Airbus Defence and Space Patente

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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.

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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La présente invention concerne un procédé d'autorisation de vol d'un aéronef (1) muni d'une installation motrice hybride (10) ayant au moins un moteur thermique (15) et au moins un moteur électrique (20) relié électriquement à une source d'énergie électrique (30) comprenant plusieurs accumulateurs électriques (31). Le procédé comporte un prélèvement (STP1) au sol d'une énergie électrique ou d'une puissance électrique à prélever à partir de la source d'énergie électrique (30) pendant une durée prédéterminée et une détermination (STP2) pour les accumulateurs électriques (31) de valeurs initiales respectives d'un paramètre de fonctionnement, un calcul (STP3) d'une valeur moyenne à partir des valeurs initiales, une détermination (STP4) d'une valeur minimale parmi les valeurs initiales mesurées, une autorisation de vol lorsqu'une différence entre la valeur moyenne et la valeur minimale est inférieure à un seuil et une interdiction lorsque ladite différence entre la valeur moyenne et la valeur minimale est supérieure ou égale au seuil.

A vehicle management system (10) includes a missile avoidance system (11) that generates command for controlling at least one function of a vehicle. The missile avoidance system (11) includes a maneuver control unit (100) and a missile avoidance management unit (50). The maneuver control unit (100) includes at least two control models. Each of the at least two control models generates the command for controlling the at least one function of the vehicle (1), and each of the at least two control models can be selectively put in an active state or an inactive state. The missile avoidance management unit (50) selects one of the at least two control models and putts it in the active state. The maneuver control unit (100) outputs the command for controlling the at least one function of the vehicle (1) provided by the control model that is in the active state.

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A fuselage (3) for an aircraft (1) is described. The fuselage has a control element (20) with an integrated engine outlet (23). The control element (20) is integrated at a rear end (2) of the fuselage (3), so that the control element (20) terminates flush with an outer skin (4) of the fuselage in a circumferential direction of the fuselage (3). An outer wall (40) of the control element (20) surrounds the engine outlet (23) so that the engine outlet (23) is directed towards an open rear side (6) of the control element (20). The control element (20) is connected to the fuselage (3) such that the control element (20) jointly the engine outlet (23) is pivotable about a rotation axis (26) with respect to the fuselage (3). The rotation axis (26) runs transversely to a longitudinal direction (8) of the fuselage (3) and the control element (20) functions as a tailplane when pivoting about the rotation axis (26).

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