A drive unit (16) for an aircraft running gear (2) having at least a first wheel (4) and a second wheel (6) on a common wheel axis (A), wherein the drive unit (16) is drivingly coupleable to at least one of the first and second wheels (4, 6), is characterized in that the drive unit (16) comprises at
A drive unit (16) for an aircraft running gear (2) having at least a first wheel (4) and a second wheel (6) on a common wheel axis (A), wherein the drive unit (16) is drivingly coupleable to at least one of the first and second wheels (4, 6), is characterized in that the drive unit (16) comprises at least one power output assembly (122, 124) for driving at least one of the first and second wheels (4, 6), with each of the at least one power output assembly (122, 124) comprising a power transmission chain (136) selectively engageable with a sprocket element (108, 110) coupled to one of the first and second wheels (4, 6).
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1. A drive unit (16) for an aircraft running gear (2) having at least a first wheel (4) and a second wheel (6) on a common wheel axis (A), wherein the drive unit (16) is drivingly coupleable to at least one of the first and second wheels (4, 6), characterized in that the drive unit (16) comprises:at
1. A drive unit (16) for an aircraft running gear (2) having at least a first wheel (4) and a second wheel (6) on a common wheel axis (A), wherein the drive unit (16) is drivingly coupleable to at least one of the first and second wheels (4, 6), characterized in that the drive unit (16) comprises:at least one power output assembly (122, 124) for driving at least one of the first and second wheels (4, 6), with each of the at least one power output assembly (122, 124) comprising a power transmission chain (136) selectively engageable with a sprocket element (108, 110) coupled to one of the first and second wheels (4, 6), with the power transmission chain (136) being moveable in operation of the drive unit between a position of engagement with the sprocket element and a position of disengagement with the sprocket element. 2. The drive unit (16) according to claim 1, wherein the drive unit (16) is drivingly coupleable to both the first and second wheels (4, 6), wherein the drive unit (16) comprises a first and a second power output assembly (122, 124) for driving a respective one of the first and second wheels (4, 6), with each power output assembly (122, 124) comprising a power transmission chain (136) selectively engageable with a respective sprocket element (108, 110) coupled to the respective wheel (4, 6). 3. The drive unit (16) according to claim 2, comprising: a first motor (18) drivingly coupleable to the first wheel (4) via a first gear structure and the first power output assembly (122), and a second motor (20) drivingly coupleable to the second wheel (6) via a second gear structure and the second power output assembly (124), wherein the first and second motors (18, 20) are arranged in tandem along the direction of longitudinal extension (C) of the drive unit (16). 4. The drive unit (16) according to claim 3, wherein: the first motor (18) in operation drives a first bevel gear (38), with the first bevel gear (38) being drivingly coupleable to the first wheel (4) via the first gear structure and the first power output assembly (122), and the second motor (20) in operation drives a second bevel gear (40), with the second bevel gear (40) being drivingly coupleable to the second wheel (6) via the second gear structure and the second power output assembly (124). 5. The drive unit (16) according to claim 3, wherein the first and second motors (18, 20) are arranged in a coaxial manner. 6. The drive unit (16) according to claim 3, wherein the first motor (18) has a first motor shaft (28) and the second motor (20) has a second motor shaft (30), with the first motor shaft (28) being hollow and being arranged around the second motor shaft (30). 7. The drive unit (16) according to claim 3, wherein the first and second motors (18, 20) are electric motors or hydraulic motors. 8. The drive unit (16) according to claim 3, wherein the first gear structure comprises a first gear element (42) having a third bevel gear (54) and a first gear element shaft (66) and the second gear structure comprises a second gear element (44) having a fourth bevel gear (56) and a second gear element shaft (68), with one of the first and second gear element shafts (66, 68) having a hollow portion and the other one of the first and second gear element shafts (66, 68) being supported in the hollow portion. 9. The drive unit (16) according to claim 3, wherein the first and second gear structures comprise a planetary gear (46, 48), respectively. 10. The drive unit (16) according to claim 2, comprising: a motor (120) and a differential gear (150), with the motor (120) being drivingly coupleable to the first and second wheels (4, 6) via the differential gear (150) and the first and second power output assemblies (122, 124). 11. The drive unit (16) according to claim 10, wherein the motor (120) comprises a bevel gear (140) for engaging with the differential gear (150). 12. The drive unit (16) according to claim 10, wherein the differential gear (150) is coupleable to the first and second wheels (4, 6) by first and second gear structures and the first and second power output assemblies (122, 124), respectively. 13. The drive unit (16) according to claim 10, wherein the differential gear (150) is a bevel differential or planetary differential or ball differential or face gear differential. 14. The drive unit (16) according to claim 10, wherein the motor (120) is an electric motor or a hydraulic motor. 15. The drive unit (16) according to claim 1, wherein each power output assembly (122, 124) comprises a first sprocket wheel (132) and a second sprocket wheel (134), with the power transmission chain (136) running endlessly over the first sprocket wheel (132) and the second sprocket wheel (134). 16. The drive unit (16) according to claim 15, wherein the first sprocket wheel (132) is drivingly coupled to a power train of the drive unit (16). 17. The drive unit (16) according to claim 16, wherein the second sprocket wheel (134) is an idler sprocket wheel. 18. The drive unit (16) according to claim 16, wherein both the first sprocket wheel (132) and the second sprocket wheel (134) are drivingly coupled to the power train of the drive unit (16). 19. The drive unit (16) according to claim 15, wherein the power transmission chain (136) is in engagement with the first and second sprocket wheels (132, 134) on an inner side of the power transmission chain (136). 20. The drive unit (16) according to claim 15, wherein the first sprocket wheel (132) of the first power output assembly (122) and the first sprocket wheel of the second power output assembly (124) are aligned on a common output stage axis, which is substantially orthogonal to a direction of longitudinal extension (C) of the drive unit (16). 21. The drive unit (16) according to claim 1, wherein the power transmission chain (136) is selectively engageable with the sprocket element (108) on an outer side of the power transmission chain (136). 22. The drive unit (16) according to claim 1, wherein the endless power transmission chain (136) defines a loop and is selectively engageable with the sprocket element (108) in a preset engagement section of the loop. 23. The drive unit (16) according to claim 22, wherein the engagement section is between the first and second sprocket wheels (132, 134). 24. The drive unit (16) according to claim 22, wherein a guiding of the power transmission chain (136) in the engagement section is provided, the guiding preferably being adapted to a shape of the sprocket element. 25. The drive unit (16) according to claim 22, wherein the loop is convex with the exception of the engagement section where the loop is concave. 26. The drive unit (16) according to claim 1, wherein each of the at least one power output assembly (122, 124) is in the form of an arm, with the power transmission chain (136) being arranged along the respective arm. 27. The drive unit (16) according to claim 26, wherein the arm is rotatable around a rotation axis fixed with respect to the remainder of the drive unit (16). 28. The drive unit (16) according to claim 27, wherein the rotation axis substantially corresponds to an axis of the first sprocket wheel (132). 29. The drive unit (16) according to claim 26, wherein the arm is rotatable by means of a hydraulic or electric actuator. 30. The drive unit (16) according to claim 1, wherein each of the at least one power output assembly (122, 124) comprises a pivoting cylinder for rotating the respective power output assembly. 31. The drive unit (16) according to claim 30, wherein an axis of the pivoting cylinder substantially corresponds to a rotation axis of the respective power output assembly (122, 124). 32. The drive unit (16) according to claim 30, wherein the pivoting cylinder is a hydraulic actuator. 33. The drive unit (16) according to claim 1, wherein the power transmission chain (136) is one of a roller chain, a sleeve type chain, and Galle-chain. 34. The drive unit (16) according to claim 1, wherein each one of the at least one power output assembly (122, 124) comprises a plurality of power transmission chains running in parallel or wherein each one of the at least one power output assembly (122, 124) comprises a multi-row power transmission chain. 35. The drive unit (16) according to claim 1, wherein a direction of longitudinal extension (C) of the drive unit (16) is in a plane orthogonal to the common wheel axis (A). 36. The drive unit (16) according to claim 1, wherein the drive unit comprises a mounting structure for being mounted to the aircraft running gear and the entire drive unit (16) with the exception of the mounting structure is movable with respect thereto such that the power transmission chain (136) is selectively engageable with the sprocket element (108). 37. The drive unit (16) according to claim 36, wherein the drive unit (16) with the exception of the mounting structure is at least one of pivotally rotatable and laterally displacable with respect to the mounting structure. 38. The drive unit (16) according to claim 36, wherein the drive unit (16) with the exception of the mounting structure is movable by means of an electric or hydraulic actuator. 39. The drive unit (16) according to claim 1, comprising an integrated free-wheel arrangement. 40. The drive unit (16) according to claim 39, wherein a free wheeling direction of the free-wheel arrangement is reversible. 41. The drive unit (16) according to claim 1, comprising a self-securing engagement/disengagement mechanism. 42. The drive unit (16) according to claim 41, wherein the self-securing engagement/disengagement mechanism is operated in a pneumatic, hydraulic or electric manner. 43. The drive unit (16) according to claim 1, comprising an engagement/disengagement mechanism adapted to synchronize the rotating speed of the power transmission chain (136) of each of the at least one power output assembly (122, 124) with the respective sprocket element (108, 110) by sensing the wheel speed and adjusting the motor speed. 44. The drive unit according to claim 43, comprising a sensing device for sensing the relative positioning of sprocket teeth for targeted engaging of the power transmission chain of each of the at least one power output assembly (122, 124) with the respective sprocket element (108, 110). 45. An aircraft running gear (2), comprising: at least a first wheel (4) and a second wheel (6) on a common wheel axis (A), anda drive unit (16) drivingly coupleable to at least one of the first and second wheels (4, 6), the drive unit comprising at least one power output assembly (122, 124) for driving at least one of the first and second wheels (4, 6), with each of the at least one power output assembly (122, 124) comprising a power transmission chain (136) selectively engageable with a sprocket element (108, 110) coupled to one of the first and second wheels (4, 6), with the power transmission chain (136) being moveable in operation of the drive unit between a position of engagement with the sprocket element and a position of disengagement with the sprocket element. 46. The aircraft running gear (2) according to claim 45, comprising: a first sprocket element (108), which is coupled to the first wheel (4), engageable to the power transmission chain (108) of the first power output assembly (122) of the drive unit (16), and a second sprocket element (110), which is coupled to the second wheel (6), engageable to the power transmission chain of the second power output assembly (124) of the drive unit (16). 47. The aircraft running gear (2) according to claim 46, wherein the first and second sprocket elements (108, 110) are mounted on a respective rim of the first and second wheels (4, 6). 48. The aircraft running gear (2) according to claim 45, having a running gear leg (14) supporting the first and second wheels (4, 6), with the drive unit (16) being mounted to the running gear leg (14). 49. The aircraft running gear (2) according to claim 48, wherein a direction of longitudinal extension of the drive unit (16) is substantially parallel to the running gear leg (14). 50. The aircraft running gear (2) according to claim 45 adapted to be used as a nose running gear or a main running gear. 51. The aircraft running gear (2) according to claim 45, wherein at least one of the first and second sprocket elements (108, 110) and the respective rims are made of light metal, such as aluminum or titanium.
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이 특허에 인용된 특허 (2)
Christensen, Donald J.; Gaines, Louie T.; Charles, David L., Aircraft taxi system including drive chain.
Leynaert, Francois-Noel; Quenerch'Du, Marc; Durand, Guillaume, Device for measuring a relative rotation speed and/or a relative angular position between a first rotating element and a second rotating element mounted to rotate relative to a static part.
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