Abstract: A lubrication distribution system is provided for mechanical systems, including gearboxes, to evenly and precisely apply lubricant to system structures during operation. The system includes a rotating lubrication distribution component that functions both to pump and to precisely direct lubricant. Machined locator elements enable accurate positioning of the rotating lubrication distribution component within the system. A plurality of lateral ports and surface features in the rotating lubrication distribution component receive and distribute lubricant transferred during rotation from one or more lubricant collection components with profiled lubricant transfer elements that enables collection of lubricant from eddies produced by profiles of the lubricant transfer elements during rotation of the rotating lubrication distribution component.

Abstract: A lubrication distribution system is provided for mechanical systems, including gearboxes, to evenly and precisely apply lubricant to system structures during operation. The system includes a rotating lubrication distribution component that functions both to pump and to precisely direct lubricant. Machined locator elements enable accurate positioning of the rotating lubrication distribution component within the system. A plurality of lateral ports and surface features in the rotating lubrication distribution component receive and distribute lubricant transferred during rotation from one or more lubricant collection components with profiled lubricant transfer elements that enables collection of lubricant from eddies produced by profiles of the lubricant transfer elements during rotation of the rotating lubrication distribution component.

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 method for designing and operating aircraft nose landing gear wheel-mounted electric taxi systems to move aircraft during ground travel. Electric taxi system components are engineered and sized to produce optimal ground travel torque to move aircraft during the majority of aircraft ground travel and are operated in conjunction with the aircraft steering to turn the nose wheels to an effective angle that moves the aircraft during pushback and in breakaway situations. The nose landing gear wheels are turned to an effective angle and the electric taxi systems are operated simultaneously to get the aircraft moving. After breaking away, the aircraft is driven with electric taxi systems at the optimal ground travel torque in a forward or reverse direction with the nose wheels parallel or in a desired ground travel direction with the nose wheels steered in the desired direction of ground travel.

Abstract: A method for designing and operating an aircraft nose landing gear wheel-mounted electric taxi system to move 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 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: An epicyclic gearbox with an integral arrangement of meshing gear elements, including an annulus gear, planet gears, and sun gears, to transfer power from a motive power source to a driven element with a range of applications is provided. The annulus gear, in contact with the power source, forms an exterior gearbox input and is in meshing contact with a number of stepped planet gears supported on floating planet carriers. Each stepped planet gear is positioned internally of the annulus gear and includes two planet stages in meshing contact with corresponding sun gear stages. One of the sun gear stages is an interior gearbox output and transfers power to a machine or device to be driven. Meshing surfaces of the gear elements support helical teeth or spur teeth, with numbers of teeth on meshing gear elements selected for optimal torque transfer from the exterior input to the interior output.

Abstract: An epicyclic gearbox with an integral arrangement of meshing gear elements, including an annulus gear, planet gears, and sun gears, to transfer power from a motive power source to a driven element with a range of applications is provided. The annulus gear, in contact with the power source, forms an exterior gearbox input and is in meshing contact with a number of stepped planet gears supported on floating planet carriers. Each stepped planet gear is positioned internally of the annulus gear and includes two planet stages in meshing contact with corresponding sun gear stages. One of the sun gear stages is an interior gearbox output and transfers power to a machine or device to be driven. Meshing surfaces of the gear elements support helical teeth or spur teeth, with numbers of teeth on meshing gear elements selected for optimal torque transfer from the exterior input to the interior output.

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 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 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 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 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.