Abstract: A battery housing for the structural integration of batteries in a vehicle, in particular an aircraft or spacecraft, includes an inner housing for receiving a battery, and an outer housing which surrounds the inner housing such that a cavity is formed between the inner housing and the outer housing, wherein pins are formed in the cavity and connect the inner housing to the outer housing. A battery arrangement includes at least one battery housing of this type and at least one battery which is arranged in the inner housing of the at least one battery housing.

Abstract: A battery arrangement for the structural integration of batteries in a vehicle, in particular an aircraft or spacecraft, includes at least one battery; and two supporting, multi-layered structural laminates, between which the at least one battery is held on both sides via battery holders, wherein each multi-layered structural laminate has a cooling plate layer and a current collector layer, wherein the at least one battery is coupled electrically to the current collector layer.

Abstract: Methods aiding in proving shuffles of re-encryptions of ciphertexts and a mixnet employing such methods. A method for compacting ciphertexts includes encrypting a plaintext using an asymmetric key encryption scheme for a ciphertext, dividing the ciphertext into partial ciphertexts, encrypting each of the partial ciphertexts using the asymmetric key encryption scheme to obtain re-encrypted partial ciphertexts, creating hash exponents from a digest of a cryptographic hash function taking the partial ciphertexts, the re-encrypted partial ciphertexts and arbitrary salt values as argument of the cryptographic hash function, calculating a compacted ciphertext by multiplying all of the partial ciphertexts exponentiated by a respective one of the plurality of hash exponents, and calculating a compacted re-encrypted ciphertext by multiplying all of the re-encrypted partial ciphertexts exponentiated by a respective one of the hash exponents.

Abstract: An indication device for monitoring the structural integrity of a repair location on a laminate structure, produced from a composite material, of a part of an aircraft outer skin is specified. The indication device has at least one elongate, thin indicator strip. The indicator strip is detachably applied to the outer layer of the laminate structure in the immediate vicinity of the repair location. The indicator strip is designed to indicate a predefined residual strength of an adhesive joint of a repair patch to the surrounding composite material.

Abstract: A device for checking the consistency of a positioning includes: a transmitter, a receiver, a time measuring unit, a distance determining module and a check module. The transmitter emits at least one signal, and the receiver receives at least four response signals from at least four different response elements. A response element receives the at least one signal and, upon receipt, emits a response signal. The time measuring unit determines, for each response signal, a total delay time from a transmission time of the signal and a reception time of the respective signal. The distance determination module determines a distance to the respective response element based on each total delay time, and the check module performs a consistency check of a determination of a position based on distances to the different response elements. With the device, erroneous distance values may be detected in ground-based positioning systems.

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 battery arrangement for structurally integrating batteries in a vehicle, in particular an aircraft or spacecraft, includes at least one battery, two supporting cooling plates between which the at least one battery is held on both sides via battery holders, and connecting rods which connect the two cooling plates to one another.

Abstract: A LIDAR arrangement comprising a laser transmitter for transmitting pulses of a laser radiation to a measurement object, and a receiver for receiving pulses of the laser radiation backscattered from the measurement object, wherein the laser transmitter is configured to transmit a pulse sequence in which successive pulses respectively comprise a particular optical frequency shift to each other and wherein the receiver either includes a dispersive element for separating the pulses in time depending on the optical frequency by a frequency-based deflection, and a position resolution optical matrix transmitter on which the pulses separated in time by the dispersive element are mapped, or includes a frequency analyzer for the frequency-based separation of the pulses by superimposition with a reference radiation.

Abstract: An object identification unit contains an artificial neural network and is designed to identify human faces. For this purpose, a face is divided into a number of triangles. The relative component of the area of each triangle in the total of the areas of all triangles is ascertained to ascertain a rotational angle of the face. The relative component of the area of each triangle in the total of the area of all triangles is then scaled to a rotation-invariant dimension of the face. The scaled area of the triangles is supplied to the artificial neural network in order to identify a person.

Abstract: The present disclosure is directed a process for the electrolytic polishing of a metallic substrate, including the steps of (i) providing an electrolyte in an electrolytic cell having at least one electrode, (ii) disposing a metallic substrate as an anode in the electrolytic cell, (iii) applying a current at a voltage of 270 to 315 V from a power source between the at least one electrode and the metallic substrate, and (iv) immersing the metallic substrate in the electrolyte, wherein the electrolyte includes at least one acid compound, at least one fluoride compound, and at least one complexing agent.

Abstract: A structural component, in particular for an aircraft, spacecraft or rocket, has a ply of fiber reinforced polymer; a first carbon nanotube mat; and a metallic layer, wherein the carbon nanotube mat and the metallic layer are arranged on the ply of fiber reinforced polymer to form a hybrid lightning strike protection layer. A component for manufacturing such a structural component, a method for manufacturing a component of this type, a method for manufacturing a structural component and an aircraft or spacecraft with such a structural component are described.

Abstract: A method of localizing a device within an environment includes a step, in which a first location information is acquired that is representative of a first specified position. In another step, a first sensor information is acquired that is representative of the first specified position. In another step, the first sensor information is allocated to the first location information in order to generate a first condition information that is unique for the first specified position. In another step, a knowledge base is provided which includes the first condition information. In another step, the device provides a current sensor information indicating a current condition of the environment present at the current position of the device. In another step, the device is localized based on a matching between the current sensor information and the plurality of condition information.

Abstract: The present disclosure relates to an aircraft. The aircraft has a primary structural element, which extends along a main axis of the aircraft, and at least one monolithic structural component, which is produced by a three-dimensional printing method. The aircraft also has an aircraft system for carrying out an aircraft-specific function. The at least one monolithic structural component is fixed on the primary structural element by a fixing device, system, means, or mechanism. The monolithic structural component is embodied to accommodate the aircraft system. The disclosure also relates to a method for producing an aircraft.

Abstract: A method for producing a layer of a device for electromagnetic radiation absorption, includes: providing a ply of powder material in the layer to be produced of the device; providing a predefined concentration distribution of particles for electromagnetic radiation absorption in the layer; providing a first binder and a second binder for the powder materials, wherein the first binder includes particles for the absorption of electromagnetic radiation, wherein the second binder includes a lower concentration of identical and/or different particles than the first binder; determining a mixing ratio between the first binder and the second binder for every position in the layer; selecting a position of the layer; mixing the first and second binder according to the mixing ratio for the selected position; wetting the powder material at the selected position using the mixed first and second binders; and repeating selecting, mixing, and wetting to produce the layer.

Abstract: A device to fasten a system to a structure of a vehicle includes a drive unit that provides rotary movement of a drive element relative to the structure. The device has first and second supporting elements. The first supporting element is rotatably coupled to the drive element via a first rotation axis, and is rotatably mounted to the structure via a second rotation axis. The second supporting element is rotatably coupled to the first supporting element, and a first connecting element, which is rotatably mounted to the structure via a third rotation axis. The first connecting element is rotatably coupled to the second supporting element via a fourth rotation axis. The second supporting element is rotatably coupled to the first supporting element via a fifth rotation axis. During movement, the first supporting element has a different rotational speed than the second supporting element.

Abstract: Secure logging systems and methods using cryptography and/or encryption with crash recovery. In some embodiments, the secure logging system includes an initialization module to initialize cells of a logging database, including inserting a pseudorandom number into each cell of the logging database. In some embodiments, the secure logging system includes an addition module to encrypt new log messages and add them to the logging database in a given number of pseudorandom cells of the logging database. In some embodiments, the secure logging system includes a listing module to determine where in the logging database the log message was stored and then to decrypt the encrypted log messages. These systems and methods improve computer related technology including by improving crash reconstruction, root cause analysis, network systems security, and logging system encryption and security.

Abstract: A circuit board includes a substantially planar component carrier and a microstrip which is applied to a surface of the component carrier. The microstrip extends towards a connection transition which is arranged on a lateral edge of the component carrier. A waveguide portion of an antenna element which is produced by a 3D printing process is coupled to this connection transition.

Abstract: An aircraft structure has a fuselage, a wing and an air inlet for receiving air for an engine. The air inlet contains an elevation which rises from the fuselage and the wing. The elevation is arranged in a transition region between the wing and the fuselage and extends asymmetrically with respect to an angle bisector of an angle between a surface of the wing and the lateral surface of the fuselage. By virtue of this construction, a leading edge of the wing can be arranged further forward than the air inlet, and the air inlet configured according to these principles can positively influence a flow boundary layer on the aircraft structure.

Abstract: An apparatus and a method for the metallization of an object including placing the object in an electrolyte, placing an anode in contact with the electrolyte, placing a metallization contact of a cathode in contact with the object, applying an electrical tension between the anode and the cathode, wherein the metallization contact is displaced in relation to the object during the metallization of the object to achieve a complete and continuous metallization of the object's surface.

Abstract: A battery cell includes an anode, a cathode, and a separator between the anode and the cathode, wherein at least one of the anode or the cathode includes at least a carbon fiber ply comprising carbon fibers, the carbon fiber ply having a thickness of less than 90 micrometers. Also disclosed are a battery and an aircraft including such battery cell, and a method for manufacturing such battery cell.