Method for braking an aircraft turbine engine including a fan or a propeller connected to a turbine by a shaft and an electric generator connected to the shaft, the method comprising the following steps: a request to brake the turbine engine by thrust reversal; a calculation of a turbine braking setpoint by a control system; and in response to the braking setpoint, an adjustment by the control system of a resistance of a dissipative load to draw electric power from the electric generator to the dissipative load.

Method for braking an aircraft turbine engine including a fan or a propeller connected to a turbine by a shaft and an electric generator connected to the shaft, the method comprising the following steps: a request to brake the turbine engine by thrust reversal; a calculation of a turbine braking setpoint by a control system; and in response to the braking setpoint, an adjustment by the control system of a resistance of a dissipative load to draw electric power from the electric generator to the dissipative load.