Abstract: A motor-driven landing gear apparatus for taxiing an aircraft includes a motor attached to a bogie. A wheel-driving device is attached to an axle of the landing gear apparatus. A telescoping shaft provides a torque-transmitting interconnection between the motor and the wheel-driving device during taxiing of the aircraft. The telescoping shaft includes an internally-splined shaft rotatably supported within a housing attached to the bogie.

Abstract: An actuator includes an actuator housing, a screw, a nut, a rod end, a torque bar, and a bidirectional stop. The torque bar extends through the screw and is configured to rotate therewith. The torque bar has a first end and a second end. The bidirectional stop is formed on the first end of the torque bar and is disposed external to the screw. The bidirectional stop has a first side and a second side. The first side has a third dog stop formed thereon, and the second side has a fourth dog stop formed thereon. The first dog stop engages the third dog stop when the nut is in the fully extended position, and the second dog stop engages the fourth dog stop when the nut is in the fully retracted position.

Abstract: A motor-driven landing gear apparatus for an aircraft may include one or more motors attached to a bogie of the landing gear. At least one wheel-driving device may be attached to an axle of the landing gear. At least one telescoping shaft may interconnect the at least one motor and the at least one wheel-driving device.

Abstract: A method of taxing an aircraft with an electric taxi system (ETS) comprising of drive units producing airflow through rotors to pre-cool drive motors and produce rotation of aircraft wheels. The drive motors may be used to produce reverse motion of the aircraft and of operating the drive motors independently of one another so one can operate at a rate of speed and/or direction that is different from the second one of the drive units which may provide enhanced maneuverability of the aircraft during taxing. The drive motors may be controlled to produce regenerative power producing a deceleration of the aircraft that does not shift a center of gravity of the aircraft.

Abstract: A method of taxing an aircraft with an electric taxi system (ETS) comprising of drive units producing airflow through rotors to pre-cool drive motors and produce rotation of aircraft wheels. The drive motors may be used to produce reverse motion of the aircraft and of operating the drive motors independently of one another so one can operate at a rate of speed and/or direction that is different from the second one of the drive units which may provide enhanced maneuverability of the aircraft during taxing. The drive motors may be controlled to produce regenerative power producing a deceleration of the aircraft that does not shift a center of gravity of the aircraft.

Abstract: A electric taxi system (ETS) for an aircraft may comprise drive units mounted coaxially with wheels of the aircraft and dedicated motor control units for the drive units. The motor control units may be operable independently of one another so that a first one of the drive units can be operated at a speed different from an operating speed of a second one of the drive units. Independent operability of the drive units may provide enhanced maneuverability of the aircraft during taxiing.

Abstract: A electric taxi system (ETS) for an aircraft may comprise drive units mounted coaxially with wheels of the aircraft and dedicated motor control units for the drive units. The motor control units may be operable independently of one another so that a first one of the drive units can be operated at a speed different from an operating speed of a second one of the drive units. Independent operability of the drive units may provide enhanced maneuverability of the aircraft during taxiing.

Abstract: A roller bearing assembly includes an annular outer ring with first and second outer ring shoulders that define a first raceway in the outer ring. An annular inner ring may be disposed substantially concentrically within the outer ring, the inner ring including a base portion and first and second inner ring shoulders that extend from and are integral with the base portion to define a second raceway in the inner ring. A plurality of rolling elements may be arranged between the inner ring and outer ring and within the first and second raceways to rotatably couple the outer ring to the inner ring.

Abstract: Butterfly valves assemblies are provided that include a flowbody, a butterfly plate, an actuator and an upper chimney and a lower chimney disposed within the flowbody. The flowbody has an inner surface defining a channel. The butterfly plate is disposed in the channel, is rotationally mounted to the flowbody, and has an outer periphery. The actuator has an actuator output shaft that is coupled to the valve shaft via a serrated spline coupling. The upper chimney and the lower chimney are configured to include bearing assemblies that constrain radial loads and thrust loads exerted upon the valve shaft and minimize misalignment of the serrated spline coupling.

Abstract: A electric taxi system (ETS) for an aircraft may comprise drive units mounted coaxially with wheels of the aircraft and dedicated motor control units for the drive units. The motor control units may be operable independently of one another so that a first one of the drive units can be operated at a speed different from an operating speed of a second one of the drive units. Independent operability of the drive units may provide enhanced maneuverability of the aircraft during taxiing.

Abstract: A electric taxi system (ETS) for an aircraft may comprise drive units mounted coaxially with wheels of the aircraft and dedicated motor control units for the drive units. The motor control units may be operable independently of one another so that a first one of the drive units can be operated at a speed different from an operating speed of a second one of the drive units. Independent operability of the drive units may provide enhanced maneuverability of the aircraft during taxiing.

Abstract: A wind turbine energy conversion device that can take advantage of the higher speed and more persistent winds at higher altitudes is hereinafter disclosed. The wind turbine energy conversion device includes an unmanned aerial vehicle (UAV) connected to one end of a tether (which may include multiple shorter tethers), the other end being connected to a terrestrial anchorage point. The UAV flies at altitudes where wind speeds can reach 40 mph or higher. The UAV comprises a flying wing with one or more trailing wind power turbines and flies airborne maneuvers designed to increase relative wind speed up to about four times the true wind speed.

Abstract: Butterfly valves assemblies are provided that include a flowbody, a butterfly plate, an actuator and an upper chimney and a lower chimney disposed within the flowbody. The flowbody has an inner surface defining a channel. The butterfly plate is disposed in the channel, is rotationally mounted to the flowbody, and has an outer periphery. The actuator has an actuator output shaft that is coupled to the valve shaft via a serrated spline coupling. The upper chimney and the lower chimney are configured to include bearing assemblies that constrain radial loads and thrust loads exerted upon the valve shaft and minimize misalignment of the serrated spline coupling.

Abstract: A roller bearing assembly includes an annular outer ring with first and second outer ring shoulders that define a first raceway in the outer ring. An annular inner ring may be disposed substantially concentrically within the outer ring, the inner ring including a base portion and first and second inner ring shoulders that extend from and are integral with the base portion to define a second raceway in the inner ring. A plurality of rolling elements may be arranged between the inner ring and outer ring and within the first and second raceways to rotatably couple the outer ring to the inner ring.

Abstract: A wind turbine energy conversion device that can take advantage of the higher speed and more persistent winds at higher altitudes is hereinafter disclosed. The wind turbine energy conversion device includes an unmanned aerial vehicle (UAV) connected to one end of a tether (which may include multiple shorter tethers), the other end being connected to a terrestrial anchorage point. The UAV flies at altitudes where wind speeds can reach 40 mph or higher. The UAV comprises a flying wing with one or more trailing wind power turbines and flies airborne maneuvers designed to increase relative wind speed up to about four times the true wind speed.