Dual engine hybrid-electric aircraft
View Patent ↗An aircraft propulsion system includes at least one hybrid-electric power plant for delivering power to an air mover for propelling an aircraft. The at least one hybrid-electric power plant includes a first thermal engine and an electrical motor arranged in a parallel drive configuration or in an in-line drive configuration. The aircraft propulsion system includes a second thermal engine operatively connected to the electrical motor to power the electrical motor. A method for providing propulsion to an aircraft includes delivering power to an air mover for propelling the aircraft with at least one hybrid-electric power plant. The at least one hybrid-electric power plant includes a first thermal engine and an electrical motor arranged in a parallel drive configuration or in an in-line drive configuration. The method includes powering the electrical motor with a second thermal engine.
1. An aircraft propulsion system, comprising:
first and second hybrid-electric power plants for delivering power to respective air movers for propelling an aircraft, wherein each hybrid-electric power plant includes a respective thermal engine and a respective electrical motor arranged in a parallel drive configuration; and
a second thermal engine operatively connected to the electrical motor of the first hybrid-electric power plant and the electrical motor of the second hybrid-electric power plant through an electrical machine and a power conversion electronics system to power the electrical motors of the first and second hybrid-electric power plants.
2. The aircraft propulsion system as recited in claim 1 , further comprising a fuel storage in fluid communication with each thermal engine to provide fuel thereto.
3. The aircraft propulsion system as recited in claim 1 , wherein the power conversion electronics system is operatively connected to the electrical machine between the electrical machine and the respective electrical motors of the first and second hybrid-electric power plants.
4. The aircraft propulsion system as recited in claim 1 , wherein the first hybrid-electric power plant is positioned on a first wing of the aircraft.
5. The aircraft propulsion system as recited in claim 4 , wherein the second hybrid-electric power plant is positioned on a wing of the aircraft opposite from the first wing of the aircraft.
6. A method for providing propulsion to an aircraft comprising:
delivering power to respective air movers for propelling the aircraft with first and second hybrid-electric power plants, wherein each hybrid-electric power plant includes a respective thermal engine and a respective electrical motor arranged in a parallel drive configuration; and
powering the electrical motor of the first hybrid-electric power plant and the electrical motor of the second hybrid-electric power plant with a second thermal engine through an electrical machine and a power conversion electronics system.
7. The method as recited in claim 6 , providing fuel from a fuel storage to each thermal engine.