Abstract: An example method includes combining an interlayer and a carbon fiber fabric, wherein the interlayer comprises a highly oriented milled carbon fiber ply comprising a plurality of out-of-plane carbon fibers. The method further includes winding the interlayer and the carbon fiber fabric around a core to form a composite fiber preform comprising a plurality of layers defining an annulus extending along a central axis. The method further includes densifying the composite fiber preform.

Abstract: In some examples, a disc brake assembly and methods of forming and assembling said brake disc assembly. The brake disc assembly including a core structure and a plurality of wear pads. The core structure having a first major surface comprising at least one curved ridge or curved channel that extends in a radial direction along the first major surface between an inner and outer diameter of the core structure. Each wear pad defining a friction surface and a mounting surface such that the mounting surfaces of the plurality of wear pads are positioned adjacent to, and in contact with, the first major surface of the core structure, where at least one of the mounting surfaces of the plurality of wear pads includes a corresponding curved ridge or curved channel configured to interlink with the at least one curved ridge or curved channel of the core structure.

Abstract: In some examples, a disc brake assembly and methods of forming and assembling said brake disc assembly. The brake disc assembly including a core structure and a plurality of wear pads. The core structure having a first major surface comprising at least one curved ridge or curved channel that extends in a radial direction along the first major surface between an inner and outer diameter of the core structure. Each wear pad defining a friction surface and a mounting surface such that the mounting surfaces of the plurality of wear pads are positioned adjacent to, and in contact with, the first major surface of the core structure, where at least one of the mounting surfaces of the plurality of wear pads includes a corresponding curved ridge or curved channel configured to interlink with the at least one curved ridge or curved channel of the core structure.

Abstract: An electric taxi system (ETS) for an aircraft may include an annular output gearbox positioned between a wheel and a main strut of a main landing gear of the aircraft. The output gearbox may surround a brake piston assembly of the wheel of the aircraft. One or more selectively operable engaging assemblies, for selectively coupling the ETS with the wheel of the aircraft, may be positioned between the output gearbox and the wheel of the aircraft. The one or more selectively operable engaging assemblies may be coupled with an output gear of the output gearbox to rotate with the output gear.

Abstract: An electric taxi system (ETS) for an aircraft may include an annular output gearbox positioned between a wheel and a main strut of a main landing gear of the aircraft. The output gearbox may surround a brake piston assembly of the wheel of the aircraft. One or more selectively operable engaging assemblies, for selectively coupling the ETS with the wheel of the aircraft, may be positioned between the output gearbox and the wheel of the aircraft. The one or more selectively operable engaging assemblies may be coupled with an output gear of the output gearbox to rotate with the output gear.

Abstract: A drive ring may be configured to receive a drive key from a wheel rim in a bushing on the ring. The bushing may include a slot with clearance to allow movement of the drive key within the slot during axial or rim flexure events. The axial or rim flexure events may occur for example, during taxiing of a vehicle and the loads of the vehicle can impart flexure forces on the connection between the wheel rim and the drive system. In one exemplary embodiment, the bushing may be movable on the drive ring to accommodate movement of the drive key during flexure.

Abstract: An electric taxi system (ETS) for an aircraft may comprise drive motors mounted coaxially with wheels of the aircraft. A clutch assembly may be interposed between the drive motor the wheel. The clutch assembly may transmit torque from the motor to the wheel when the wheel and a rotor of the motor rotate at the same rotational speed. The clutch assembly may self-disengage a rotor of the motor from the wheel when the wheel rotates faster than the rotor.

Abstract: An electric taxi system (ETS) for an aircraft may comprise drive motors mounted coaxially with wheels of the aircraft. A clutch assembly may be interposed between the drive motor the wheel. The clutch assembly may transmit torque from the motor to the wheel when the wheel and a rotor of the motor rotate at the same rotational speed. The clutch assembly may self-disengage a rotor of the motor from the wheel when the wheel rotates faster than the rotor.

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: An electric taxi system (ETS) for an aircraft may comprise drive motors mounted coaxially with wheels of the aircraft. A clutch assembly may be interposed between the drive motor the wheel. The clutch assembly may transmit torque from the motor to the wheel when the wheel and a rotor of the motor rotate at the same rotational speed. The clutch assembly may self-disengage a rotor of the motor from the wheel when the wheel rotates faster than the rotor.

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 drive ring may be configured to receive a drive key from a wheel rim in a bushing on the ring. The bushing may include a slot with clearance to allow movement of the drive key within the slot during axial or rim flexure events. The axial or rim flexure events may occur for example, during taxiing of a vehicle and the loads of the vehicle can impart flexure forces on the connection between the wheel rim and the drive system. In one exemplary embodiment, the bushing may be movable on the drive ring to accommodate movement of the drive key during flexure.

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: An electric taxi system (ETS) for an aircraft may comprise drive motors mounted coaxially with wheels of the aircraft. A clutch assembly may be interposed between the drive motor the wheel. The clutch assembly may transmit torque from the motor to the wheel when the wheel and a rotor of the motor rotate at the same rotational speed. The clutch assembly may selfdisengage a rotor of the motor from the wheel when the wheel rotates faster than the rotor.

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.