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    SATELLITE SYSTEM COMPRISING TWO SATELLITES ATTACHED TO EACH OTHER AND METHOD FOR LAUNCHING THEM INTO ORBIT
    111.
    发明申请
    SATELLITE SYSTEM COMPRISING TWO SATELLITES ATTACHED TO EACH OTHER AND METHOD FOR LAUNCHING THEM INTO ORBIT 有权
    包含与其他任何附件相关的两个卫星的卫星系统和将其发射到ORBIT的方法

    公开(公告)号：US20160075453A1

    公开(公告)日：2016-03-17

    申请号：US14783654

    申请日：2014-04-07

    Applicant: AIRBUS DEFENCE AND SPACE SAS

    Inventor： Emmanuel SAUZAY ,  Nathanael CHABERT

    IPC: B64G1/10 ,  B64G1/00

    CPC classification number: B64G1/10 ,  B64G1/002 ,  B64G1/005 ,  B64G1/007 ,  B64G1/1085 ,  B64G2001/1092 ,  B64G2001/643

    Abstract: A satellite system includes a so-called carrier satellite and a so-called piggyback satellite, each one having an Earth face. The piggyback satellite is attached to the carrier satellite by fastening elements that can be released on command. The piggyback satellite includes propulsion elements suitable for maintaining same in orbit, and the carrier satellite includes propulsion elements for performing a change of orbit of the satellite system including the carrier satellite and the piggyback satellite. The piggyback satellite is attached to the Earth face of the carrier satellite in such a way that the Earth face of the piggyback satellite is essentially perpendicular to the Earth face of the carrier satellite.

    Abstract translation: 卫星系统包括所谓的载波卫星和所谓的背负式卫星，每个卫星都具有地球面。 背负式卫星通过可以按照命令释放的紧固元件连接到载体卫星。 背负式卫星包括适于在轨道上保持相同的推进元件，载波卫星包括用于执行包括载波卫星和背负式卫星在内的卫星系统的轨道改变的推进元件。 背负式卫星以载波卫星的地球表面基本上垂直于载波卫星的地球表面的方式附着在载波卫星的地球表面上。

    GLASS PANEL FOR A SPACE AIRCRAFT
    113.
    发明申请
    GLASS PANEL FOR A SPACE AIRCRAFT 审中-公开
    玻璃面板空间飞机

    公开(公告)号：US20160031544A1

    公开(公告)日：2016-02-04

    申请号：US14781937

    申请日：2014-04-04

    Applicant: AIRBUS DEFENCE AND SPACE SAS

    Inventor： Yohann CORABOEUF

    IPC: B64C1/14 ,  B64D15/00 ,  B64G1/22

    CPC classification number: B64C1/1492 ,  B64D15/00 ,  B64G1/22

    Abstract: The invention relates to a glass panel for an aircraft suitable for a suborbital flight and an aeronautical flight, including an outer panel made of polycarbonate or aluminosilicate for temperature resistance, a main panel for pressure resistance, sized according to standard aeroplane safety factors, and an inner panel, providing redundancy for the main panel, sized with a minimum pressure margin, the outer, main and internal redundancy panels being separated from one another by spaces. The invention also relates to an aircraft including windscreen elements and portholes made using the glass panel.

    Abstract translation: 本发明涉及一种用于适用于亚轨道飞行和航空飞行的飞行器的玻璃面板，包括由聚碳酸酯或硅铝酸盐制成的耐温性外板，根据标准飞机安全系数尺寸的耐压主板，以及 内部面板，为主面板提供冗余，尺寸为最小压力裕度，外部，主要和内部冗余面板通过间隔彼此分开。 本发明还涉及一种包括使用玻璃面板制成的挡风玻璃元件和舷窗的飞行器。

    STARTER DEVICE FOR ROCKET MOTOR TURBOPUMP
    114.
    发明申请
    STARTER DEVICE FOR ROCKET MOTOR TURBOPUMP 审中-公开
    用于摇臂电动机的起动器装置

    公开(公告)号：US20150354452A1

    公开(公告)日：2015-12-10

    申请号：US14761401

    申请日：2014-01-16

    Applicant: AIRBUS DEFENCE AND SPACE SAS

    Inventor： Jean-Philippe DUTHEIL ,  Pierre VINET

    IPC: F02C6/08 ,  F02K9/46 ,  F02K9/78 ,  F02C7/32

    CPC classification number: F02C6/08 ,  F02C7/26 ,  F02C7/32 ,  F02K9/46 ,  F02K9/78

    Abstract: The subject of the invention is a device for starting a turbopump of a rocket motor of an aircraft including a turbine engine for propelling the aircraft and a rocket motor, which includes a pneumatic supply of compressed air to a turbine of the turbopump, this compressed air being tapped from a tapping on a compressor stage of the aircraft propulsion turbine engine upstream of the combustion chamber of the turbine engine. It applies notably to an aircraft of the space airplane type.

    Abstract translation: 本发明的主题是用于启动飞行器的火箭发动机的涡轮泵的装置，包括用于推进飞行器的涡轮发动机和包括向涡轮泵的涡轮机供应压缩空气的火箭发动机，该压缩空气 从在涡轮发动机的燃烧室上游的飞行器推进涡轮发动机的压缩机级上的攻丝开始。 它特别适用于飞机类型的飞机。

    STOP CRITERION FOR DECODING AN LDPC CODE
    116.
    发明申请
    STOP CRITERION FOR DECODING AN LDPC CODE 有权

    公开(公告)号：US20250167807A1

    公开(公告)日：2025-05-22

    申请号：US18864829

    申请日：2023-03-23

    Applicant: AIRBUS DEFENCE AND SPACE SAS

    Inventor： Lyonel BARTHE ,  Benjamin GADAT

    IPC: H03M13/11

    Abstract: An LDPC decoding method is disclosed in which the LDPC code is defined by a parity matrix having a layered structure, and the method involves performing iterations until a stop criterion is satisfied. Each iteration involves the successive processing of the different layers. Processing a layer involves calculating variable messages (αn,m), calculating parity check messages, calculating a posteriori estimation variables (γn), and calculating a partial syndrome. The evaluation of the stop criterion involves checking if, for a plurality of successive iterations, the number of iterations for which all the partial syndromes are zero, from which the number of iterations for which at least one of the partial syndromes is non-zero is subtracted, is greater than or equal to a predetermined stop threshold.

    Method for optimising the orbital transfer of an electrically propelled spacecraft, and satellite using said method
    117.
    发明授权
    Method for optimising the orbital transfer of an electrically propelled spacecraft, and satellite using said method 有权

    公开(公告)号：US12280896B2

    公开(公告)日：2025-04-22

    申请号：US17926543

    申请日：2021-05-19

    Applicant: AIRBUS DEFENCE AND SPACE SAS

    Inventor： Ivan Laine ,  Eric Martin ,  Marie Catherine Maag ,  Jean Francois Diraison

    IPC: B64G1/00 ,  B64G1/24 ,  B64G1/40

    Abstract: A method for transferring a spacecraft (10), such as an artificial satellite, from an initial elliptical orbit (30) to a final geostationary orbit (50), the spacecraft taking at least one intermediate elliptical orbit (40) propelled by electric propulsion means (12, 13), the method includes: when the spacecraft is in an intermediate orbit, a nominal thrust step (410) in which the propulsion means generate nominal thrust while the spacecraft is on at least part of a first orbital arc (41) passing through the apogee A of the intermediate orbit, and a minimum thrust step (420), in which the propulsion means are partly stopped or slowed while the spacecraft is on at least part (43) of a second orbital arc (42) passing through the perigee P of the intermediate orbit, the two orbital arcs being complementary.

    Protocol for monitoring communication traffic
    118.
    发明授权
    Protocol for monitoring communication traffic 有权

    公开(公告)号：US12192088B2

    公开(公告)日：2025-01-07

    申请号：US18090201

    申请日：2022-12-28

    Applicant: Airbus Defence and Space SAS

    Inventor： René Veyland

    IPC: H04L43/50 ,  H04L43/087 ,  H04L43/106 ,  H04L43/12 ,  H04L47/34

    Abstract: A first network probe is associated with a first router and with a first end-point of the first router, and a second network probe is associated with a second router and with a second end-point of the second router. The first network probe periodically injects flag packets in parallel to the traffic of a communication tunnel between the first and second end-points, with each flag packet including timestamp information expressing a time reference for the injection of the flag packet. Information relating to a timing variation in traffic in the communication tunnel is gathered, with the timing variation being measured due to a difference between the timestamp information contained in the flag packets and timestamp information relating to the instant the flag packets were captured by the second probe. Possible congestion situations experienced by the communication tunnel are assessed as a function of the gathered information.

    Network equipment with inter-network policy-based routing function
    119.
    发明授权
    Network equipment with inter-network policy-based routing function 有权

    公开(公告)号：US12170615B2

    公开(公告)日：2024-12-17

    申请号：US17416333

    申请日：2019-12-19

    Applicant: Airbus Defence and Space SAS

    Inventor： Claude Poletti

    IPC: H04L12/741 ,  H04L45/74 ,  H04L69/08

    Abstract: In order to route a data packet in a communication network, a network element implements a traditional routing process including taking a routing decision as a function of the destination of the data packet according to route learning in the communication network. The routing element reviews the routing decision taken by the traditional routing process via an internetwork policy-based routing function selected from among a plurality of candidate internetwork policy-based routing functions, each candidate internetwork policy-based routing function being assigned to an egress interface of the network element and vice versa. The selected internetwork policy-based routing function is that which is assigned to the egress interface selected by the traditional routing process for routing the data packet in the communication network.

    DEVICE FOR CONTROLLING THE ANGULAR VELOCITY OF A SPACECRAFT, AND CORRESPONDING SPACECRAFT
    120.
    发明申请
    DEVICE FOR CONTROLLING THE ANGULAR VELOCITY OF A SPACECRAFT, AND CORRESPONDING SPACECRAFT 有权

    公开(公告)号：US20240400233A1

    公开(公告)日：2024-12-05

    申请号：US18694826

    申请日：2022-09-20

    Applicant: AIRBUS DEFENCE AND SPACE SAS

    Inventor： Laurent BOYER ,  Kristen LAGADEC

    IPC: B64G1/24 ,  B64G1/32

    Abstract: A device for controlling the angular velocity of an out-of-service spacecraft is disclosed, in which the device makes it possible to facilitate the operations of active removal of the spacecraft as space debris. The device includes a stator and a rotor able to move on a rotation axis with respect to the stator, the stator is configured to be driven by the spacecraft to be stabilized, the rotor is configured to orient itself along the terrestrial magnetic field. The stator includes an electrically conductive non-ferromagnetic body while the rotor includes a magnetized system configured to induce, in the stator, eddy currents for braking a relative movement of the rotor with respect to the stator.

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