Abstract: An aircraft fuel cell system is provided. The system includes a fuel tank, a reactor for generating hydrogen gas from a fuel, a heating apparatus and a fuel cell. The reactor can process a synthetic fuel produced from biomass. The use, in an aircraft, of a synthetic fuel, produced from biomass, for generating a gas that contains hydrogen is also provided.

Abstract: The invention relates to a system for reducing the loads acting on the fuselage structure in means of transport, in particular in aircraft, comprising at least one sensor element 6, at least one actuator, an active material integrated in the fuselage structure or a supporting active force or position set system, and at least one control unit 11. According to the invention, the amplitude characteristic and/or a phase characteristic of fuselage structure design loads, accelerations and/or deformations are/is modifiable such that a reduction in the design load or acceleration acting on a fuselage structure 5 of a means of transport occurs, as a result of which a significant reduction in weight or improvement in comfort of a means of transport is possible in a particular frequency interval.

Abstract: A device for damping at least one rigid body mode and/or at least one elastic mode of an aircraft, especially for blast load reduction and increase of stability and comfort, in an airplane having at least one sensor, a regulation unit connected to the sensor, and at least one actuator controlling, guiding and/or regulating surfaces of the aircraft. The controller modifies the rigid body modes and/or the one or more elastic modes of the aircraft. With only one sensor signal of a sensor, which is preferably an acceleration signal, an arbitrary number and an arbitrary combination of rigid body modes and/or elastic modes, respectively, may specifically be modified, and the modes obtained are not influenced.

Abstract: The application describes a device 21 for damping at least one rigid body mode and/or at least one elastic mode of an aircraft, especially for blast load reduction and increase of stability and comfort in an airplane 1,22 having at least one sensor means 8,27 as well as a regulation unit 33,42,66 connected to the one or the several sensor means 8, 27 and at least one actuator acting upon controlling, guiding and/or regulating surfaces 40 of the aircraft. By means of the controller 33,42,66, at least one respective rigid body mode and/or at least one elastic mode of the aircraft may be modified, whereby with only one sensor signal of a sensor means 8,27, which is preferably an acceleration signal, an arbitrary number and an arbitrary combination of rigid body modes or rigid body modes and/or elastic modes or modes, respectively, may specifically be modified, and the modes to be obtained are not influenced.

Abstract: The invention relates to a system for reducing the loads acting on the fuselage structure in means of transport, in particular in aircraft, comprising at least one sensor means 6, at least one actuator, and at least one control unit 11. According to the invention, an amplitude characteristic and/or phase characteristic of loads acting on the fuselage structure are/is modifiable such that a reduction in the load acting on a fuselage structure 5 of a means of transport occurs, as a result of which a significant reduction in the loads acting on the fuselage structure of a means of transport is possible in a particular frequency interval. Furthermore, the invention relates to a method for reducing the loads acting on the fuselage structure in means of transport, in particular in aircraft, comprising at least one sensor means 6, at least one actuator, and at least one control unit 11.