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: 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 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 disclosure provides an apparatus for depositing poly(p-xylylene) onto a component (4). The apparatus comprises (i) a platen, (ii) an electrode, and (iii) a first feed means. The platen comprises an electrically conductive material, is electrically connected to an electrical power supply and is configured to support a component. The electrode is electrically insulated from the platen. The first feed means is configured to feed a poly(p-xylylene) monomer to the platen. Furthermore, the component either comprises an electrically conductive material or consists of an electrically insulating material. If the component consists of an electrically insulating material the electrical power supply is an alternating current power supply and generated an alternating electrical field which couples to the component, and is thereby able to penetrate through the component to create the plasma.

Abstract: An electric thruster comprises a propellant delivery system, wherein the propellant delivery system comprises: a pipe for carrying propellant; a valve which is adapted to adjust a volume or mass flow of the propellant in the pipe; and an expansion actuator which is adapted to actuate the valve for adjusting the volume or mass flow of the propellant. The electric thruster further comprises at least one tank which is adapted to receive propellant for the electric thruster; and a discharge chamber. The at least one tank thereby at least partially encloses an end of the discharge chamber and/or an element thermally coupled with the discharge chamber, and the valve of the propellant delivery system is arranged between the tank and the end of the discharge chamber.

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: An unmanned aircraft is described. The unmanned aircraft includes a signal output unit and a control unit. The control unit receives at least one signal to be output by the signal output unit. The control unit transmits at least a first signal to the signal output unit, so that the signal output unit outputs the first signal. The unmanned aircraft may be used stand-alone or autonomous as a movable signal output device, but it may also be coupled with a carrier vehicle to meet the function of a signal output device at the carrier vehicle.

Abstract: A device for a variable and adaptable diverterless bump engine inlet of an aircraft comprises a flexible inlet, a mechanism to change the shape of the flexible inlet, and a processing unit to control the mechanism. The flexible inlet of the device includes a plurality of edges attached partly to a fuselage skin and partly to an engine inlet duct. With this device, the shape of the flexible inlet can be controlled according to the flight conditions, and hence the engine air intake will perform more efficient at all speeds while fulfilling requirements for less radar visibility.

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.

Abstract: A device for accommodating and deploying at least one payload on a flying machine includes at least one housing. The housing includes at least two opposite first side surfaces which extend over at least a portion of a length of a payload to be accommodated. The payload to be accommodated is releasably held between the two first side surfaces of the housing. The housing is at least partially arranged in a cavity on an outer surface of a flying machine. The cavity includes at least one outwardly open first opening, and the housing can be at least partially moved out of the cavity for deploying and/or receiving the payload to be accommodated.

Abstract: A system with a self-test function has at least one system component which has at least one technical function, a fault simulation unit integrated in the system, a self-test unit integrated in the system, and a verification control unit integrated in the system, wherein the at least one system component is coupled to the fault simulation unit, wherein the fault simulation unit is designed to influence the operation of the system component to the effect that the at least one technical function is selectively impaired, wherein the self-test unit is designed to monitor operating parameters of the system component and to respectively generate a warning signal which indicates impairment of the respective at least one technical function, and wherein the verification control unit is designed to compare the warning signals generated by the self-test unit with expected warning signals on the basis of the impaired technical functions.

Abstract: A monitoring system for monitoring a kinematic coupling between an actuator and an element controlled by the latter includes a first sensor to detect the operative movement of the actuator. A second sensor is designed to detect the actual movement of the controlled element. A computer unit, based on the operative movement of the actuator, determines an anticipated movement of the controlled element and compares this anticipated movement with the actual movement of the controlled element. An error message is emitted when a value of the deviation between the anticipated movement and the actual movement exceeds a predefined threshold value.

Abstract: Hollow waveguide termination device utilizing a housing and a cup shaped inner attenuation element arranged therein and made of a material which absorbs electromagnetic oscillations. The attenuation element has a tubular section and a front wall section closing the tubular section on one side.

Abstract: The disclosure herein relates to a receiver for use in a user satellite, located among other things partly or wholly on orbits remote from Earth, for example. The receiver comprises a receiving unit and a processing unit. The receiving unit is configured to receive signals transmitted by navigation satellites of one or more global navigation satellite systems (GNSS). The processing unit is configured to determine measurements based on the data contained in the signals received. The processing unit is further configured to carry out a calculation of position, velocity and time (PVT) based on batch processing of the measurements. The disclosure herein further relates to a method and a user satellite.