Abstract: A wind power rotor has a first and second rotor device. The first rotor device rotates about a first axis of rotation and has at least two rotor blades moving on a peripheral track about the first axis of rotation. The rotor blades are such that they describe a virtual first shell surface of a virtual first rotating body upon rotation about the first axis of rotation. The second rotor device rotates about a second axis of rotation and has a second rotating body with a closed second shell surface. The second rotating body is arranged at least partially inside of the virtual first rotating body. The first rotor device can be driven by wind in a first direction of rotation and the second rotor device has a drive device, and can be driven in a second direction of rotation which is opposite that of the first direction of rotation.

Abstract: A camera system for detecting and tracking moving objects located at a great distance includes a camera having a camera lens system, and a position stabilizing device. The camera includes a first image sensor and a second image sensor. The camera lens system includes optical elements for focusing incident radiation onto a radiation sensitive surface of the first image sensor and/or the second image sensor with a reflecting telescope arrangement and a target tracking mirror arrangement, and a drive device for a movable element of the target tracking mirror arrangement and with a control system for the drive device. The optical elements includes a first subassembly of optical elements having a first focal length and associated with the first image sensor, and a second subassembly of optical elements having a second focal length that is shorter than the first focal length and associated with the second image sensor.

Abstract: An apparatus for making contact between a T/R module and a test device, the apparatus including a mechanically guided contact-making unit having a plurality of contact elements for contacting the T/R module. A triplate line substrate is arranged is electrically connected to the T/R module, via which the RF signals can be passed to the test device. One or more register pins for defined alignment of the T/R module with respect to the contact-making unit and a fixing unit for mechanical fixing of the T/R module are provided. A shifting device has a plurality of inclined planes that convert a shifting movement of the shifting device to a movement of the contact-making unit toward the T/R module at right angles to the shifting direction. When the contact-making unit reaches a defined final position the contact is made with the T/R module via the contact elements in one process.

Abstract: A method for adding calcium to an aluminum-scandium alloy to produce an aluminum-scandium-calcium alloy involves combining aluminum, scandium, and calcium in a melt and the common melt is quenched at a high velocity.

Abstract: A method for the identification of objects in a predetermined target area involves recording a first and a second height profile of the target area, wherein the two height profiles are recorded at a predeterminable time interval. A height difference profile is determined from the first and the second height profile. The height difference profile is subdivided in equidistant horizontal height sections. The positions of the centroids of the surface areas enclosed by the respective contour lines of the horizontal height sections are calculated and the determined height difference profile and the calculated centroids of the surface areas are supplied to a system for classifying objects.

Abstract: Method for determining a distance between two external stores on an aircraft or aerial vehicle and aircraft with at least two external stores. The method includes separating one of the two stores from the aircraft or aerial vehicle in flight, and determining a chronological course of a distance during the separation operation with at least one magnetic field sensor.

Abstract: In a method for determining the distance of an object flying through the atmosphere and emitting radiation energy, the spectral intensity distribution of the radiation emitted by the object in a predefined wavelength range is detected. An intensity distribution spectrum of the object is measured in the region of an absorption structure of the atmosphere, and a point having an extremal gradient on a flank of an intensity rise or fall, caused by the atmospheric absorption structure, in the measured intensity distribution spectrum is determined. The path length traveled by the radiation through the atmosphere, and therefore also the distance between the detector and the object, are determined by comparison with known transmission data for the atmosphere.

Abstract: The invention relates to a device (100) for identifying biotic particles in a medium to be analyzed, comprising a measuring cell (104), through which the medium to be analyzed can flow and in which the identification of the biotic particles is carried out by means of Raman spectroscopy, and a feed (102) by means of which the medium to be analyzed can be fed to the measuring cell (104). The device (100) according to the invention is characterized in that the feed (102) comprises at least one sensor (101) with which the presence of biotic particles in the medium flowing through the feed (102) can be ascertained. The feed (102) has a controllable bypass valve (103) downstream of the sensor (101), and the medium can be selectively fed to the measuring cell (104) or to a bypass channel (106) via said bypass valve.

Abstract: The invention relates to a process and a device for manufacturing a perform (42) for a load path aligned fiber composite structure. The process includes cutting off relatively short fiber band pieces (40, 40?, 40?) from a spread fiber band (14), placing the fiber band pieces (40, 40?, 40?) at a predetermined position and fixing them at this position by means of a binder material (38).

Abstract: A laying device (28) that is configured to lay fiber pieces (40, 40?, 40?) has a flexible surface (164) that applies and presses the fiber pieces against a preform surface.

Abstract: An annular slot antenna includes an inner conductor divided by a dielectric gap into a rear section and a front section. An inner conductor of a coaxial feed line is contacted with the front section of the inner conductor and the outer conductor of the coaxial feed line is contacted with the rear section.

Abstract: A fuel cell supply device that generates hydrogen for fuel cells in an aircraft includes a reaction chamber which reacts hydrogenated polysilanes or mixtures thereof with water; a feed device that feeds at least one reactant into the reaction chamber; and a discharge device that leads hydrogen formed in the reaction to a fuel cell.

Abstract: A hybrid rotor for an aircraft includes a Magnus rotor rotatable around a Magnus rotor axis and a transverse flow rotor that is kept rotating around an axis of rotation and has a number of axially extending rotor blades that are actuatable to rotate around the axis of rotation and are configured stationary relative to the tangential angle position. The Magnus rotor is located within the transverse flow rotor and has an axis extending in the direction of the axis of rotation. The guide mechanism has a housing segment partially surrounding the transverse flow rotor in the circumferential direction. The housing segment has an adjustment mechanism and is deflectable relative to the Magnus rotor axis. The housing segment is aligned such that the transverse flow rotor generates a propulsion force and causes a transverse flow onto the Magnus rotor to generate lifting force by way of a Magnus effect.

Abstract: A method for presenting the current drift values of an aircraft on a display device in which the drift values are presented in a vector presentation. The length of the drift vector above a predefined threshold value is presented in a manner proportional to the current drift velocity, and the length of the drift vector below the threshold value is presented in a manner disproportionate to the current drift velocity. There is a continuous transition between the two ways of presentation at the threshold value.

Abstract: An aircraft is provided includes at least one drive flow passage, which runs from an air inlet directed forward on the body surface via a jet engine through the body to a jet nozzle that opens towards the rear on the body surface. At least a part of the jet engine is arranged upstream of the air inlet seen in the flight direction of the aircraft and the drive flow passage has curvature sections embodied and arranged for this in a suitable manner.

Abstract: A method for recognition of a predetermined pattern in an image data set recorded by a device for recording of at least two electromagnetic frequency spectra is provided. A first difference value is formed for the image points of the selected area as a function of a difference between a data vector of a corresponding image point and a first reference data vector. A second difference value is formed for an image point of a selected area as a function of a difference between the data vector of this image point and a second reference data vector. A predetermined pattern is recognized when it is determined at least one pattern correlation quantity is below a predetermined threshold value and a local minimum is present.

Abstract: A method for detecting explosive substance particles in a gas flow includes passing the gas flow through an adsorption net for a specified time period so as to adsorb explosive-substance particles in the gas flow on the adsorption net. The adsorption not includes a microfilter having a pore size that is smaller than the particle size of the explosive-substance particles. The adsorption net is heated to a heating temperature so as to desorb the explosive-substance particles from the adsorption net. A gas flow comprising the desorbed explosive-substance particles is supplied to a detector so as to detect the explosive-substance particles.

Abstract: An air-to-surface surveillance and/or weapons system includes a base aircraft and an unmanned slave aircraft that can be uncoupled from a base aircraft and coupled back to it again. The base aircraft and slave aircraft are equipped with coupling equipment designed to work together. The base aircraft is equipped with surveillance and monitoring equipment. The slave aircraft is equipped with monitoring equipment and/or weapons. The slave aircraft can be connected to a control station via a data link for data exchange and can be controlled from this control station.

Abstract: A monitoring device for a repair patch that can be placed on or in a wall of an aircraft to repair a defect has a sensor device for detecting properties of the repair patch placed in the wall, an energy supply device for supplying energy at least to the sensor device, and a communication device so as to read out the sensor data. A repair kit that can be placed in or on a wall of an aircraft to repair defects comprises a repair patch for repairing a defect in or on a wall of an aircraft and also comprises a monitoring device. A method for monitoring a repair patch in or on a wall of an aircraft by means of a monitoring device comprises the steps of detecting a measurement phase on the basis of the amount of energy provided by the energy supply device, measuring load parameters in and/or on the repair patch during the measurement phase, and reading out the load parameters.

Abstract: A system for open space data communication comprising a transmitting device and an optical receiver using multiple varying levels of emitted radiation output. The transmitting device includes multiple emitter groups that are capable of being switched on and off and each of which can be activated in parallel to emit fixed, varying radiation outputs. A total radiation output emitted by the transmitting device is defined by a sum of the emitted radiation outputs of the emitter groups, wherein to transmit a bit vector (b0 . . . bn) an emitter group assigned to a most significant bit (b0) emits a maximum radiation output Pmax and emitter groups assigned to the less significant bits (b1 . . . bn) of the bit vector emit radiation outputs: Px=Pmax/2x where x=1 . . . n.