Abstract: An aircraft propulsion module comprising a hydrogen storage system (9), at least one electrochemical converter (7) connected to the hydrogen storage system, wherein the at least one electrochemical converter is adapted to convert hydrogen supplied from the hydrogen storage system into electric energy, and at least one electric motor (5) electrically connected to the at least one electrochemical converter, wherein the electric motor is adapted to generate thrust: wherein the propulsion module comprises a first part (1) and a second part (2), each of which comprise a respective fairing (4, 10); the first part and the second part are separable from each other; the first part comprises the at least one electrochemical converter and the at least one electric motor; and the second part comprises a hydrogen storage housing of the hydrogen storage system for storing a reusable hydrogen storage unit. An aircraft comprising at least one such aircraft propulsion module.

Abstract: An aircraft propulsion module comprises a hydrogen storage system, an electrochemical converter (7) connected to the hydrogen storage system, wherein the at least one electrochemical converter is adapted to convert hydrogen supplied from the hydrogen storage system (12) into electric energy, and an electric motor (5) electrically connected to the electrochemical converter, wherein the electric motor is adapted to generate thrust; wherein the propulsion module comprises at least one separation means (9) adapted to separate at least one component of the propulsion module from the propulsion module. An aircraft comprises at least one such aircraft propulsion module. A method for operating a propulsion module comprises that: during operation of the propulsion module, at least one separation means is actuated, by which actuation at least one component of the propulsion module is separated from the remaining propulsion module and then falls from the remaining propulsion module.

Abstract: A fixed-wing aircraft (1) at least comprises at least one vortex generator (6, 7, 8, 11) movable through an outer surface of the aircraft (1) between a retracted state and a fully extended state by at least one electric motor (12), this at least one electric motor (12) being exclusively adapted to actuate this at least one vortex generator (6, 7, 8, 11), and comprises an electronic control unit (13) adapted to control operation of the at least one electric motor (12) for actuation of the at least one vortex generator (6, 7, 8, 11).