Abstract: A monitoring system and method are provided for real time monitoring of flaps, landing gears, or tail skids to determine safe taxi, takeoff, and flight readiness. Monitoring units, including scanning LiDAR devices combined with cameras or sensors, mounted in aircraft exterior locations produce a stream of meshed data that is securely transmitted to a processing system to generate a real time visual display of the flaps, landing gears, or tail skid for communication to aircraft pilots to ensure safe aircraft taxi, takeoff, and flight readiness. Actual flap position alignment with optimal flap setting, proper retraction and extension positions of landing gears, and tail skid condition is ensured. Safety of aircraft taxi, takeoff and flight and airport operations are improved when the present system and method are used to prevent incidents related to misaligned flaps and improperly positioned landing gears or tail skids.

Abstract: A method is provided that enhances wheel drive assembly acceleration, heat reduction, and energy efficiency performance during ground travel in aircraft equipped with landing gear wheel-mounted drive assemblies to move aircraft on the ground without reliance on the aircraft's engines or external tow vehicles. Inflation pressure levels of tyres on the landing gear wheels are monitored with pressure and/or temperature sensors to determine and maintain an optimum defined high inflation pressure level for the specific kind of aircraft tyre or the aircraft. A clutch-activated drive assembly may be prevented from transferring torque and driving the aircraft when the optimum high inflation pressure levels are not present in the tyres during ground travel. Tyre pressures may be manually or automatically adjusted in response to processed sensor information to maintain the optimum high inflation pressure level in all tyres as the aircraft is driven with the drive assemblies or with engine thrust.

Abstract: An integrated monitoring system and method are provided with the capability for monitoring ground surface movements of electric taxi drive system-driven aircraft, ground vehicles and personnel, and objects within airport ramp areas. Monitoring units may include a scanning LiDAR device with and without cameras or other sensing devices to transmit meshed real time encrypted data from multiple locations to an artificial intelligence-based processing system that generates a visual display of the monitored area for communication to aircraft cockpits and locations responsible for controlling ramp operations. Monitoring units may be mounted in single or multiple exterior locations on aircraft and/or in locations on ground vehicles and equipment, ground personnel, and the airside portion of an airport terminal.

Abstract: A clutch driven aircraft electric taxi system is provided with a clutch assembly designed to be automatically selectively engaged or disengaged as required to drive an aircraft autonomously during ground operations. The clutch assembly is mounted integrally with other electric taxi system components completely within an aircraft landing gear wheel and may be designed with one way overrunning or selectable clutch engagement capability in one or both rotational directions, preferably using an arrangement of ratcheting struts and clutch elements adapted specifically for use in an aircraft landing gear drive wheel environment. The clutch assembly may automatically disengage in response to predetermined defined conditions or operating parameters.

Abstract: An improved ground collision avoidance system and method is provided for aircraft driven during ground operations by electric taxi drive systems. One or more monitoring devices employing scanning LiDAR technology may be mounted in exterior locations on or near aircraft landing gears or aerodynamically in locations on the aircraft fuselage selected to generate panoramic three-dimensional images from any point of view within or without the aircraft as the aircraft is driven independently within an airport ramp area. The point of view images are transmitted in real time to displays in the aircraft cockpit and may be transmitted to displays outside and remote from the aircraft, allowing the pilot and airport personnel to monitor the aircraft moving within the ramp environment and to respond quickly to control the aircraft's electric taxi drive system-powered ground travel to avoid and prevent a potential collision.

Abstract: A monitoring system and method are provided to monitor ground movement of aircraft driven with electric taxi drive systems and movement of ground service vehicles and equipment and personnel within airport ramp areas. Monitor and sensor devices, including those that are intelligent and employ scanning technology to generate image, positional, and other data may be mounted in locations on aircraft, ground service vehicles and equipment, passenger loading bridges, an airport terminal, and other ramp locations to generate a constant stream of data as the aircraft moves into, within, and out of an airport ramp area. The data stream is transmitted to an artificial intelligence-based processing system to identify and communicate possible safety hazards to multiple locations so that the aircraft's ground travel or a ground vehicle's travel may be altered to avoid identified safety hazards and to avoid collisions.

Abstract: A cockpit control system and method for efficiently controlling ground travel in an aircraft equipped with engine-free electric taxi drive systems are provided. The cockpit control system is configured with a display that provides a maximum amount of information during aircraft ground movement with a minimal amount of input from and distraction to pilots or cockpit crew to facilitate essentially hands free operation and control of aircraft ground travel. System test and drive procedures ensure safe aircraft ground travel with the engine-free electric taxi system. Constant pilot hand or other input is not required to achieve safe and maximally efficient aircraft ground travel powered by the aircraft's engine-free electric taxi drive systems or, under selected defined conditions, by the aircraft's engines to achieve this maximum efficiency. The system may further be designed to be uninterruptible by unauthorized persons.

Abstract: A method for designing and operating an aircraft nose landing gear wheel-mounted electric taxi system moves aircraft with optimal torque during a broad range of ground travel conditions. Electric taxi system components may be sized to produce optimal ground travel torque to move aircraft during the majority of aircraft ground travel conditions and operated to produce a maximum or breakaway torque to move the aircraft with the electric taxi system when a higher level of torque is required. Turning the nose landing gear wheels to a selected angle or through a range of angles simultaneously as the electric taxi system is operated produces the breakaway torque required to get the aircraft moving. When lower torque is needed, the aircraft may be driven with the nose landing gear wheels parallel to the longitudinal axis to produce optimal torque for electric taxi system-powered aircraft ground travel.

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 cockpit control system and method for efficiently controlling ground travel in an aircraft equipped with an engine-free electric taxi system are provided. The cockpit control system is configured with a display that provides a maximum amount of information during aircraft ground movement with a minimal amount of input from and distraction to pilots or cockpit crew to facilitate essentially hands free operation and control of aircraft ground travel. System test and drive procedures ensure safe aircraft ground travel with the engine-free electric taxi system. Constant pilot hand or other input is not required to achieve safe and maximally efficient aircraft ground travel powered by the aircraft's engine-free electric taxi system or, under selected defined conditions, by the aircraft's engines to achieve this maximum efficiency. The system may further be designed to be uninterruptible by unauthorized persons.

Abstract: A clutch assembly for an aircraft drive wheel drive system to move an aircraft independently on the ground is provided. The clutch is mounted within an aircraft drive wheel to be operatively engaged and disengaged to selectively actuate a roller traction or other drive system to activate a non-engine drive means to drive the wheel and the aircraft. One embodiment of the clutch assembly includes a plurality of pivoted sprag elements selectively activatable to transmit torque between inner and outer clutch members and activate the drive wheel drive system. The clutch assembly may also include mating crown gear and straight gear elements integrated with the drive system to reduce stresses on the drive system as the drive means is actuated. Various arrangements of sprags and clutch assembly components may be provided to monitor and selectively control disengagement of the clutch assembly and communicate disengagement to selectively prevent drive system actuation.

Abstract: A vehicle wheel drive assembly, particularly useful in an aircraft, is provided. The vehicle wheel drive assembly is mounted completely within a space defined by structural dimensions of a vehicle wheel and includes a drive means controllable to power the wheel and move the vehicle autonomously on a ground surface, a gear assembly drivingly connected to the drive means, and a clutch assembly operatively connected to the gear assembly. The clutch assembly is operatively mounted with respect to the gear assembly completely within an interior portion of a vehicle wheel axle on which the wheel drive assembly is mounted, thereby maximizing the space functionally available for all of the other components of the wheel drive assembly.

Abstract: A method for reducing aircraft turnaround time by improving airport ramp safety is provided. The method minimizes the time interval between an aircraft's landing and takeoff by independently moving the aircraft on the ground without the aircraft's engines by eliminating hazards from jet blast, the possibility of engine ingestion, and the time previously required to wait in the gate area upon arrival or at departure until jet blast or engine ingestion did not pose a danger. Turnaround time is further reduced by providing an onboard driver controllable to drive at least one of the aircraft's wheels between landing and takeoff, thereby eliminating the need for a tow vehicle and the time required to move the aircraft with a tow vehicle.

Abstract: A method for accelerated power push back of an aircraft equipped with a pilot-controlled engines-off taxi system that drives the aircraft without reliance on the aircraft's main engines or tugs is provided. An aircraft is quickly and efficiently moved out of a gate where it is positioned in a nose-in orientation. The pilot controls the taxi system to drive the aircraft in reverse along a perpendicular path away from the terminal to a location where there is sufficient space for the aircraft to stop and turn, and the aircraft is turned and driven in a forward direction to a takeoff runway. Pilot reliance on ground personnel guidance during push back maneuvers is minimized by providing a monitoring system designed to monitor gate and ramp areas around the aircraft in any visibility or environmental conditions and provide feedback to the pilot.

Abstract: A powered clutch assembly is provided for an aircraft landing gear or other vehicle wheel drive system equipped with wheel drive motors controllable to move the aircraft or vehicle during ground travel. Electric power for the clutch assembly is transferred to clutch actuation elements by a rotary power transfer assembly mounted between stationary and rotating elements within the landing gear wheel drive system to clutch actuation elements. Actuation elements are powered to securely lock clutch rotating elements when required to improve the reliability of failsafe operation of the clutch assembly when torque should not be transferred and to unlock clutch rotating elements when torque should be transferred when the landing gear wheel drive system is used to drive the aircraft during ground travel. Power transferred from the rotary power transfer assembly may also be used to operate components associated with the aircraft drive wheel other than the powered clutch assembly.

Abstract: A surface travel system for military aircraft is provided that enables efficient, quiet, and safe ground operations of one or more aircraft in a wide range of military missions and operations. The surface travel system includes controllable onboard drive means that effectively drives one or more of the aircraft's wheels to move the aircraft autonomously, efficiently, quietly, and safely on any travel surface required for a military mission. The present invention allows the rapid safe deployment of multiple aircraft from tight spaces and enhances the readiness and availability of aircraft for a wide range of military operations.

Abstract: A force limiting system and method are provided for limiting loads in aircraft nose or main landing gear having wheels powered by taxi drive systems mounted within the landing gear wheels to drive aircraft on the ground. The force limiting system may include mechanical components selected to limit or minimize spin-up mass and to releasably connect the taxi drive system to a landing gear wheel section so that operation of the taxi drive system to drive a landing gear wheel is prevented in the presence of a predetermined maximum load. The load limiting system employs mechanical components engineered to securely connect the taxi drive system to the landing gear wheel during operation and to release the taxi drive system from connection to the wheel when loads applied to system components exceed an established or recommended maximum load.

Abstract: A powered aircraft wheel is designed to include multiple wheel sections configured to define a cavity within the wheel and to support completely within the wheel cavity an onboard non-engine drive means controllable to move an aircraft autonomously without reliance on aircraft engines during taxi and ground travel. Each part of the powered wheel may be constructed of a material specifically selected to emphasize a functional property of the material that is optimal for the function of the wheel part at a specific location. The selected combination of functionally distinct materials gives the powered aircraft wheel a unique optimal structural and functional capability.

Abstract: A powered clutch assembly is provided for an aircraft landing gear or other vehicle wheel drive system equipped with wheel drive motors controllable to move the aircraft or vehicle during ground travel. Electric power for the clutch assembly is transferred to clutch actuation elements by a rotary power transfer assembly mounted between stationary and rotating elements within the landing gear wheel drive system to clutch actuation elements. Actuation elements are powered to securely lock clutch rotating elements when required to improve the reliability of failsafe operation of the clutch assembly when torque should not be transferred and to unlock clutch rotating elements when torque should be transferred when the landing gear wheel drive system is used to drive the aircraft during ground travel. Power transferred from the rotary power transfer assembly may also be used to operate components associated with the aircraft drive wheel other than the powered clutch assembly.

Abstract: A method is provided for restoring mobility to an aircraft equipped with at least one self-propelled drive wheel powered by a driver when the aircraft has been rendered immobile as a result of one or more wheel tires adhering to and becoming stuck to tarmac or another ground surface. The method uses forces generated by the cooperative action of the wheel driver, the aircraft steering, and the aircraft braking system to release adherent tires of each set of main wheels and/or nose gear wheels by applying differential force to one set of wheels at a time to release any adherent tires so that the aircraft is able to move on the ground surface and travel in a desired direction at a desired speed.