Abstract: A rotary device associated with drive means. The rotary device comprises a shaft and/or a hub and balancing means for balancing its rotational motion. The balancing means has a hollow chamber surrounding the hub and a solid/fluidic material with thixotropic properties, which fills partly the hollow chamber.

Abstract: A rotor brake for a rotary-wing aircraft includes a rotor shaft, a braking-force actuator configured to be hydraulically actuated, a braking-force pick-up element connected to the rotor shaft and operationally connected to the braking-force actuator, an electromechanical piston control element, and a first hydraulic line connecting the electromechanical piston control element to the braking-force actuator so that the braking-force actuator can be actuated electrohydraulically by the electromechanical piston control element.

Abstract: A three-dimensional stack-type piezo element has at least one surface that is shaped perpendicular to layer planes of the stack, so that, at least in sections, it is not parallel to a stacking direction of the piezo element.

Abstract: Nowadays floor structures in the fuselage of airplanes, which floor structures comprise transverse floor girders, are usually connected to the frame on the right and left by means of rivets and are in turn supported vertically downward by the frame by way of Samer rods. According to one embodiment of the present invention a structural element for an aircraft is stated, comprising an active element and a passive element. In this way additional stiffening of the fuselage, a reduction in fuselage deformation, or active vibration dampening can be provided without additional weight.

Abstract: A three-dimensional stack-type piezo element has at least one surface that is shaped perpendicular to layer planes of the stack, so that, at least in sections, it is not parallel to a stacking direction of the piezo element.

Abstract: A flexible control surface (1; 11, 14) comprises at least two actuators (3), which act on the control surface (1; 11, 14) at different points of action (2) which are offset laterally with respect to the circulating-flow direction (6) with respect to one another. The at least two actuators (3) are designed such that the points of action (2) can be deflected differently when the actuators (3) are operated at the same time. It is thus possible to elastically deform the control surface (1; 11, 14), in particular along the span width direction (9), without kinks, in which case it is possible to achieve uniform transitions along the control surface laterally with respect to the flow direction (6). The invention makes it possible to reduce vortices and noise induced by the control surface.

Abstract: A force generator is configured for attachment to a structure in order to controllably introduce vibrational forces into the structure in order to influence the vibration thereof. The force generator encompasses a flexural arm that is fastenable at least at one end to the structure; and an inertial mass that is coupled to the flexural arm remotely from the fastening end of the flexural arm; the flexural arm being equipped with at least one electromagnetic transducer, and a driving system being provided for the transducer, which system is set up such that by driving the transducer, it warps the flexural arm with the inertial mass and the transducer, and thereby displaces the inertial mass, in such a way that vibrational forces of variable amplitude, phase, and frequency are introducible into the structure.

Abstract: A rotor brake for a rotary-wing aircraft includes a rotor shaft, a braking-force actuator configured to be hydraulically actuated, a braking-force pick-up element connected to the rotor shaft and operationally connected to the braking-force actuator, an electromechanical piston control element, and a first hydraulic line connecting the electromechanical piston control element to the braking-force actuator so that the braking-force actuator can be actuated electrohydraulically by the electromechanical piston control element.

Abstract: Nowadays floor structures in the fuselage of aeroplanes, which floor structures comprise transverse floor girders, are usually connected to the frame on the right and left by means of rivets and are in turn supported vertically downward by the frame by way of Samer rods. According to one embodiment of the present invention a structural element for an aircraft is stated, comprising an active element and a passive element. In this way additional stiffening of the fuselage, a reduction in fuselage deformation, or active vibration dampening can be provided without additional weight.