically shaped.

6. The strut support system of claim 1, wherein a leading edge of each strut is rounded in cross-section relative to a trailing edge of the strut, which forms a sharp edge in cross-section.

7. The strut support system of claim 1, wherein a thickness of a profile of each strut of the plurality of struts is thinnest near the highlight of the leading edge of the ducted fan fuselage and widest near the engine.

8. The strut support system of claim 1, wherein each strut of the plurality of struts has a lean in the range of 0 to 20 degrees.

9. The strut support system of claim 8, wherein each strut of the plurality of struts has substantially no lean.

10. The strut support system of claim 1, wherein the second leg has forward sweep in the range of 0 to 60 degrees.

11. The strut support system of claim 10, wherein a profile of each strut of the plurality of struts is aerodynamically shaped.

12. The strut support system of claim 10, wherein a leading edge of each strut is rounded in cross-section relative to a trailing edge of the strut, which forms a sharp edge in cross-section.

13. The strut support system of claim 10, wherein a width of the profile of each strut of the plurality of struts is thinnest near the highlight of the leading edge of the ducted fan fuselage and widest near the engine.

14. The strut support system of claim 10, wherein each strut of the plurality of struts has a lean in the range of 0 to 20 degrees.

15. The strut support system of claim 1, wherein the second leg has aft sweep in the range of 0 to 60 degrees.

16. The strut support system of claim 15, wherein a profile of each strut of the plurality of struts is aerodynamically shaped.

17. The strut support system of claim 15, wherein a leading edge of each strut is rounded in cross-section relative to the trailing edge of the strut, which forms a sharp edge in cross-section.

18. The strut support system of claim 1, wherein a width of a profile of each strut of the plurality of struts is thinnest near the highlight of the leading edge of the ducted fan fuselage and widest near the engine.

19. The strut support system of claim 18, wherein each strut of the plurality of struts has a lean in the range of 0 to 20 degrees.

20. The strut support system of claim 19, wherein each strut of the plurality of struts has substantially no lean.