Abstract: An adaptive aircraft electrical power distribution system includes an aircraft power source, a power connector, an aircraft power distribution bus, and a bidirectional power controller. The aircraft power source is operable to generate and supply electrical power. The power connector is mounted on a fuselage of the aircraft. The aircraft power distribution bus is operable to distribute electrical power to an aircraft electrical load. The bidirectional power controller is mounted in the aircraft and is electrically coupled to the aircraft power source, the aircraft power connector, and the aircraft power distribution bus. The bidirectional power controller is configured to: sense when the aircraft power source is generating and supplying electrical power, sense when electrical power is being supplied to the power connector from an external power source, and selectively couple at least one of the aircraft power source or the power connector to the aircraft power distribution system.

Abstract: An adaptive aircraft electrical power distribution system includes an aircraft power source, a power connector, an aircraft power distribution bus, and a bidirectional power controller. The aircraft power source is operable to generate and supply electrical power. The power connector is mounted on a fuselage of the aircraft. The aircraft power distribution bus is operable to distribute electrical power to an aircraft electrical load. The bidirectional power controller is mounted in the aircraft and is electrically coupled to the aircraft power source, the aircraft power connector, and the aircraft power distribution bus. The bidirectional power controller is configured to: sense when the aircraft power source is generating and supplying electrical power, sense when electrical power is being supplied to the power connector from an external power source, and selectively couple at least one of the aircraft power source or the power connector to the aircraft power distribution system.

Abstract: An auxiliary power unit with integral firebox provides an integral unit for aircraft to utilize an APU without the use of a separate firebox. The present invention comprises a turbomachine intake air duct secured to an enclosure, and said enclosure having a bleed air port extending from the combustor to outside of the enclosure, with an APU secured therein. The APU can be retrofitted to existing aircraft, or installed in newly built aircraft.

Abstract: An auxiliary power unit (APU) includes a compressor, a turbine, a combustor, and a starter-generator unit all integrated within a single containment housing. The turbine has an output shaft on which the compressor is mounted, and the starter-generator unit is coupled to the turbine output shaft without any intervening gears. The rotating components are all rotationally supported within the containment housing using bearings that do not receive a flow of lubricating fluid.