A universal wheel driving system includes a sun gear provided to receive power from a power source, a ring gear provided so that a rotation axis thereof is moved relative to a rotation axis of the sun gear and a wheel is concentrically connected to the ring gear, at least one gear train engaged to the sun gear and the ring gear and configured to allow relative motion between the rotation axes of the sun gear and the ring gear and to form a continuous power transmission state therebetween, a carrier constantly supporting a position of a rotation axis of a final pinion of the at least one gear train with respect to a position of the rotation axis of the ring gear, and a suspension portion configured to support the carrier to be movable upward and downward with respect to a vehicle body.

A uni-directional drive gear includes a plurality of teeth each pivotably mounted on a mounting seat to be turned between driving and idle positions so as to permit the gear to rotate in a uni-rotational direction. A gear transmission device having the uni-directional drive gear can be configured to perform different transmissions to suit a wide variety of requirements.

A drive system for an aircraft landing gear, the drive system including a pinion gear, a drive shaft arranged to rotate the pinion gear about a drive axis, a driven gear arranged to mesh with the pinion gear to be rotatable by the pinion gear, the driven gear being connectable to a wheel of the landing gear to be capable of rotating the wheel about a wheel axis; and a flexible interface. The flexible interface includes a plurality of driven gear coupling members, each driven gear coupling member having a first connection portion attached to the driven gear, a second connection portion adapted to be attached to the wheel at an offset distance from the wheel axis, and a joint between the first connection portion and the second connection portion, the joint permitting relative movement between the first connection portion and the second connection portion.

Known autonomous taxi systems for aircraft include a rigid connection between the aircraft wheel and a gear which is used to drive it. Such arrangements have been found to suffer from the problem that wheel deformation modes cause unacceptable wear and/or stresses within the drive system and/or wheel. The present invention thus proposes a drive system for an aircraft landing gear, the drive system comprising: a pinion gear; a drive shaft arranged to rotate the pinion gear about a drive axis; a driven gear arranged to mesh with the pinion gear to be rotatable by the pinion gear, the driven gear being connectable to a wheel of the landing gear to be capable of rotating the wheel about a wheel axis; and a flexible interface. The flexible interface comprises a plurality of driven gear coupling members, each driven gear coupling member having a first connection portion attached to the driven gear, a second connection portion adapted to be attached to the wheel at an offset distance from the wheel axis, and a joint between the first connection portion and the second connection portion, the joint permitting relative movement between the first connection portion and the second connection portion.

Device and method for providing rotational power using power transmission are disclosed. The device enables multi-dimensional and angle-agnostic displacement of the rotational power output with respect to the input location and transference of high-torque and high-speed rotational movement, while preserving maximal efficiency and quick response. The device is a transmission gear that comprises at least two gear-links in a multi-link articulated gear (MLAG). Each of the links comprising at least two gear wheels. The transmission gear further comprising a common axis adapted to allow the links to rotate freely with respect to each other about the common axis and thus to allow change of the angle between the at least two links and thereby to change the distance between the input shaft and the output shaft.

Device and method for providing rotational power using power transmission are disclosed. The device enables multi-dimensional and angle-agnostic displacement of the rotational power output with respect to the input location and transference of high-torque and high-speed rotational movement, while preserving maximal efficiency and quick response. The device is a transmission gear that comprises at least two gear-links in a multi-link articulated gear (MLAG). Each of the links comprising at least two gear wheels. The transmission gear further comprising a common axis adapted to allow the links to rotate freely with respect to each other about the common axis and thus to allow change of the angle between the at least two links and thereby to change the distance between the input shaft and the output shaft.

A support assembly for coupling a first gearbox to an airframe of an aircraft. The first gearbox has an output gear operable to transfer torque to an input gear of a second gearbox via a common shaft rotatable about a longitudinal axis. The support assembly includes a fixed joint proximate the longitudinal axis. A first directional reacting joint remote from the longitudinal axis provides a first radial growth degree of freedom to the first gearbox relative to the longitudinal axis. A second directional reacting joint remote from the longitudinal axis provides a second radial growth degree of freedom to the first gearbox relative to the longitudinal axis. The first radial growth degree of freedom is not parallel with the second radial growth degree of freedom such that the support assembly maintains the output gear of the first gearbox in substantial collinear alignment with the input gear of the second gearbox.

A support assembly for coupling a first gearbox to an airframe of an aircraft. The first gearbox has an output gear operable to transfer torque to an input gear of a second gearbox via a common shaft rotatable about a longitudinal axis. The support assembly includes a fixed joint proximate the longitudinal axis. A first directional reacting joint remote from the longitudinal axis provides a first radial growth degree of freedom to the first gearbox relative to the longitudinal axis. A second directional reacting joint remote from the longitudinal axis provides a second radial growth degree of freedom to the first gearbox relative to the longitudinal axis. The first radial growth degree of freedom is not parallel with the second radial growth degree of freedom such that the support assembly maintains the output gear of the first gearbox in substantial collinear alignment with the input gear of the second gearbox.

A medical instrument with a hollow shaft, a handle at the proximal end, and a tool at the distal end such that the tool is rotatable about the longitudinal axis of the shaft via an actuation rod connected to the handle, the actuation rod composed of two parts, with mutually facing end-face toothing arrangements.

A drive system for a tiltrotor aircraft includes a first gearbox rotatably mounted to the airframe and rotatable about a longitudinal axis to operate the tiltrotor aircraft between helicopter and airplane modes. A second gearbox extends generally normal to the longitudinal axis of the first gearbox. A common shaft, rotatable about the longitudinal axis, transfers torque from an output gear of the second gearbox to an input gear of the first gearbox. A support assembly couples the second gearbox to the airframe and includes a fixed joint proximate the longitudinal axis, a first directional reacting joint remote from the longitudinal axis providing a first radial growth degree of freedom to the second gearbox and a second directional reacting joint remote from the longitudinal axis providing a second radial growth degree of freedom to the second gearbox that is not parallel with the first radial growth degree of freedom.