Modular power units for aircraft
AssigneeRolls-Royce North American Technologies Inc.
InventorsStephen Long, Dwayne Bevis, Sean Guitar
Life of this patent
Estimating the term…
Abstract
Systems and methods are disclosed for providing flexible, scalable, and controllable electrical power to an aircraft. In some embodiments, a modular power unit comprises a container containing a power generation unit, a control system, a conditioning system, and an environmental control system. The power generation unit produces a generated power. The control system provides control signals to the power generation unit and controls at least one parameter of the generated power. The conditioning system receives and conditions the generated power and provides an output power to the power bus of the aircraft. The environmental control system provides a temperature regulating fluid to the power generation unit.
Claims13
A modular power unit for an aircraft, the aircraft having a power bus and a data bus, the modular power unit comprising:
- a container dimensioned as a standardized unit load device to be received in a cargo hold of the aircraft, the container containing:
- a power generation unit for producing a generated power, the power generation unit comprising a chemical power generation device;
- a control system for providing control signals to the power generation unit, the control signals controlling at least one parameter of the generated power of the power generation unit;
- a conditioning system for receiving and conditioning the generated power of the power generation unit;
- and
- an environmental control system for providing a temperature regulating fluid to at least the power generation unit and the conditioning system;
- a data connection for connecting the control system of the container to the data bus of the aircraft;
- and
- a power connection for connecting the conditioning system to the power bus of the aircraft, wherein the conditioning system provides a power output to the power bus, wherein the power output supplies propulsive electrical demands of the aircraft using a hybrid electric or turbo-electric propulsion system.
A system for supplying electrical power comprising:
- an aircraft having a power bus and a data bus;
- a plurality of modular power units, each modular power unit comprising a container dimensioned as a standardized unit load device, containing:
- a power generation unit for producing a generated power;
- a control system for providing control signals to the power generation unit, the control signals controlling at least one parameter of the generated power of the power generation unit;
- a conditioning system for receiving and conditioning the generated power of the power generation unit;
- and
- an environmental control system for providing a temperature regulating fluid to at least the power generation unit and the conditioning system;
- one or more data connections for connecting the control system of each modular power unit to the data bus of the aircraft;
- and
- one or more power connections for connecting the conditioning system of each modular power unit to the power bus of the aircraft;
- wherein the conditioning system of one or more modular power units provides a power output to the power bus, wherein the power output meets propulsive electrical demands of the aircraft using a hybrid electric or turbo-electric propulsion system.
Dependencies are inferred from the claim text.