An electronic device (1) suitable for use on board a spacecraft, including a motherboard (2) electrically connected to daughterboards (3a, 3b, 3c), the motherboard and the daughterboards each include a support plate (4a, 4b, 4c, 5) in order to form a printed circuit board, each support plate extending in a respective main plane, wherein each daughterboard includes a first electrical connector (6a, 6b, 6c, 6d) fixed to its support plate and the motherboard includes a corresponding number of second connectors (7a, 7b, 7c, 7d) fixed to the support plate of the motherboard, each first electrical connector engages with one of the second connectors, the first electrical connector of each daughterboard is arranged on a portion of the support plate forming a tab (8a, 8b, 8c, 8d) configured for deflection relative to the main plane of the printed circuit board.
H01R 12/73 - Coupling devices for rigid printing circuits or like structures coupling with the edge of the rigid printed circuits or like structures connecting to other rigid printed circuits or like structures
The invention relates to a decoder (30) for decoding low-density parity-check (LDPC) codewords. The decoder includes at least one core (10) and a memory (20) in which a number NC of predefined configurations is stored. The core is suitable for being dynamically configured with any one of the NC predefined configurations stored in the memory in order to decode an LDPC codeword using this configuration. The NC predefined configurations form a sub-group, in the strict sense, of 5G LDPC configurations defined in the 3GPP TS 38.212 standard. Each configuration corresponds to a triplet of three parameters {K, R, Z}, and to a parity matrix constructed according to at least a portion of these parameters. K is a message size encoded by the LDPC code, Z is an expansion factor of the parity matrix, and R is a code rate of the LDPC code. Advantageously, the NC predefined configurations include different values of the parameter Z.
H03M 13/11 - Error detection or forward error correction by redundancy in data representation, i.e. code words containing more digits than the source words using block codes, i.e. a predetermined number of check bits joined to a predetermined number of information bits using multiple parity bits
H03M 13/00 - Coding, decoding or code conversion, for error detection or error correctionCoding theory basic assumptionsCoding boundsError probability evaluation methodsChannel modelsSimulation or testing of codes
The invention relates to a multicore decoder (31) for decoding low-density parity-check (LDPC) codewords. The multicore decoder includes at least one group of a plurality of cores (10), a plurality of these cores (10) being capable of each simultaneously decoding a different LDPC codeword. The at least one group includes a memory (20) shared between the various cores (10) in which a number NC of predefined configurations is stored. Each predefined configuration includes a binary parity matrix corresponding to an LDPC code. Each core is suitable for being dynamically configured with any one of the NC predefined configurations stored in the shared memory (20) in order to decode an LDPC codeword using this configuration.
H03M 13/11 - Error detection or forward error correction by redundancy in data representation, i.e. code words containing more digits than the source words using block codes, i.e. a predetermined number of check bits joined to a predetermined number of information bits using multiple parity bits
H03M 13/00 - Coding, decoding or code conversion, for error detection or error correctionCoding theory basic assumptionsCoding boundsError probability evaluation methodsChannel modelsSimulation or testing of codes
H04L 1/00 - Arrangements for detecting or preventing errors in the information received
4.
METHOD FOR PERFORMING NON-LOCAL DEMOSAICING OF AN IMAGE, AND ASSOCIATED DEVICE
A demosaicing method is disclosed as being applied to an initial image in order to obtain a demosaiced image, enabling an improved demosaicing due to the fact that it includes a noise variance stabilization transformation, for each reference patch: a determination of a set of similar patches, a determination of a covariance matrix for said set of similar patches, and for each similar patch, a calculation of estimates of the interpolated spectral bands according to a block-based deconstruction of the covariance matrix as a function of the phasing, a determination of the interpolated spectral bands by an aggregation of estimates of the interpolated spectral bands, and an inverse transformation of the stabilization transformation.
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.
H03M 13/11 - Error detection or forward error correction by redundancy in data representation, i.e. code words containing more digits than the source words using block codes, i.e. a predetermined number of check bits joined to a predetermined number of information bits using multiple parity bits
6.
OPTIMIZATION OF THE COMPUTATION OF PARITY CHECK MESSAGES IN A MIN-SUM LDPC DECODING METHOD
The disclosure relates to an LDPC decoding method which involves performing iterations until a stop criterion is satisfied. Each iteration involves computing variable messages (αn,m), computing parity check messages (βm,n), and computing a posteriori estimation variables. Computing a parity check message (βm,n) for a parity check node (CNm) involves determining the two smallest values (Min1, Min2) among the absolute values of the variable messages associated with the parity check node (CNm), comparing a difference between said values with a threshold, determining a correction value according to the result of the comparison, and computing the parity check message according to the correction value.
H03M 13/11 - Error detection or forward error correction by redundancy in data representation, i.e. code words containing more digits than the source words using block codes, i.e. a predetermined number of check bits joined to a predetermined number of information bits using multiple parity bits
7.
ADAPTIVE SCALING OF PARITY CHECK MESSAGES FOR LDPC DECODING
The disclosure relates to an LDPC decoding method which involves performing iterations until a stop criterion is satisfied. Each iteration involves calculating variable messages (αn,m), calculating parity check messages (βm,n), and calculating a posteriori estimation variables. The parity check messages (βm,n) and the posteriori estimation variables (γn) being saturated at a predetermined maximum value. At the end of an iteration, when the number of saturations reaches a specified threshold, the method involves at least a first scaling of the parity check messages (βm,n) and the a posteriori estimation variables (γn). Scaling corresponds to assigning, to a value, an integer which has the same sign and whose absolute value is the nearest integer greater than the absolute value of the value divided by two.
H03M 13/11 - Error detection or forward error correction by redundancy in data representation, i.e. code words containing more digits than the source words using block codes, i.e. a predetermined number of check bits joined to a predetermined number of information bits using multiple parity bits
8.
SPACE SYSTEM FOR THE CRYOGENIC COOLING OF AN ITEM OF EQUIPMENT TO BE COOLED AND METHOD FOR SEPARATING A THERMAL COUPLING BETWEEN A CRYOGENERATOR AND AN ITEM OF EQUIPMENT TO BE COOLED
The invention relates to a cryogenic cooling space system with a system (1) for managing a thermal coupling between a thermal link (4) and a finger (2; 3) of a cryogenerator or an item of equipment to be cooled, the space system comprising: - a fastening system (5) configured to provide, in a pretensioned state, a direct coupling between the finger (2; 3) and the thermal link (4), in a coupling configuration; - a separation system (6) configured to reduce or eliminate the pretensioned state of the fastening system (5) in order to reduce or eliminate the coupling between the finger (2; 3) and the thermal link (4), in a separation configuration.
The invention relates to a device (20) for retaining and releasing an on-board system (2) on and from a spacecraft (1), the device comprising: a support base (4); a tie rod (3); a preload system (5) comprising a head (21); a holding and releasing mechanism; and a magnetic damping system (10) having at least one electrically conductive tube (11) that has two open ends (25) forming a through-passage (26), the tube (11) being arranged around the tie rod (3), between the head (21) and the holding and releasing mechanism (6), the tube (11) being stationary relative to the support base (4), at least in the launch configuration, and being connected to the support base (4) or to the on-board system (2), the magnetic damping system also having at least one permanent magnet (12) attached to the tie rod (3) and inserted between the tie rod (3) and the at least one tube (11), the at least one magnet (12) and the at least one tube (11) being configured such that the speed of movement of the at least one magnet (12), in the deployment configuration, creates eddy currents in the at least one tube (11) so as to dissipate the kinetic energy into heat and thus reduce the speed of movement of the tie rod (3) to a negligible or zero final speed after the at least one magnet has travelled a determined distance (dmax) facing the at least one tube (11).
An active antenna is disclosed including a passive portion of an antenna array extended at one end by a plate in which apertures are formed, at least one active assembly for transmitting radiofrequency RF waves, called assembly, through said apertures, each assembly including a first row of active modules facing apertures of the plate, a second row of active modules facing apertures of the plate and attached to the first row of active modules, a beam attached to the plate and held clamped between the first and second rows of active modules, a heat-transfer duct in contact with the first and second rows of active modules and jutting out on either side of said first and second rows of active modules.
H01Q 1/02 - Arrangements for de-icingArrangements for drying-out
H01Q 3/12 - Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical relative movement between primary active elements and secondary devices of antennas or antenna systems
The invention relates to a redundant thermal-control device comprising two two-phase structures (1, 2) with stages obtained by additive manufacturing, each stage (5, 6) comprising a sealed enclosure with a capillary medium and a vapour channel. Each two-phase structure has an assembly end where the stages each have an open connection end (50, 60; 51, 61) and where the first stage has a section that projects from the second stage. At their connection ends (50, 51), the sealed enclosures of the first stages of the two-phase structures are joined and welded together by a closed sealed peripheral bead (20, 21). A bridge (10), comprising a sealed enclosure with a vapour channel and a capillary medium, is housed in the space between the connection ends (60, 61) of the second stages; a sealed and closed weld bead (22, 23) connects the sealed enclosures of the bridge and the two-phase structures.
The invention relates to a data processing device (32) installed on board a spacecraft (30), the device comprising a computing machine (38) that implements a neural network. The computing machine performs "slow" multiplication and division operations and "fast" deterministic multiplication and division operations that consume less computational power than the "slow" operations and/or a second amount of electrical power that is less than the amount of electrical power of the slow operations, while achieving a result accuracy that is less than or equal to the corresponding slow operation. The computing machine performs at least one training phase of the neural network comprising an adjustment of the neural network by an iterative algorithm, each iteration of which comprises inference calculations using at least one fast deterministic division operation.
The invention relates to a method for ejecting a stack (2) of satellites contained in a launcher (1), wherein each stage of the stack comprises at least two satellites arranged around a central geometric axis (A-A) of the stack, and wherein the satellites of one of the stages, with the exception of the first stage, are stacked on top of the satellites of the preceding stage, so as to simultaneously eject the stack of satellites while minimising the risk of collision, in the long term, between the satellites. The invention also relates to a space system for ejecting a stack of satellites, for implementing this method.
The invention describes a method for optical-link communication between at least one satellite (10) and a plurality of transmitting and/or receiving ground stations (20), comprising: - obtaining cloud coverage data from the ground stations, and data relating to an orbit of the satellite, - determining, for each ground station (20), forecasts on the possibility of establishing an uninterrupted optical link between the satellite and the ground station, for at least two given short-term and long-term time horizons, and - selecting at least one of the ground stations (20) to establish an uplink or downlink optical-link communication with the satellite, based on the longest predicted duration for which it is possible to establish an uninterrupted optical link between the station and the satellite.
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.
The invention relates to a device (1) for adjusting the position of a space apparatus, comprising: an actuator (10) for generating a movement along an axis (X-X), a kinematic reduction stage (20) comprising an interface (201) for being joined to the apparatus, comprising: o two input arms (21) of the reduction stage, which are articulated to one another at a second interface for being joined to the actuator; o two external arms (22) which are articulated to the frame (19) and to the two input arms; o two internal arms (24) which are articulated at the joins between the external arms and the input arms and to an interface arm (23) arranged transversely to the axis, the reduction stage being dimensioned such that a movement of the interface with the actuator along the axis causes a movement of the interface arm, in the same direction and at a reduced amplitude of a reduction ratio which is based on the relative lengths of the arms.
G02B 7/183 - Mountings, adjusting means, or light-tight connections, for optical elements for prismsMountings, adjusting means, or light-tight connections, for optical elements for mirrors for mirrors specially adapted for very large mirrors, e.g. for astronomy
G02B 7/182 - Mountings, adjusting means, or light-tight connections, for optical elements for prismsMountings, adjusting means, or light-tight connections, for optical elements for mirrors for mirrors
B64G 1/22 - Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
B64G 1/66 - Arrangements or adaptations of apparatus or instruments, not otherwise provided for
The invention relates to a deployable sun-protection screen for a piece of space equipment (1) configured to switch from a stored configuration to a deployed configuration and comprising: -- first rods (21); -- second rods (22) for deploying the screen (2) in a radial direction (r, Θ); -- third rods (23) for deploying the screen (2) in an axial direction (z); and -- rotary links (24, 25) joining rods (21, 22, 23) to one another, the rotary links being active (25), storing an amount of energy, or passive (24), the second rods (22) and third rods (23) being folded when the screen (2) is in the stored configuration, the active rotary links (25) being configured to unfold the second and third rods (22, 23) and trigger the transition from the stored configuration to the deployed configuration, by driving the rotation of the passive rotary links (24) and a deployment in an axial direction and in a radial direction.
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.
The invention relates to an integrated readout circuit (10) with a silicon substrate, the circuit being suitable for being connected to an infrared detection circuit (20) in order to form a hybrid sensor (1). The readout circuit comprises additional photodetectors (15) that are distinct from the photodetectors (21) of the infrared detection circuit. By virtue of the additional photodetectors of the readout circuit, integration of the hybrid sensor into an optical instrument can be facilitated and simplified by using an operating mode of the readout circuit that uses only the additional photodetectors. In particular, integration can no longer require the implementation of low-temperature and/or low-pressure conditions.
The present disclosure relates to a method (20) for determining an absolute pose of a camera (11), in a reference coordinate system, said camera (11) being located on board a craft (10) that is able to move with respect to a scene, said method comprising: - obtaining (S20) a sequence of images of said scene, said images being acquired by the camera at various respective times, said sequence being able to be considered to be a video stream, - determining (S21), from the sequence of images, a local 3D model in a coordinate system of the camera, said local 3D model representing part of the scene at the time of acquisition of one image, called the target image, among the sequence of images, - determining (S22) the absolute pose of the camera at the time of acquisition of the target image, by aligning the position and attitude of the local 3D model in the coordinate system of the camera with a predetermined 3D reference model corresponding to said scene represented in three dimensions in the reference coordinate system.
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.
A device (10) for interleaving data blocks for an optical communications system between a satellite and an earth station. The interleaving device (10) includes a control module (11), a cache memory (15) and an external memory (12). The cache memory (15) includes buffer areas (16). The control module (11) is configured to write each new frame of blocks (21) received in an available buffer area (16), to form (102) groups (22) of interleaved blocks from different blocks (21) belonging to different frames (20) stored in different buffer areas (16), and to write (103) each group (22) of interleaved blocks thus formed in a sequential area (13b) of the external memory (12).
H04L 1/00 - Arrangements for detecting or preventing errors in the information received
H03M 13/27 - Coding, decoding or code conversion, for error detection or error correctionCoding theory basic assumptionsCoding boundsError probability evaluation methodsChannel modelsSimulation or testing of codes using interleaving techniques
H04B 10/118 - Arrangements specific to free-space transmission, i.e. transmission through air or vacuum specially adapted for satellite communication
The invention relates to an optical sensor (5) which comprises an array (M60) of photodetectors (60) and is suitable for detecting a fringe position that can be produced from Mie backscattering radiation or for detecting intensities of interference patterns that can be produced from Rayleigh backscattering radiation. Such an optical sensor can be a CMOS sensor or a CCD. It can be used in a LIDAR device, in particular a LIDAR device that is on-board a satellite to provide airspeed profiles through the Earth's atmosphere.
A spacecraft is disclosed including a frame, an electrical device powered and/or controlled by electrical cables, and a system for orienting the electrical device, which orientation system includes at least two rotary actuators with non-parallel axes (Δa, Δb), a junction part between the two rotary actuators, one or more guide forks, arranged outside the junction part and fastened to the latter, each guide fork including fingers configured to support the electrical cables and to form a guide path for said cables so that the electrical cables never exert, on the rotary actuators, a torque higher than the torque capacity of the actuators, at least one of the forks having a main axis which passes through the center of intersection of the axes of rotation of the actuators.
The invention relates to a resupply space station (10) for resupplying a spacecraft in orbit around a celestial body with propellant, the space station comprising a main body (11) carrying a store of resupply propellant (16). A flexible fluid pipe (18) that is capable of extending and bending outside the main body (11) connects this store (16) to a connector (19) for fluidic connection to the spacecraft carried by a nanosatellite (12). This nanosatellite (12) comprises a propulsion module, a docking sensor, a system (21) for reversibly anchoring to the spacecraft and a system for transferring fluid from the store (16) to the spacecraft via the pipe (18) operable when the nanosatellite (12) is anchored to the spacecraft.
An electronic spatial system is disclosed including an electronic circuit that is sensitive to spatial radiation, including at least one signal input port and/or at least one signal output port; a signal processing unit; an electronic spatial radiation detection unit electrically connected to the signal processing unit; and at least one protective switch electrically connected between the electrical ground of the electronic spatial system and at least one out of the signal input or signal output ports of the sensitive electronic circuit, and controlled by the signal processing unit. The signal processing unit is configured to switch the at least one protective switch to the electrical ground upon detecting an amplitude of a signal that is representative of an amount of spatial radiation greater than a predefined radiation threshold.
H02H 7/20 - Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for electronic equipment
H02H 1/00 - Details of emergency protective circuit arrangements
A testing method guaranteeing a predefined lifespan of an electronic spatial system is disclosed including an electronic circuit that is sensitive to spatial radiation, including at least one signal input port and/or at least one signal output port; a signal processing unit; an electronic spatial radiation detection unit electrically connected to the signal processing unit; and at least one protective switch electrically connected between the electrical ground of the electronic spatial system and at least one out of the signal input or signal output ports of the sensitive electronic circuit, and controlled by the signal processing unit. The signal processing unit is configured to switch the at least one protective switch to the electrical ground upon detecting an amplitude of a signal that is representative of an amount of spatial radiation greater than a predefined radiation threshold.
A telescopic mast is disclosed including coaxial segments that can be controlled from a stowed position to a deployed position, a set of guide systems disposed between the adjacent segments, a set of systems for synchronising the segments during deployment and a system for driving the segments from the stowed position to the deployed position. Each segment includes the same determined number of angle sections secured together and extending over the entire length of the segment, the number of angle sections being at least three, each segment having a cross-section forming a polygon whose angle sections occupy the vertices of the polygon, each angle having a flat central portion bordered by two side wings, the angle sections of two adjacent segments facing one another. Each guide system is disposed between two adjacent segments being fastened on one of the angle sections of one of the two adjacent segments.
An electronic spatial system is disclosed including an electronic circuit that is sensitive to spatial radiation, including at least one signal input port and/or at least one signal output port; a signal processing unit; an electronic spatial radiation detection unit electrically connected to the signal processing unit; and at least one protective switch electrically connected between the electrical ground of the electronic spatial system and at least one out of the signal input or signal output ports of the sensitive electronic circuit, and controlled by the signal processing unit. The signal processing unit being configured to switch the at least one protective switch to the electrical ground upon detecting an amplitude of a signal that is representative of an amount of spatial radiation greater than a predefined radiation threshold.
H02H 7/20 - Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for electronic equipment
VALIDATING THE PAYLOAD OF A TELECOMMUNICATIONS SATELLITE BASED ON A CALCULATION OF RADIATED POWER RATIO BETWEEN CARRIER SIGNAL AND INTERMODULATION NOISE
The invention relates to a method (100) for monitoring the performance, in terms of radiated noise power, of a payload of a telecommunications satellite based on a multibeam active antenna. The method comprises in particular determining (105) a spectral density of radiated intermodulation noise power on the ground by all antenna sources from: - the carrier allocation plan and the associated RF powers that make it possible to carry out the telecommunications mission of the satellite; - the weighting coefficients of the beamforming network that make it possible to form the radio beams required for the mission; - the linearity characteristics of the amplifiers associated with the various antenna sources; and - the radiation patterns of the various sources. The method makes it possible to determine (109) a radiated power ratio between carrier signal and intermodulation noise ("radiated C/IM") for at least one carrier and for at least one geographical area of interest.
SPACECRAFT PROVIDED WITH AN AUTONOMOUS ORBIT CONTROL MODULE AND AN ANTI-COLLISION MODULE, AND ANTI-COLLISION AND STATION-KEEPING AUTONOMOUS MANAGEMENT METHOD FOR A SPACECRAFT
The invention relates to a method for managing a satellite receiving CDM messages relating to a secondary object (2) capable of colliding with the satellite at a time TCA. With each orbit, an autonomous orbit control module establishes a risk-free current plan on board defining station-keeping manoeuvres (14, 15). Preliminary filtering of the received CDMs is carried out on board according to geometric and/or temporal criteria. For each selected high-risk CDM, a collision risk level is estimated on board according to items of onboard navigation data propagated to the time TCA of the high-risk CDM. In the event of a confirmed risk, a collision risk management module ACA produces a new plan on board by removing or replacing at least one manoeuvre in the risk-free current plan with a manoeuvre (16, 17) that both maintains a mission window (301-302) and prevents collision.
The invention relates to a device (1) for controlling the angular velocity of an out-of-service spacecraft, comprising: - a stator (3) and a rotor (4) movable about an axis (A21) of rotation with respect to the stator, the stator (3) comprising an electrically conductive and non-ferromagnetic body (6) while the rotor (4) comprises a magnetized system (7) configured to induce, in the stator (3), eddy currents for braking a relative movement of the rotor (4) with respect to the stator (3); - a magnetic-suspension magnet (11) intended to cooperate with a magnetic field generated by an external source in order to suspend the rotor (4) magnetically with respect to the stator (3). The device (1) consists of one or more non-ferromagnetic materials in a zone (11ZI) of influence of the magnetic field generated by the magnetic-suspension magnet.
A method (50) for image acquisition by a spacecraft (10) comprising an observation instrument (20) and a laser transmission module (30), the method includes: acquiring an image of a calibration area referred to as a calibration image, by the observation instrument (S50), obtaining reference data associated with the calibration area (S51), determining a pointing error of a laser line of sight by comparing the calibration image and the reference data (S52), controlling the pointing of the spacecraft by correcting the pointing error, in order to point the laser line of sight towards a laser reception module (S53), and transmitting data to the laser reception module by the laser transmission module (S54).
An electronic spatial system is disclosed including an electronic circuit that is sensitive to spatial radiation, comprising at least one signal input port and/or at least one signal output port; a signal processing unit; an electronic spatial radiation detection unit electrically connected to the signal processing unit; and at least one protective switch electrically connected between the electrical ground of the electronic spatial system and at least one out of the signal input or signal output ports of the sensitive electronic circuit, and controlled by the signal processing unit. The signal processing unit being configured to switch the at least one protective switch to the electrical ground upon detecting an amplitude of a signal that is representative of an amount of spatial radiation greater than a predefined radiation threshold.
H02H 7/12 - Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for convertersEmergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for rectifiers for static converters or rectifiers
35.
Satellite platform having improved characteristics in respect of electromagnetic decoupling between radiating elements and corresponding construction process
A satellite platform is disclosed having a plurality of radiating elements configured to receive and/or transmit electromagnetic radiation and including at least one transmitter radiating element, and at least one block of material that absorbs electromagnetic radiation in a frequency band of interest in order to decrease electromagnetic coupling between the radiating elements. The block of material is implemented in at least one region of interest in the satellite platform to decrease electromagnetic coupling, the region of interest intersecting at least one predominant coupling path between at least two of the radiating elements.
The invention relates to a method (100) for managing operational flows for configuring a payload of a telecommunications satellite. The method comprises the following steps: - storing (101) a set of reference operational flows each associated with a reference mission; - associating (102) each reference operational flow with an identity value of the associated reference mission; - obtaining (103) a target mission for which a payload of the telecommunications satellite (30) is to be configured; - determining (104) an identity value of the target mission; - selecting (105) one of the reference operational flows for which the mission identity value satisfies a similarity criterion with the identity value of the target mission.
A method of manufacturing a spacecraft is disclosed including electing an outer cover material for the spacecraft, the outer cover material having an inner surface and an outer surface, the outer surface being electrically conductive, and the method further includes partially exposing the outer surface of the outer cover material to laser source to achieve a marking on the outer surface.
A thermoregulated thermomechanical structure for a focal plane suitable for operating in a space environment is disclosed having an interface for supporting dissipative electronic equipment, the structure being monolithic, metallic and including a radiator and a first two-phase heat-transfer fluid transport cavity, extending within the radiator and providing direct thermal transport between the interface and the radiator. The structure also includes a second cavity encapsulating a phase change material.
A method for transmitting content (A) in a communication network (N) comprising a quantum key distribution network (QKDN) for keys, called quantum keys (Knj), the communication network comprising a key management device (KM) connected to transmission nodes (N1, N2, N3, N4, N5) and connected to said quantum key distribution network (QKDN), said transmission nodes (N1, N2, N3, N4, N5) being able to communicate in the communication network and transmit and receive quantum keys (Knj) in said quantum key distribution network, said method comprising sending and receiving control messages from and to said control plan manager (CP) in order to organise the transfer of said content (A) in said communication network (N). Also a control plan management device (CP) configured to execute such a method.
The invention relates to an arrangement (300) of at least one electrical cable (100), suitable for a space environment, comprising an outer sheath (110) and comprising at least a plurality of elongate conductors (120) arranged in the sheath, the sheath having an outer diameter corresponding to the diameter of the cable, the cable arrangement comprising a cable pinching member (200), configured to exert at least one pinching force (F) on the sheath in order to clamp the conductors and the sheath transversely, the pinching force being determined to create a deformation of the section of the cable creating bridges by thermal conduction directly connecting the elongate conductors and an outer surface of the sheath, thus discharging heat produced by a flow of electric current in the cable. The invention also relates to a spacecraft (10) including such an arrangement.
The invention relates to a method for data collection by optical link, which comprises: - collecting past cloud coverage conditions of a plurality of client transmitting stations on the ground; - collecting past cloud coverage conditions of at least one data receiving centre on the ground; - determining the likelihood of success for data transfers from a transmitting station to a receiving centre, via at least one predetermined telecommunication satellite, for several predetermined amounts of data, on the basis of past cloud coverage conditions at the same time of the year; - collecting, for each transmitting station, information relating to the data to be transferred; - determining a priority order associated with the client transmitting stations for transfers of predetermined volumes of data; - selecting an active client transmitting station, according to the predetermined priority order; and - activating the data transfer for the selected client transmitting station.
A method and a system are proposed for determining an initial orbit of a piece of space debris (15). Each one of a group of at least two satellites (10) flying in formation in orbit around the Earth embed a radar instrument and an optical camera configured to scan a volume of interest that is common to all the satellites of the group. The satellites (10) provide a mix of radar and optical measurements for at least eight independent geometrical parameters of the piece of space debris (15) when it passes in the volume of interest. Each independent geometrical parameter is one of: - a radar measurement comprising a mono-static range or range rate, or a bi-static range or range rate, - an optical measurement comprising an azimuth or an elevation angle. The initial orbit of the piece of space debris (15) is determined based on the measurements provided.
The invention relates to a heat transfer structure (1) capable of being used in space for the thermal control of at least one component (2a, 2b, 2c) arranged at at least one interface, comprising: a cavity (4) for transporting heat energy between a heat source and a cold source, the cavity comprising a channel for circulating steam (6) and a capillary structure (5) receiving a first two-phase fluid, a radiator (3), which is thermally connected to the cavity, constituting the cold source in a first position relative to the sun, the interface constituting the heat source in the first position, the capillary structure comprising a capillary discontinuity (7) capable of being filled by an excess liquid plug (8) containing two-phase fluid in the first position, the excess liquid plug clearing the capillary discontinuity in a second position relative to the sun.
F28D 15/04 - Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls in which the medium condenses and evaporates, e.g. heat-pipes with tubes having a capillary structure
B64G 1/50 - Arrangements or adaptations of devices for control of environment or living conditions for temperature control
The invention relates to a two-phase heat transfer device (1) capable of operating in a space environment, the device comprising: - a cavity (10) containing a two-phase fluid in the liquid-vapour equilibrium state; - a flexible portion (30) and two interface parts (40), one of the interface parts, the flexible portion and the other interface part being successively connected to one another, the device being characterised in that the flexible portion comprises a sealed flexible sheath (31) inside which at least one flexible internal liquid circulation duct (32) extends, which duct is surrounded by a space (33) for circulating the vapour.
F28D 15/02 - Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls in which the medium condenses and evaporates, e.g. heat-pipes
45.
DEVICE FOR TESTING AN ELECTRICAL POWER SUPPLY ASSEMBLY FOR A GRIDDED ION THRUSTER
The invention relates to a device (2S) designed to mimic the operation of a gridded ion thruster when the device is electrically connected to a power supply assembly (1) instead of the thruster. The device comprises: terminals (C1-C14) for connecting to the power supply assembly, which replace the terminals of the thruster; and two dependent current sources (16S, 17S). Using such a device it is possible to check the capacity of the power supply assembly to apply an electron backstreaming test to the thruster, for example during a spacecraft assembly, integration and test procedure. The device can alternatively be adapted to mimic a continuous discharge gridded ion thruster or a radiofrequency discharge gridded ion thruster.
The invention relates to a spacecraft stack comprising: a stack of spacecraft (1) made up of a plurality of stages which are placed one on top of the other and each comprise a number of vehicles greater than or equal to N; a lower adapter (50) which forms an interface between the stack of vehicles and a launcher; and a longitudinal preloading system (60). Each spacecraft comprises three peripheral pillars which are located on a circular cylinder of diameter dN, the spacecraft not including a pillar inside this cylinder dN, and falling within an angular sector of the cylinder with an angle equal to 360°/N. The pillars comprise first and second end half-posts which are spaced apart from one another by 360°/N and have cross-sections configured to allow the coupling of the first end half-post of one spacecraft to the second end half-post of an adjacent spacecraft in order to form a shared post, wherein the third peripheral pillar of the spacecraft is additionally a complete intermediate post.
A method of testing a gridded-ion thruster (2) is performed on board a spacecraft (100) while the spacecraft is in thrust in extraterrestrial space. The test method is a perveance-type test which makes it possible to update a thrust operating point of the thruster and to monitor an ageing of said thruster, in particular an aging by erosion of an acceleration grid (25) disposed at the plasma chamber outlet (20).
The invention relates to an optical terminal (1) for communication by laser signals, which is suitable for emitting, in addition to a useful laser beam (FU) which carries data to be transmitted, a jamming light beam (FB), such that the two beams are superimposed in a receiving plane (PR). The optical terminal enables a destination receiver (2) to receive the data with a sufficiently high signal-to-noise ratio value, while simultaneously producing another signal-to-noise ratio value that is effective for a spy receiver (3), and that is sufficiently low for preventing the spy receiver from receiving the data.
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.
H01Q 19/17 - Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces wherein the surfaces are concave the primary radiating source comprising two or more radiating elements
H01Q 3/20 - Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical relative movement between primary active elements and secondary devices of antennas or antenna systems for varying relative position of primary active element and a reflecting device wherein the primary active element is fixed and the reflecting device is movable
H01Q 3/16 - Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical relative movement between primary active elements and secondary devices of antennas or antenna systems for varying relative position of primary active element and a reflecting device
H01Q 3/18 - Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical relative movement between primary active elements and secondary devices of antennas or antenna systems for varying relative position of primary active element and a reflecting device wherein the primary active element is movable and the reflecting device is fixed
50.
METHOD AND DEVICE FOR PROCESSING A SEQUENCE OF IMAGES FOR IDENTIFYING TRACKED OBJECTS IN THE SEQUENCE OF IMAGES
The present disclosure relates to a method for processing a sequence of images acquired by a vision sensor of a scene, the method comprising at least one step of identifying, in an image referred to as the reference image, object positions, independently of the content of the reference image, and a step of tracking the objects on the basis of the object positions in the reference image in each of a plurality of images, referred to as the tracking images, acquired after the reference image, the step of tracking the objects in each processed tracking image comprising: determining a predicted overall registration transformation between the reference image and the processed tracking image; predicting object positions in the processed tracking image according to the object positions in the reference image and the predicted overall registration transformation for the processed tracking image; searching for the objects in the processed tracking image on the basis of the predicted object positions.
The invention relates to a power supply assembly (1) for a plasma thruster (2) of a spacecraft (100) for controlling a keeper current (Ikeeper) supplied to a keeper electrode (22) of the plasma thruster. The power supply assembly takes into account a contribution to a return current (Ibody) from the plasma thruster, which is constituted by a leakage current (Ileak) flowing to an electrical ground (102) of the spacecraft. This avoids premature ageing or degradation of the plasma thruster.
The invention relates to a symbol timing synchronization device with a parallel architecture comprising: - a module (20) for storing and rescheduling samples, comprising a control unit (22) and 2 x P cyclically ordered FIFOs (21), - an interpolation module configured to deliver, at each clock pulse, a time error indication (Err-Ind) adopting one value from "nominal", "undershoot" or "overshoot", at a current clock pulse, the control unit (22) is configured to: - write a sample to each of P successive FIFOs (21), - read a sample from each of P, P - 1 or P + 1 successive FIFOs (21) depending on whether the time error indication (Err-Ind) is respectively "nominal", "undershoot" or "overshoot", - reschedule samples to be delivered to the interpolation module using a permutation network (23).
The invention relates to improving the propulsion of a HET, RIT or GIT engine during solar eclipses and comprises, before the solar eclipse: deactivating the thrust and then disconnecting the bus supplied with power by the solar panel (TDoff); decreasing the flow rate of the fluid (Db) feeding the temperature-maintaining plasma in the electron-emitting member for neutralising the ion beam; increasing the current (Ch) through the temperature-maintaining plasma supplied by the battery; at the end of the solar eclipse: increasing the flow rate of the fluid feeding the temperature-maintaining plasma; decreasing the current through the temperature-maintaining plasma; when the eclipse finishes: reconnecting the bus supplied with power by the solar panel and then reactivating the thrust.
A system (1) for thermal regulation of a spacecraft (S), comprising: - a hot source (C) interface, - a radiator (10) having a thermally conductive body (11) comprising at least one radiative surface (12), - two separate single-phase cooling fluid circuits (20) arranged in or on said hot source interface, each single-phase cooling circuit comprising a pump for activating the circulation of the single-phase cooling fluid, the system (1) further comprising a heat exchange device (30) arranged in or on the body (11) of the radiator, the heat exchange device comprising a casing (31) comprising at least two internal cavities (310, 310") each having input (311, 311') and output ports (312, 312') for separately connecting each of said single-phase cooling fluid circuits to the heat exchange device, and wherein the heat exchange device (30) comprises a plurality of thermal interfaces with a plurality of diphasic ducts (13), the diphasic ducts being separate from each other and separate from the single-phase cooling fluid circuits (20), the diphasic ducts (13) being arranged around the heat exchange device (30), each diphasic duct extending at least from a first section (135) of said diphasic duct to a second section (136) of said diphasic duct, said first (135) section being arranged on one of said thermal interfaces of the heat exchange device and said second section (136) of said diphasic duct being arranged in or on said body of said radiator (10), the second sections of the diphasic ducts extending around the heat exchange device.
B64G 1/50 - Arrangements or adaptations of devices for control of environment or living conditions for temperature control
F28D 7/00 - Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
B33Y 80/00 - Products made by additive manufacturing
F28D 15/02 - Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls in which the medium condenses and evaporates, e.g. heat-pipes
F28D 15/04 - Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls in which the medium condenses and evaporates, e.g. heat-pipes with tubes having a capillary structure
F28F 3/12 - Elements constructed in the shape of a hollow panel, e.g. with channels
F28F 13/18 - Arrangements for modifying heat transfer, e.g. increasing, decreasing by applying coatings, e.g. radiation-absorbing, radiation-reflectingArrangements for modifying heat transfer, e.g. increasing, decreasing by surface treatment, e.g. polishing
55.
METHOD AND DEVICE FOR DETERMINING A POINTING LAW FOR A SATELLITE BY DETERMINING A SPACE-TIME DISTRIBUTION
The present disclosure relates to a method for determining at least one pointing law, in a time window, for an observation instrument of at least one EO satellite (20) searching for EO space objects (50), the determination method comprising: - determining, from a list of space objects, space objects that are observable from the at least one satellite in an observation window, the duration of which is equal to or greater than the duration of the time window; - determining, in the time window and in a given satellite reference frame, referred to as the observation reference frame, a space-time distribution of the space objects that are observable in the observation window from the at least one satellite; - determining a pointing law for the observation instrument, in the time window and in the observation reference frame, according to the space-time distribution.
This specification relates to systems, methods and apparatus for controlling a global attitude of a satellite using machine-learning models, and the training of such machine-learning models. According to a first aspect of this specification there is described a computer implemented method for controlling a global attitude of a satellite comprising: for at least one machine learning model and one predefined nominal control model able to generate a nominal control command which is operational for controlling at least the attitude of the satellite controlling the satellite for an episode of time (6.1). The controlling comprises: computing, by one or more processors of the satellite, the nominal control command for the satellite from data representing a current attitude state of the satellite using the predefined nominal control model; generating, by the one or more processors and using said machine learning model, one or more corrections to said nominal control command from the current attitude state of the satellite and said nominal control command (6.2); generating, by the one or more processors, an improved control command by applying said correction to said nominal control command (6.3); and controlling the satellite based on said improved control (6.4). The method further comprises evaluating, by the one or more processors, a performance of the improved control commands for said episode of time using a reward function providing rewards; and after each episode of time, updating, by the one or more processors, said machine learning model based on the rewards, wherein updates are determined using a metaheuristic optimisation algorithm.
09 - Scientific and electric apparatus and instruments
42 - Scientific, technological and industrial services, research and design
Goods & Services
Scientific apparatus and instruments, namely, scientific measurement equipment of inertial attitude in the nature of optical fiber gyro sensors, exclusively intended for use in space systems; downloadable and recorded computer software for controlling satellite control and navigation; scientific apparatus and instruments, navigation and positioning equipment for space systems, namely, optical sensor interferometric instruments for use in satellites, space vehicles, space launchers and space platforms Engineering service and data establishment, namely, planning, conceiving, designing, and improving space vehicles, satellites, space launchers, space platforms and navigation systems, and recognition and self-directional systems relating to aeronautical field; scientific, physical and technical analyses for manufacture, exploitation and maintenance of satellites, space vehicles, space launchers and space platforms; software conception and development for others in the field of telecommunications, data establishment and information management systems, namely, for planning, conceiving, designing, manufacturing, operating, maintaining, overhauling, preparing for launching, and improving space vehicles, satellites, space launchers and space platforms; computer software maintenance for others
58.
METHOD FOR GENERATING A MODEL FOR REPRESENTING RELIEF BY PHOTOGRAMMETRY
A method for generating a relief representation model using a plurality of N pairs of stereo images, each of the N pairs of stereo images being associated with a map of photogrammetric disparities which is obtained by correlation calculation based on the pair of stereo images in question, comprises: a calculation of maps of geometric disparities based on a predetermined relief representation model, by projection of the predetermined relief representation model into an epipolar geometry of the pairs of stereo images; a calculation of a cost function, representative of a difference between the geometric and photogrammetric disparities, associated with the predetermined relief representation model; and an updating of the predetermined relief representation model by optimization of the gradient descent type of the cost function, and iteration until a predefined endpoint criterion is reached. Also a computer program and a system.
09 - Scientific and electric apparatus and instruments
42 - Scientific, technological and industrial services, research and design
Goods & Services
Scientific apparatus and instruments, namely scientific equipment for measuring inertial altitude based on fiber optic gyrometric sensors, intended exclusively for space systems, in particular satellites, space vehicles, space launchers and space platforms; computer software; scientific apparatus and instruments, namely navigation and positioning equipment for space systems, in particular satellites, space vehicles, space launchers and space platforms; navigation systems, reconnaissance systems and self-guided systems in the aeronautical field; information processing apparatus for the supply of technical information and logistical services relating to space systems, in particular satellites, space vehicles, space launchers and space platforms. Engineering; conducting surveys, projects and technical consultancy regarding satellites, space vehicles, space launchers and space platforms; scientific, physical and technical analyses and surveys for the manufacture, operation and maintenance of satellites, space vehicles, space launchers and space platforms; design and development of computer software, leasing of access time to computers, maintenance of software.
60.
THERMOREGULATED SPACE EQUIPMENT HAVING THERMALLY INSULATING MECHANICAL SUPPORT
The invention relates to thermoregulated space equipment (10) which comprises at least one mechanical support structure (1) comprising a first metal portion (2) for interfacing with the equipment, which first metal portion is rigidly connected to at least one second metal portion (3) for interfacing with a space platform (20), characterised in that the mechanical support structure further comprises at least one metal mesh (4) which forms a mechanical connection between the first and second interface portions, the mechanical support structure also comprising at least one mechanically rigid and thermally insulating block of material (5) which continuously and rigidly connects the first and second interface portions and fills the metal mesh.
n,mm,nm,nmmm), - comparing (143) a difference between said values with a threshold, - determining (145) a correction value according to the result of the comparison, - computing (146) the parity check message according to the correction value.
H03M 13/11 - Error detection or forward error correction by redundancy in data representation, i.e. code words containing more digits than the source words using block codes, i.e. a predetermined number of check bits joined to a predetermined number of information bits using multiple parity bits
62.
ADAPTIVE SCALING OF PARITY CHECK MESSAGES FOR LDPC DECODING
n,mm,nnm,nm,nm,n) and the a posteriori estimation variables (γn). Scaling corresponds to assigning, to a value, an integer which has the same sign and whose absolute value is the nearest integer greater than the absolute value of the value divided by two.
H03M 13/11 - Error detection or forward error correction by redundancy in data representation, i.e. code words containing more digits than the source words using block codes, i.e. a predetermined number of check bits joined to a predetermined number of information bits using multiple parity bits
The invention relates to an LDPC decoding method (100). The LDPC code is defined by a parity matrix having a layered structure. The method (100) involves performing iterations until a stop criterion is satisfied. Each iteration involves the successive processing of the different layers. Processing a layer involves: - computing (111) variable messages (αn,m), - computing (112) parity check messages (βm,n), - computing (113) a posteriori estimation variables (γn), - computing (114) a partial syndrome. The evaluation (130) 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.
H03M 13/00 - Coding, decoding or code conversion, for error detection or error correctionCoding theory basic assumptionsCoding boundsError probability evaluation methodsChannel modelsSimulation or testing of codes
H03M 13/11 - Error detection or forward error correction by redundancy in data representation, i.e. code words containing more digits than the source words using block codes, i.e. a predetermined number of check bits joined to a predetermined number of information bits using multiple parity bits
64.
METHOD FOR GENERATING AN IMAGE USING A SATELLITE BY THE ON-BOARD FUSION OF IMAGES CAPTURED BY SAID SATELLITE
The present disclosure relates to a method (50) for generating an image using a satellite (10), wherein partial zones are processed successively and the processing of each partial zone comprises: - receiving (S51) at least two basic partial images representing the partial zone being processed, which images were captured at different respective times, - estimating (S52) shifts between the pixels of the at least two basic partial images by means of a Kalman filter, wherein the shifts for the partial zone being processed are estimated according to shifts that are predicted on the basis of a partial zone processed beforehand, the predicted shifts for the partial zone being processed being updated according to the at least two basic partial images, - merging (S53), on-board the satellite, the at least two basic partial images according to the estimated shifts.
H04N 25/40 - Extracting pixel data from image sensors by controlling scanning circuits, e.g. by modifying the number of pixels sampled or to be sampled
65.
METHOD FOR DETECTING A PLURALITY OF GEOLOCATION SIGNALS
The invention relates to a method for detecting a plurality of geolocation signals within a signal of the type transmitted by geolocation satellites. Such a method comprises: - using detection to acquire (E310), within a sequence of samples of the signal, a first geolocation signal conveying a first satellite identifier; - estimating (E320) a set of characteristics of the first geolocation signal; - generating (E340) a first digital signal representative of at least part of the first geolocation signal on the basis of a set of characteristics; - subtracting (E350) the generated first digital signal from the new sequence in order to supply a preprocessed sequence; and - using detection to acquire anew (E360), within the preprocessed sequence, a second geolocation signal conveying a second satellite identifier.
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).
The invention provides a demosaicing method applied to an initial image to obtain a demosaiced image allowing improved demosaicing by virtue of the fact that it comprises: applying a stabilization transform to stabilize noise variance, and, for each reference patch: • determining (310) a set of similar patches • determining (320) a covariance matrix of said set of similar patches and • for each similar patch, computing estimates of interpolated spectral bands, depending on a block decomposition of the covariance matrix (340) depending on phasing, determining interpolated spectral bands by aggregating (350) the estimates of the interpolated spectral bands, and performing an inverse transform on the stabilization transform.
A transmitter device of a bi-static or multi-static radar system is disclosed and implemented for aerial surveillance. The transmitter device is intended to be on board a satellite orbiting the Earth. Once in orbit, the transmitter device is configured to obtain information relating to a region of interest monitored by at least one receiver device of the radar system, and to transmit a signal in a radio beam illuminating at least one portion of the region of interest.
G01S 13/00 - Systems using the reflection or reradiation of radio waves, e.g. radar systemsAnalogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
G01S 13/02 - Systems using reflection of radio waves, e.g. primary radar systemsAnalogous systems
G01S 13/58 - Velocity or trajectory determination systemsSense-of-movement determination systems
G01S 13/91 - Radar or analogous systems, specially adapted for specific applications for traffic control
69.
Method for the non-local demosaicing of an image, and associated device
A demosaicing method applied to an image having pixels each corresponding to an initial spectral band, to obtain a demosaiced image with several spectral bands having pixels each corresponding to the initial spectral band or to an interpolated spectral band. The method includes: on the basis of reference patches and for each reference patch: a determination of a set of patches similar to the reference patch, a determination of a covariance matrix for |the set of patches, and for each patch, a calculation of estimates of the interpolated spectral bands according to a block-based deconstruction of the covariance matrix, where the deconstruction into four blocks is according to phasing of each patch, and a determination of the interpolated spectral bands by an aggregation of estimates of the interpolated spectral bands, where the estimates of the interpolated spectral bands are aggregated for each pixel.
Disclosed is a telescope (10) comprising a primary mirror (M1) and a secondary mirror (M2), with a hole (T1) at an intersection of the primary mirror with an optical axis (A-A) of the telescope, so that reception light rays (Rx) forming an image in a focal plane (PF) of the telescope pass via the hole through the primary mirror after having been reflected by the secondary mirror. The secondary mirror is provided with a surface alteration at an intersection of said secondary mirror with the optical axis, so that light rays (Tx0) that originate from the focal plane and that reach the surface alteration of the secondary mirror are prevented, at least in part, from being reflected, backscattered or re-emitted by said secondary mirror towards said focal plane. Such a telescope suppresses or decreases a Narcissus signal in an emitting-receiving device incorporating said telescope.
G02B 27/00 - Optical systems or apparatus not provided for by any of the groups ,
G02B 23/02 - Telescopes, e.g. binocularsPeriscopesInstruments for viewing the inside of hollow bodiesViewfindersOptical aiming or sighting devices involving prisms or mirrors
71.
METHOD AND SYSTEM FOR ALLOCATING EARTH OBSERVATIONS TO BE MADE TO A PLURALITY OF SATELLITES
The present invention relates to a method (10) for allocating requests for observations of geographical areas (ZG) to be made to a plurality of satellites (30), the method comprising the steps of: - (S10) breaking down each geographical area to be observed into one or more elementary areas to be acquired; - for each elementary area: (S11) determining at least one acquisition opportunity to acquire the elementary area by means of at least one of the satellites in a predetermined time window; - (S12) provisionally allocating the elementary areas to the plurality of satellites according to the acquisition opportunities and according to a preliminary model of each satellite; - for each satellite: (S13) evaluating the feasibility in the time window to acquire the elementary areas provisionally allocated to the satellite according to an operational model; and definitively allocating each validated elementary area to the satellite according to the operational model.
A first network probe is associated with a first end-point of a first router. The first network probe detects, by filtering packets coming from or going to the first router, a communication tunnel between the first end-point and a second end-point of a second router. The first network probe deduces an address of a second network probe associated with the second end-point, by applying a bijective translation function relative to an address of the second end-point retrieved from the filtered packets. Inter-probe communications are set-up between the first and second network probes, using the deduced address of the second network probe, and data traffic in the communication tunnel is jointly monitored by the first and second network probes.
The invention relates to a method (100) for operating a radar system (10), comprising: - transmitting (101) a signal comprising a plurality of pulses transmitted in different frequency channels and over different time intervals, - receiving (102) a signal comprising a reflection of the transmitted signal by a target, - filtering (103) the signal received using a bank of digital filters which are associated respectively with the frequency channels, - adaptively filtering (104) the signal of each frequency channel during an integration sub-period, - Doppler filtering (107) the adaptive filtering results obtained for the different frequency channels for a plurality of successive integration sub-periods, forming a coherent integration period, - determining (108) a distance and a Doppler steering vector which maximise a more cluttered signal-to-noise ratio for the received signal, - estimating (109) the position and/or speed of the target.
G01S 13/00 - Systems using the reflection or reradiation of radio waves, e.g. radar systemsAnalogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
G01S 13/06 - Systems determining position data of a target
G01S 13/58 - Velocity or trajectory determination systemsSense-of-movement determination systems
G01S 13/87 - Combinations of radar systems, e.g. primary radar and secondary radar
G01S 13/91 - Radar or analogous systems, specially adapted for specific applications for traffic control
G01S 13/95 - Radar or analogous systems, specially adapted for specific applications for meteorological use
G01S 13/30 - Systems for measuring distance only using transmission of interrupted, pulse modulated waves using more than one pulse per radar period
G01S 13/26 - Systems for measuring distance only using transmission of interrupted, pulse modulated waves wherein the transmitted pulses use a frequency- or phase-modulated carrier wave
G01S 13/10 - Systems for measuring distance only using transmission of interrupted, pulse modulated waves
G01S 13/22 - Systems for measuring distance only using transmission of interrupted, pulse modulated waves using irregular pulse repetition frequency
G01S 13/53 - Discriminating between fixed and moving objects or between objects moving at different speeds using transmissions of interrupted pulse modulated waves based upon the phase or frequency shift resulting from movement of objects, with reference to the transmitted signals, e.g. coherent MTi performing filtering on a single spectral line and associated with one or more range gates with a phase detector or a frequency mixer to extract the Doppler information, e.g. pulse Doppler radar
G01S 13/02 - Systems using reflection of radio waves, e.g. primary radar systemsAnalogous systems
74.
Method for adjusting the orbital path of a satellite
A method for adjusting the path of a satellite to limit a risk of collision with items of debris each having a date of closest pass with the satellite is disclosed including: propagating at least one orbit from the reference path of the satellite according to at least one manoeuvre to the farthest date of closest pass; determining a probability of collision for each item of debris according to the at least one orbit; determining at least one overall probability according to the set of probabilities determined; selecting the lowest overall probability from among the at least one overall probability obtained; determining a command for the satellite including the manoeuvre associated with the lowest overall probability.
A method for orbit control of a satellite in orbit around the Earth and for desaturation of an angular momentum storage device of satellite is disclosed having two articulated arms each supporting a propulsion unit. The method includes determining a maneuver plan having at least two thrust maneuvers, a first thrust maneuver to be executed using the propulsion unit of one of the articulated arms and a second thrust maneuver to be executed using the propulsion unit of the other articulated arm, controlling the articulated arms and the propulsion units according to the maneuver plan, at least one of the first and second thrust maneuvers being a thrust maneuver referred to as discontinuous, composed of at least two separate consecutive thrust sub-maneuvers.
A terminal (100) for optical communication by laser signals including a matrix image sensor used as a tracking and acquisition detector (2). The matrix image sensor is used simultaneously to check that a portion of the laser signals received by the terminal are injected into an optical fibre (1). A spectral filter element (22) is associated with the matrix image sensor to allow such a combination of functions.
A data encoding device suitable for encoding a plurality of LDPC codes is disclosed including an input interface and an output interface, and a first circuit for encoding quasi-cyclic LDPC code, connected at an input to the input interface and at an output to the input of a first multiplexer circuit, a second circuit for encoding quasi-cyclic LDPC code, connected at an input to the input interface and at an output to the input of the first multiplexer circuit, a third circuit for encoding quasi-cyclic LDPC code, connected at an input to the output of the first multiplexer circuit and at an output to the input of a second multiplexer circuit.
H03M 13/00 - Coding, decoding or code conversion, for error detection or error correctionCoding theory basic assumptionsCoding boundsError probability evaluation methodsChannel modelsSimulation or testing of codes
H03M 13/11 - Error detection or forward error correction by redundancy in data representation, i.e. code words containing more digits than the source words using block codes, i.e. a predetermined number of check bits joined to a predetermined number of information bits using multiple parity bits
78.
Method for estimating collision between at least one piece of space debris and a satellite
A method for estimating collision between a satellite in orbit and at least one piece of space debris having a time of closest approach to the satellite is disclosed including: obtaining the reference orbit of the satellite; determining an ephemeris of state transition data representative of the trajectory of the reference orbit; communicating the reference orbit and the ephemeris of state transition data to the satellite. The method includes the steps on board the satellite of: determining the true orbital position of the satellite; propagating the true orbit; calculating a probability of collision between the satellite and the piece of debris.
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.
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.
A system for fastening a mirror to a support is disclosed including intermediate structures, for example bipod structures. At least some of the intermediate structures are provided with torsion devices making it possible to at least partially compensate for optical aberrations of an instrument that includes the mirror. Each torsion device may comprise an elastic element and a variator. The variator is designed to control a deformation of the elastic element, resulting in a torque which is applied to the mirror.
G02B 7/183 - Mountings, adjusting means, or light-tight connections, for optical elements for prismsMountings, adjusting means, or light-tight connections, for optical elements for mirrors for mirrors specially adapted for very large mirrors, e.g. for astronomy
82.
ACTIVE ANTENNA ESPECIALLY FOR THE SPACE-TECHNOLOGY FIELD
L'invention concerne une antenne active (100) comprenant: - une portion passive (200) d'un réseau d'antennes prolongée à une extrémité (201) par un plateau (300) dans lequel sont aménagées des ouvertures (310), - au moins un ensemble actif d'émission d'ondes radiofréquences RF, dit ensemble, par lesdites ouvertures, chaque ensemble comprenant : - une première rangée de modules actifs (410) venant en vis-à-vis d'ouvertures (310) du plateau (300), - une seconde rangée de modules actifs (410) venant en vis-à-vis d'ouvertures (310) du plateau (300) et rattachée à la première rangée de modules actifs, - une poutrelle (450) rattachée au plateau (300) et maintenue serrée entre la première et la seconde rangée de modules actifs, - un conduit caloporteur (460) en contact avec la première et la seconde rangée de modules actifs et saillant de part et d'autre desdites première et seconde rangées de modules actifs.
The invention relates to an active antenna (100) comprising: - a passive segment (200) of an antenna array, said segment being extended at one end (201) by a plate (300) in which apertures (310) are formed, - one or more active assemblies for transmitting RF (i.e. radio-frequency) waves through said apertures, each of said one or more active assemblies being referred to as an assembly, each assembly comprising: - a first row of active modules (410) located facing apertures (310) of the plate (300), - a second row of active modules (410) located facing apertures (310) of the plate (300) and attached to the first row of active modules, - a beam (450) attached to the plate (300) and held clamped between the first and second rows of active modules, - a duct (460) for heat-transfer fluid, said duct making contact with the first and second rows of active modules and jutting out on either side of said first and second rows of active modules.
A device for deploying and pointing an equipment item is disclosed including a mobile platform for receiving the equipment item, a carrier integrally secured to a wall of a spacecraft, and three identical linear actuators which connect the carrier to the mobile platform and are suitable for moving the platform in translation along one axis and for orienting the platform in rotation about two axes. Each linear actuator including a first portion connected to the platform by a universal joint, a second portion connected to the carrier by a pivot connection, a motor, and a screw/nut joint interconnecting the two portions, each universal joint being suitable for preventing the screw/nut joint from rotating about the axis, such that driving the motor causes a translational movement between the first and the second portion.
The invention relates to an assembly (1) for emitting entangled photons in free space, the assembly comprising at least one source (EPS1, EPS2,…, EPSN) of entangled photons, optical connection means and an emitting optical unit (5). The emitting optical unit is common to two optical exits (2a, 2b) of each source of entangled photons, and each of the two optical exits of the source is connected by the optical connection means to a location on a focal surface (6) of the emitting optical unit that is at a distance from the location to which the other optical exit of the same source is connected. Thus, the two photons of one and the same pair of entangled photons are transmitted out by the emitting optical unit in different respective directions of emission (D7a, D7b).
The invention relates to a cryostat for receiving a space component operating at cryogenic temperature, the cryostat comprising: a central, closed, cooled enclosure (14) configured to receive the space component; consecutive metal shields (13), including an inner shield, an outer shield and one or more intermediate shields arranged around one another so as to each delimit a closed volume receiving the preceding smaller shield; a cooling device for cooling the central enclosure to cryogenic temperature; and inner inter-shield joining elements which keep the shields (13) spaced apart from one another. The cryostat comprises at least one integral portion (10a) comprising a series of partitions (13a) including an inner partition (13a(1)), an outer partition (13a(3)) and one or more intermediate partitions (13a(2)), corresponding to a portion of the inner shield, a portion of the outer shield and a portion of the one or more intermediate shields, respectively.
A method (100) for routing packets in a communication network (10) having a variable and predictable topology. The network includes a plurality of nodes, and each node can be connected, at least temporarily, to one or more other nodes in the network. The packets are transmitted from a source node (21) to a destination node (23). An orchestration entity (25) determines (101) a plurality of temporary paths (31) between the source node and the destination node for several successive time periods (Pi), the existence of a temporary path being guaranteed for the time period with which it is associated. The orchestration entity (25) generates (102) a table (T) of label stacks (LSi), in which table each label stack corresponds to the temporary path defined for one of the successive time periods, and each label (Lj, i) corresponds to a node of the temporary path.
A heat-insulating multi-layer blanket for a spacecraft is disclosed including a stack of numerous heat-insulating layers, and an external layer superimposed on the stack. The external layer includes a second surface mirror (SSM) film, including a mirror layer placed under a fluorinated ethylene propylene (FEP) layer, and a polyimide layer joined to the SSM film. The blanket has two different configurations depending on the side of the external layer that is exposed to space.
B32B 27/08 - Layered products essentially comprising synthetic resin as the main or only constituent of a layer next to another layer of a specific substance of synthetic resin of a different kind
B32B 27/28 - Layered products essentially comprising synthetic resin comprising copolymers of synthetic resins not wholly covered by any one of the following subgroups
The present invention relates to a process (50) for the acquisition, by a spacecraft (20) 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 to a proximal region, comprising the steps of: - controlling (S50) the orientation of an array-type detection sensor in order to orient it towards the space object located in the upstream distal region, - acquiring (S51), via the array-type detection sensor, a so-called detection image of the space object located in the upstream distal region, - determining (S52) trajectory-following information on the basis of the detection image, - controlling (S53) the orientation of an array-type acquisition sensor on the basis of trajectory-following information in order to orient it towards the space object located in the proximal region, - acquiring (S54), via the array-type acquisition sensor, a useful image of the space object located in the proximal region.
A method for producing a satellite to facilitate the inclusion of one or more reflector antennas on a surface of the satellite is disclosed. A reusable generic configuration is determined in advance separately from the satellite mission. The generic configuration generally features the following parameters for each reflector: diameter, focal distance, offset distance of the reflector in the deployed position, position of the deployment device, position of the radiofrequency source. The generic configuration is determined such that an antenna points by default towards the centre of the earth when its reflector is in a deployed position. A specific configuration step then consists of defining a limited number of specific parameters depending on the satellite mission. The specific configuration is rendered possible in particular by controlling the deployment device, i.e., by changing the direction in which the antenna points, once the reflector has been deployed.
A method (100) for referencing a digital elevation model (10), involving a step of obtaining (110) two SAR images (12, 14) having a common area (15) that their area of overlap (16, 17) shares with the digital model (10); the method (100) involving, for the SAR images (12, 14), steps of: selecting (120) an AOI (18) in the common area (15); calculating (130) a simulated image (22) in the AOI (18); estimating (140) an offset (di,dj) between the simulated image (22) and the SAR image (12); the method (100) involving steps of selecting a reference point (26) in the AOI (18); projecting (160) the reference point (26) into the SAR images (12, 14) to obtain one connection point per SAR image (12, 14); correcting (170) the connection points by the offsets (di,dj); calculating (180) the readjusted reference point (26); referencing (190) the digital model (10).
09 - Scientific and electric apparatus and instruments
12 - Land, air and water vehicles; parts of land vehicles
39 - Transport, packaging, storage and travel services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Telecommunications services, namely, communication services provided via space vehicles, satellites and satellite constellations;
satellite transmission of messages and images, in particular high-resolution and very high-resolution images and geographic
information; provision of access to databases, in particular satellite or antenna image databases; electronic transmission of data
from global digital elevation models and geographic information; telecommunications, namely, satellite communications services
via laser communication networks; laser communications via satellite laser communication terminals, namely, satellite
communications services Scientific apparatus and instruments for measuring distance, gravity or inertia in space; radar sensors; microwave sensors;
infrared sensors; data processing equipment for the provision of technical information and logistics services related to space
systems, namely, satellites, space vehicles, rockets, in particular launch vehicles, space platforms; downloadable software for
navigation and positioning of space systems, namely, satellites, space vehicles, rockets, in particular launch vehicles, and space
platforms; apparatus and instruments for earth observation, coding and data transmission by satellites; apparatus and instruments
for monitoring the altitude and orbit of satellites; satellite antennas; terrestrial systems consisting of satellite control devices;
devices for monitoring the altitude and position of satellites; equipment and instruments for Earth observation and satellite data
encoding and transmission; terrestrial systems consisting of satellite operation and control devices; downloadable computer
program for satellite management; downloadable computer program for satellite monitoring; avionics and service modules for
satellites, spacecraft and launch vehicles; satellites for scientific and commercial purposes; telecommunications satellites;
navigation satellites; telemetry, remote control, radio-altimetry, proximity and approach apparatus and instruments for the
aeronautics and space sector as well as aeronautical and space instruments; satellite transmitters and receivers, electric
converters and transponders; electronic equipment for civil and military use, namely, onboard electronic equipment for control of
space vehicles, satellites, launch vehicles, rockets; electronic equipment intended for use on the ground and in control posts for
control of spacecraft, satellites, launch vehicles, rockets; space navigation instruments; satellite and wireless hardware and
downloadable computer software for embedded data networks; apparatus and equipment for the acquisition, compression,
transmission, analysis and restoration of satellite images and aerial photographs; computer hardware and downloadable computer
software programs for position determination, control and monitoring in specific geographical areas; satellite positioning and
navigation apparatus and equipment; satellite communication and radio communication network apparatus; satellites for scientific
use and satellites designed to receive and transmit radio signals; satellite communications equipment and satellite
communications stations; recorded and stored software and programs for communication networks and radio communication for
satellite data transmission; recorded and stored computer software used to examine and identify spatial segments in two
dimensions or three dimensions; industrial geoproduction systems consisting of downloadable computer software for a digital
processing chain for the production of satellite, aerial or terrestrial images of 3D data; downloadable computer software
exclusively for imaging of satellite data; apparatus for data processing, in particular by satellite; downloadable computer software
packages for processing and analyzing photographs, such as aerial, satellite or ground photography; apparatus for processing
data, in particular from satellites; downloadable computer software for the processing and analysis of photographs, such as aerial
and satellite photographs; satellite navigation equipment; satellites for scientific purposes, in particular Earth observation
satellites; electronic equipment for processing, analyzing, reproducing and storing images, aerial or satellite photographs;
downloadable database management software, intended for stereographic reproduction, storage, preparation, processing and
analysis of drawings, images, photos, aerial and satellite photo maps, surface models; satellite-aided navigation systems;
satellites for scientific purposes, in particular Earth observation satellites and radar satellites; apparatus for processing, analyzing,
reproducing and storing satellite images; photovoltaic modules Spacecraft, namely, space vehicles; structural parts and structural fittings for the aforementioned goods Realization of scientific missions by satellites, namely, launching of satellites for others; Remote positioning and control of
satellites and spacecraft, namely, launch and suspension of satellites for third parties; transport of cargo in space; recovery of
satellites and spacecraft for others Providing online non-downloadable software for navigation and positioning of space systems, namely, satellites, space vehicles, rockets, in particular launch vehicles, and space platforms; providing online non-downloadable software exclusively for imaging of satellite data; providing online non-downloadable software packages for processing and analyzing photographs, such as aerial, satellite or ground photography; providing online non-downloadable computer software for the processing and analysis of photographs, such as aerial and satellite photographs; providing online non-downloadable database management software, intended for stereographic reproduction, storage, preparation, processing and analysis of drawings, images, photos, aerial and satellite photo maps, surface models; Scientific and technological services, namely, research and design in the field of space applications; industrial analysis, industrial research and industrial design in the field of space applications; design and development of hardware and software in the field of space applications; technology advisory services in the field of space applications; scientific and technological services, namely, the provision of data generated by Earth observation satellites, precise measurements of relief, and physics of measurements based on characterization of objects observed on the ground on the basis of their spectral signature and atmospheric influence; research and design services relating to satellite imagery and data exploitation, namely, the design of data processing facilities for satellite imagery and data exploitation, the design of satellite observation data processing facilities, and the design and development of processing chains for the exploitation of satellite data for the production of geographic information and programming engineering images taken by a constellation of observation satellites; research and design services relating to satellite imagery and data exploitation, namely, the design of data processing facilities for satellite imagery and data exploitation, the design of satellite observation data processing facilities, and the design and development of processing chains for the exploitation of satellite data for the production of geographic information and programming engineering images taken by a constellation of observation satellites; professional assistance, namely, consulting in the field of mapping; engineering services relating to terrestrial, aerial and satellite photography, monochrome or multispectral, on behalf of third parties
A method (100) for referencing an optical image (19) including: obtaining (110, 120) a stereoscopic image pair (19, 23) of the optical image (19) and a SAR image (35), the surface areas covered by the images (19, 23, 35) on the ground having an overlapping area (39); selecting (130) an area of interest (42) in the overlapping area (39); from the area of interest (42): obtaining (140) a 3D model (40); calculating (150) a simulated radar image (44); estimating (160) an offset (di, dj) between the simulated image (44) and the radar image (35); selecting (170) a reference point (46); projecting (180) and shifting (di, dj) the reference point (46) in the radar image (35) to correct the radar connection point (46′″); determining (175) a pair of connection points (46′, 46″) in the image pair; and referencing the optical image (19) based on the connection points (46′, 46″, 46′″).
COMMISSARIAT A L'ENERGIE ATOMIQUE ET AUX ENERGIES ALTERNATIVES (France)
AIRBUS DEFENCE AND SPACE SAS (France)
Inventor
Mariotto, Mathieu
Champel, Bénédicte
Gruss, Jean-Antoine
Claudet, Vincent
Lioger-Arago, Robin
Abstract
The invention essentially consists of a heat pipe with re-entrant grooves, in which the connection channels between the liquid channels and vapour channel are open more widely in the condenser than in the other zones of the heat pipe (evaporator, adiabatic zone), unlike in the heat pipes of the prior art which have the same internal cross-section along the entire length of the pipe.
F28D 15/04 - Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls in which the medium condenses and evaporates, e.g. heat-pipes with tubes having a capillary structure
B64G 1/50 - Arrangements or adaptations of devices for control of environment or living conditions for temperature control
95.
CAPILLARY-PUMPED-TYPE HEAT PIPE WITH RE-ENTRANT GROOVES, HAVING INCREASED BOILING AND CAPILLARY LIMITS
COMMISSARIAT A L'ENERGIE ATOMIQUE ET AUX ENERGIES ALTERNATIVES (France)
AIRBUS DEFENCE AND SPACE SAS (France)
Inventor
Mariotto, Mathieu
Champel, Bénédicte
Gruss, Jean-Antoine
Claudet, Vincent
Abstract
The invention essentially consists of a heat pipe with re-entrant grooves, having specific designs whereby the internal cross-section is differentiated according to the different heat pipe zones (evaporator, adiabatic zone, condenser), in order to provide a more tailored solution to the problems in each of these zones, and thus to optimize the operation of the heat pipe, improve its performance and extend its operating range (limits), unlike in the heat pipes of the prior art which have the same internal cross-section along the entire length of the pipe.
F28D 15/04 - Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls in which the medium condenses and evaporates, e.g. heat-pipes with tubes having a capillary structure
96.
CAPILLARY-PUMPED-TYPE HEAT PIPE WITH RE-ENTRANT GROOVES, HAVING INCREASED THERMAL CONDUCTIVITY
COMMISSARIAT A L'ENERGIE ATOMIQUE ET AUX ENERGIES ALTERNATIVES (France)
AIRBUS DEFENCE AND SPACE SAS (France)
Inventor
Mariotto, Mathieu
Champel, Bénédicte
Gruss, Jean-Antoine
Abstract
The invention essentially consists of a heat pipe with re-entrant grooves, having thicker walls between liquid channels in the evaporator and, advantageously, in the condenser, unlike in the heat pipes of the prior art which have the same internal cross-section along the entire length of the pipe.
F28D 15/02 - Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls in which the medium condenses and evaporates, e.g. heat-pipes
F28D 15/04 - Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls in which the medium condenses and evaporates, e.g. heat-pipes with tubes having a capillary structure
97.
Method for orbit control and desaturation of a satellite by means of a single articulated arm carrying a propulsion unit
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.
A space optical instrument is disclosed including a primary mirror having an optical axis and including a first face, referred to as the front face, oriented towards an observed area, and a second face opposite to the first, referred to as the rear face, the optical instrument further including a thermal stabilization device for the primary mirror, comprising a thermally conductive wall extending around the optical axis (O) on the front face side of the primary mirror towards which this face is oriented. The thermal stabilization device further includes a temperature regulating device for the circumferential wall that is capable of using the measurement of an incident heat flux on the mirror, and adapting the temperature of the circumferential wall according to the measured incident heat flux, in order to keep the front face of the mirror at a constant temperature.
G02B 7/02 - Mountings, adjusting means, or light-tight connections, for optical elements for lenses
G02B 23/00 - Telescopes, e.g. binocularsPeriscopesInstruments for viewing the inside of hollow bodiesViewfindersOptical aiming or sighting devices
G02B 7/18 - Mountings, adjusting means, or light-tight connections, for optical elements for prismsMountings, adjusting means, or light-tight connections, for optical elements for mirrors
G02B 23/02 - Telescopes, e.g. binocularsPeriscopesInstruments for viewing the inside of hollow bodiesViewfindersOptical aiming or sighting devices involving prisms or mirrors
G02B 23/16 - HousingsCapsMountingsSupports, e.g. with counterweight
G05D 23/19 - Control of temperature characterised by the use of electric means
99.
Method and receiver device for detecting the start of a frame of a satellite communications signal
A method and a receiver device for detecting the start of a frame of a satellite communication signal. A shaping filtering is applied directly after sampling of the signal, before a frequency correction is applied. During a first phase, an approximate frequency error and a candidate first sample for the start of the frame are estimated by performing several correlations respectively associated with different frequency hypotheses. The samples obtained after sampling or after shaping filtering are buffered during the execution of the first phase. Then, during a second phase, a final candidate sample for the start of the frame is determined from the memorised samples, using the approximate frequency error and the candidate first sample estimated during the first phase.
Disclosed is a two-phase heat-transfer device, said device comprising a closed cavity comprising at least one evaporation zone (20) subjected to heat exchange with at least one heat source and at least one condensation zone (30) subjected to heat exchange with at least one cold source, the closed cavity containing a two-phase fluid with a liquid-steam balance and comprising at least one channel (13) for circulating the two-phase fluid in the steam phase and at least one main capillary structure (14) suitable for allowing the two-phase fluid to circulate in the liquid phase between the cold source and the heat source, the two-phase device being characterised in that it further comprises at least one additional capillary medium (15) for storing and restoring excess liquid relative to a maximum capacity of liquid contained in the main capillary structure, the additional capillary structure and the main capillary structure being connected to each other so as to ensure capillary continuity for the two-phase fluid in the liquid phase.
F28D 15/04 - Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls in which the medium condenses and evaporates, e.g. heat-pipes with tubes having a capillary structure
