Honeywell International Inc.

Kevin S Dittmar

Yogendra Y Sheoran

Bjoern Schenk

Nicholas A Williams

David H Edmonds

Jeffrey A Turner

Murali Mohan Talapureddi

Jonathan Luc Dion

Jeffrey Sloat

Michael Popescu

Leticia Montes

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.

Adaptive aircraft electrical power distribution system

A micro-auxiliary power unit for supplying electric power to a vehicle includes a thermal resistant enclosure having an intake duct for receiving air, and a source of fuel. A fuel valve is fluidly coupled from the enclosure, and the fuel valve is movable between an opened position and a closed position. The micro-auxiliary power unit includes a Wankel engine to drive an output shaft and a starter-generator coupled to the output shaft to generate electric power. The micro-auxiliary power unit includes a system that has at least one sensor disposed within the enclosure that observes a condition of the enclosure and generates sensor signals, and a controller having a processor that receives the sensor signals, determines the presence of a thermal event within the enclosure and based on the determination, outputs one or more control signals to the fuel valve to move the fuel valve to the closed position.

Micro-auxiliary power units

An auxiliary power unit (APU) 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, the 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.

Auxiliary power unit with integral firebox

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.

Integrated gearless and nonlubricated auxiliary power unit

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Phoenix, AZ, United States of America

Kevin S Dittmar