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81.发明授权公开(公告)号：US11005691B2
公开(公告)日：2021-05-11
申请号：US16759238
申请日：2018-10-22
Applicant: AIRBUS DEFENCE AND SPACE SAS
Inventor： Benjamin Gadat , Mehdi Anteur
Abstract: A method (50) for estimating a frequency shift and a frequency drift affecting a useful signal including a code word formed by a channel encoder, including an analysis phase (51) including: for two analysis frequency drifts: a compensation (52) of the analysis frequency drift on the useful signal, an estimation (53) of the frequency shift on each useful signal obtained after compensation, a selection (54) of frequency hypotheses,
and an estimation phase (55) including: for each frequency hypothesis: a frequency recalibration (56) of the useful signal depending on the frequency hypothesis, in order to obtain sample sequences, an evaluation (57) of the probability of each sample sequence to be a code word of said channel encoder, an estimation (58) of the frequency shift and of the frequency drift depending on the most probable frequency hypothesis.-
公开(公告)号：US20210081289A1
公开(公告)日：2021-03-18
申请号：US16956850
申请日：2018-12-20
Applicant: AIRBUS DEFENCE AND SPACE SAS , AIRBUS
Inventor： Jean-Luc MARTY , David CANU , Alexandre ARNOLD
Abstract: A system and a method for assisting with troubleshooting a complex system is disclosed in which the troubleshooting procedure can be modeled by a Markov decision process. Combining the fault tree technique with a Markov decision process, in order to determine in an optimal manner the sequence of troubleshooting actions will quickly address the consequences of a failure and ensure maintainability of the complex system.
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公开(公告)号：US10931364B2
公开(公告)日：2021-02-23
申请号：US16761981
申请日：2018-11-08
Applicant: AIRBUS DEFENCE AND SPACE SAS
Inventor： Andrew Thain , Vincent Tugend
Abstract: A satellite payload (20) including a reflector (22), a network (23) of sources (24) and a beam forming network connected to said sources in order to form beams for carrying signals in a first frequency band, called “band B1”, and in a second frequency band, called “band B2”. The reflector comprises two reflective surfaces (22a, 22b) positioned one behind the other in relation to the network of sources and having different curvatures so that each reflective surface generates an image of the network of sources with a different magnification factor. The reflective surface closest to the network of sources is transparent for all the signals carried on the band B2 and is adapted to reflect signals carried in the band B1. The other reflective surface is adapted to reflect signals carried in the band B2.
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公开(公告)号：US20210012528A1
公开(公告)日：2021-01-14
申请号：US16955428
申请日：2018-12-19
Applicant: AIRBUS DEFENCE AND SPACE SAS
Inventor： Roland BROCHARD , Cyril ROBIN
Abstract: A method for locating a three-dimensional target with respect to a vehicle is disclosed including capturing an image of the target, and from a three-dimensional mesh of the target, and from an estimation of the pose of the target, determining a set of projecting edges of the mesh of the target in the pose. The step of determining the projecting edges of the mesh of the target includes positioning the mesh of the target according to the pose, projecting in two dimensions the mesh so positioned, scanning the projection of the mesh in a plurality of scanning rows and, for each scanning row: defining a set of segments, each segment corresponding to the intersection of a face of the mesh with the scanning row and being defined by its ends, analyzing the relative depths of the ends of the segments, the depth being the position along a third dimension orthogonal to the two dimensions of the projection, in order to select a set of end points of segments corresponding to projecting edges of the mesh.
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公开(公告)号：US10718319B2
公开(公告)日：2020-07-21
申请号：US16315144
申请日：2017-07-06
Applicant: AIRBUS DEFENCE AND SPACE SAS
Inventor： Cyril Brotons , Dimitry Loubere , Guillaume Scremin , Matthias Guilhem-Ducleon
Abstract: An electric power supply system for a Hall effect electric thruster. The Hall effect electric thruster includes an anode, a cathode, a heater for the cathode and an igniter. The electric power supply system includes a first power supply source to power the anode, a second power supply source to power the heater and a power supply unit to electrically supply the igniter. The power supply unit includes a third power supply source and a passive electric circuit. The third power supply source powers the passive electric circuit and is configured to generate a voltage in the form of at least one pulse.
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Patent Agency Ranking
公开(公告)号：US10677533B2
公开(公告)日：2020-06-09
申请号：US15772444
申请日：2016-11-16
Applicant: AIRBUS DEFENCE AND SPACE SAS
Inventor： Christian Flemin , Typhaine Coquard , Andrew Walker
Abstract: Disclosed is a heat exchange device for effecting a heat exchange between a heat transfer fluid of a first network of capillary heat pipes and a heat transfer fluid of a second network of capillary heat pipes. The heat exchange device includes a solid block provided with a first channel and a second channel which are independent of one another, the first channel having at least one opening intended to be connected to a capillary heat pipe of the first network, the second channel having at least one opening intended to be connected to a capillary heat pipe of the second network, the first channel having a portion which lies near a portion of the second channel such that the heat transfer fluid of the first network is able to exchange heat with the heat transfer fluid of the second network via the heat exchanging portions.
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公开(公告)号：US10659159B2
公开(公告)日：2020-05-19
申请号：US16341274
申请日：2017-09-28
Applicant: AIRBUS DEFENCE AND SPACE SAS
Inventor： Jean Sperandei , Gilles Planche
IPC: H04B10/118 , H04B10/50
Abstract: A combined system for imaging and communication by laser signals including a telescope (10) in which the primary (1) and secondary (2) mirrors are shared between an imaging function and a function involving the emission of laser transmission signals. The accuracy required for the direction of emission (DE) of the laser transmission signals is obtained by additionally placing a geolocation device on board a satellite carrying the combined system. No coarse pointing assembly is used and it is also possible for the system to be devoid of any fine pointing assembly and target acquisition and tracking detector.
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88.发明申请公开(公告)号：US20190390996A1
公开(公告)日：2019-12-26
申请号：US16468200
申请日：2017-12-08
Applicant: AIRBUS DEFENCE AND SPACE SAS
Inventor： Sophie JALLADE , Mathieu MONGE-CADET , Sylvain ARNAUD , Barbara BUSSET
Abstract: Disclosed is a method for gauging the liquid propellant tank of a spacecraft during a phase of high-thrust along an axis, the tank being thermally conductive and having a known geometry. The method includes steps of: attaching, on a wall of the tank, a heating member and at least one temperature sensor in proximity to the heating member and in a plane of interest perpendicular to the thrust axis; during the high-thrust phase, heating the wall of the tank and acquiring temperature measurements of the wall of the tank at rapid frequency; determining the instant I when the temperature measured by the sensor changes, such change indicating the presence of the liquid-gas interface in the tank in the plane of interest; and determining the volume of liquid propellant present in the tank at instant I.
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89.发明授权公开(公告)号：US10513352B2
公开(公告)日：2019-12-24
申请号：US15501168
申请日：2015-08-04
Applicant: AIRBUS DEFENCE AND SPACE SAS
Inventor： Dominique Poncet , Cyril Tourneur , René Cheynet De Beaupre
Abstract: A system and method for transferring a satellite from an initial orbit into a mission orbit. The method includes anchoring to the satellite of an external unit having a tank containing a reserve of propellants. The system includes an autonomous spacecraft having an electric propulsion module and a small internal reserve of propellants, located in a parking orbit close to the initial orbit. The spacecraft with the external unit attached to the satellite is docketed in an initial orbit, to produce a fluidic connection of the propellant tank of the external unit to the propulsion module of the spacecraft. The external unit and satellite is transferred into the mission orbit by the electric propulsion module of the spacecraft supplied with propellants directly from the external unit, thereby releasing the satellite into the mission orbit.
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公开(公告)号：US20190339125A1
公开(公告)日：2019-11-07
申请号：US16341278
申请日：2017-09-29
Applicant: AIRBUS DEFENCE AND SPACE SAS
Inventor： Frédéric PASTERNAK
Abstract: A spectrophotometric device is disclosed having a plurality of spectral measurement bands including a single telescope and a single spectrophotometer. The plurality of spectral bands is obtained by placing pupillary separating prisms at an entrance pupil of the telescope, and by using spectral band selection filters. Such a device has a lower weight, smaller dimensions, and a lower price. In particular, it may be integrated into a satellite, in particular for a mission to characterize flows of carbon compounds that are produced on the Earth's surface.
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