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US 2023/0399115 A1Published application
Range extending energy pod (reep) for an aircraft
AssigneeVerdeGo Aero, Inc.
InventorsRichard Pat Anderson, David N. Spitzer, Austin Cassels, Eric Richard Bartsch
Life of this patent
Estimating the term…
Abstract
An energy source for an aircraft includes an enclosure, an engine, an electric generator, and at least one fuel tank configured to provide fuel to the engine; and electrical connectors for outputting power generated by the electric generator to at least one electrical component or electrical bus of the aircraft. The engine, the electric generator, and the at least one fuel tank are each housed within the enclosure.
Claims30
An energy source for an aircraft comprising:
- an enclosure;
- an engine;
- an electric generator;
- at least one fuel tank configured to provide fuel to the engine;
- and
- electrical connectors for outputting power to a propulsion system of the aircraft, wherein the power is generated by the electric generator and output to at least one electrical component or electrical bus of the aircraft,
- wherein the engine, the electric generator, and the at least one fuel tank are each housed within the enclosure, and
- wherein the propulsion system of the aircraft is not within the enclosure of the energy source.
5 more elements
A method for using a first energy source for an aircraft comprising:
- mounting the first energy source to the aircraft, wherein:
- the first energy source comprises an engine and an electric generator,
- the engine and the electric generator are each housed within the enclosure,
- the aircraft comprises a second energy source configured to provide power to a propulsion motor of the aircraft, and
- the second energy source is not located within the enclosure of the first energy source;
- connecting first electrical connectors of the first energy source to second electrical connectors of the aircraft;
- and
- outputting power from the electric generator of the first energy source to at least one electrical component or electrical bus of the aircraft via the first and second electrical connectors, wherein the at least one electrical component or the electrical bus is connected to the propulsion motor of the aircraft, and further wherein the propulsion motor of the aircraft is configured to be powered by the second energy source without use of the first energy source.
5 more elements
Dependencies are inferred from the claim text.