Abstract: In at least one embodiment, an energy recovery and regeneration system includes at least one pyroelectric energy recovery module (ERM), a coolant line, a valve and an energy storage module. The at least one pyroelectric ERM generates a voltage in response to realizing a temperature change. The coolant line includes a first end in fluid communication with a coolant source to receive a coolant and a second end disposed adjacent the at least one pyroelectric ERM to deliver the coolant thereto. The valve is interposed between the coolant source and the at least one pyroelectric ERM. The valve modulates the coolant delivered to the at least one pyroelectric ERM to generate the temperate change. The energy storage module is in electrical communication with the pyroelectric ERM to store the voltage generated by the at least one pyroelectric ERM.

Abstract: A landing gear for an aircraft has a pair of spaced wheels, and a drive and steering arrangement operable to drive each of the wheels in either rotational direction. The drive and steering arrangement includes two permanent magnet rotors, with each of the permanent magnet rotors connected to rotate with one of the wheels. A single stator is positioned to drive both of the rotors. The drive and steering arrangement is mounted between the pair of wheels.

Abstract: Embodiments of the disclosure include a de-icing system for an aircraft. The de-icing system includes a plurality of resistive-inductive heating elements inserted adjacent to a flight control surface and a controller configured to provide a supply current to each of the plurality of resistive-inductive heating elements. Each of the plurality of resistive-inductive heating elements produces an electromagnetic field normal to the flight control surfaces and resistive heat in response to the supply current. The electromagnetic field induces an eddy current in the flight control surface.

Abstract: A fire suppression system for an aircraft includes an air separation module configured to receive exhaust air and ram air, conditioned compressor bleed air, and any combination thereof. The air separation module is also configured to provide nitrogen-enriched air and inert gas. The nitrogen-enriched air flows into a nitrogen-enriched air distribution network for fuel tank inerting. The inert gas flows into an inert gas distribution network for fire suppression in areas of the aircraft other than fuel tanks.

Abstract: An apparatus has a first member having an exposed peripheral surface and an electrically and thermally conductive portion. A circumferential array of magnets of alternating polarity are mounted for rotation about an axis relative to the first member inboard of the peripheral surface, the magnets being in sufficient proximity to the electrically and thermally conductive portions so that the rotation of the magnets about the axis is effective to generate eddy currents, in turn, is effective to heat the electrically and thermally conductive portion and, thereby, heat the exposed peripheral surface.

Abstract: A wind turbine generator comprises a stator disposed between first and second generator rotors. The first generator rotor comprises a first rotor shaft and an inner permanent magnet rotor. The second generator rotor is configured to contra-rotate relative to the first generator rotor, and comprises a second rotor shaft and an outer permanent magnet rotor. Inner and outer annular ferromagnetic cores are anchored respectively to radially inner and outer portions of the stator. First and second inner permanent magnets of opposite polarity are anchored to a radially outer surface of the inner permanent magnet rotor adjacent the inner annular ferromagnetic core across an inner air gap, and first and second outer permanent magnets of opposite polarity are anchored to a radially inner surface of the outer permanent magnet rotor adjacent the outer annular ferromagnetic core across an outer air gap.

Abstract: A propulsion system includes a prime mover for providing primary power to propel a vehicle; a flywheel energy storage device for providing secondary power to propel the vehicle when primary power is not being provided, wherein the flywheel energy storage device stores power provided by the prime mover; and a controller for commanding the prime mover on and off.

Abstract: A permanent magnet rotary machine includes a rotor and a plurality of circumferentially spaced permanent magnets spaced circumferentially about a rotational axis of the rotor. A stator is positioned adjacent the rotor, and includes a plurality of circumferentially spaced U-shaped cores. The U-shaped cores are provided with a separate coil. The cores are arranged such that at least three phases of electric power are created by three sets of the cores.

Abstract: An electrical machine, especially permanent magnet machine, is comprised of a stator and a rotor rotatable relative to the stator. The rotor and stator are separated from each other by an air gap. A boundary layer control maintains a desired boundary layer thickness in the air gap. The boundary layer control maintains optimal cooling, which minimizes the electrical machine's overall dimensions while maximizing its power density.

Abstract: A landing gear for an aircraft has a pair of spaced wheels, and a drive and steering arrangement operable to drive each of the wheels in either rotational direction. The drive and steering arrangement includes two permanent magnet rotors, with each of the permanent magnet rotors connected to rotate with one of the wheels. A single stator is positioned to drive both of the rotors. The drive and steering arrangement is mounted between the pair of wheels.

Abstract: A landing gear for an aircraft has a set of axially spaced wheels rotatable about a common axis drive by a transverse flux drive. In another feature, a transverse flux drive includes a first rotor and a second rotor. One of the first and second rotors is positioned radially inwardly of the other. A single stator is positioned radially intermediate the first and second rotors. In another feature, a landing gear combination for use on an aircraft has a nose wheel assembly including at least one nose wheel to be associated with a nose cone on an aircraft. A main landing gear assembly is also associated with the aircraft. A transverse flux motor provides on-ground propulsion and/or braking to the aircraft.

Abstract: A dual rotor machine having a stator includes at least one excitation element, a first rotor located between the at least one excitation element and an axis, the first rotor configured to rotate about the axis, and a second rotor on the other side of the at least one excitation element from the axis, the second rotor configured to rotate about the axis.

Abstract: A turbomachine comprises a turbine shaft, first and second rotors, first and second propulsion stages, and a magnetic stator. The first rotor is rotationally coupled to the turbine shaft, and coaxially arranged along an axis. The first propulsion stage is rotationally coupled to the first rotor, opposite the turbine shaft. The second rotor is coaxially arranged about the first rotor, and the second propulsion stage is rotationally coupled to second rotor, opposite the turbine shaft and adjacent the first propulsion stage. The magnetic stator is coaxially arranged between the first rotor and the second rotor, forming a magnetic coupling between the and second rotors to drive the second propulsion stage in contra-rotation with respect to the first propulsion stage.

Abstract: A turbomachine comprises a turbine shaft, first and second rotors, first and second propulsion stages, and a magnetic stator. The first rotor is rotationally coupled to the turbine shaft, and coaxially arranged along an axis. The first propulsion stage is rotationally coupled to the first rotor, opposite the turbine shaft. The second rotor is coaxially arranged about the first rotor, and the second propulsion stage is rotationally coupled to second rotor, opposite the turbine shaft and adjacent the first propulsion stage. The magnetic stator is coaxially arranged between the first rotor and the second rotor, forming a magnetic coupling between the and second rotors to drive the second propulsion stage in contra-rotation with respect to the first propulsion stage.