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

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

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

Abstract: 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).

Abstract: 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.

Abstract: 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.

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

Abstract: 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.

Abstract: A device for orienting a load about a main axis X and a secondary axis Y is disclosed having a first shaft, called transmission shaft, intended to support the load and configured to be rotated about the main axis and the secondary axis, a second shaft configured to be rotated about the main axis X, a third shaft configured to be rotated about a third axis of rotation, in the same direction as the main axis, a first connection component between the transmission shaft and the second shaft, configured to prevent relative movements between the transmission shaft and the second shaft in, on the one hand, a degree of rotational freedom about the main axis X and, on the other hand, three degrees of translational freedom.

Abstract: An assembly for supplying power to an aircraft is disclosed having at least one battery housed in a respective housing, each housing comprising a wall in which a through-opening is arranged, and an exhaust device including a discharge duct connecting each housing opening to a common discharge port, a valve mounted on each opening. Each valve includes a membrane arranged so as to seal the opening closed and having a surface of pressure application towards the inside of the housing and a surface of pressure application towards the outside of the housing. The surface of pressure application towards the outside of the housing is larger than the surface of pressure application towards the inside of the housing, so that the membrane bursts at a bursting pressure inside the housing that is lower than a bursting pressure reached outside the housing.

Abstract: 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.

Abstract: The device includes a database (8) storing a digital cartography (MAP) of a terrain, an acquisition unit (4) configured to acquire a digital image (IMG) of the terrain, as well as a processing unit (2) configured to receive from the acquisition unit (4) the digital image (IMG) and determine a similarity between the digital cartography (MAP) and the digital image (IMG), so as to deduce a position (POS) of said machine from a result of said similarity.

Abstract: Computer systems (100) for satellite image acquisition and mission-plan calculation devices (120) for satellite and also Earth observation satellites (110). Based on the observation that the uncertainty connected with meteorological conditions can lead to the development of mission plans, for satellites, with low effectiveness, the uncertainty is characterized and used to improve the preparation of mission plans for satellite. A model of the uncertainties is built upon observations and/or past meteorological forecasts. Next, at the time of planning, the model is used by presenting the observations and/or the current forecast as input to the model. In that way, the acquisition zones for which it is unlikely to get acceptable images on the preferred acquisition date may be identified.

Abstract: A device for avoiding a potential conflict detected in a predetermined trajectory prediction horizon between a first trajectory of a first ship or aircraft and a second trajectory of a second ship or aircraft is disclosed. Each trajectory includes a plurality of segments formed between multiple navigation points. The device includes a determination unit for determining at least one lateral peripheral envelope of the first trajectory, a division unit for dividing the lateral peripheral envelope into a plurality of juxtaposed sections arranged longitudinally the ones after the others and delimited by transition lines marking the change between sections, each transition line cutting, at a first point of intersection, a segment of the first trajectory and, at a second point of intersection, and an edge of the lateral peripheral envelope, a discretisation unit, and a computing unit.

Abstract: 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.

Abstract: Simulation sighting binoculars include a camera, a screen, a pair of lenses which are arranged to face the screen, and electronic circuitry which is configured to: obtain a video frame from the camera; transmit, to a simulation platform, geolocation information and orientation information for the camera; receive simulation graphical elements and spatial positioning information for corresponding virtual objects; carry out a two-dimensional rendering of the virtual objects, in order to display them in a projection window E2; superimpose the two-dimensional rendering of the virtual objects in the projection window E2 and the video frame in a projection window E3; obtain a mixed-reality stereoscopic image using a pair of virtual cameras reproducing binocular vision which is adapted to the pair of lenses; and carry out, on the screen, a right-eye and left-eye display of the obtained mixed-reality stereoscopic image.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: A system for preparing a mission from a digital mapping, includes a mission editor generating mission elements that can change over the course of several determined temporal phases, including on a network a mission server, a mapping server, a server for sharing at least one centre of the map and a plurality of augmented reality headsets, at least one of the augmented reality headsets, called master headset, being able to generate at least one command for modifying the centre, each headset being able to receive at least two sets of elevation and terrain tiles from the mapping server, the mission server interfacing with the headsets to share and update the mission elements and to change them over time.