Abstract: A monitoring system is provided to ensure continued efficient reliable operation of an aircraft drive wheel drive system, preferably an aircraft drive wheel drive system driven by actuating drive system-actuated drive means, designed to drive an aircraft autonomously during ground operations. The monitoring system includes an array of sensor elements capable of obtaining desired information relating to selected drive system operating parameters and performance indicators during aircraft ground operations. The sensor elements are designed to be functionally located externally of drive system components to obtain information during aircraft ground movement under a range of operating conditions. The operating parameters and/or performance indicators to be monitored preferably include at least drive wheel speed and direction, drive means speed, drive means temperature, and drive means clutch engagement.

Abstract: A torque transmission system is provided for an aircraft drive wheel drive system mounted on nose or main landing gear wheels to move the aircraft autonomously on the ground that effectively transmits torque through drive system components. The drive system includes a drive means capable of generating sufficient torque to move the aircraft, a drive system capable of generating a high torque capacity that activates the drive means, a clutch assembly that can be selectively engaged to control torque transmission to the drive system and activate the drive means, and a landing gear torque takeout element. The clutch assembly is configured to be inactivated and prevented from transmitting torque to other drive wheel drive system components when an overtorque event occurs. Aircraft drive wheel drive system components in the present torque transmission system are designed to withstand torque in excess of a determined maximum for the system.

Abstract: A torque transmission system is provided for an aircraft drive wheel drive system mounted on nose or main landing gear wheels to move the aircraft autonomously on the ground that effectively transmits torque through drive system components. The drive system includes a drive means capable of generating sufficient torque to move the aircraft, a drive system capable of generating a high torque capacity that activates the drive means, a clutch assembly that can be selectively engaged to control torque transmission to the drive system and activate the drive means, and a landing gear torque takeout element. The clutch assembly is configured to be inactivated and prevented from transmitting torque to other drive wheel drive system components when an overtorque event occurs. Aircraft drive wheel drive system components in the present torque transmission system are designed to withstand torque in excess of a determined maximum for the system.

Abstract: A monitoring system is provided to ensure continued efficient reliable operation of an aircraft drive wheel drive system, preferably an aircraft drive wheel drive system driven by actuating drive system-actuated drive means, designed to drive an aircraft autonomously during ground operations. The monitoring system includes an array of sensor elements capable of obtaining desired information relating to selected drive system operating parameters and performance indicators during aircraft ground operations. The sensor elements are designed to be functionally located externally of drive system components to obtain information during aircraft ground movement under a range of operating conditions. The operating parameters and/or performance indicators to be monitored preferably include at least drive wheel speed and direction, drive means speed, drive means temperature, and drive means clutch engagement.

Abstract: A gear assembly includes a single piece gear body having a first axis of rotation and including opposing first and second surfaces each having spiroid gear teeth formed therein. The gear teeth radially extend outward from the first axis of rotation. The gear teeth on the first surface also extend from the first surface toward the second surface and the gear teeth on the second surface also extend from the second surface toward the first surface. The gear teeth on the first surface and the gear teeth on the second surface are configured to concurrently engage teeth of a pinion such that rotation of the pinion is translated to rotation of the gear body around the first axis of rotation.

Abstract: A power takeoff and gearbox is configured for use with an associated vehicle transmission to provide rotational power to an associated auxiliary component. The power takeoff and gearbox includes a housing. An input gear set includes an input gear and a transfer gear mounted for common rotation. The input gear is driven by the associated vehicle transmission. A primary drive gear is disposed on a drive shaft. The primary drive gear is meshed with the transfer gear for rotation with the transfer gear. A planetary gear system includes a carrier, a plurality of planet gears mounted for rotation within the carrier and a sun gear disposed central to the planet gears. The carrier is connected to the primary drive shaft for rotation with the shaft and for rotation of the planet gears relative to the carrier. An output is mounted to the sun gear for providing rotational power to the associated auxiliary component.

Abstract: A power takeoff and gearbox is configured for use with an associated vehicle transmission to provide rotational power to an associated auxiliary component. The power takeoff and gearbox includes a housing. An input gear set includes an input gear and a transfer gear mounted for common rotation. The input gear is driven by the associated vehicle transmission. A primary drive gear is disposed on a drive shaft. The primary drive gear is meshed with the transfer gear for rotation with the transfer gear. A planetary gear system includes a carrier, a plurality of planet gears mounted for rotation within the carrier and a sun gear disposed central to the planet gears. The carrier is connected to the primary drive shaft for rotation with the shaft and for rotation of the planet gears relative to the carrier. An output is mounted to the sun gear for providing rotational power to the associated auxiliary component.