Hybrid-electric propulsion system for an aircraft
First Claim
1. A method of operating a hybrid-electric propulsion system for an aircraft, the method comprising:
- determining a flight phase parameter for the aircraft is equal to a first value;
operating the hybrid-electric propulsion system in an electric charge mode in response to determining the flight phase parameter for the aircraft is equal to the first value, wherein operating the hybrid-electric propulsion system in the electric charge mode comprises driving the electric machine with a combustion engine to generate electrical power, driving a prime propulsor with the combustion engine to generate thrust, and charging an energy storage unit with at least a portion of the electrical power generated;
determining the flight phase parameter for the aircraft is equal to a second value different from the first value;
operating the hybrid-electric propulsion system in an electric discharge mode in response to determining the flight phase parameter for the aircraft is equal to the second value, wherein operating the hybrid-electric propulsion system in the electric discharge mode comprises providing electrical power from the energy storage unit to at least one of an electric propulsor assembly to drive the electric propulsor assembly or to the electric machine to drive one or more components of the combustion engine; and
modifying operation of the combustion engine in response to determining the flight phase parameter for the aircraft is equal to the second value, wherein modifying operation of the combustion engine comprises operating the combustion engine in an idle or sub-idle mode.
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Accused Products
Abstract
A method of operating a hybrid-electric propulsion system for an aircraft includes determining a flight phase parameter for the aircraft is equal to a first value, and operating the hybrid-electric propulsion system in an electric charge mode in response to determining the flight phase parameter for the aircraft is equal to the first value. The method also includes determining the flight phase parameter for the aircraft is equal to a second value different from the first value, and operating the hybrid-electric propulsion system in an electric discharge mode in response to determining the flight phase parameter for the aircraft is equal to the second value.
35 Citations
20 Claims
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1. A method of operating a hybrid-electric propulsion system for an aircraft, the method comprising:
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determining a flight phase parameter for the aircraft is equal to a first value; operating the hybrid-electric propulsion system in an electric charge mode in response to determining the flight phase parameter for the aircraft is equal to the first value, wherein operating the hybrid-electric propulsion system in the electric charge mode comprises driving the electric machine with a combustion engine to generate electrical power, driving a prime propulsor with the combustion engine to generate thrust, and charging an energy storage unit with at least a portion of the electrical power generated; determining the flight phase parameter for the aircraft is equal to a second value different from the first value; operating the hybrid-electric propulsion system in an electric discharge mode in response to determining the flight phase parameter for the aircraft is equal to the second value, wherein operating the hybrid-electric propulsion system in the electric discharge mode comprises providing electrical power from the energy storage unit to at least one of an electric propulsor assembly to drive the electric propulsor assembly or to the electric machine to drive one or more components of the combustion engine; and modifying operation of the combustion engine in response to determining the flight phase parameter for the aircraft is equal to the second value, wherein modifying operation of the combustion engine comprises operating the combustion engine in an idle or sub-idle mode. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17)
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18. A hybrid-electric propulsion system for an aircraft comprising:
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an electric machine; prime propulsor; a combustion engine mechanically coupled to the prime propulsor for driving the prime propulsor and further coupled to the electric machine; an electrical energy storage unit electrically connectable to the electric machine; an electric propulsor assembly electrically connectable to the electrical energy storage unit, the electric machine, or both; and a controller comprising memory and one or more processors, the memory storing instructions that when executed by the one or more processors cause the hybrid-electric propulsion system to perform functions, the functions including; determining a flight phase parameter for the aircraft is equal to a first value; operating the hybrid-electric propulsion system in an electric charge mode in response to determining the flight phase parameter for the aircraft is equal to the first value, wherein operating the hybrid-electric propulsion system in the electric charge mode comprises driving the electric machine with the combustion engine to generate electrical power, driving the prime propulsor with the combustion engine to generate thrust, and charging the energy storage unit with at least a portion of the electrical power generated; determining the flight phase parameter for the aircraft is equal to a second value different from the first value; and operating the hybrid-electric propulsion system in an electric discharge mode in response to determining the flight phase parameter for the aircraft is equal to the second value, wherein operating the hybrid-electric propulsion system in the electric discharge mode comprises providing electrical power from the energy storage unit to the electric propulsor assembly to drive the electric propulsor assembly; modifying operation of the combustion engine in response to determining the flight phase parameter for the aircraft is equal to the second value, wherein modifying operation of the combustion engine comprises operating the combustion engine in a sub-idle mode.
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19. A method of operating a hybrid-electric propulsion system for an aircraft, the method comprising:
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determining a flight phase parameter for the aircraft is equal to a first value; operating the hybrid-electric propulsion system in an electric charge mode in response to determining the flight phase parameter for the aircraft is equal to the first value, wherein operating the hybrid-electric propulsion system in the electric charge mode comprises driving the electric machine with a combustion engine to generate electrical power, driving a prime propulsor with the combustion engine to generate thrust, and charging an energy storage unit with at least a portion of the electrical power generated; determining the flight phase parameter for the aircraft is equal to a second value different from the first value; and operating the hybrid-electric propulsion system in an electric discharge mode in response to determining the flight phase parameter for the aircraft is equal to the second value, wherein operating the hybrid-electric propulsion system in the electric discharge mode comprises providing electrical power from the energy storage unit to at least one of an electric propulsor assembly to drive the electric propulsor assembly or to the electric machine which supplements an output power of the combustion engine and provides power to drive one or more components of the combustion engine while the combustion engine is operated in a low power mode. - View Dependent Claims (20)
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Specification