公开(公告)号：US20160169646A1

公开(公告)日：2016-06-16

申请号：US14908834

申请日：2014-07-31

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Patrick Comtesse ,  Felipe Medina ,  Luc Preaud

IPC: F42B15/36

CPC classification number: F42B15/36 ,  B64G1/641 ,  B64G1/645 ,  F42B15/38

Abstract: A method and device enable the linear separation of two elements attached to each other through two connecting surfaces which are conical in this example, of a first element and a second element respectively, using thermite placed on the other side of the wall of the outer element, facing a connecting arrangement placed between both connecting surfaces. An electrical triggering of the thermite causes a quick and local warming-up, at the connecting arrangement which, after melting, enables both elements to be separated.

Abstract translation: 一种方法和装置能够通过两个连接表面彼此附接的两个元件进行线性分离，所述两个连接表面在本实例中是分别为第一元件和第二元件的圆锥形，使用放置在外部元件的壁的另一侧上的热绝缘体 面对放置在两个连接表面之间的连接装置。 在热连接装置上，电热触发铝电解质会导致快速和局部的预热，熔化之后可以使两个元件分离。

公开(公告)号：US20160069299A1

公开(公告)日：2016-03-10

申请号：US14786143

申请日：2014-04-22

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Fabrice Ruffino ,  Benjamin Faure

IPC: F02K9/84

CPC classification number: F02K9/84 ,  F02K9/56 ,  F05B2240/9121 ,  F05B2250/43

Abstract: A system allowing for the tilting of the rocket motor such that, in the tilted position, the centre of the nozzle is located at least approximately on the neutral orientation axis of said rocket motor.

Abstract translation: 一种允许火箭发动机倾斜的系统，使得在倾斜位置，喷嘴的中心至少位于所述火箭发动机的中立方位轴线上。

公开(公告)号：US20160052650A1

公开(公告)日：2016-02-25

申请号：US14781938

申请日：2014-03-28

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Eugénio FERREIRA ,  Angélique SANTERRE ,  Benjamin FAURE ,  Samuel CHEVROLLIER ,  Pierre PARPAITE ,  Christophe FAVRE

IPC: B64G1/62 ,  B64C25/10 ,  B64C9/32 ,  B64G1/14

CPC classification number: B64G1/62 ,  B64C9/323 ,  B64C25/10 ,  B64C25/16 ,  B64G1/14 ,  Y02T50/32

Abstract: A spaceplane suitable for aeronautical flight comprising a body and a wing defining a lower airfoil surface in addition to attitude control means that comprise one or a plurality of shutters disposed under the lower airfoil surface of same and maneuverable between a stowed position and an inclined extended position for aerodynamic braking during the transition from a phase of space flight to a phase of aeronautical flight of the aircraft.

Abstract translation: 适用于航空飞行的太空飞机除了包括设置在其下翼面下方的一个或多个快门的姿态控制装置之外，还包括限定下翼面的机体和机翼，并且在收起位置和倾斜延伸位置之间可操纵 在从空间飞行阶段到飞机航空飞行阶段的过渡期间进行空气动力学制动。

公开(公告)号：US09207446B2

公开(公告)日：2015-12-08

申请号：US14563976

申请日：2014-12-08

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Frederick Pasternak

IPC: G02B26/08 ,  G02B23/02 ,  G02B26/10 ,  G01C21/02 ,  G01S3/786 ,  G02B17/06 ,  G02B27/64

CPC classification number: G02B23/02 ,  G01C21/025 ,  G01S3/786 ,  G02B17/0663 ,  G02B26/10 ,  G02B26/105 ,  G02B27/642

Abstract: An optical system has a rotary scanning mirror, an optical instrument and an optical image rotation device. The rotary scanning mirror receives an incident beam of rays and returns an input beam along a first axis. The optical instrument receives the input beam from the scanning mirror and returns an output beam parallel to the input beam along a second axis in a direction opposite to the input beam towards the optical rotation device. The optical image rotation device is positioned on the second axis and receives the output beam. The scanning mirror has an axis of rotation aligned on the first axis. The optical image rotation device has an axis of rotation aligned on the second axis. The optical system comprises a common driving device for rotationally driving the optical image rotation device and the scanning mirror about their respective rotation axes.

Abstract translation: 光学系统具有旋转扫描镜，光学仪器和光学图像旋转装置。 旋转扫描镜接收入射光束并且沿第一轴返回输入光束。 光学仪器接收来自扫描反射镜的输入光束，并沿着与输入光束相对的方向朝着光学旋转装置返回平行于输入光束的输出光束沿第二轴返回。 光学图像旋转装置位于第二轴上并接收输出光束。 扫描镜具有在第一轴上对准的旋转轴。 光学图像旋转装置具有在第二轴上对准的旋转轴。 光学系统包括用于旋转地驱动光学图像旋转装置和围绕它们各自旋转轴线的扫描镜的公共驱动装置。

公开(公告)号：US20150015436A1

公开(公告)日：2015-01-15

申请号：US14388806

申请日：2013-03-28

Applicant: AIRBUS DEFENCE AND SPACE SAS ,  CENTRE NATIONAL D'ETUDES SPATIALES CNES

Inventor： Renaud Broquet ,  Bernard Polle ,  Johan Montel

IPC: G01S19/54 ,  G01S19/55 ,  G01S19/22

CPC classification number: G01S19/55 ,  G01S3/46 ,  G01S3/48 ,  G01S5/0247 ,  G01S5/06 ,  G01S19/22 ,  G01S19/53 ,  G01S19/54

Abstract: A method for calibrating spatial errors induced by phase biases having a detrimental effect on the measurements of phase differences of radio signals received by three unaligned receiving antennas of a vehicle. An inter-satellite angular deviation of a pair of satellites is estimated in two different ways: on the basis of the respective positions of the vehicle and of the satellites to obtain a theoretical inter-satellite angular deviation; and on the basis of the respective directions of incidence of the satellites relative to the vehicle, which are determined from phase measurements, to obtain an estimated inter-satellite angular deviation. The space errors are estimated on the basis of said theoretical and estimated inter-satellite angular deviations. Also, a method and system for estimating the attitude of a vehicle, in particular a spacecraft.

Abstract translation: 校准由相位偏差引起的空间误差的方法，其对由车辆的三个未对准的接收天线接收的无线电信号的相位差的测量具有不利影响。 以两种不同的方式估计一对卫星的卫星间角度偏差：基于车辆和卫星的相应位置以获得理论上的卫星间角度偏差; 并且基于从相位测量确定的卫星相对于车辆的各个入射方向，以获得估计的卫星间角度偏差。 基于所述理论和估计的卫星间角度偏差来估计空间误差。 另外，用于估计车辆，特别是航天器的姿态的方法和系统。

公开(公告)号：US12292262B2

公开(公告)日：2025-05-06

申请号：US17757604

申请日：2020-12-15

Applicant: Airbus Defence and Space SAS

Inventor： Nicolas Launay

IPC: B64C39/02 ,  F41G7/34 ,  F41G9/00 ,  G05D1/00 ,  B64U101/15

Abstract: A method for securing a geographical area encompassing a route. A map of the area is obtained. A weapon is associated with a firing modeling consisting of a probability model of hitting its target when shooting, as a function of the firing distance. Positions of potential shelters of threats on the map are determined by using a trained artificial intelligence device. The modeling is applied for each weapon and potential shelter while relating the shots to the route and summing all the probabilities of hitting its target on each portion of the route. The potential shelters most likely to constitute attack threats along the route are determined. A path is defined in order to address these potential shelters most likely to constitute attack threats.

公开(公告)号：US12250464B2

公开(公告)日：2025-03-11

申请号：US18711010

申请日：2022-11-16

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Cyrille Tourneur

IPC: H04N23/695

Abstract: A process for the acquisition, by a spacecraft in terrestrial orbit, of a useful image of a space object in terrestrial orbit that is gradually approaching the spacecraft from an upstream distal region towards a proximal region is disclosed including controlling the orientation of an array-type detection sensor in order to orient it towards the space object located in the upstream distal region, acquiring, via the array-type detection sensor, a so-called detection image of the space object located in the upstream distal region, determining trajectory-tracking information on the basis of the detection image, controlling the orientation of an array-type acquisition sensor on the basis of trajectory-tracking information, in order to orient it towards the space object located in the proximal region, acquiring, via the array-type acquisition sensor, a useful image of the space object located in the proximal region.

公开(公告)号：US12187461B2

公开(公告)日：2025-01-07

申请号：US18014870

申请日：2021-07-02

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Florian Gacoin ,  Jean-Marc Pierinet ,  Mireya Joya ,  Julien Pradal ,  Sara Lopez-Sanchez ,  Nicolas Fabre

IPC: B64G1/22

Abstract: A primary structure (100) for a spacecraft (200) including an interface ring (10) and a predetermined number of panels defining a box arranged to close an interior volume of the spacecraft. The box is connected to the interface ring. Side panels of the box are parallel to a geometric axis (A) of the interface ring, the interface ring is temporarily fastened to a system supporting the spacecraft in a launcher. Each panel is a one-piece panel formed by machining a metal material. The side panels at the base of the box are connected to the interface ring (10) via damping inserts (60).

公开(公告)号：US20240383619A1

公开(公告)日：2024-11-21

申请号：US18690082

申请日：2022-09-05

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Mehdi GHEZAL ,  Emmanuel GIRAUD

IPC: B64G1/10 ,  B64G1/24 ,  H04B10/118

Abstract: A method for acquiring images by a spacecraft is disclosed having an observation instrument and a laser transmission module, the method including a phase of acquiring an image of the surface of the Earth and a phase of transmitting images using the laser transmission module, and during each acquisition phase and each transmission phase, the attitude control includes: a pointing modification step during which the attitude of the spacecraft is modified so as to orient the satellite towards a predetermined setpoint, a pointing immobilization step during which the attitude of the spacecraft is controlled for a time interval referred to as an immobilization period so as to keep the spacecraft oriented towards the setpoint.

公开(公告)号：US12077324B2

公开(公告)日：2024-09-03

申请号：US17785628

申请日：2020-12-09

Applicant: AIRBUS DEFENCE AND SPACE SAS

Inventor： Catherine Berthomieu ,  Carole Chossiere ,  Andrew Walker ,  Franck Levallois ,  Vincent Claudet

IPC: B64G1/64 ,  B64G1/10 ,  B64G1/22

CPC classification number: B64G1/64 ,  B64G1/10 ,  B64G1/223

Abstract: A method for assembling devices on a satellite structure is disclosed including attaching the devices to a first face of a plate drilled with a through-hole provided with a fluid connector, on a second face of the plate, depositing a continuous peripheral bead of polymerisable adhesive composition and depositing a plurality of discontinuous and disjointed inner beads of polymerisable adhesive composition, pressing the second face of the plate against a continuous face of the structure, performing suction so as to create a pressure differential between the plate and the structure, at least partially polymerising the polymerisable adhesive compositions so as to form adhesive joints between the plate and the structure, and interrupting the suction.