An aircraft propulsion system includes: a gas turbine engine attached to an airframe of an aircraft; a generator connected to an engine shaft of the engine; a first electric motor driven using electric power including electric power generated by the generator; a rotor attached to the airframe of the aircraft and driven using a driving force output by the first electric motor; and a control device configured to control an operating state of the engine. The control device includes a flow rate controller which reduces the flow rate of fuel supplied to the engine so that the engine does not misfire when a decrease in output of the engine is promoted using a driving force output by a second electric motor included in the generator, and a drive controller which controls the magnitude of the driving force output by the second electric motor so that the temperature of the engine does not exceed an allowable temperature.
AIRCRAFT PROPULSION SYSTEM
2022-09-15
Patent
Electronic Resource
English