Abstract: A carrier system for carrying out interception maneuvers of a loadbearing paraglider which has a glider having a trailing edge for carrying out the maneuver with at least one interception line is fixed to said edge includes at least one carried load unit, which is connected to the carrier system via a first, short load carrier belt and a second, longer load carrier belt. A carried load connected to the carried load unit is carried by way of the first, short load carrier belt. The trailing edge is adjusted to carry out the maneuver by the gravitational force of the carried load, in that the first, short load carrier belt is separated and the carried load is carried by way of the longer, second load carrier belt.

Abstract: A system for determining the position of a transmitting unit has an arrangement of at least four transmitting units. A first transmitting unit is designed to emit a first transmission signal to each of the three remaining units, each of which is designed to receive the first transmission signal and, thereafter, to return a first response signal to the first unit. The three remaining units each have stored position data relating to desired positions of the arrangement. The first unit is designed to: determine its relative position data relative to the three remaining units based on the returned first response signals, obtain the stored position data relating to the desired positions from the three remaining units, and assign the determined relative position data to the obtained position data relating to a single desired position to determine the position of the first unit within the arrangement based on the assignment.

Abstract: A propeller arrangement for an aircraft, and an aircraft having a propeller arrangement of said type, are specified. The propeller arrangement has a first propeller blade and a second propeller blade, and a propeller mount on which both the first propeller blade and the second propeller blade are mounted. The propeller arrangement furthermore has a drive shaft with a holding unit, and a first connecting unit. The first propeller blade is rotatable about a first axis of rotation and the second propeller blade is rotatable about a second axis of rotation. The propeller mount is pivotable about a pivot axis. The first connecting unit is coupled to the first propeller blade and to the holding unit, such that, in the event of a pivoting of the propeller mount about the pivot axis, the first propeller blade is set in rotational motion about the first axis of rotation.

Abstract: A welding method for connecting at least two workpieces at a connection region by means of friction stir welding using a welding tool having a probe and a shoulder. The method includes rotating the probe around a rotation axis, wherein the connection region is softened by friction heat provided by the probe during said friction stir welding to form a welded seam at the connection region. The method also includes molding, simultaneously with forming the welded seam, at least one of a bevel, a rounding and a chamfer on an edge of the connection region using the shoulder, wherein the shoulder is configured to separate the connection region from the surroundings.

Abstract: A cusped-field thruster for a space system, wherein the cusped-field thruster comprises: at least two substantially annular permanent magnets arranged in an antipolar manner, wherein a magnetic pole piece is formed between the permanent magnets, and an anode, which comprises a permanent-magnetic material. The cusped-field thruster is configured such that a cusp is formed in a region adjacent to the anode of the cusped-field thruster.

Abstract: A welding method for producing an integral bond of fiber-reinforced plastics parts includes a welding head penetrating one of the plastics parts. The method includes reinforcing at least a first plastics part by a plurality of directional fibers. The re-inforcing fibers reorient themselves within the connection region without severing or breaking.

Abstract: To provide a simple seat fastening device with enhanced flexibility and the possibility of an easy movement of vehicle seats, a seat fastening device for fastening vehicle seats in a vehicle is provided comprising a seat track and a slider in a sliding engagement with the seat track. The slider includes a seat fixation element to fix a foot of a vehicle seat, wherein the seat track includes a C-shaped profile and the slider includes a base inserted in the C-shaped profile and wherein the slider includes a clamp to clamp the slider against an inner surface of the C-shaped profile. At least one linear roller contact bearing is located between the C-shaped profile and the slider.

Abstract: A device for consolidating a thermoplastic preform, in particular a carbon fiber thermoplastic preform includes a heating element, e.g., an LED array, for heating the preform and a consolidation element, e.g., a consolidation roller, for exposing the preform to pressure and for cooling the preform. In order to consolidate the preform, the heating element and consolidation element are arranged and movable relative to each other in such a way that the preform can be exposed to pressure and cooled by the consolidation element after heated by means of the heating element.

Abstract: A method for providing spacers on a construction component to be adhered involves applying a planar formation, including passages, on the construction component to be adhered, and inserting a setting liquid in the passages of the planar formation, so that the liquid forms spacer on the construction component to be adhered after setting and peeling off the planar formation. The spacer ensures a predetermined minimum bondline when adhering the construction component.

Abstract: A testing arrangement serves for controlling the manufacturing of a fiber reinforced component. The testing arrangement includes an inspection device with a sensor system, with the inspection device being configured to move on and/or above one or more material layer(s) and/or a surface of the component and to examine the material layer(s) or the surface with the sensor system. A device serves for automated manufacturing of a fiber reinforced plastic laminate. The device includes a forming tool, a laying head for automated laying of material layers in the forming tool as well as a testing arrangement.

Abstract: A transition piece, which can be mounted in a recess, and which can form a continuous surface from a structural component of an airplane to a control surface, which is connected to the structural component in a pivotable manner is described. The transition piece can be mounted between an edge of the structural component and a lateral edge of the control surface such that the transition piece is fastened in a pivotable manner both to the edge of the structural component and to the lateral edge of the control surface. According to an example, the transition piece has a planar design and can be deformed within said plane, that is, the transition piece can be stretched or compressed within this plane.

Abstract: A connection element includes a composite component with a cured epoxy resin, a first layer including a first thermoplastic polymer and an intermediate layer arranged between the composite component and the first layer, the first layer containing both the cured epoxy resin of the composite component and the first thermoplastic polymer of the first layer. The first thermoplastic polymer has a melting point above a curing temperature of the epoxy resin and is soluble at a temperature of at least 150° C. in the epoxy resin used for producing the composite component.

Abstract: A fiber-reinforced composite material includes a bulk portion with a bulk matrix having reinforcing fibers embedded therein, and a surface portion with a plurality of laminated first layers serving as “expanding layers”, which expand and/or delaminate during fire impact. The surface portion also includes a plurality of laminated second layers different from the first layers and serving as “barrier layers”. The expanding layers and barrier layers can be arranged in an alternating sequence.

Abstract: An aerial vehicle having a low radar signature includes a first side on which turbine openings, and payload bays or landing gear bays are disposed. A second side of the aerial vehicle is designed to have a smaller radar signature than the first side.

Abstract: The invention relates to an aircraft which can both take off and land vertically and can hover and also fly horizontally at a high cruising speed. The aircraft has a support structure, a wing structure, at least three and preferably at least four lifting rotors and at least one thrust drive. The wing structure is designed to generate a lifting force for the aircraft during horizontal motion. To achieve this the wing structure has at least one mainplane provided with a profile that generates dynamic lift. The wing structure is preferably designed as a tandem wing structure. Each of the lifting rotors is fixed to the support structure, has a propeller and is designed to generate a lifting force for the aircraft by means of a rotation of the propeller, said force acting in a vertical direction. The thrust drive is designed to generate a thrust force on the support structure, said force acting in a horizontal direction. The lifting rotors can have a simple construction, i.e.

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: The present invention relates to an arrangement for providing a test environment for testing test objects. The arrangement includes a first test case implementation unit and a second test case implementation unit, as well as a first test object and a second test object. In one embodiment, the test environment is configured such that at least the first test case implementation unit is coupled to at least one of the first test object and the second test object for implementing a test case.

Abstract: The embodiments relate to a switch device for an electrochemical energy store having: a film transistor device that comprises at least one organic transistor, can be mounted in a planar manner on at least one electrode of the electrochemical energy store, can be controlled by an external voltage source, and is designed in the form of a controllable electrical resistor that is connected, in series, to an internal resistor of said electrochemical energy store.

Abstract: A method for an aircraft for handling potential collisions in air traffic includes providing by a collision avoidance system a collision avoidance maneuver to avoid a collision with one or more intruders. The collision avoidance system is configured to obtain information about these intruders. The method includes further providing flight management constraints from an onboard flight system. Further, the method includes providing flight situation data from a navigation system. The method includes generating a modified collision avoidance maneuver based on the collision avoidance maneuver provided by the collision avoidance system, the flight situation data and the flight management constraints.

Abstract: A network module for sending and/or receiving of data packages from a network arrangement located in a network with ring structure, wherein the data package includes at least one data package segment, a source address, a destination address and an identification number. The network module includes a first network interface and a second network interface, for receiving and/or sending of data packages via the ring structure, a processor configured to determine, based on the destination address, if data packages received are directed to the network module and to determine if the source address and/or the destination address are contained in a predefined list of the network participants, to determine, based on the source address and the identification number, if a copy of a data package directed to the network module is already created in a memory, to create a copy of the data package in the memory.