A drive system for rotating one or more wheels of an aircraft landing gear for ground taxiing and/or spin-up prior to landing has a motor operable to rotate a first drive pinion via a first drive path, and a driven gear adapted to be fixed to the wheel. The drive system has a first configuration in
A drive system for rotating one or more wheels of an aircraft landing gear for ground taxiing and/or spin-up prior to landing has a motor operable to rotate a first drive pinion via a first drive path, and a driven gear adapted to be fixed to the wheel. The drive system has a first configuration in which the first drive pinion meshes with the driven gear to permit the motor to drive the driven gear via the first drive path. One of the first drive pinion and the driven gear comprises a first sprocket and the other comprises a series of rollers arranged in two or more rows, each row of rollers being arranged to form a ring. The rollers are rotatable about pins fixed to an annular support member, and adjacent rows may be out of phase by a fraction of roller pitch.
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1. A drive system for rotating a wheel of an aircraft landing gear, the drive system including a motor operable to rotate a first drive pinion via a first drive path, and a driven gear adapted to be fixed to the wheel, wherein the drive system has a first configuration in which the first drive pinio
1. A drive system for rotating a wheel of an aircraft landing gear, the drive system including a motor operable to rotate a first drive pinion via a first drive path, and a driven gear adapted to be fixed to the wheel, wherein the drive system has a first configuration in which the first drive pinion meshes with the driven gear to permit the motor to drive the driven gear via the first drive path, and wherein one of the first drive pinion and the driven gear comprises a first sprocket and the other of the first drive pinion and the driven gear comprises a series of rollers arranged in two or more rows, each row of rollers being arranged to form a ring, each roller being rotatable about a roller axis at a fixed distance from an axis of rotation of the first drive pinion or driven gear, respectively, wherein each of the series of rollers is rotatable about a pin, the pins each being fixed to an annular support member, and wherein the drive system is switchable between the first configuration and a second configuration in which the first drive pinion does not mesh with the driven gear. 2. The drive system according to claim 1, wherein two of the rows of rollers are arranged one on each side of the annular support member. 3. The drive system according to claim 2, further comprising two annular rings, wherein the rows of rollers extend between the annular support member and a respective one of the annular rings. 4. The drive system according to claim 1, wherein the first sprocket is provided with two or more rows of teeth, and wherein in the first configuration each row of teeth meshes with a respective row of rollers. 5. The drive system according to claim 1, wherein the first drive pinion comprises the first sprocket and the driven gear comprises the series of rollers. 6. The drive system according to claim 1, wherein adjacent rows of rollers are out of phase by a fraction of the roller pitch. 7. The drive system according to claim 1, including a second drive pinion, the motor being operable to rotate the second drive pinion via a second drive path, wherein the drive system is switchable between the first configuration and a third configuration in which the second drive pinion meshes with the driven gear to permit the motor to drive the driven gear via the second drive path, wherein if the first drive pinon comprises the first sprocket then the second drive pinion comprises a second sprocket and the driven gear comprises the series of rollers, or if the first drive pinon comprises the series of rollers then the second drive pinon comprises another series of rollers and the driven gear comprises the first sprocket, and wherein the first drive path has a higher gearing ratio than the second drive path. 8. The drive system according to claim 7, wherein the first drive pinon comprises the first drive sprocket, the second drive pinion comprises the second sprocket and the driven gear comprises the series of rollers. 9. The drive system according to claim 7, wherein the drive system is switchable between the first and third configurations and second configuration in which neither the first nor second drive pinions mesh with the driven gear. 10. The drive system according to claim 7, wherein the first and second drive pinions are movable relative to the driven gear such that the first and second pinions cannot both mesh with the driven gear at the same time. 11. The drive system according to claim 7, including an actuator arranged to move the drive system between the first and third configurations. 12. An aircraft landing gear having a wheel and the drive system according to claim 1, wherein the driven gear of the drive system is fixed to the wheel. 13. The An aircraft landing gear according to claim 12, wherein the wheel is driveable for taxiing the aircraft on the ground and/or spinning-up the wheel prior to landing. 14. The aircraft landing gear as claimed in claim 13, wherein the drive system is supported by a bracket which is rigidly connected to an axle, main fitting or slider part of the landing gear. 15. The aircraft landing gear as claimed in claim 12, wherein the drive system is supported by a bracket which is rigidly connected to an axle, main fitting or slider part of the landing gear. 16. A drive system for rotating a wheel of an aircraft landing gear, the drive system including a motor operable to rotate a first drive pinion via a first drive path, and a driven gear adapted to be fixed to the wheel, wherein the drive system has a first configuration in which the first drive pinion meshes with the driven gear to permit the motor to drive the driven gear via the first drive path, and wherein one of the first drive pinion and the driven gear comprises a first sprocket and the other of the first drive pinion and the driven gear comprises a series of rollers arranged in two or more rows, each row of rollers being arranged to form a ring, each roller being rotatable about a roller axis at a fixed distance from an axis of rotation of the first drive pinion or driven gear, respectively, wherein each of the series of rollers is rotatable about a pin, the pins each being fixed to an annular support member, and wherein two of the rows of rollers are arranged one on each side of the annular support member. 17. A drive system for rotating a wheel of an aircraft landing gear, the drive system including a motor operable to rotate a first drive pinion via a first drive path, and a driven gear adapted to be fixed to the wheel, wherein the drive system has a first configuration in which the first drive pinion meshes with the driven gear to permit the motor to drive the driven gear via the first drive path, and wherein one of the first drive pinion and the driven gear comprises a first sprocket and the other of the first drive pinion and the driven gear comprises a series of rollers arranged in two or more rows, each row of rollers being arranged to form a ring, each roller being rotatable about a roller axis at a fixed distance from an axis of rotation of the first drive pinion or driven gear, respectively, wherein each of the series of rollers is rotatable about a pin, the pins each being fixed to an annular support member, and wherein adjacent rows of rollers are out of phase by a fraction of the roller pitch.
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이 특허에 인용된 특허 (5)
Christensen, Donald Jeffrey; Mitchell, Robert, Aircraft landing gear wheel with integral gear drive.
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