ROTATING PROPROTOR ARRANGEMENT FOR A TILTROTOR AIRCRAFT
First Claim
1. A propulsion system for a tiltrotor aircraft, the propulsion system comprising:
- an engine disposed within a fuselage;
a first gearbox coupled to the engine;
a wing member having a first rib, a second rib, a first spar, second spar and an 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;
a drive shaft mechanically coupled to the first gearbox and disposed within the wing member;
a second gear box coupled to the drive shaft and disposed either outboard from the second rib or inboard from the first rib;
a rotatable proprotor mechanically coupled to the second gear box, the rotatable proprotor comprising;
a plurality of rotor blades;
a rotor mast having a rotor mast axis of rotation; and
a proprotor gearbox coupled to the rotor mast, the proprotor 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 located in a central region within the torque box and above an airfoil surface profile of the upper wing skin.
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Accused Products
Abstract
A propulsion system includes an engine disposed within a fuselage, a first gearbox coupled to the engine, a wing member having an upper wing skin and torque box formed by a first rib, a second rib, a first spar and second spar, a drive shaft coupled to the first gearbox and disposed within the wing member, a second gear box coupled to the drive shaft and disposed outboard from the second rib or inboard from the first rib, and a rotatable proprotor coupled to the second gear box. The rotatable proprotor includes a plurality of rotor blades, a rotor mast having a mast axis of rotation, and a proprotor gearbox coupled to the rotor mast. The proprotor gearbox is rotatable about a conversion axis, which intersects with the mast axis of rotation at a point within a central region of the torque box and above the upper wing skin.
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Citations
31 Claims
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1. A propulsion system for a tiltrotor aircraft, the propulsion system comprising:
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an engine disposed within a fuselage; a first gearbox coupled to the engine; a wing member having a first rib, a second rib, a first spar, second spar and an 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; a drive shaft mechanically coupled to the first gearbox and disposed within the wing member; a second gear box coupled to the drive shaft and disposed either outboard from the second rib or inboard from the first rib; a rotatable proprotor mechanically coupled to the second gear box, the rotatable proprotor comprising; a plurality of rotor blades; a rotor mast having a rotor mast axis of rotation; and a proprotor gearbox coupled to the rotor mast, the proprotor 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 located in a central region within the torque box and above an airfoil surface profile of the upper wing skin. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14)
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15. A tiltrotor aircraft, comprising:
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a fuselage; an engine disposed within the fuselage; a first gearbox coupled to the engine; a wing member having a first rib, a second rib, a first spar, second spar and an 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; a drive shaft mechanically coupled to the first gearbox and disposed within the wing member; a second gear box coupled to the drive shaft and disposed either outboard from the second rib or inboard from the first rib; a rotatable proprotor mechanically coupled to the second gear box, the rotatable proprotor comprising; a plurality of rotor blades; a rotor mast having a rotor mast axis of rotation; and a proprotor gearbox coupled to the rotor mast, the proprotor 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 located in a central region within the torque box and above an airfoil surface profile of the upper wing skin. - View Dependent Claims (16, 17, 18, 19, 20, 21, 22, 23, 24, 25, 26, 27, 28, 29, 30, 31)
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Specification