IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
UP-0543222
(2003-01-23)
|
등록번호 |
US-7594625
(2009-10-12)
|
국제출원번호 |
PCT/US03/002049
(2003-01-23)
|
§371/§102 date |
20060530
(20060530)
|
국제공개번호 |
WO04/067380
(2004-08-12)
|
발명자
/ 주소 |
- Robertson, Daniel B.
- Smith, Dudley E.
- Hollimon, Charles L.
- Narramore, Jimmy C.
- Mullins, Robert B.
|
출원인 / 주소 |
- Bell Helicopter Textron Inc.
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
5 인용 특허 :
9 |
초록
▼
A proprotor blade (27a, 27b, 127a, 127b) having a fixed, spanwise, leading edge slot (215) located in at least the inboard portion of the proprotor is disclosed. The slot (215) is formed by a selectively shaped slat (217) disposed in a selectively shaped recessed area (219) located at the leading ed
A proprotor blade (27a, 27b, 127a, 127b) having a fixed, spanwise, leading edge slot (215) located in at least the inboard portion of the proprotor is disclosed. The slot (215) is formed by a selectively shaped slat (217) disposed in a selectively shaped recessed area (219) located at the leading edge (202) of the main portion of the proprotor blade. The slot (215) is selectively shaped so the a portion of the airflow over the lower airfoil surface of the proprotor blade is diverted between the main portion of the proprotor blade and the slat (217) and exits at the upper airfoil surface of the proprotor blade. The present invention may be used on both military-type tiltrotor aircraft (11) and civilian-type tiltrotor aircraft (111) with only minor variations to accommodate the different shapes of the proprotor blades.
대표청구항
▼
The invention claimed is: 1. A proprotor blade comprising: a proprotor airfoil for a tiltrotor aircraft having an inboard end and an opposing outboard end, an upper airfoil surface and an opposing lower airfoil surface, and a leading edge and an opposing trailing edge, wherein the inboard end is ad
The invention claimed is: 1. A proprotor blade comprising: a proprotor airfoil for a tiltrotor aircraft having an inboard end and an opposing outboard end, an upper airfoil surface and an opposing lower airfoil surface, and a leading edge and an opposing trailing edge, wherein the inboard end is adapted for coupling to a rotor hub; a recessed portion disposed proximate the inboard end of the airfoil in the leading edge; a fixed slat having an inboard end and an opposing outboard end, the slat being disposed over the recessed portion forming a leading edge slot passing from the lower airfoil surface to the upper airfoil surface; a structural member disposed at the inboard end of the airfoil; and a tension/shear joint for coupling the inboard end of the slat to the structural member; whereby centrifugal force loads are transmitted from the slat to the airfoil only through the structural member. 2. The proprotor blade according to claim 1, further comprising: a fairing for coupling the outboard end of the slat to the airfoil. 3. The proprotor blade according to claim 1, wherein the tension/shear joint is a ball joint comprising: a rigid link adapted at one end for coupling to the structural member and having a barrel retainer at the other end, the barrel retainer being adapted for pivotal coupling to inboard end of the slat. 4. The proprotor blade according to claim 2, further comprising: a friction reducing shim disposed between the fairing and the slat; whereby the slat carries shear loads from lift and drag, but does not transmit centrifugal force loads through the fairing. 5. The proprotor blade according to claim 1, further comprising: at least one brace member disposed between the slat and the recessed portion for supporting the slat. 6. The proprotor blade according to claim 1, wherein the leading edge slot extends only partially along the spanwise length of the airfoil. 7. The proprotor blade according to claim 1, wherein the leading edge slot extends substantially along the entire spanwise length of the airfoil. 8. The proprotor blade according to claim 1, wherein the leading edge slot forms a smooth channel that curves upward and rearward, the channel being configured to prevent airflow from separating from the upper and lower airfoil surfaces. 9. The proprotor blade according to claim 1, wherein the leading edge slot forms a smooth channel that curves upward and rearward, the channel being configured to prevent airflow from separating from the airfoil. 10. The proprotor blade according to claim 1, wherein the cross-sectional profile of the leading edge slot varies along the spanwise length of the airfoil. 11. A tiltrotor aircraft comprising: a fuselage; a wing member coupled to the fuselage; a tiltrotor nacelle assembly pivotally coupled to the wing member; a drive means carried by the tiltrotor nacelle assembly, the drive means having an engine, a transmission, and a rotor hub; and at least one proprotor coupled to the rotor hub, the proprotor including an airfoil having an inboard end and an opposing outboard end, an upper airfoil surface and an opposing lower airfoil surface, and a leading edge and an opposing trailing edge, wherein the inboard end is adapted for coupling to a rotor hub, a recessed portion disposed proximate the inboard end of the airfoil in the leading edge, a fixed slat having an inboard end and an opposing outboard end, the slat being disposed over the recessed portion forming a leading edge slot passing from the lower airfoil surface to the upper airfoil surface, a structural member disposed at the inboard end of the airfoil; and a tension/shear joint for coupling the inboard end of the slat to the structural member; whereby centrifugal force loads are transmitted from the slat to the airfoil only through the structural member. 12. The tiltrotor aircraft according to claim 11, further comprising: a fairing for coupling the outboard end of the slat to the airfoil. 13. The tiltrotor aircraft according to claim 11, wherein the tension/shear joint is a ball joint comprising: a rigid link adapted at one end for coupling to the structural member and having a barrel retainer at the other end, the barrel retainer being adapted for pivotal coupling to inboard end of the slat. 14. The tiltrotor aircraft according to claim 12, further comprising: a friction reducing shim disposed between the fairing and the slat; whereby the slat carries shear loads from lift and drag, but does not transmit centrifugal force loads through the fairing. 15. The tiltrotor aircraft according to claim 11, further comprising: at least one brace member disposed between the slat and the recessed portion for supporting the slat. 16. The tiltrotor aircraft according to claim 11, wherein the leading edge slot extends only partially along the spanwise length of the airfoil. 17. The tiltrotor aircraft according to claim 11, wherein the leading edge slot extends substantially along the entire spanwise length of the airfoil. 18. The tiltrotor aircraft according to claim 11, wherein the leading edge slot forms a smooth channel that curves upward and rearward, the channel being configured to prevent airflow from separating from the upper airfoil surface. 19. The tiltrotor aircraft according to claim 11, wherein the leading edge slot forms a smooth channel that curves upward and rearward, the channel being configured to prevent airflow from becoming turbulent. 20. The tiltrotor aircraft according to claim 11, wherein the cross-sectional profile of the leading edge slot varies along the spanwise length of the airfoil. 21. A method of increasing helicopter mode lift without increasing airplane mode drag in a tiltrotor aircraft, the method comprising the steps of: providing a tiltrotor aircraft having a fuselage, a wing member coupled to the fuselage, a tiltrotor assembly pivotally coupled to the wing member, and a drive means carried by the tiltrotor assembly, the drive means having an engine, a transmission, and a rotor hub; coupling at least one proprotor to the rotor hub, the proprotor including an airfoil having an inboard end and an opposing outboard end, an upper airfoil surface and an opposing lower airfoil surface, and a leading edge and an opposing trailing edge; forming a leading edge slot in the proprotor passing from the lower airfoil surface to the upper airfoil surface by creating a recessed portion rroximate the inboard end of the airfoil in the leading edge and disposing a fixed slat having an inboard end and an opposing outboard end over the recessed portion; providing a structural member disposed at the inboard end of the airfoil; and providing a tension/shear joint for coupling the inboard end of the slat to the structural member, whereby centrifugal force loads are transmitted from the slat to the airfoil only through the structural member. 22. The method according to claim 21, wherein the step of disposing the slat over the recessed portion comprises the steps of: providing a fairing; coupling the fairing to the proprotor; and coupling the outboard end of the slat to the fairing.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.