NOISE-SUPPRESSING STRUT SUPPORT SYSTEM FOR AN UNMANNED AERIAL VEHICLE

• US 20100108809A1
• Filed: 10/31/2008
• Published: 05/06/2010
• Est. Priority Date: 10/31/2008
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Burdisso, Ricardo, Bouldin, Bruce Dan
• Granted Patent: US 8,070,092 B2
• Time in Patent Office: Days
• US Class Current: 244/119
• CPC Class Codes: B64C 27/20 Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• 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 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 to suppress noise comprising:

a ducted fan fuselage that defines an opening;

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

a plurality of struts extending between the ducted fan fuselage and the centerbody, 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, and 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.

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

3. The strut support system of claim 2, wherein the first leg and the second leg are substantially perpendicular to each other.

4. The strut support system of claim 3, wherein the 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 4, wherein the profile of each of the plurality of struts is aerodynamically shaped.

6. The strut support system of claim 5, wherein a leading edge of the strut is rounded in cross-section relative to the trailing edge of the strut, which forms a sharp edge in cross-section.

7. The strut support system of claim 6, wherein the thickness of the profile of each of the plurality of struts is thinnest near the highlight of the ducted fan fuselage and widest near the engine.

8. The strut support system of claim 7, wherein each 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 of the plurality of struts has substantially no lean.

10. The strut support system of claim 2, wherein the second leg has forward sweep in the range of 0 to 60 degrees.

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

12. The strut support system of claim 11, wherein a leading edge of the strut is rounded in cross-section relative to the trailing edge of the strut, which forms a sharp edge in cross-section.

13. The strut support system of claim 12, wherein the width of the profile of each of the plurality of struts is thinnest near the highlight of the ducted fan fuselage and widest near the engine.

14. The strut support system of claim 13, wherein each of the plurality of struts has a lean in the range of 0 to 20 degrees.

15. The strut support system of claim 2, wherein the second leg has aft sweep in the range of 0 to 60 degrees.

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

17. The strut support system of claim 16, wherein a leading edge of the 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 17, wherein the width of the profile of each of the plurality of struts is thinnest near the highlight of the ducted fan fuselage and widest near the engine.

19. The strut support system of claim 18, wherein each 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 of the plurality of struts has substantially no lean.