Abstract: An external load for an aircraft includes a first control unit, designed to be coupled to the aircraft and to exchange control data therewith by a first specified input signal protocol and a first specified output signal protocol; a first payload space for accommodating a first payload; and a second control unit. The first payload is realized as a first function module for performing a function, the performance initiated by the aircraft by transferring control data to the first control unit. The second control unit is, arranged such that the control data according to the first specified output signal protocol serve as input signals for the second control unit. The second control unit is designed to convert the received input signals into a second output signal protocol in accordance with a first conversion protocol and to adapt said input signals to a control protocol of the first function module.

Abstract: A method of kinematic ranging for finding the range R of a jammer moving on a trajectory involves measuring the bearing of the jammer and the rate of change thereof using an airborne detector radar at a first position (24), causing the airborne detector radar to carry out a manoeuvre such that is it displaced in the horizontal plane by a displacement having orthogonal components ?x, ?y, and measuring the bearing of the jammer at a second position subsequent to the manoeuvre. By making an appropriate choice for the components ?x, ?y, the range R may be found with a desired relative range accuracy, and the error in R may be minimized.

Abstract: A multifunctional pod for an aircraft has at least two separate regions. At least one first region of the pod is provided for receiving fuel. A second region of the pod includes at least one receiving device for releasably attaching at least one additional load. The additional load can be releasably attached to the receiving device via a loading opening on the side of the pod facing away from the aircraft.

Abstract: The embodiment relates to the production of reinforced materials, for example reinforced foam materials or reinforced textiles. A multi-needle machine is provided with a plurality of serially arranged repeating units, which are able to move sliders and pins toward and past each other along a circular path so as to create the semi-finished textile products. In this way, it is possible to reinforce components with curved surfaces.

Abstract: An interface apparatus is provided for exchange of different time-critical user data between a host device and a divided medium, by way of a first interface and by way of a second interface, having a resource management device and a temporary memory device. The first interface works with a first clock pulse and the second interface works with a second clock pulse. The first interface and the second interface are connected with the temporary memory device. The resource management device is set up for controlling the exchange of the different time-critical user data between the first interface and the second interface, in such a manner that collisions of the different time-critical user data within the interface apparatus and/or on the divided medium are avoided, in order to allow deterministic behavior during exchange of the different time-critical user data.

Abstract: An optical sensor arrangement includes two sensors arranged one behind the other. The operational spectral ranges of the sensors match, and the first sensor forms an attenuation filter for the second sensor, which is arranged behind the first sensor.

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: A reactive radio interferer includes a plurality of time synchronized transmitting/receiving lines, each of which is designed to alternately carry out-monitoring phases in order to receive the radio spectrum and interference phases in order to transmit an interference signal on the basis of the radio spectrum received in the monitoring phase. Testing of the reactive radio interferer is performed by having one of the transmitting/receiving lines transmit a test signal within a monitoring phase, the test signal being received and evaluated by at least one other transmitting/receiving line.

Abstract: An ejection device for a flight data recorder includes an ejection spindle, which can be detachably connected to the flight data recorder by means of a bayonet coupling. The bayonet coupling can be released by means of force application by the ejection spindle, a disengaging device, which has a compression-resistant housing and into which the ejection spindle can be screwed, and a gas pressure generator, a valve, which is located within the disengaging device and which permits a flow connection between the outlet of the gas pressure generator and the ejection spindle when the ejection spindle is screwed in and which disables the flow connection between the outlet of the gas pressure generator and the ejection spindle when the ejection spindle is unscrewed.

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: 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 welding method for producing an integral bond of fibre-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 fibres. The re-inforcing fibres reorient themselves within the connection region without severing or breaking.

Abstract: A component includes at least first and second plastics component parts which are interconnected in a connection zone. A reinforcing element includes at least one wire which bridges the connection zone. The first and second plastics component parts are welded together and/or are fused together in the connection zone. The plastics component parts may be bonded to one another.

Abstract: A device for machining workpieces a machining tool, a first workpiece-guiding element and a second workpiece-guiding element. The first workpiece-guiding element and the second workpiece-guiding element are designed to guide a workpiece, in a defined way, relative to the machining tool. The machining tool has an axis of rotation and a co-axial opening. The machining tool rotates about the axis of rotation for machining the workpiece. The first workpiece-guiding element is arranged in the opening of the machining tool co-axially to the axis of rotation.

Abstract: A reversible decoupling device is connected to an electromechanical actuator. The reversible decoupling device has an energy storage element configured to store the energy required for a decoupling in the decoupling device. The decoupling device can be re-coupled again after a completed test run so that the decoupling functionality can be easily tested.

Abstract: An automatic learning method for the automatic learning of the forms of appearance of objects in images in the form of object features from training images for using the learned object features in an image processing system comprises determining a feature contribution by a training image to object features by weighted summation of training image features by means of linear filter operations, applied to the feature image, by using a weight image obtained at least from an annotation image and a classification image. This allows faster learning processes and also the learning of a greater variance of forms of appearance of objects and backgrounds, which increases the robustness of the system in its application to untrained images.

Abstract: A pneumatic decoupling device for an electromechanical actuator, in particular, for flight applications includes a pressure accumulator housing for storing a compressed gas, which can be released to a decoupling mechanism of an electromechanical actuator for separating the drive components, so that in the event of a decoupling the electromechanical actuator runs totally freely.

Abstract: A helical actuator includes a plurality of piezo elements for controlling a rotor blade of an aircraft. In this case, the actuator is designed to be arranged so as to be wound around a rotor blade neck and to be fastened to a rotor mast and a rotor blade in each case. Applying a control voltage to the piezo elements causes the actuator to expand, which, in turn, causes the rotor blade to rotate.

Abstract: A flow aid for an infusion structure for infiltrating fibre material with resin to produce a fibre composite component includes a resin-impermeable upper layer and a lower layer which are joined together in a peripheral region of the flow aid and provide a flow space between the two layers. The lower layer provides an outlet for discharging resin out of the flow aid into an interior of the infusion structure. The flow aid includes an inlet for feeding the resin into the flow space, thereby facilitating uniform distribution of the resin over all of the fibre material.

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.