Unmanned Aircraft and Operation Method for the Same
An unmanned aircraft includes a propulsion system having a diesel or kerosene internal combustion engine and a charger device for engine charging. The propulsion system can be a hybrid propulsion system or a parallel hybrid propulsion system.
1 - 15 . (canceled)
16 . An unmanned aircraft, comprising:
a propulsion system that comprises a diesel or kerosene internal combustion engine; and
a charging device configured to charge the internal combustion engine of the unmanned aircraft.
17 . The unmanned aircraft of claim 16 , wherein the propulsion system is a hybrid propulsion system which, in addition to the internal combustion engine, comprises an electric motor and an energy storage device configured to store electric energy for driving the electric motor.
18 . The unmanned aircraft of claim 17 , wherein the hybrid propulsion system comprises a switchable coupling device with which the internal combustion engine or the electric motor can be selectively connected to a thrust generator.
19 . The unmanned aircraft of claim 17 , wherein the internal combustion engine and the electric motor are configured to be selectively operated in parallel or in series.
20 . The unmanned aircraft of claim 16 , wherein the charging device is configured for multi-stage charging or comprises at least a first charger and a second charge for multi-stage charging.
21 . The unmanned aircraft of claim 16 , wherein the charging device comprises at least one charger that is configured to be driven by exhaust gas energy.
22 . The unmanned aircraft of claim 16 , wherein the charging device comprises at least one mechanical charger.
23 . The unmanned aircraft of claim 22 , wherein the at least one mechanical charger is driven by an output shaft of the internal combustion engine or through an electric motor.
24 . The unmanned aircraft of claim 23 , wherein
the propulsion system is a hybrid propulsion system which, in addition to the internal combustion engine, comprises an electric motor and an energy storage device configured to store electric energy for driving the electric motor, and
the mechanical charger is configured to be driveable by the electric motor of the hybrid propulsion.
25 . The unmanned aircraft of claim 17 , further comprising:
a controller configured to control the charging device or the hybrid propulsion in accordance with various parameters in flight operation.
26 . The unmanned aircraft of claim 25 , wherein the controller is configured to control switching on and off of a first or second stage of the engine charging or the switching on and off of the electric motor, in accordance with at least one of the parameters of altitude, angle of a takeoff or landing flight to the vertical, desired velocity, allowable heat output, allowable operating noise level, or temperature.
27 . The unmanned aircraft of claim 16 , wherein the internal combustion engine is a rotary piston engine.
28 . The unmanned aircraft of claim 16 , wherein the aircraft has a maximum takeoff weight of more than 250 kg.
29 . A method for operating an unmanned aircraft, the method comprising:
controlling charging of an internal combustion engine of a propulsion system of the unmanned aircraft or a cooperation between an internal combustion engine and electric motor of a hybrid propulsion in accordance with at least one of the parameters of altitude, angle of a takeoff or landing flight to the vertical, desired velocity, allowable heat output, allowable operating noise level, or temperature.
30 . The method of claim 29 , wherein upon violation of a predetermined limit value for the at least one parameter, then the method comprises switching on or off:
a first charging stage;
a second charging stage,
a mechanical charger,
an electric charger,
a first turbocharger,
a second turbocharger,
an electric motor in addition to the running internal combustion engine, or
the internal combustion engine in addition to the running electric motor.