Abstract: A power control unit configured to supply hydraulic pressure and mechanical torque. To this end, the power control unit includes an electric motor coupled to a differential output transmission and a hydraulic pump. A switchable transmission device allows the torque of the motor to be redirected either to the output transmission, e.g., to drive high-lift devices, or to the hydraulic pump, e.g., to extend or retract landing gears.

Abstract: The invention provides a drive system for rotating a wheel of an aircraft landing gear. The drive system includes a motor operable to rotate a drive pinion, and a driven gear adapted to be mounted to the wheel. The drive system has a first configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear and a second configuration in which the drive pinion is not capable of meshing with the driven gear. The drive system includes a linear positioning actuator for moving the drive pinion relative to the driven gear. The positioning actuator has a first end and a second end, the first end having a pivotal connection with a pivot axis spaced at a fixed distance from an axis of rotation of the driven gear, and the second end having a pivotal connection with a pivot axis spaced at a fixed distance from an axis of rotation of the drive pinion.

Abstract: A drive system 20, 20? for rotating a wheel 11, 11? of an aircraft landing gear 10, 10?, is disclosed having a drive element 24, 24?, a motor 21, 21? operable to rotate the drive element, and a driven gear 25, 25? adapted to be attached to the wheel. The drive system has a drive configuration in which the drive element is capable of meshing with the driven gear to drive the driven gear, wherein the drive system further comprises a transmission error measurement apparatus 30, 40, the apparatus configured to obtain, over time, measurement data of one or more characteristics of the drive system when in the drive configuration, the measurement data providing an indication of a transmission error between a torque commanded by the motor and a resulting torque at the driven gear. An aircraft 100 and a method of providing an indication of a transmission error in a drive system is disclosed.

Abstract: A power control unit configured to supply hydraulic pressure and mechanical torque. To this end, the power control unit includes an electric motor coupled to a differential output transmission and a hydraulic pump. A switchable transmission device allows the torque of the motor to be redirected either to the output transmission, e.g., to drive high-lift devices, or to the hydraulic pump, e.g., to extend or retract landing gears.

Abstract: A roller gear for use in a roller gear and sprocket configuration of a drive system is disclosed, particularly for use in a landing gear drive system of an aircraft. Alternative embodiments and, in particular, means for permitting removal and replacement of rollers and roller mounting pins in the roller gear are disclosed.

Abstract: Disclosed is a landing gear bogie pitch trimmer, comprising a hydraulic actuator for adjusting a pitch of a landing gear bogie, in use, a fluid interface for receiving, from an aircraft hydraulic system external to the landing gear bogie pitch trimmer, hydraulic fluid for use in actuating the hydraulic actuator, and a flow control valve for controlling flow of the hydraulic fluid through the fluid interface in use. Also disclosed is a system, a landing gear controller, a method, and an aircraft.

Abstract: 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.

Abstract: The present invention provides an aircraft described as an Airborne Urban Mobility Vehicle with VTOL (Vertical Take-Off and Landing) capability. The aircraft has a 5 fuselage freely pivoted between lateral arms of a yoke; the arms of the yoke extending fore and aft and, at or towards the extremities of the arms: the respective fore portions are linked laterally together by an aerofoil; and the respective aft portions are linked laterally together by an aerofoil; and at least one of the fore and aft aerofoils having mounted thereon one or more propulsion units.

Abstract: A drive system for an aircraft landing gear is described. The drive system includes a drive pinion, a drive shaft arranged to rotate the drive pinion about a drive axis, and a casing which rotatably supports the drive shaft. The drive pinion is rotatably supported on the casing by a self-aligning bearing. The drive pinion is coupled to the drive shaft by a flexible coupling adapted to transfer torque between the drive pinion and the drive shaft and to permit tilting of the drive pinion relative to the drive axis.

Abstract: A roller gear for use in a roller gear and sprocket configuration of a drive system is disclosed, particularly for use in a landing gear drive system of an aircraft. Alternative embodiments and, in particular, means for permitting removal and replacement of rollers and roller mounting pins in the roller gear are disclosed.

Abstract: 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 comprising a crowned spline joint between the drive shaft and the pinion gear. The crowned spline joint is arranged to permit tilting of the pinion gear relative to the drive axis. In some embodiments a first spline joint between the drive shaft and the pinion gear is arranged to permit tilting of the pinion gear relative to the drive axis; and a second spline joint is arranged to permit translation of the pinion gear along the drive axis relative to the drive shaft.

Abstract: A wheel assembly is disclosed, in which a ring gear is movably mounted to the rim of the wheel, so that torque can be transmitted between wheel and rim, while the ring gear is isolated from deformations induced in the wheel rim.

Abstract: Examples of a gaming robot are described. The gaming robot may be controlled by a computing device such as a smartphone or tablet. The gaming robot may be used in solo or group gaming activities. In one case a gaming robot has one or more primary modules. These include a main module with a main processing module to control at least one locomotion module of the gaming robot in response to commands received from the computing device. Secondary modules may be attached to the primary modules via mechanical couplings and electrical interfaces. The main processing module is configured to obtain data identifying the secondary module from the secondary module via the electrical interface, and transmit the data to the computing device. The computing device alters the commands sent to the main processing module based on the data obtained from the secondary module such that control of at least one locomotion module is modified based on connection of the secondary module.

Abstract: A drive system for rotating a wheel of an aircraft landing gear is disclosed. The drive system includes a motor operable to rotate a drive pinion via a drive path, and a driven gear adapted to be mounted to the wheel. The drive system has a first configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear via the drive path. The drive path has a plurality of shafts rotatable about respect shaft axes, including an output shaft. The output shaft is operable to pivot about the axis of rotation of another shaft axis spaced from the output shaft axis. Also, an aircraft landing gear having a wheel and the drive system, where the driven gear of the drive system is mounted to the wheel.

Abstract: A roller gear for use in a roller gear and sprocket configuration of a drive system is disclosed, particularly for use in a landing gear drive system of an aircraft. Alternative embodiments and, in particular, means for permitting removal and replacement of rollers and roller mounting pins in the roller gear are disclosed.

Abstract: The invention relates to a drive system for rotating a wheel of an aircraft landing gear. The drive system includes a motor operable to rotate a drive pinion, and a driven gear adapted to be mounted to the wheel. The drive system has a first configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear and a second configuration in which the drive pinion is not capable of meshing with the driven gear. The drive system further includes a lock-stay including a first lock link and a second lock link pivotally connected to the first lock link, the lock-stay being switchable between a first position, a second position, and an intermediate position between the first and second positions in which the first and second lock links are substantially aligned. The lock-stay is in the first position when the drive system is in the first configuration and the lock-stay is in the second position when the drive system is in the second configuration.

Abstract: A drive system for rotating a wheel of an aircraft landing gear is disclosed. The drive system includes a motor operable to rotate a drive pinion via a drive path, and a driven gear adapted to be mounted to the wheel. The drive system has a first configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear via the drive path. The drive path has an input shaft having an axis of rotation spaced from an axis of rotation of an output shaft. The output shaft is operable to pivot about the axis of rotation of the input shaft. Also, an aircraft landing gear having a wheel and the drive system, where the driven gear of the drive system is mounted to the wheel.

Abstract: The invention is a drive system for rotating a wheel of an aircraft landing gear. The drive system includes a motor operable to rotate a drive pinion via a drive path, and a driven gear adapted to be mounted to the wheel. The drive system has a first configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear via the drive path. The drive path has a plurality of shafts rotatable about respect shaft axes, including an output shaft. The output shaft is operable to pivot about the axis of rotation of another shaft axis spaced from the output shaft axis. Also, an aircraft landing gear having a wheel and the drive system, where the driven gear of the drive system is mounted to the wheel.

Abstract: The invention is a drive system for rotating a wheel of an aircraft landing gear. The drive system includes a motor operable to rotate a drive pinion via a drive path, and a driven gear adapted to be mounted to the wheel. The drive system has a first configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear via the drive path. The drive path has an input shaft having an axis of rotation spaced from an axis of rotation of an output shaft. The output shaft is operable to pivot about the axis of rotation of the input shaft. Also, an aircraft landing gear having a wheel and the drive system, where the driven gear of the drive system is mounted to the wheel.

Abstract: The invention provides a drive system for rotating a wheel of an aircraft landing gear. The drive system includes a motor operable to rotate a drive pinion, and a driven gear adapted to be mounted to the wheel. The drive system has a first configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear and a second configuration in which the drive pinion is not capable of meshing with the driven gear. The drive system includes a linear positioning actuator for moving the drive pinion relative to the driven gear. The positioning actuator has a first end and a second end, the first end having a pivotal connection with a pivot axis spaced at a fixed distance from an axis of rotation of the driven gear, and the second end having a pivotal connection with a pivot axis spaced at a fixed distance from an axis of rotation of the drive pinion.