Airbus Defence and Space Patente

A display arrangement (10) for presenting video information to a human operator in a vehicle (1) is described. The display arrangement (10) senses movements of the vehicle (1) and movements of a head mounted display unit (100) of the display arrangement (10). Based on the movements of the vehicle (1) and of the relative movements of the display unit (100) with respect to the vehicle (1), a virtual scenario with background video data and application video data are generated and provided to the display arrangement. The background video data are modified so that the background video moves opposite to the vehicle movements. The application video data are modified so that the application video moves in accordance with the vehicle movement. A perspective onto the application video can be modified based on the relative movements of the display unit with respect to the vehicle. This approach may reduce conflicts between sensory impressions of the vestibular system and the eyes of the operator because the movements of the vehicle as well as the movements of the display unit are considered when generating and modifying the background and application video data presented to the operator.

Systems and methods for operating an optical arrangement (100) are described. An optical pilot tone with an original phase is applied to a detector arrangement (28) and received by the detector arrangement (28). The detector arrangement (28) senses a phase of the received optical pilot tone and determines a pilot tone delay between the phase of the received optical pilot tone and the original phase of the optical pilot tone. A delay correction value is determined based on the determined pilot tone delay. The delay correction value is applied to a signal of a first beam (19) containing measurement information received by the detector arrangement (28), wherein the detector arrangement (28) senses a phase or time delay of the first beam. Thereby, phase noise introduced by the detector in the optical and electrical domain of the optical arrangement (100) into the first beam can be quantified and reduced.

In order to improve operation and functionality of a hydrogen system, especially for aircrafts, the invention provides a hydrogen receptacle (1) for a vehicle (12), especially an aircraft, comprising a receptacle wall (2) made from fibre reinforced composite material defining a volume (3) for storing or conducting hydrogen (82, 84), especially liquid hydrogen (82), wherein the receptacle wall (2) comprises an inner layer (4) of graphene. Further, manufacturing methods for components of the receptacle (1) and for the receptacle (1) itself are described.

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To improve LIDAR measurements in terms of accuracy and usability, the present invention provides a LIDAR arrangement (10) comprising a laser transmitter (12) for transmitting pulses of a laser radiation to a measurement object (40), and a receiver (13) for receiving pulses of the laser radiation backscattered from the measurement object (40), wherein the laser transmitter (12) is designed for transmitting a pulse sequence in which successive pulses respectively comprise a particular optical frequency shift to each other and wherein the receiver (13) 1.1 includes a dispersive element (16) for separating the pulses in time depending on the optical frequency by a frequency-based deflection, and a position resolution optical matrix transmitter (39) on which the pulses separated in time by the dispersive element are mapped, or 1.2 includes a frequency analyzer (60) for the frequency-based separation of the pulses by superimposition with a reference radiation.

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A structural part (10) for lightning strike protection, preferably of an aircraft is described. The structural part (10) comprises a first structure element (12), wherein the first structure element (12) comprises a conducting material and is adapted to conduct electric currents into a grounded conducting airframe structure, and a second structure element (14), wherein the second structure element (14) comprises an outer layer with a first surface (16), wherein the outer layer comprises a composite, preferably carbon-fibre reinforced plastic, CFRP or glass-fibre reinforced plastic GFRP. The structural part (10) further comprises a first elongated, preferably wedge-shaped, electrical conductor (18), with a first end and a second end, wherein the first end of the first elongated electrical conductor (18) is connected to the first structure element (12) and extends through the second structure element (14) to the first surface (16), so that the second end of the first elongated electrical conductor (18) serves as a lightning receptor without impairing the radar cross section of the aircraft.

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We generally describe an optical system for performing in-orbit instrument spectral response function measurements, the optical system comprising: an optical detection unit; and an optical frequency comb generator for projecting a frequency comb comprising a plurality of discrete, equally spaced elements onto said optical detection unit.

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The present invention relates to a system (10) for determining the spectral sensitivity of a spectrograph (44), comprising an irradiation device (20) configured to emit first electromagnetic radiation (23) with a first spectrum including at least three substantially simultaneously emitted, equidistant spectral lines (S1-Sk), and a spectrograph (44) comprising a spectral separator (30) and a photodetector (40) with a plurality of pixels (Pl-Pm), wherein the spectral separator (30) is arranged so as to receive the first electromagnetic radiation (23) and to separate the first electromagnetic radiation (23) so that the at least three spectral lines (S1-Sk) are assigned to different pixels from among the plurality of pixels (P1-Pm). Furthermore, the invention relates to a method of determining the spectral sensitivity of a spectrograph (44).

An air direction arrangement (100) for an aircraft is described. The air direction arrangement contains an inlet opening (110) and an inlet channel (111) which is connected thereto and which is at least partially surrounded by an outer wall (125). The inlet channel (111) is configured to guide air to an engine (30) of the aircraft. The outer wall (125) contains at least one outlet channel (135) and at least one outlet element (130). The outlet element (130) is configured to selectively release or close the outlet channel (135) for an air flow from the inlet channel (111) into the environment of the aircraft. The air direction arrangement (100) contains a heat exchanger (140) which is arranged in the outlet channel (135) in order to discharge thermal energy to the air flow which is flowing from the inlet channel into the environment of the aircraft.

A method for calculating real-time immission values at locations within an area of interest is provided. The method comprises providing an emission dispersion model with real-time information on one or more mobile emitters, for example vehicles. The one or more mobile emitters are within an area of interest. The method further comprises providing the emission dispersion model with respective emission characteristics of the one or more mobile emitters. The method further comprises providing the emission dispersion model with information comprising influencing environmental factors on emission dispersion for an environment within the area of interest. The method further comprises calculating real-time immission values at locations within the area of interest based on the emission dispersion model. Further, a system for calculating real-time immission values at locations within an area of interest is provided.

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Guidance system and method of an element (1) towards a target (2). The guidance system comprising: - at least one imaging device to view the target (2) and the element (1), - a control means in communication with the imaging device and with the element (1) that receives the images taken by the imaging device, the control means configured to: - locate in the images a reference mark of the element (1) and of the target (2), - send an instruction to move the element (1) so that the reference mark of the element (1) is located in a predetermined position with respect to the target (2) in the received images, - while the element (1) is controlled to keep the predetermined position, send an instruction to move the element (1) towards the target (2), and - continuously perform the above steps until the element (1) reaches the target (2).

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