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1. 发明申请

US20180030631A1 METHOD FOR DRAPING COMPOSITE MATERIALS ON A FORM AND MATERIAL SUITABLE FOR SAID METHOD 审中-公开
公开(公告)号：US20180030631A1
公开(公告)日：2018-02-01
申请号：US15729445
申请日：2017-10-10
申请人： AIRBUS DEFENCE & SPACE SAS
发明人： Jean-Baptiste DEYTS , Florian CHOTARD , Eric SOCCARD
IPC分类号： D04H3/11 , D04H3/07 , D04H3/002 , B29C70/54 , D04H1/485 , D04H1/46 , B29C70/30 , D04H3/105 , D04H1/559
CPC分类号： D04H3/11 , B29C70/30 , B29C70/54 , D04H1/46 , D04H1/485 , D04H1/559 , D04H3/002 , D04H3/07 , D04H3/105 , Y10T442/60 , Y10T442/682 , Y10T442/689
摘要： The subject matter of the invention is a method for draping on a form, which includes a step of deposition on the form of a first fold support in the form of one or more polymer nonwoven fabrics. The invention further relates to a thermoplastic nonwoven material manufactured with a nonwoven fabric of polymer fibers.

2. 发明申请

US20150361714A1 DRY CONTAINMENT CURTAIN DEVICE 审中-公开
标题翻译：干燥装饰幕
公开(公告)号：US20150361714A1
公开(公告)日：2015-12-17
申请号：US14653672
申请日：2013-12-18
申请人： AIRBUS DEFENCE & SPACE SAS
发明人： Thibault DERODE , Jean-Marc TUGAYÉ
IPC分类号： E06B5/12 , E05F15/72 , E06B5/18
CPC分类号： E06B5/12 , E05F15/72 , E06B5/125 , E06B5/18 , E06B9/0692 , E06B9/17007
摘要： A confinement mechanism that includes a dry curtain of dimensions greater than the dimensions of a discharge surface to be re-confined, formed by an opening in a building, such as, for example, a door, the curtain deploying in response to a high-pressure wave emitted by an explosion. Advantageously, the curtain is arranged in an envelope and is released from the envelope and deployed in response to the high-pressure wave emitted by the explosion.
摘要翻译：一种限制机构，其包括尺寸大于待重新限制的排放表面的尺寸的干式帘幕，所述尺寸由建筑物（例如门）中的开口形成，所述窗帘响应于高速爆炸发射的压力波。有利地，帘幕布置在信封中并且从信封释放并且响应于爆炸发射的高压波而展开。

3. 发明授权

US10316796B2 Combustion gas discharge nozzle for a rocket engine provided with a sealing device between a stationary part and a moving part of the nozzle 有权
公开(公告)号：US10316796B2
公开(公告)日：2019-06-11
申请号：US14905923
申请日：2014-07-23
申请人： AIRBUS DEFENCE & SPACE SAS
发明人： Jean-Philippe Dutheil
IPC分类号： F02K9/86 , F02K1/80 , F02K9/90 , F02K9/97
摘要： The invention relates to a combustion gas discharge nozzle for a rocket engine including a stationary part and a moving part extending from the stationary part, the moving part made using flaps positioned downstream from the stationary part and forming an extension of the nozzle, the nozzle including a sealing device extending between the fixed part and the moving part in the form of a flexible membrane withstanding a local temperature of the combustion gases at the nozzle outlet and connecting the end of the stationary part to a border of the flaps or petals forming the moving part, the flexible membrane forming an annular tubing, the sealing device being provided with a duct for injecting gas at the flexible membrane between the stationary part and the moving part extending the nozzle.

4. 发明申请

WO2016135091A1 DISPOSITIF DE LEVAGE DE CHARGES 审中-公开
标题翻译：升降装置
公开(公告)号：WO2016135091A1
公开(公告)日：2016-09-01
申请号：PCT/EP2016/053661
申请日：2016-02-22
申请人： AIRBUS DEFENCE & SPACE SAS
发明人： CEPA, Frédéric
IPC分类号： B66C1/66 , B66C1/10
CPC分类号： B66C1/66 , B66C1/107
摘要： Il est proposé un interface de manutention de type flasque de manutention (1) pourvu d'un moyen (2) d'accrochage à un dispositif de levage et d'une lumière (3) de réception d'un moyen de levage (4), telle qu'une barre comportant une gorge (5), l'interface comportant un dispositif protecteur sous forme d'un capot (6) adapté à recouvrir une partie comportant la lumière (3) d'une face du flasque (1).
摘要翻译：本发明涉及一种端板式操纵接口（1），其设置有用于联接到提升装置的装置（2）和用于接收提升装置（4）的孔（3），所述提升装置所述接口包括覆盖件（6）形式的保护装置，所述保护装置能够覆盖包括所述端板（1）的一个表面的所述孔（3）的部分。

5. 发明申请

WO2015086594A3 METHOD FOR CONTROLLING A POLYPHASE SYNCHRONOUS MACHINE 审中-公开
标题翻译：控制多相同步电机的方法
公开(公告)号：WO2015086594A3
公开(公告)日：2015-11-26
申请号：PCT/EP2014077042
申请日：2014-12-09
申请人： AIRBUS DEFENCE & SPACE SAS
发明人： LORÉA MARC
IPC分类号： H02P6/10 , G05D1/08
CPC分类号： H02P6/10 , B64G1/00 , G05D1/0883
摘要： The present invention relates to a method for controlling a polyphase synchronous machine (3), implemented to control the attitude of a spacecraft, said machine comprising at least one rotor, one stator, and a plurality N of phases (RA, RB, RC) electrically powered to generate a predetermined torque, said control method comprising a step of electrically powering the synchronous machine (3) based on a six-step control mode, wherein the phases (RA, RB, RC) are activated in pairs. The method comprises, during the powering step, for each rotor position (Φ), the steps of: obtaining the intensities of the currents traveling within the two active phases and in the phase that has just been deactivated; estimating a torque (C*) based on values of the intensities of the phase currents obtained; controlling the estimated torque (C*) according to a predefined torque set-point (Ccons).
摘要翻译：本发明涉及一种用于控制多相同步电机（3）的方法，所述多相同步电机用于控制航天器的姿态，所述机器包括至少一个转子，一个定子以及多个N相（RA，RB，RC）所述控制方法包括基于六步控制模式对所述同步机（3）供电的步骤，其中所述相（RA，RB，RC）被成对激活。该方法包括在供能步骤期间针对每个转子位置（Φ）的步骤：获得在两个有效相位内以及在刚被停用的相位内行进的电流的强度; 基于所获得的相电流的强度的值估计转矩（C *）; 根据预定的转矩设定点（Ccons）控制估计转矩（C *）。

6. 发明专利

FR3122410A1 Satellite réflecteur et ensemble satellitaire comprenant un tel satellite 未知
公开(公告)号：FR3122410A1
公开(公告)日：2022-11-04
申请号：FR2104584
申请日：2021-04-30
申请人： AIRBUS DEFENCE & SPACE SAS , AIRBUS DEFENCE AND SPACE SA
发明人： CAVIGNAC AXEL , MONTESANO ANTONIO
IPC分类号： B64G1/10 , B64G1/22 , B64G1/24 , B64G1/28 , H01Q1/28 , H01Q15/14 , H01Q19/19
摘要： L’invention concerne un satellite réflecteur (1) comprenant au moins une surface de réflexion (11) incurvée, caractérisé par le fait qu’il comprend au moins une structure porteuse (10) reliée à au moins quatre systèmes de positionnement et d’orientation (12) du satellite réflecteur pour réaliser un contrôle d’attitude et d’orbite, lesdits systèmes de positionnement et d’orientation comprenant au moins un système propulseur, lesdits systèmes de positionnement et d’orientation étant synchronisés et disposés de façon à permettre une orientation du satellite réflecteur selon au moins deux axes de rotation. Il est également décrit un ensemble satellitaire comprenant un satellite source et un satellite réflecteur. Figure de l’abrégé : Figure 1

7. 发明专利

ES2925961T3 Dispositivo y procedimiento de determinación de actitud de un satélite equipado con accionadores giroscópicos, y satélite que incorpora un dispositivo de este tipo 未知
公开(公告)号：ES2925961T3
公开(公告)日：2022-10-20
申请号：ES20726224
申请日：2020-03-17
申请人： AIRBUS DEFENCE & SPACE SAS
发明人： LAURENS PHILIPPE , LESPRIER JEREMY
IPC分类号： B64G1/28 , B64G1/36 , G01C21/24
摘要： La invención se refiere a un dispositivo (30) para determinar la actitud de un satélite (10), comprendiendo el satélite un sistema de control de actitud que comprende un actuador giroscópico (20) que comprende un volante (21) montado de manera que puede girar alrededor de un eje de rotación y llevado por una junta universal (22) articulada para girar alrededor de un eje de rotación. Este dispositivo (30) comprende: un sensor de actitud (31) capaz de medir la actitud del satélite; un sensor de posición (32) capaz de medir la posición angular de la junta universal (22) alrededor de su eje de rotación; un sensor de velocidad (33) capaz de medir la velocidad de giro del volante (21); y medios de cálculo (34) configurados para determinar la actitud del satélite (10) a partir de la medida de la posición angular de la junta universal (22), la medida de la velocidad de giro del volante (21) y la medida de la actitud de el satélite (10). (Traducción automática con Google Translate, sin valor legal)

8. 发明专利

AU2021227304A1 Radiator with reduced insolation and improved guidance system for geostationary satellite 未知
公开(公告)号：AU2021227304A1
公开(公告)日：2022-08-11
申请号：AU2021227304
申请日：2021-02-09
申请人： AIRBUS DEFENCE & SPACE SAS
发明人： PUPILLE GILLES , DELTOUR BERNARD
IPC分类号： B64G1/50
摘要： The application proposes a radiator (1) for a geostationary satellite (2), comprising: - a radiating panel (4) perpendicular to a radiation axis (S), and pivoting relative to the radiation axis (S), - a support leg (7) for the panel, - a motor pivoting the support leg about a rotation axis (R), the radiation axis and the rotation axis being inclined relative to each other by an angle (α) corresponding to the angle of the plane of the satellite's orbit relative to the ecliptic plane of the planet, and - a guidance system (12) for the panel limiting the rotation of the panel about the rotation axis, comprising a connecting arm (14) pivoting relative to the satellite about a first axis (X), and relative to the panel about a second axis (Y) intersecting the first axis at a point of intersection (O) of all the axes.

9. 发明专利

ES2920573T3 Procedimiento de fijación de un equipo disipativo, pared de vehículo espacial y vehículo espacial 未知
公开(公告)号：ES2920573T3
公开(公告)日：2022-08-05
申请号：ES19845712
申请日：2019-12-18
申请人： AIRBUS DEFENCE & SPACE SAS
发明人： WALKER ANDREW
IPC分类号： B64G1/50
摘要： La invención se refiere a un método para unir una pieza de equipo disimulante de calor y un tubo de calor capilar en un panel de una pared de una nave espacial, dicho método que comprende los siguientes pasos: a) Posicionamiento (18) Un tubo de calor capilar en parte de la parte de la parte de la parte de la parte de panel; b) Ajustar (26) cuerpos de fijación femeninos al panel, los cuerpos de fijación femeninos que se proyectan con respecto a la tubería de calor capilar; c) colocar (38) una pasta de conducción térmica y autocurenadora sobre parte de la tubería de calor capilar o sobre un equipo de disipación de calor; d) colocar (46) un equipo de disipación de calor en la pasta que conduce térmicamente y en los cuerpos de accesorio femenino, dijo el equipo disipador de calor que se lleva y está en contacto directo con los cuerpos de unión femeninos, y e) unir (48) el equipo de disipación de calor y dicho tubo de calor capilar al panel uniendo elementos de fijación masculina a los elementos de fijación femenina. (Traducción automática con Google Translate, sin valor legal)

10. 发明专利

AU2020407421A1 Device for damping docking to a satellite 未知
公开(公告)号：AU2020407421A1
公开(公告)日：2022-07-07
申请号：AU2020407421
申请日：2020-12-17
申请人： AIRBUS DEFENCE & SPACE SAS
发明人： TAJAN FLORENT , BLAIS THIERRY
IPC分类号： B64G1/64
摘要： The invention relates to a device for docking with a satellite, comprising: a mobile receiving platform (10) suitable for bearing against a protruding element of the satellite, a device for capturing the protruding element, and a device for damping and positioning (20) the receiving platform, comprising: - a set (21) of link arms (210) connecting the satellite receiving platform to a member that is stationary relative to a spacecraft carrying the docking device, the set of link arms being suitable for allowing the platform to move in six degrees of freedom, and - a set of magnetic dampers (25), suitable for damping the contact between the satellite and the mobile receiving platform in proportion to the relative speed between the satellite and the mobile receiving platform. The invention also provides a method for docking and undocking this device to a satellite.

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