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公开(公告)号：US20230122828A1
公开(公告)日：2023-04-20
申请号：US17924094
申请日：2021-05-10
Applicant: AIRBUS DEFENCE AND SPACE SAS
Inventor： Philippe LAURENS
Abstract: A method (50) for orbit control of a satellite (10) in Earth orbit and for desaturation of an angular momentum storage device of the satellite, the satellite (10) including an articulated arm (21) suitable for moving a propulsion unit (31) within a motion volume included in a half-space delimited by an orbital plane when the satellite is in a mission attitude, the method (50) including a single-arm control mode using only the propulsion unit (31) carried by the articulated arm (21), the single-arm control mode using a maneuvering plan including only thrust maneuvers to be executed when the satellite (10) is located within an angular range of at most 180° centered on a target node in the orbit of the satellite (10), including two thrust maneuvers to be performed respectively upstream and downstream of the target node.
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公开(公告)号：US11597539B2
公开(公告)日：2023-03-07
申请号：US17440559
申请日：2020-03-16
Applicant: AIRBUS DEFENCE AND SPACE SAS , AIRBUS ONEWEB SATELLITES SAS
Inventor： Yannick Neubrand , Alexandre Jullien , Marie Sachot
Abstract: A method for attitude control of a satellite in inclined low orbit in survival mode is disclosed, the satellite including at least one solar generator, at least one solar sensor, magnetic torquers capable of forming internal magnetic moments in a satellite reference frame having three orthogonal axes X, Y, and Z, and inertial actuators capable of forming internal angular momentums in the satellite reference frame. The at least one solar sensor has a field of view at least 180° wide within the XZ plane around the Z axis, the method including a step of attitude control using a first control law, a step of searching for the sun by means of the at least one solar sensor, when a first phase of visibility of the sun is detected, and a step of attitude control using a second control law.
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公开(公告)号：US20230018576A1
公开(公告)日：2023-01-19
申请号：US17787209
申请日：2020-12-08
Applicant: AIRBUS DEFENCE AND SPACE SAS
Inventor： Thierry BLAIS , Alain GOSSANT , Victor PIRES
Abstract: A device for orienting a load about a main axis X and a secondary axis Y is disclosed having a first shaft, called transmission shaft, intended to support the load and configured to be rotated about the main axis and the secondary axis, a second shaft configured to be rotated about the main axis X, a third shaft configured to be rotated about a third axis of rotation, in the same direction as the main axis, a first connection component between the transmission shaft and the second shaft, configured to prevent relative movements between the transmission shaft and the second shaft in, on the one hand, a degree of rotational freedom about the main axis X and, on the other hand, three degrees of translational freedom.
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公开(公告)号：US20220358725A1
公开(公告)日：2022-11-10
申请号：US17618651
申请日：2020-06-10
Applicant: AIRBUS DEFENCE AND SPACE SAS
Inventor： François LEBEAUPIN , Fabien DUMON , Nicolas RAGGUENEAU , Olivier FROUIN , Bertrand OUSTRIERE , Guillaume VAUCLIN
IPC: G06T19/00
Abstract: A system for preparing a mission from a digital mapping, includes a mission editor generating mission elements that can change over the course of several determined temporal phases, including on a network a mission server, a mapping server, a server for sharing at least one centre of the map and a plurality of augmented reality headsets, at least one of the augmented reality headsets, called master headset, being able to generate at least one command for modifying the centre, each headset being able to receive at least two sets of elevation and terrain tiles from the mapping server, the mission server interfacing with the headsets to share and update the mission elements and to change them over time.
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公开(公告)号：US11472578B2
公开(公告)日：2022-10-18
申请号：US16320925
申请日：2017-07-27
Applicant: AIRBUS DEFENCE AND SPACE SAS
Inventor： Jean-Marc Aymes , Sébastien Mazuel , Antoine Poulet
Abstract: A method for estimating a direction of a satellite in the transfer phase. The direction of the satellite is estimated relative to a measurement antenna by executing steps for measuring the reception power, by the measurement antenna, of a target signal emitted by the satellite, for different pointing directions of the measurement antenna. The target signal has a substantially sinusoidal component referred to as a single-frequency component. Each power measurement step includes a transposition in the frequency domain of a digital signal, obtained from a signal supplied by the measurement antenna, to obtain a frequency spectrum of the digital signal over a predetermined frequency band having the single-frequency component. The power measurement for the pointing direction being considered is determined based on a maximum value of the frequency spectrum.
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Patent Agency Ranking
76.发明申请公开(公告)号：US20220250771A1
公开(公告)日：2022-08-11
申请号：US17429270
申请日：2020-02-07
Inventor： Benoît SERIES , Mathieu PICARD , Jonathan GUERRA
Abstract: Computer systems (100) for satellite image acquisition and mission-plan calculation devices (120) for satellite and also Earth observation satellites (110). Based on the observation that the uncertainty connected with meteorological conditions can lead to the development of mission plans, for satellites, with low effectiveness, the uncertainty is characterized and used to improve the preparation of mission plans for satellite. A model of the uncertainties is built upon observations and/or past meteorological forecasts. Next, at the time of planning, the model is used by presenting the observations and/or the current forecast as input to the model. In that way, the acquisition zones for which it is unlikely to get acceptable images on the preferred acquisition date may be identified.
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公开(公告)号：US11268790B2
公开(公告)日：2022-03-08
申请号：US16463294
申请日：2017-11-23
Applicant: Airbus Defence and Space SAS
Inventor： Hervé Biran
Abstract: A firing simulation scope, for installation on a rifle, includes an inertial measurement unit, a windage correction adjustment device, an electronic system, a microphone, a display and an interface for connection to a control station. The electronic system is configured for: receiving, via the connection interface, video data representing a field of view, through a simulated scope, in the virtual environment; displaying on the display the received video data; obtaining a real time audio microphone recording; comparing the audio recording with a predetermined firing-triggering signature of the rifle; and transmitting, to the control station via the connection interface, when the audio recording matches the predetermined signature, a firing triggering detection signal associated with inertial measurements supplied by the first inertial measurement unit and with a first adjustment setting supplied by the windage correction adjustment device, to enable the control station to determine a firing trajectory in the virtual environment.
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公开(公告)号：US11183970B2
公开(公告)日：2021-11-23
申请号：US17256379
申请日：2019-06-12
Applicant: AIRBUS DEFENCE AND SPACE SAS
Inventor： Dominique Vergnet , Marc Sabathe
IPC: H02S50/15 , H01L31/0443 , H01L31/05 , F21S8/00 , G01R31/26
Abstract: A test device for testing a solar generator of a satellite or solar drone, the solar generator includes an array of solar cells, each junction being capable of converting photons of a respective wavelength band into electric current, the test device includes: an array of light sources including at least one row of light sources, wherein each light source emits light in each of the electrical conversion wavelength bands of the junction(s) of the solar cells, and a control unit for the array of light sources, and capable of controlling the turning on and off of each of the light sources of the array individually, wherein the array of light sources selectively illuminates each solar cell of the solar generator by turning on one or more light sources of the array, with the solar cell receiving an irradiance that is greater than at least 130W/m2.
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公开(公告)号：US20210296780A1
公开(公告)日：2021-09-23
申请号：US17259918
申请日：2019-07-12
Inventor： Simon Stirland , Denis Fragnol
Abstract: An Array-Fed Reflector (AFR) antenna assembly is provided comprising an AFR antenna comprising a feed array a reflector, and a mechanism for moving a position of the reflector relative to a position of the feed array such that a focal region of the reflector is movable with respect to the position of the feed array.
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公开(公告)号：US20210160677A1
公开(公告)日：2021-05-27
申请号：US17045382
申请日：2019-04-04
Applicant: AIRBUS DEFENCE AND SPACE SAS
Inventor： Franck SCHOLLER , Jean-Marc MONTENOT
Abstract: A cellular telecommunications system comprises a radio access portion enabling user equipment to access services of the cellular telecommunications system; and a core network portion comprising a quality of service policy control equipment connected to a gateway via which radio bearers are set up in order to access said services. An orchestrator equipment: receives regular reports from said gateway relating to the radio bearers that are set up; detects the occurrence of a crisis situation; identifies cells affected by the crisis situation; applies, during the crisis situation, crisis situation management rules, by declining to authenticate user equipment for which the crisis situation management rules indicate that access to said services is barred during the crisis situation; and by asking the gateway to close any session set up for user equipment for which the crisis situation management rules indicate that access to said services is barred during the crisis situation.
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