Abstract: An aircraft includes a gas turbine engine, an electric motor, and a propulsion device. The gas turbine engine and the electric motor are configured to provide a target cumulative output to the propulsion device. An electronic control unit is configured to set the gas turbine engine to a first engine mode to provide a first engine output to the propulsion device, set the electric motor to a first motor mode to provide a first motor output to the propulsion device, a sum of the first engine output and the first motor output being within a predetermined range of the target cumulative output, and in response to a speed of the aircraft reaching a target speed and the first engine output increasing to a second engine output, set the electric motor to a second motor mode.