Hybrid airmobile, comprising the following: a motor (1) and a generator (2); a battery (3) and a
drive motor (4) which is electrically connected to the generator (2); a first
propeller (5) connected to the
drive motor (4), and a second
propeller (6) connected to the generator (2) via a
coupling (7); and a control (8) that is set up: to control the drive of the motor (1), the
clutch (7) and the
drive motor (4) on the basis of a flight factor which includes at least one flight mode, a required power, a
battery charge quantity or a surrounding flight environment of the
hybrid air vehicle, wherein The flight mode includes hovering,
cruise flight and taxiing. the required power needed during hovering or cruising flight is determined based on the
airspeed of the
hybrid air vehicle, and The surrounding flight environment includes: the
population density of a flight area in which the
hybrid aircraft flies, whether a
safety zone exists in the flight area, the presence of a
noise abatement facility, and the
flight altitude of the hybrid aircraft. wherein, when the flight mode transitions from hovering to
cruise flight and the
battery charge is at its maximum charge level, the control (8) is set to operate the first
propeller (5) and the second propeller (6) using power from the battery (3), and wherein the drive motor (4) is configured to drive the first propeller (5), and the generator is configured to drive the second propeller (6) via the
coupling (7) which is configured to selectively connect the generator (2) to the second propeller (6), and where the control (8) is set up to determine, based on the
battery charge level, that the battery (3) should be conserved: to operate the first propeller (5) by driving the drive motor (4) with the power of the battery (3), and to operate the second propeller (6) with power generated by the motor (1), which engages with the generator (2) via the
coupling (7).