Airbus Defence and Space Patente

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A receptacle device (40) for guided missiles (3) for launching from aircraft (2) in the air, and a launching device (50) for launching guided missiles (3) in the air are proposed, wherein the launching device (50) has a receptacle device (40) and/or is designed to interact with the receptacle device (40), and wherein the receptacle device (40) comprises a container (41) having a receptacle (43) for at least one guided missile, which container is designed to disintegrate in a predetermined manner due to an air flow prevalent during launching in the air.

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Method and system of safe separation analysis among elements dropped with a parachute from an aircraft (1) comprising the following steps: • providing at least a camera device located on the aircraft (1), • dropping a plurality of deployment bags (2) and a plurality of elements, • recording by the at least one camera device the images of the trajectories of the deployment bags (2) and of the elements dropped, • displaying in a visual computer program photograms, • identifying over the photograms a movement area (5) for each deployment bag (2) and the trajectories (6) of each dropped element, • overlapping the photograms to determine the number of deployment bag movement areas (2) that is crossed by an element trajectory (6), • calculating in a processing unit the risk of interference (7) for each pair of element trajectory (6) and of deployment bag movement area (2).

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The invention relates to an over-voltage-protection-circuit 100 that is configured to protect a high-speed digital signal driver (200) against a positive and negative over voltage injection from an application hardware (210). An embodiment of an over-voltage-protection-circuit 100 comprises: a first semiconductor switch (400) that is configured to short a fault current (231) in the event of an over voltage injection; and an input-circuit-element (300) that is configured to reduce the fault current (231) in the event of an over voltage injection; and a power supply (430) that is connected to a control input of the first semiconductor switch and that is configured to switch the first semiconductor switch (400) in the event of an over voltage injection and to be inactive in a normal operating mode.

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A system for information transmission in a quantum communication network is provided. An embodiment of the system comprises:- a first laser signal source configured to generate a first laser signal, and- a second laser signal source configured to generate a second laser signal,wherein each laser signal source is configured to provide the corresponding laser signal to- a coupler unit, wherein said coupler unit is configured to receive and to couple both laser signals, and to provide coupled laser signals to- an optical waveguide, wherein said optical waveguide is configured to- receive the coupled laser signals and- cause a concentric alignment of the coupled laser signals by allowing the received coupled laser signals a mode propagation to provide concentrically aligned laser signals to- a directional unit, wherein said directional unit is configured to receive the concentric aligned laser signals and to provide the concentrically aligned laser signals to a second terminal of the quantum communication network.

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In order to allow for compressing the signal dynamics of a radio frequency (RF) signal (16) that includes a desired signal (18) and an interference signal (20), the invention proposes to sample the RF signal (16) received by one or more antenna elements (14). One of the samples is used as a reference sample and subtracted at each sampling epoch (t₀, t₁, ...) from the received signal as it is output from each antenna element (14). The reference signal (30) and the subtracted signal are quantized such that the subtracted signal is quantized with a smaller number of quantization bits than the reference signal samples.

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In order to improve de-icing systems for an aircraft (10), a de-icing system (26) is proposed. The de-icing system (26) comprises a thin film heating foil (28) that is adhesively bonded to the leading edge portion (24). The heating foil (28) comprises a plurality of heating elements (36). In addition, an ice detecting device (30) is provided, which is able to detect the presence of ice on the leading edge portion (24) by optical, acoustical or thermal means. The de-icing system (26) has a control device (34), which is configured for periodically and selectively energizing the heating elements (36). To further improve the performance of the de-icing system (26), a silicone nanofilament network (SNF) is added as a superhydropho-bic coating (98) on a microperforated skin (100) and within the microperforations (94).

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The present invention belongs to the field of power supply, in particular to the field of power generation and conversion. More specifically, the invention is of the special application in the aeronautic industry for powering electrical equipment such electrical engines, radar antennas, energy laser systems or any other DC (Direct Current) network boarded within the aircrafts.

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Un procédé de génération d'un modèle de représentation de relief à partir d'une pluralité de N paires d'images stéréo, chacune des N paires d'images stéréo étant associée à une carte de disparités photogrammétriques qui est obtenue par calcul de corrélation à partir de la paire d'images stéréo en question, comporte : un calcul (3002) de cartes de disparités géométriques (3003) à partir d'un modèle de représentation de relief prédéterminé (3001), par projection du modèle de représentation de relief prédéterminé (3001) dans une géométrie épipolaire (203) des paires d'images stéréo ; un calcul (3005) d'une fonction de coût, représentative d'une différence entre les disparités géométriques et photogrammétriques, associée au modèle de représentation de relief prédéterminé (3001) ; et une mise à jour du modèle de représentation de relief prédéterminé (3001) par optimisation de type descente de gradient de la fonction de coût, et réitération jusqu'à atteinte d'un critère d'arrêt prédéfini.

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In order to reduce power consumption for de-icing or ice prevention, the invention proposes to provide an aircraft component (36) of an aircraft (10) or the aircraft (10) on its exposed surface (44) with a phase change material (48). The phase change material (48) stores thermal energy above a first temperature (T1) and releases the previously stored thermal energy below a second temperature (T2).

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In order to allow manned-unmanned-teaming of a main vehicle (12) with a companion vehicle (14), the invention proposes to predict a kinematic state of the main vehicle (12) from a current kinematic state and a motion model for the main vehicle (12) by employing a Kalman-type filter. The predicted kinematic state is transmitted to the companion vehicle (14) that generates a control signal that causes the companion vehicle (14) to maintain a predetermined relative position to the main vehicle (12) within a given tolerance.

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