Abstract: An arrangement for mechanically changing a surface includes an insulating layer, a pair of electrodes, which is arranged on or in the insulating layer, and a piezo element, which is arranged on or in the insulating layer. The piezo element is separated from the pair of electrodes by the insulating layer. The pair of electrodes is designed to generate in a region of the piezo element an electric field, which causes the piezo element to carry out a mechanical change of shape, in order in this way to mechanically change a surface of the arrangement. The pair of electrodes is also designed to generate the electric field such that the electric field has a minimum field strength in a surrounding area of the arrangement, in order in this way to generate a plasma in the surrounding area of the arrangement.

Abstract: A method of preventing separation of a fluid flow flowing over a flow surface is described. The method includes generating longitudinal vortices for suppressing or delaying separation of the flow, and enhancing the longitudinal vortices. A flow body system having a flow body and a flow control arrangement is further described.

Abstract: An arrangement for mechanically changing a surface includes an insulating layer, a pair of electrodes, which is arranged on or in the insulating layer, and a piezo element, which is arranged on or in the insulating layer. The piezo element is separated from the pair of electrodes by the insulating layer. The pair of electrodes is designed to generate in a region of the piezo element an electric field, which causes the piezo element to carry out a mechanical change of shape, in order in this way to mechanically change a surface of the arrangement. The pair of electrodes is also designed to generate the electric field such that the electric field has a minimum field strength in a surrounding area of the arrangement, in order in this way to generate a plasma in the surrounding area of the arrangement.

Abstract: A cleaning assembly for leading edges of airfoils, in particular airfoil profiles of aircraft or spacecraft, has a cleaning device that is provided with at least one cleaning member and is intended for applying mechanical pressure to a planar region of an airfoil, and has a drive having at least one drive element, which drive moves the cleaning device along the surface to be cleaned. It is proposed to adhesively hold the cleaning device on the airfoil by the at least one cleaning member and/or for the at least one cleaning member to have a sticky surface and for the at least one cleaning member to be dimensionally stable and have flexible contours.

Abstract: In order to maintain a surface region of an aircraft free of ice in a particularly energy-efficient manner, a device for deicing and/or for preventing ice formation is provided on an aircraft. The device includes a heat emitting device for emitting heat at a surface region of the aircraft, the heat emitting device is designed to dissipate heat along a line in order to produce a predetermined breaking point or a predetermined breaking line or parting line in ice accumulating on the surface region.

Abstract: A coupling device for supporting a first wing section against a second wing section of an aircraft, and configured for passive flight load alleviation includes a housing including a chamber including a first portion and a second portion and filled with a fluid, a piston device movably arranged in the chamber and separating the first portion from the second portion in a fluid tight manner, a first fluid pathway connecting the first portion to the second portion, a first pressure relief valve arranged in the first fluid pathway and blocking the first fluid pathway, if the pressure in the second portion is smaller than a first relief pressure and opening the first fluid pathway, if the pressure in the second portion is greater than the first relief pressure. In addition, the coupling device can be used to actuate the second wing section against the first wing section.

Abstract: A flow actuator module having a support device, a flow actuator mounted on the support device to be movable between a retracted position and a deployed position and which has an actuation portion and a flow plate rigidly connected to the actuation portion, an electrical coil arranged on the support device, and an armature on the actuation portion of the flow actuator and which has a magnetizable metal material. The flow actuator, in the retracted position, can be fixed in a positionally static manner relative to the support device by the armature by generation of an electrical current flow through the coil. A flow body system having a flow actuator module of the type, and an aircraft, are also disclosed.

Abstract: An actuator mounting method for mounting at least one actuator involves providing a skin structure and at least one actuator, and fixing the at least one actuator to the inner surface of the skin structure.

Abstract: A method of preventing separation of a fluid flow flowing over a flow surface is described. The method includes generating longitudinal vortices for suppressing or delaying separation of the flow, and enhancing the longitudinal vortices. A flow body system having a flow body and a flow control arrangement is further described.

Abstract: A cleaning assembly for leading edges of airfoils, in particular airfoil profiles of aircraft or spacecraft, has a cleaning device that is provided with at least one cleaning member and is intended for applying mechanical pressure to a planar region of an airfoil, and has a drive having at least one drive element, which drive moves the cleaning device along the surface to be cleaned. It is proposed to adhesively hold the cleaning device on the airfoil by the at least one cleaning member and/or for the at least one cleaning member to have a sticky surface and for the at least one cleaning member to be dimensionally stable and have flexible contours.

Abstract: A coating method for producing a function layer on mechanically loaded components or surfaces includes providing or applying a first material layer of a first material or substrate matrix having a mechanical flexibility higher than that of a second material on a substrate constituting the component or the surface, respectively, structuring the first material layer such that the material layer surface of the first material layer, which is opposite to the substrate, obtains a three-dimensionally molded basic structure with projections and recesses, and coating the material layer surface of the first material layer with a second material layer of the second material in such a way that the second material layer adopts substantially the basic structure of the material layer surface with the projections and recesses. Also, surface layer structures can be produced by this method.

Abstract: A force generator for introducing vibrational forces into a structure for vibration control of the structure includes an inertial mass, at least one actuator for generating a vibratory movement of the inertial mass relative to the structure, and a drive circuit constructed from components for driving the at least one actuator. At least part of the inertial mass is formed by one component of the drive circuit.

Abstract: An improved actuator arrangement for operating a driven element with different actuators. The actuator arrangement comprises a first actuator that drives a driven element in a first direction via a first output member and a second actuator that drives the driven element in a second direction opposite to the first direction via a second output member. The first and second actuators are configured to work in a counter-acting manner to move the driven element in the first and second directions. An additional connecting and supporting device is connected between the first and second output members to support the output members to bear transversal forces transversal to the moving direction and/or to bear pre-load force for pre-loading the actuators.

Abstract: A coupling device for supporting a first wing section against a second wing section of an aircraft, and configured for passive flight load alleviation includes a housing including a chamber including a first portion and a second portion and filled with a fluid, a piston device movably arranged in the chamber and separating the first portion from the second portion in a fluid tight manner, a first fluid pathway connecting the first portion to the second portion, a first pressure relief valve arranged in the first fluid pathway and blocking the first fluid pathway, if the pressure in the second portion is smaller than a first relief pressure and opening the first fluid pathway, if the pressure in the second portion is greater than the first relief pressure. In addition, the coupling device can be used to actuate the second wing section against the first wing section.

Abstract: The invention relates to a fluid valve arrangement having a bistable fluid valve for at least one fluid line with a valve body which can be moved into two positions for two switching states, a pressure pulse generator being provided for valve switchover in the feed line for switching over a feed line and a return line between two flow lines, and the fluid valve comprising a reversing unit which has two chambers which are separated from one another by a bistable surface element, the two chambers being connected to the two flow lines and the bistable surface element being operatively coupled to the valve body in order to actuate it. As a result, a bistable fluid valve is provided which can be reversed by way of pressure pulses or pressure flanks and otherwise has no energy requirement.

Abstract: An electric circuit with one power amplifier (V1) for at least two piezoelectric actuators (C1, C2), said piezoelectric actuators (C1, C2) being in preferably antagonist arrangement connected mechanically in series and being connected electrically with each other and operated or clocked by a control circuit, such as a pulse modulator circuit, for time-variant energizing of the piezoelectric actuators (C1, C2) in push-pull fashion, said power amplifier (V1) being connected to a junction point between the two piezoelectric actuators (C1, C2), characterized in that said power amplifier (V1) is connected to a one directional diode (D1) and in that two buffer capacitors (C3, C4) and two static resistors (R3, R4) are provided downstream the one directional diode (D1) with regard to the power amplifier (V1).

Abstract: A bistable fluid valve is characterized by two valve chambers which are arranged adjacent to one another and are closed off with respect to one another by a partition and each have an inlet opening and an outlet opening situated opposite one another, by an S-shaped elastic strip element which extends through both valve chambers, is articulatedly mounted in the region of the partition and can assume two positions in which it sealingly closes off either one or the other outlet opening, and also by an actuation element which is fastened to the strip element and by means of which the strip element can be switched between the two positions. The fluid valve according to the invention comprises only a single movable component of very low mass, which can thus operate in a fast-reacting manner.

Abstract: To simplify the construction of lever kinematics under difficult installation and boundary conditions, a construction method for constructing a lever kinematics comprises a main lever and at least one connecting strut. The main lever can be rotated about a main lever axis by a predetermined angle, and the connecting strut connects a force application point to a hinge point on the main lever. A first position of the force application point is predetermined at the beginning of the rotational angle and a second position of the force application point is predetermined at the end of the rotational angle. The method includes representing a line of the possible hinge points for the given rotational angle, the main axis and the first and second positions of the force application point, and selecting the hinge point on the line.

Abstract: A device for reducing structural vibrations of airfoils in an aircraft comprises, in the region of the airfoil tips, at least one force generator acting substantially in the direction of movement of the vibrations. This arrangement has the advantage that such a force generator is considerably less susceptible to wear than conventional aerodynamic flaps and therefore effective vibration damping is possible with a reduced outlay on maintenance and greater efficiency.

Abstract: A force generator for introducing vibrational forces into a structure for vibration control of the structure includes an inertial mass, at least one actuator for generating a vibratory movement of the inertial mass relative to the structure, and a drive circuit constructed from components for driving the at least one actuator. At least part of the inertial mass is formed by one component of the drive circuit.