Rotorcraft, in particular helicopter, comprising a hybrid drive, with at least one, preferably a plurality of electric drives for driving a main rotor of a rotorcraft, in particular a helicopter, wherein the at least one electric drive comprises: means for coupling the at least one electric drive to a rotor mast which is configured to be coupled in a rotationally fixed manner to a drive unit of a helicopter rotor gear and which is coupled in a rotationally fixed manner to the main rotor or a tail rotor of the rotorcraft, wherein the at least one electric drive is designed as at least one electric ring motor, and wherein the at least one electric ring motor is arranged and mounted coaxially to the rotor mast, and: a second drive designed as a thermodynamic prime mover, for example an internal combustion engine, turbine engine, spark ignition engine, diesel engine, fuel cell drive or the like characterized in that the rotorcraft comprises a control unit and a power electronics unit, wherein the power electronics unit is configured to interact with the control unit, an electrical energy source in the form of a battery storage unit, and the electric drive, and in particular the power electronics unit is configured to receive electrical energy from the energy source and pass it on to the electric drive in the form of electrical current, wherein the control unit is configured to receive sensor input data from the second drive, from the electric drive, from the pilot control, and from the electric energy source; and is configured to forward output data to the power electronics unit, and wherein the control unit is designed with a logic such that, starting from the power electronics unit, the output power of the electric drive is configured to be adjusted depending on the flight conditions, the flight profile, the battery level and the output power originating from the second drive, and wherein the rotorcraft comprises additional power generation modules mechanically coupled to the second drive for charging the battery storage unit, whereby a hybrid drive of serial design is obtained. means for coupling the at least one electric drive to a rotor mast which is configured to be coupled in a rotationally fixed manner to a drive unit of a helicopter rotor gear and which is coupled in a rotationally fixed manner to the main rotor or a tail rotor of the rotorcraft, wherein the at least one electric drive is designed as at least one electric ring motor, and wherein the at least one electric ring motor is arranged and mounted coaxially to the rotor mast, and: a second drive designed as a thermodynamic prime mover, for example an internal combustion engine, turbine engine, spark ignition engine, diesel engine, fuel cell drive or the like characterized in that the rotorcraft comprises a control unit and a power electronics unit, wherein the power electronics unit is configured to interact with the control unit, an electrical energy source in the form of a battery storage unit, and the electric drive, and in particular the power electronics unit is configured to receive electrical energy from the energy source and pass it on to the electric drive in the form of electrical current, wherein the control unit is configured to receive sensor input data from the second drive, from the electric drive, from the pilot control, and from the electric energy source; and is configured to forward output data to the power electronics unit, and wherein the control unit is designed with a logic such that, starting from the power electronics unit, the output power of the electric drive is configured to be adjusted depending on the flight conditions, the flight profile, the battery level and the output power originating from the second drive, and wherein the rotorcraft comprises additional power generation modules mechanically coupled to the second drive for charging the battery storage unit, whereby a hybrid drive of serial design is obtained. a second drive designed as a thermodynamic prime mover, for example an internal combustion engine, turbine engine, spark ignition engine, diesel engine, fuel cell drive or the like characterized in that the rotorcraft comprises a control unit and a power electronics unit, wherein the power electronics unit is configured to interact with the control unit, an electrical energy source in the form of a battery storage unit, and the electric drive, and in particular the power electronics unit is configured to receive electrical energy from the energy source and pass it on to the electric drive in the form of electrical current, wherein the control unit is configured to receive sensor input data from the second drive, from the electric drive, from the pilot control, and from the electric energy source; and is configured to forward output data to the power electronics unit, and wherein the control unit is designed with a logic such that, starting from the power electronics unit, the output power of the electric drive is configured to be adjusted depending on the flight conditions, the flight profile, the battery level and the output power originating from the second drive, and wherein the rotorcraft comprises additional power generation modules mechanically coupled to the second drive for charging the battery storage unit, whereby a hybrid drive of serial design is obtained.