IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0966678
(2013-08-14)
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등록번호 |
US-9174731
(2015-11-03)
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발명자
/ 주소 |
- Ross, Brent C.
- Bockmiller, David R.
- McCullough, John R.
- Carlson, David G.
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출원인 / 주소 |
- Bell Helicopter Textron Inc.
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대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
14 인용 특허 :
10 |
초록
▼
A tiltrotor aircraft includes a fuselage; a wing member having a first rib, a second rib, a first spar, second spar; and an upper wing skin; an engine disposed at a fixed location relative to the wing member; and a proprotor having a spindle gearbox, rotor mast, and a plurality of rotor blades driva
A tiltrotor aircraft includes a fuselage; a wing member having a first rib, a second rib, a first spar, second spar; and an upper wing skin; an engine disposed at a fixed location relative to the wing member; and a proprotor having a spindle gearbox, rotor mast, and a plurality of rotor blades drivable in rotation about the rotor mast, the spindle gearbox being rotatable about a conversion axis. The spindle gearbox is located above the upper wing skin of the wing member.
대표청구항
▼
1. A propulsion system for a tiltrotor aircraft, the propulsion system comprising: an engine disposed at a fixed location relative to a wing member, the wing member having a first rib, a second rib, a first spar, second spar; and an upper wing skin;a proprotor mechanically coupled to the engine, the
1. A propulsion system for a tiltrotor aircraft, the propulsion system comprising: an engine disposed at a fixed location relative to a wing member, the wing member having a first rib, a second rib, a first spar, second spar; and an upper wing skin;a proprotor mechanically coupled to the engine, the proprotor comprising: a plurality of rotor blades;a rotor mast having a rotor mast axis of rotation;a spindle gearbox coupled to the rotor mast, the spindle gearbox being rotatable about a conversion axis, the conversion axis and the rotor mast axis of rotation intersecting at an intersection point, the intersection point being centrally located in a central portion, the central portion being a central region aft of the first spar, forward of the second spar, outboard of the first rib, and inboard of the second rib, and above an airfoil surface profile of the upper wing skin;wherein the first rib, the second rib, the first spar, and the second spar are coupled together to form a torque box. 2. The propulsion system according to claim 1, wherein the conversion axis is parallel to a lengthwise axis of the wing member. 3. The propulsion system according to claim 1, the propulsion system further comprising: a fixed gearbox in a drive path between the engine and the proprotor. 4. The propulsion system according to claim 3, further comprising: an interconnect drive shaft coupled to the fixed gearbox, the interconnect drive shaft be rotatable about an interconnect axis;wherein the conversion axis of the spindle gearbox is parallel to the interconnect axis, the conversion axis also being located forward and upward from the interconnect axis. 5. The propulsion system according to claim 3, the fixed gearbox further comprising: a plurality of gears in a gear train, the plurality of gears including a first gear coupled to an interconnect drive shaft and a second gear coupled to a quill shaft. 6. The propulsion system according to claim 5, wherein the rotational axis of the plurality of gears are parallel to the conversion axis of the spindle gearbox. 7. The propulsion system according to claim 1, the propulsion system further comprising: an outboard housing;an inboard housing;wherein an outboard portion of the spindle gearbox is rotatably coupled to the outboard housing, and the inboard portion of the spindle gearbox is rotatably coupled to the inboard housing. 8. The propulsion system according to claim 7, the propulsion system further comprising: an inboard bearing assembly configured to provide rotational capability between the inboard housing and the inboard portion of the spindle gearbox;an outboard bearing assembly configured to provide rotational capability between the outboard housing and the outboard portion of the spindle gearbox. 9. The propulsion system according to claim 7, the propulsion system further comprising: an inboard pillow block configured to structurally locate the inboard housing above the upper wing skin of the wing member; andan outboard pillow block configured to structurally locate the outboard housing above the upper wing skin of the wing member. 10. The propulsion system according to claim 9, wherein the inboard pillow block is coupled to the first rib. 11. The propulsion system according to claim 9, wherein the outboard pillow block is coupled to the second rib. 12. The propulsion system according to claim 1, the propulsion system further comprising: a housing configured to secure the fixed gearbox to an outboard frame that rotatably couples the spindle gearbox to a structure of the wing member. 13. The propulsion system according to claim 12, wherein the housing is a conical shaped. 14. The propulsion system according to claim 12, the housing comprising: an inboard flange configured for coupling the housing to the outboard frame; andan outboard flange configured for coupling the housing to the fixed gearbox. 15. The propulsion system according to claim 12, the propulsion system further comprising: a quill shaft configured for transferring torque to the spindle gearbox, the quill shaft being centrally located within the housing. 16. A tiltrotor aircraft, comprising: a fuselage;a wing member having a first rib, a second rib, a first spar, second spar; and an upper wing skin;an engine disposed at a fixed location relative to the wing member; anda proprotor mechanically coupled to the engine, the proprotor comprising: a plurality of rotor blades;a rotor mast having a rotor mast axis of rotation;a spindle gearbox coupled to the rotor mast, the spindle gearbox being rotatable about a conversion axis, the conversion axis and the rotor mast axis of rotation intersecting at an intersection point, the intersection point being centrally located in a central portion, the central portion being a central region aft of the first spar, forward of the second spar, outboard of the first rib, and inboard of the second rib, and above an airfoil surface profile of the upper wing skin;wherein the first rib, the second rib, the first spar, and the second spar are coupled together to form a torque box.
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