A preferred embodiment of a rotor head for a rotary-wing aircraft having a plurality of rotor blades and a drive shaft includes a gimbal mechanically coupled to the drive shaft so that the gimbal rotates with the drive shaft, and a hub pivotally coupled to the gimbal for receiving the rotor blades.
A preferred embodiment of a rotor head for a rotary-wing aircraft having a plurality of rotor blades and a drive shaft includes a gimbal mechanically coupled to the drive shaft so that the gimbal rotates with the drive shaft, and a hub pivotally coupled to the gimbal for receiving the rotor blades. The rotor head also includes an actuator mechanically coupled to the hub for causing the hub to pivot about the gimbal.
대표청구항▼
What is claimed is: 1. A rotor head for a rotary-wing aircraft having a plurality of rotor blades and a drive shaft, the rotor head comprising: a gimbal mechanically coupled to the drive shaft so that the gimbal rotates with the drive shaft; a hub pivotally coupled to the gimbal for receiving the r
What is claimed is: 1. A rotor head for a rotary-wing aircraft having a plurality of rotor blades and a drive shaft, the rotor head comprising: a gimbal mechanically coupled to the drive shaft so that the gimbal rotates with the drive shaft; a hub pivotally coupled to the gimbal for receiving the rotor blades; an actuator mechanically coupled to the hub for causing the hub to pivot about the gimbal; and a swash plate assembly comprising a rotating swash plate fixedly coupled to the hub, and a non-rotating swash plate rotatably coupled to the rotating swash plate and pivotally coupled to the actuator so that the actuator exerts a force on the swash plate assembly that causes the hub to pivot about the gimbal. 2. The rotor head of claim 1, wherein the swash plate assembly further comprises a plurality of ball bearings and the rotating swash plate rotates in relation to the non-rotating swash plate by way of the bearings. 3. The rotor head of claim 1, wherein the actuator is a screw jack. 4. The rotor head of claim 1, wherein the actuator is a screw jack, the drive shaft extends through a collar, a first end of the actuator is pivotally coupled to the collar, and a second end of the actuator is pivotally coupled the swash plate assembly so that expansion of the actuator causes the hub to pivot about the gimbal in a first direction and retraction of the actuator causes the hub to pivot about the gimbal in a second direction. 5. The rotor head of claim 1, wherein the swash plate assembly is fixedly coupled to a first side of the hub, and the rotor head further comprises a spring that contacts a second side of the hub and urges the hub toward the swash plate assembly. 6. The rotor head of claim 1, wherein the actuator can lock the hub in a particular orientation in relation to the drive shaft. 7. A rotor head for a rotary-wing aircraft having a plurality of rotor blades and a drive shaft, the rotor head comprising: a gimbal secured to the drive shaft; a hub pivotally coupled to gimbal and comprising a plurality of sleeves for receiving the rotor blades; a swash plate assembly having a first portion secured to the hub; and a screw jack mechanically coupled to a second portion of the swash plate assembly so that extension and retraction of the screw jack causes an orientation of the swash plate assembly and the hub to change in relation to the drive shaft. 8. The rotor head of claim 7, wherein the first portion of the swash plate assembly is rotatably coupled to the second portion of the swash plate assembly by a plurality of ball bearings. 9. The rotor head of claim 7, wherein the drive shaft rotates within a collar, a first end of the screw jack is pivotally coupled to the collar, and a second end of the drive shaft is pivotally coupled to the second portion of the swash plate assembly. 10. The rotor head of claim 7, wherein the hub is pivotally coupled to the gimbal by a plurality of ball bearings. 11. The rotor head of claim 10, wherein the hub has a plurality of grooves formed in an inner circumferential surface thereof, the gimbal has a plurality of grooves formed in an outer surface thereof, each of the grooves formed in the inner circumferential surface of the hub faces a corresponding one of the grooves formed in the gimbal to form a race for receiving one of the ball bearings. 12. The rotor head of claim 7, further comprising a second swash plate for varying a pitch of the rotor blades. 13. The rotor head of claim 7, wherein the first portion of the swash plate assembly is secured to a first side of the hub, and the rotor head further comprises a spring that contacts a second side of the hub and urges the hub toward the swash plate assembly. 14. The rotor head of claim 7, wherein the screw jack locks the angular position of the swash plate assembly and the hub in relation to the drive shaft when the screw jack is deactivated. 15. A rotor assembly for a rotary-wing aircraft, comprising: a plurality of rotor blades; a drive shaft; and a constant-velocity joint mechanically coupling the rotor blades to the drive shaft, the constant velocity joint comprising a gimbal coupled to the drive shaft so that the gimbal rotates with the drive shaft; a hub having a plurality of sleeves for receiving the rotor blades, and a plurality of ball bearings for pivotally coupling the hub to the gimbal, wherein the constant velocity joint is restrained from pivoting in relation to the drive shaft by an actuator and a swash plate assembly. 16. A rotor head for a rotary-wing aircraft having a plurality of rotor blades and a drive shaft, the rotor head comprising a gimbal secured to the drive shaft, a hub comprising a plurality of sleeves for receiving the rotor blades, an actuator, a swash plate assembly mechanically coupled to the actuator and fixedly coupled to a first side of the hub so that the actuator exerts a force on the swash plate assembly that causes the hub to pivot about the gimbal, and a spring that contacts a second side of the hub and urges the hub toward the swash plate assembly, wherein the hub is mechanically coupled to the gimbal and the actuator and the hub pivots about the gimbal on a selective basis in response to movement of the actuator. 17. The rotor head of claim 16, wherein the swash plate assembly comprises a rotating swash plate fixedly coupled to the hub, and a non-rotating swash plate rotatably coupled to the rotating swash plate and pivotally coupled to the actuator. 18. The rotor head of claim 16, further comprising a plurality of ball bearings, wherein the hub pivots in relation to the gimbal by way of the ball bearings. 19. The rotor head of claim 18, wherein the hub has a plurality of grooves formed in an inner circumferential surface thereof, the gimbal has a plurality of grooves formed in an outer surface thereof, each of the grooves formed in the inner circumferential surface of the hub faces a corresponding one of the grooves formed in the gimbal to form a race for receiving one of the ball bearings. 20. The rotor head of claim 16, wherein the actuator is a screw jack, the drive shaft extends through a collar, a first end of the actuator is pivotally coupled to the collar, and a second end of the actuator is pivotally coupled the swash plate assembly so that expansion of the actuator causes the hub to pivot about the gimbal in a first direction and retraction of the actuator causes the hub to pivot about the gimbal in a second direction. 21. The rotor head of claim 16, where the actuator can lock the hub in a particular angular position in relation to the drive shaft on a selective basis. 22. A method for controlling an angle between a plane of rotation of rotor blades of a rotary-wing aircraft and a drive shaft that transmits torque to the rotor blades, comprising: providing a constant-velocity joint for mechanically coupling the rotor blades and the drive shaft; and causing the rotor blades to pivot in relation to the drive shaft by way of the universal joint using a jack screw. 23. The method of claim 22, further comprising locking a hub on which the rotor blades are mounted and the plane of rotation of the rotor blades in a particular orientation in relation to the drive shaft using the jack screw. 24. A method for operating a rotary-wing aircraft having a fuselage, a plurality of rotor blades mechanically coupled to a hub of a rotor head, and a drive shaft pivotally coupled to the hub, wherein the rotor blades and the hub are rotated in relation to the fuselage by the drive shaft, the method comprising altering an angle between a plane of rotation of the rotor blades and the drive shaft, altering a pitch of the rotor blades independently of altering the angle between the plane of rotation of the rotor blades and the fuselage, and locking a plane of rotation of the rotor blades in a particular orientation in relation to the drive shaft. 25. The method of claim 24, wherein altering an angle between a plane of rotation of the rotor blades and the drive shaft comprises altering the angle between the plane of rotation of the rotor blades and the drive shaft to achieve a desired airspeed for the rotary-wing aircraft. 26. The method of claim 24, wherein locking the plane of rotation of the rotor blades in a particular orientation in relation to the drive shaft comprises locking the plane of rotation of the rotor blades in a particular orientation using an actuator mechanically coupled to the hub and a non-rotating component of the rotary-wing aircraft. 27. A rotor head for a rotary-wing aircraft having a plurality of rotor blades and a drive shaft, the rotor head comprising: a gimbal mechanically coupled to the drive shaft so that the gimbal rotates with the drive shaft; a hub pivotally coupled to the gimbal for receiving the rotor blades; an actuator mechanically coupled to the hub for causing the hub to pivot about the gimbal; and a plurality of bearings, wherein the hub pivots in relation to the gimbal by way of the bearings. 28. The rotor head of claim 27, wherein the bearings are ball bearings. 29. The rotor head of claim 27, wherein the bearings are elongated bearings. 30. The rotor head of claim 27, wherein the hub has a plurality of grooves formed in an inner circumferential surface thereof, the gimbal has a plurality of grooves formed in an outer surface thereof, each of the grooves formed in the inner circumferential surface of the hub faces a corresponding one of the grooves formed in the gimbal to form a race for receiving one of the ball bearings. 31. A rotor head for a rotary-wing aircraft having a plurality of rotor blades and a drive shaft, the rotor head comprising: a gimbal mechanically coupled to the drive shaft so that the gimbal rotates with the drive shaft; a hub pivotally coupled to the gimbal for receiving the rotor blades; an actuator mechanically coupled to the hub for causing the hub to pivot about the gimbal; a first swash plate assembly mechanically coupled to the actuator and the hub so that the actuator exerts a force on the swash plate assembly that causes the hub to pivot about the gimbal; and a second swash plate assembly for varying a pitch of the rotor blades. 32. A rotor head for a rotary-wing aircraft having a plurality of rotor blades and a drive shaft, the rotor head comprising: a gimbal mechanically coupled to the drive shaft so that the gimbal rotates with the drive shaft; a hub pivotally coupled to the gimbal for receiving the rotor blades, the hub having an inner circumferential surface defining a central opening that receives the gimbal; and an actuator mechanically coupled to the hub for causing the hub to pivot about the gimbal. 33. The rotor head of claim 32, wherein the inner circumferential surface of the hub has a contour that substantially matches a contour of an outer circumferential surface of the hub. 34. A method for operating a rotary-wing aircraft having a fuselage, a rotor head, and plurality of rotor blades mechanically coupled to a hub of the rotor head, wherein the rotor blades and the hub rotate in relation to the fuselage, the method comprising controlling an angle between a plane of rotation of the rotor blades and the fuselage using a first swash plate assembly and an actuator mechanically coupled to the first swash plate assembly and the hub, and controlling the pitch of the rotor blades in relation to the hub using a second swash plate assembly mechanically coupled to the rotor blades.
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이 특허에 인용된 특허 (17)
Ferris Donald L. (Newtown CT), Accommodating axial load in an elastomeric high torque, constant velocity joint.
Head Robert E. (Palos Verdes Estates CA) Yao Samuel S. (Fountain Valley CA), All composite, constant speed universal joint for use in a shaft driven tiltable main rotor for a helicopter.
Bird Colin A. (Sutton Coldfield GB2) Pugh Keith J. (Solihull GB2), Constant velocity ratio universal joint having improved centering of inner and outer joint members.
Byrnes Francis E. (White Plains NY) Ferris Donald L. (Newtown CT) Olsen Eric G. (Woodbury CT), Tailoring tilt in an elastomeric high torque, constant velocity joint.
Stamps, Frank B.; Rauber, Richard E.; Popelka, David A.; Tisdale, Patrick R.; Campbell, Thomas C.; Stanney, Keith; Braswell, Jr., James L.; Wasikowski, Mark; Donovan, Tom; Baskin, Bryan; Corrigan, III, John J.; Smith, Ryan, Step-over blade-pitch control system.
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