Rotor hub fairing system for a counter-rotating, coaxial rotor system
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-027/50
B64C-027/32
출원번호
UP-0436362
(2006-05-18)
등록번호
US-7530787
(2009-07-01)
발명자
/ 주소
Bertolotti, Fabio P.
Scott, Mark W.
Wake, Brian E.
Egolf, T. Alan
McCormick, Duane C.
Usta, Ebru
Ochs, Stuart S.
출원인 / 주소
Sikorsky Aircraft Corporation
대리인 / 주소
Carlson, Gaskey & Olds PC
인용정보
피인용 횟수 :
6인용 특허 :
19
초록▼
A rotor hub fairing system includes an upper hub fairing, a lower hub fairing and a shaft fairing therebetween. The rotor hub fairing system reduces the total drag on a dual, counter-rotating, coaxial rotor system. Other aerodynamic structures may be mounted to the shaft fairing, hub fairings and ai
A rotor hub fairing system includes an upper hub fairing, a lower hub fairing and a shaft fairing therebetween. The rotor hub fairing system reduces the total drag on a dual, counter-rotating, coaxial rotor system. Other aerodynamic structures may be mounted to the shaft fairing, hub fairings and airframe to facilitate flow around the upper and lower hub fairings to reduce flow separation and drag.
대표청구항▼
What is claimed is: 1. A rotor hub fairing system for a counter rotating coaxial rotor system comprising: an upper hub fairing defined about an axis; a lower hub fairing defined about said axis; and an airfoil-shaped shaft fairing between said upper hub fairing and said lower hub fairing, said airf
What is claimed is: 1. A rotor hub fairing system for a counter rotating coaxial rotor system comprising: an upper hub fairing defined about an axis; a lower hub fairing defined about said axis; and an airfoil-shaped shaft fairing between said upper hub fairing and said lower hub fairing, said airfoil-shaped shaft fairing contoured to reduce a total drag of the rotor hub fairing system, said shaft fairing defines a thickness to hub fairing diameter (t/D) greater than 0.35. 2. The rotor hub fairing system as recited in claim 1, wherein said shaft fairing is generally of an hour glass shape in cross-section taken within a contoured midsection along said axis and transverse to said airfoil. 3. The rotor hub fairing system as recited in claim 2, wherein said t/D is taken at a minimum of said contoured midsection. 4. The rotor hub fairing system as recited in claim 2, wherein said shaft fairing includes a NACA 0028 airfoil along said midsection and an NACA 0042 airfoil adjacent said upper hub fairing and said lower hub fairing. 5. The rotor hub fairing system as recited in claim 1, wherein said shaft fairing defines a trailing edge which extends beyond a periphery of said upper hub fairing and said lower hub fairing. 6. The rotor hub fairing system as recited in claim 1, wherein said shaft fairing defines a chord length divided by said rotor hub diameter (c/D) between 0.8 and 1.5. 7. The rotor hub fairing system as recited in claim 1, further comprising at least one airfoil member which extends generally transverse to said shaft fairing. 8. The rotor hub fairing system as recited in claim 7, wherein said at least one airfoil member includes an upper turning vane and a lower turning vane on each side of said shaft fairing. 9. A rotor hub fairing system for a counter rotating coaxial rotor system comprising: an upper hub fairing defined about an axis; a lower hub fairing defined about said axis; an airfoil-shaped shaft fairing between said upper hub fairing and said lower hub fairing, said airfoil-shaped shaft fairing contoured to reduce a total drag of the rotor hub fairing system; and a vortex generator mounted on at least one of said upper hub fairing and said lower hub fairing. 10. A rotor hub fairing system for a counter rotating coaxial rotor system comprising: an upper hub fairing defined about an axis; a lower hub fairing defined about said axis; an airfoil-shaped shaft fairing between said upper hub fairing and said lower hub fairing, said airfoil-shaped shaft fairing contoured to reduce a total drag of the rotor hub fairing system; and a directed synthetic jet mounted on at least one of said upper hub fairing and said lower hub fairing. 11. A rotor hub fairing system for a counter rotating coaxial rotor system comprising: an upper hub fairing defined about an axis; a lower hub fairing defined about said axis; an airfoil-shaped shaft fairing between said upper hub fairing and said lower hub fairing, said airfoil-shaped shaft fairing contoured to reduce a total drag of the rotor hub fairing system; and a centrifugal pumping system mounted on at least one of said upper hub fairing and said lower hub fairing. 12. A rotor hub fairing system for a counter rotating coaxial rotor system comprising: an upper hub fairing defined about an axis; a lower hub fairing defined about said axis; an airfoil-shaped shaft fairing between said upper hub fairing and said lower hub fairing, said airfoil-shaped shaft fairing contoured to reduce a total drag of the rotor hub fairing system; and a drive system which operates to independently move said shaft fairing in response to a control system. 13. A rotor hub fairing system for a counter rotating coaxial rotor system comprising: an upper hub fairing defined about an axis; a lower hub fairing defined about said axis; and an airfoil-shaped shaft fairing between said upper hub fairing and said lower hub fairing, said shaft fairing defining a thickness to hub fairing diameter (t/D) greater than 0.35. 14. The rotor hub fairing system as recited in claim 12, wherein said shaft fairing defines a chord length divided by said rotor hub diameter (c/D), greater than 0.8. 15. A coaxial rotor system aircraft comprising: an airframe having a rotor system pylon; an upper hub fairing defined about an axis; a lower hub fairing defined about said axis, said lower hub fairing adjacent said pylon; and an airfoil-shaped shaft fairing between said upper hub fairing and said lower hub fairing, said airfoil-shaped shaft fairing contoured to reduce a total drag of the rotor hub fairing system. 16. The aircraft as recited in claim 15, wherein said airfoil-shaped shaft fairing defines a thickness to hub fairing diameter (t/D) greater than 0.35. 17. The aircraft as recited in claim 15, wherein said airfoil-shaped shaft fairing defines a chord length divided by said rotor hub diameter (c/D) greater than 0.8. 18. The aircraft as recited in claim 15, further comprising at least one airfoil member which extends from said pylon to reduce a flow separation penalty on at least one of said upper and lower rotor hub fairings. 19. The aircraft as recited in claim 15, further comprising a directed synthetic jet mounted to said pylon to reduce a flow separation penalty on at least one of said upper and lower rotor hub fairings. 20. The aircraft as recited in claim 15, further comprising an airframe-located intake to reduce a directed synthetic jet mounted to said pylon to reduce a flow separation penalty on at least one of said upper and lower rotor hub fairings. 21. The aircraft as recited in claim 15, further comprising an airframe-located exhaust to reduce a directed synthetic jet mounted to said pylon to reduce a flow separation penalty on at least one of said upper and lower rotor hub fairings. 22. The aircraft as recited in claim 15, further comprising a centrifugal pumping system mounted to said pylon to reduce a flow separation penalty on at least one of said upper and lower rotor hub fairings. 23. The aircraft as recited in claim 15, wherein said shaft fairing includes a pitching axis which extends through said upper hub fairing and said lower hub fairing, said pitching axis including an axis of rotation of the coaxial rotor system, said pitching axis is generally parallel to said axis.
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이 특허에 인용된 특허 (19)
Miller Gordon G. (Shelton CT), Aerodynamic flexible fairing.
Marze Henri-James R. (Rognac FRX) Routhieau Vincent Jean-Luc (Aix-En-Provence FRX) Arnaud Gilles L. (Marseille FRX) Arnaud Remy E. (Vitrolles FRX), Counter-torque device with rotor and flow-straightening stator, both of which are ducted, and phase modulation of the bl.
Mouille RenL. (Aix-en-Province FRX) Rollet Philippe A. (Velaux FRX), Directional and stabilizing device having a faired and slanted antitorque rotor and a disymmetric “V”empennage, and a.
Krauss Timothy A. (Harwinton CT) Hunter David H. (Cheshire CT) Beatty Robert D. (Trumbull CT), Rotor blade subassembly for a rotor assembly having ducted, coaxial counter-rotating rotors.
Min, ByungYoung; Botros, Barbara Brenda; Florea, Razvan Virgil; Bowles, Patrick; Matalanis, Claude G.; Wake, Brian E., Active airflow system and method of reducing drag for aircraft.
Bowles, Patrick; Min, ByungYoung; Botros, Barbara Brenda; Wake, Brian E.; Matalanis, Claude G., Plate member for reducing drag on a fairing of an aircraft.
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