Aircraft propulsion system

An aircraft propulsion system comprising:

• a gas turbine engine mounted on an aircraft;
• a generator which is coupled to an engine shaft of the gas turbine engine and generates electricity using rotation of the engine shaft;
• a storage battery which stores an electric power generated by the generator;
• a motor which drives a rotor, using at least one of the electric power which is output from the generator or the electric power which is output from the storage battery;
• a detection unit which detects a torque of the engine shaft;
• an engine controller which controls at least a fuel flow rate of the gas turbine engine;
• and
• a generator controller which controls the operation of the generator,
• wherein when the rate of change in the torque satisfies a predetermined condition, at least the generator controller executes a control to suppress a change in the torque from an initial torque,
• wherein the predetermined condition is that regarding a first threshold value and a second threshold value determined depending on an operating point determined based on a rpm and the torque of the engine shaft, and one of:
• a first condition, in which the torque exceeds the first threshold value;
• or
• a second condition, in which the torque falls below the second threshold value smaller than the first threshold value, is satisfied;
• wherein, when the first condition is satisfied:
• the generator controller increases an amount of power generation of the generator as compared with the amount of power generation of the generator before the first condition is satisfied;
• and
• the engine controller reduces the fuel flow rate depending on a rate of change in the torque of the engine shaft;
• and
• wherein when the second condition is satisfied:
• the generator controller reduces the amount of power generation of the generator as compared with the amount of power generation of the generator before the second condition is satisfied.