Abstract: An operating device with a number of actuating elements, such as switches and/or pushbuttons, arranged next to one another and/or one below the other is provided. The actuating elements are delimited, at least in part, by at least one frame element. The frame element is provided, at least in some regions, with surface sections that are shaped such that they can be detected haptically. One actuating element is respectively assigned to at least a part of the haptically detectable surface sections.

Abstract: A transceiver element for an active, electronically controlled antenna system includes a transmit path, a receive path and single-pole change-over switches having a common central connection and two connections for switching between the transmit path and the receive path. An amplitude controller and a phase adjuster are arranged between the common center connections of a first and second single-pole change-over switch. Single-pole multiple toggle switches having a common central connection and a number N of connections are present. The common central connection of the first and second single-pole change-over switch is connected to the common central connection of a first and a second single-pole multiple toggle switch respectively, and an amplitude controller and a phase adjuster are connected between each connection of the number N of connections of the first multiple toggle switch and the second multiple toggle switch.

Abstract: A method and system for estimating a path-length difference between two paths followed by a target signal transmitted by a spacecraft or aircraft to a first receiving antenna and a second receiving antenna of a receiving base, respectively. A useful-phase difference is measured between signals that correspond to the target signal received by the first receiving antenna and second receiving antenna. The path-length difference is estimated in accordance with the useful-phase difference measurements. The measurement of the useful-phase difference comprises either correlating the signals received by the first receiving antenna and second receiving antenna, respectively, with a reference target signal, or analyzing the signals received by the first receiving antenna and second receiving antenna, respectively, using an FFT or a PLL.

Abstract: A data glove for generating tactile feedback at a finger upon interaction of the finger with an interaction element on an infrared touchscreen includes receiving elements for receiving the fingers of an operator and stimulators for generating tactile feedback attached on the finger-receiving elements. The date glove also includes elements for identifying the finger interacting with the infrared touchscreen and a signal generator for exciting the stimulator of the interacting finger upon successful actuation of an interaction element on the infrared touchscreen.

Abstract: A drive mechanism for deforming a skin of a deformable structural component of a fluid-dynamic flow body to provide a space-saving drive concept for large deformations under great loads. The drive mechanism comprises a linearly movably driven linear movement unit, and a transmission element configured to translate linear movement of the linear movement unit into rotary movement of a rotatably mounted load introduction device of the structural component to introduce a deformation force onto the skin.

Abstract: A satellite support structure to support at least one device of the satellite. The support structure includes structural elements with at least one of the structural elements being a damping connector linking at least two other structural elements of the support structure. The damping connector includes an elastomer element and at least one flat angle bracket having at least two wings to be linked by the respective connectors to the damped structural elements. The elastomer element is made from elastomer material with loss angle ? greater than ten degrees and is arranged such that the transmission of forces between one of the wings of the flat angle bracket and the connectors is achieved entirely via the elastomer element.

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.

Abstract: A solar array (50) for a spacecraft (10), comprising a solar concentrator that is provided with photovoltaic cells and reflective areas configured for reflecting solar radiation towards the photovoltaic cells, wherein the reflective areas and the photovoltaic cells are provided on opposite surfaces of concentrator reflector sheet members (56) that are repositionable from a retracted state wherein the concentrator reflector sheet members are in a substantially flat arrangement, to a extended state wherein the concentrator reflector sheet members are raised to allow the reflective areas to reflect solar radiation towards the exposed photovoltaic cells. Alternatively or in addition, the solar array may comprise a support panel, which may be at least partially flexible for retaining the support panel in a bent panel shape when the solar array is in the stowed state fixed at a position near a body of the spacecraft.

Abstract: A control and/or management system for a vehicle includes at least one of: (A) at least two redundant vehicle management computers configured to generate system control commands for each maneuvering actuators and for each system actor based on the data acquired by the sensors; (B) at least two redundant remote interface units for interconnecting a sensor or a system actor with a vehicle management computer; (C) at least two redundant actuator control computers configured to generate control commands for each maneuvering actuator based on received maneuvering commands; and (D) a common interface for connecting an external computer, the common interface being directly connected to at least two redundant computers.

Abstract: A method and a device for runway localization on the basis of a feature analysis of at least one image of the runway surroundings taken by a landing aircraft is characterized in that, in order to determine the central axis of the runway, feature matching between image features of the image and mirrored image features of the image is carried out, wherein features of the one runway side are made to be congruent with features of the other runway side.

Abstract: Method for detecting pulsed laser radiation having two-dimensional resolution of the direction of incidence with a CCD sensor having an imaging optic. Method includes generating, in signal processing having sampling frequency of at least 5 kHz, single images by comparing each pixel of CCD sensor to respective threshold values and by storing a pixel value exceeding the respective threshold value for an image processing, ascertaining, in the signal processing, a mean or peak value of stored pixel values of the single image pixel-by-pixel over at least 10 samples, forwarding a signal image obtained in signal processing for image processing at image frequency of 10 Hz to 500 Hz, and identifying from signal image, in an image processing, at least one signal pixel representing incident laser radiation. Method further includes determining direction of incidence of laser radiation from position of signal pixels on signal image.

Abstract: A system and method for providing an estimate of the thickness of the ice regardless of the shape of its surface at the level of the air/ice interface. To this end the system and method measure an intensity profile of a luminous pattern generated by diffusion in the ice, which enables the system to measure the thickness of the ice even when the air/ice surface is not plane.

Abstract: A lighting device and method with a lighting unit which includes several light sources having different color spectra, with a sensor for determining the spectral power distribution emitted by the lighting unit, with a control unit which, as a function of a predetermined spectral power distribution as well as of the spectral power distribution measured by the sensor, acts on a drive unit which individually energizes the light sources of the lighting unit, so that the emitted light has predetermined spectral power distribution, wherein the lighting unit includes at least four light sources, and the control unit uses an optimization algorithm which, as an optimization goal, maximizes a coefficient of weighted sensor values, the coefficient being calculable from individual drive data of the light sources. A secondary condition is met when error between the predetermined spectral power distribution and the measured spectral power distribution is smaller than a limit value.

Abstract: A vertical take-off aircraft with a propulsion drive for generating a driving force being effective in a horizontal direction and with a lift drive for generating a lifting force being effective in a vertical direction includes a motor for providing mechanical energy for the propulsion drive and a first generator for providing electrical energy for the lift drive. Moreover, the aircraft includes an exhaust gas turbocharger for the motor with a first turbine being driven by an exhaust gas flow of the motor, wherein the first turbine is configured to provide mechanical energy for the propulsion drive.

Abstract: A coupling device for supporting a first wing section against a second wing section of an aircraft, and configured for passive flight load alleviation includes a housing including a chamber including a first portion and a second portion and filled with a fluid, a piston device movably arranged in the chamber and separating the first portion from the second portion in a fluid tight manner, a first fluid pathway connecting the first portion to the second portion, a first pressure relief valve arranged in the first fluid pathway and blocking the first fluid pathway, if the pressure in the second portion is smaller than a first relief pressure and opening the first fluid pathway, if the pressure in the second portion is greater than the first relief pressure. In addition, the coupling device can be used to actuate the second wing section against the first wing section.

Abstract: An image capture instrument implements an addition of accumulation signals for photodetectors which are adjacent within a row of photodetectors. Segments are defined in the row with one and the same common length of segment, while being progressively offset by an offset length which is constant. The accumulation signals are added together for photodetectors which belong to one and the same segment. The offset length is less than the segment length, and greater than half said segment length. Artifacts in the image captured, which are due to spectrum aliasing, are thus decreased. The signal-to-noise ratio of the image is increased.