Abstract: According to the present invention, use is made of a probe provided with a central sensor, with off-centered sensors and lateral sensors, and said probe is articulated on the aircraft around two orthogonal axes.

Abstract: Disclosed is artificial satellite including: a mounting structure supporting equipment-bearing walls; a launcher-adapter rigidly connected to the mounting structure; a first radiator; and at least one first system for transporting heat by a fluid, including at least one duct having a first heat-exchange section and a second heat-exchange section, the second heat-exchange section being capable of being in thermal contact with the first radiator. The first heat-exchange section is in thermal contact with at least one portion of the launcher-adapter. Also disclosed is a method for filling a tank of propellant gas of the artificial satellite.

Abstract: The invention concerns a laser amplification system comprising a pumping device and at least one thick amplifier disc having a first face, which is reflective at the wavelengths of a pulsed laser beam of the laser amplification system and of a pump beam of the pumping device, as well as at least one heat-dissipation component to which this first face of the amplifier disc is firmly secured, the saturation fluence of the active medium of the amplifier disc being equal to or less than 3 J·cm?2.

Abstract: Satellite telecommunications system comprises a transmitting/receiving surface terminal associated with a user substantially on a surface of the Earth, a geostationary satellite configured to receive/transmit signals from/to a predefined coverage area with a line of sight to the geostationary satellite, and a traveling satellite moving above the surface of the Earth. The traveling satellite repeats signals received from the surface terminal towards the geostationary satellite and/or repeat signals received from the geostationary satellite towards the surface terminal. The same frequency band is used to communicate between the surface terminal and the traveling satellite and between the traveling satellite and the geostationary satellite. The tracking/telemetry and command signals of the traveling satellite are relayed by the geostationary satellite.

Abstract: A segmented structure includes at least two panels, a so-called main panel and a so-called secondary panel, as well as at least one deployment device configured to move the connected secondary panel into a storage position or into a deployed position. The deployment device includes a translation system provided with at least one helical geared motor configured to translate the secondary panel relative to the main panel. The translation system further includes a rotation system configured to rotate the translation system and the secondary panel connected to the translation system, relative to said main panel.

Abstract: A method for calibrating spatial errors induced by phase biases having a detrimental effect on the measurements of phase differences of radio signals received by three unaligned receiving antennas of a vehicle. An inter-satellite angular deviation of a pair of satellites is estimated in two different ways: on the basis of the respective positions of the vehicle and of the satellites to obtain a theoretical inter-satellite angular deviation; and on the basis of the respective directions of incidence of the satellites relative to the vehicle, which are determined from phase measurements, to obtain an estimated inter-satellite angular deviation. The space errors are estimated on the basis of said theoretical and estimated inter-satellite angular deviations. Also, a method and system for estimating the attitude of a vehicle, in particular a spacecraft.

Abstract: A payload for a repeater satellite of a communication system. The repeater satellite being placed into drift orbit above the surface of a celestial body. The payload being configured to repeat data received from a stationary satellite above the surface of the celestial body towards a terminal substantially at the surface of the celestial body, and to repeat data received from the terminal towards the stationary satellite. The payload is further configured to use a single frequency band for repeating data towards the stationary satellite, referred to as uplink transmission, and for repeating data towards the terminal, referred to as downlink transmission, as well as to time-division multiplex the uplink transmissions and the downlink transmissions. Also, a telecommunication system includes a repeater satellite provided with aforesaid payload, and a satellite communication method for transferring data between the terminal and the stationary satellite.

Abstract: A device for capturing a space object, the device comprising a pressure element configured to come into direct mechanical contact with the space object to be captured. The device comprises at least two reclosable elements movable between an open position for capturing the space object and a closed position for retaining the space object. The device also comprises an apparatus to mechanically transmit movement from the pressure element to each reclosable element, the mechanical transmission apparatus being configured to entrain each reclosable element in displacement between the open position and the closed position by pressure of the space object on the pressure element.

Abstract: The invention relates to a spacecraft comprising a body having two opposite faces; a first radiator carried by at least one face; the first radiator having an outer face; a first supporting arm extending substantially perpendicularly to the outer face of the first radiator; a drive motor suitable for rotating the first supporting arm about its longitudinal axis a first assembly carried by the first supporting arm, said first assembly comprising a plurality of slats stationary with respect to the first supporting arm; said slats being attached one above the other and separated from each other by a free space.

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

Abstract: An aircraft is capable of passing from the aerial domain to the spatial domain and method for automatically adapting the configuration of same. An additional breathable gas supply is provided to be activated only during a flight phase during which aerobic propulsion is interrupted, and is capable of supplying the control system of the manned cabin environment instead of the system associated with the aerobic propulsion means.

Abstract: Each terminal wishing to access a communication service implemented in a communications network transmits an identifier of subscription to this service during a phase of registration (3.1; 3.2) with the network. With each service subscription identifier is associated a call identifier to enable calling the terminal registered via the network. A system (1.2, 1.3) intended to register at least one terminal (1.4) from amongst a plurality of terminals (1.3; 1.4) in a telephony network includes means for dynamically changing the service subscription identifier (3.11, 3.12, 3.13) and the associated call identifier (3.4, 3.5, 3.6), for at least one of said terminals, and means for re-registering (3.15) with said network each terminal for which the service subscription identifier and the associated call identifier have been dynamically changed.

Abstract: A radiator for a satellite intended for being placed in geostationary orbit around the earth in a tilted plane relative to the plane of the ecliptic, includes at least one panel having at least one radiative surface, and including: a mounting foot supporting the panel; and control and motor elements for pivoting the mounting foot about an axis of rotation tilted relative to the radiative surface which is perpendicular to a radiation axis, the radiation axis and the axis of rotation being tilted relative to one another by a non-zero working angle, corresponding to the tilt angle of the plane of the orbit of the satellite relative to the plane of the ecliptic, the working angle being fixed, such that for any rotation of the mounting foot about the axis of rotation owing to the control and motor elements, the radiative surface remains parallel to the plane of the ecliptic.

Abstract: A method for controlling an attitude control system (30) for a space vehicle (10), the attitude of the space vehicle being controlled during at least one preparation phase followed by an observation phase during which an image capture is performed. In an attitude control system that includes a maneuvering subsystem (300) which includes at least one reaction wheel, the method includes, during the at least one preparation phase, a preparation step (50), during which commands are issued to the maneuvering subsystem in order to control the attitude of the space vehicle, followed by a step (55) of stopping the at least one reaction wheel prior to the observation phase. In addition, during the observation phase, a fine control subsystem (310) having a lower vibration signature than that of the maneuvering subsystem, is sent commands in order to control the space vehicle's attitude. An attitude control system for a space vehicle is also described.

Abstract: A method and system for estimating a direction of arrival of a target signal relative to a measuring antenna array of an earth-orbiting satellite. The direction of arrival of the target signal being estimated on the basis of measurement signals corresponding to the target signal received respectively by at least a first measuring antenna and a second measuring antenna of the measuring antenna array. Each of the measurement signals are combined with a reference signal corresponding to the target signal received by a receiving antenna of the satellite. The receiving antenna has a maximum gain greater than the respective maximum gains of the first measuring antenna and of the second measuring antenna. The direction of arrival of the target signal is estimated from the signals obtained by combining the measurement signals with the reference signal.

Abstract: A method and system for estimating a path-length difference between two paths followed by a target signal transmitted by a spacecraft or aircraft to a first receiving antenna and a second receiving antenna of a receiving base, respectively. A useful-phase difference is measured between signals that correspond to the target signal received by the first receiving antenna and second receiving antenna. The path-length difference is estimated in accordance with the useful-phase difference measurements. The measurement of the useful-phase difference comprises either correlating the signals received by the first receiving antenna and second receiving antenna, respectively, with a reference target signal, or analyzing the signals received by the first receiving antenna and second receiving antenna, respectively, using an FFT or a PLL.

Abstract: A satellite support structure to support at least one device of the satellite. The support structure includes structural elements with at least one of the structural elements being a damping connector linking at least two other structural elements of the support structure. The damping connector includes an elastomer element and at least one flat angle bracket having at least two wings to be linked by the respective connectors to the damped structural elements. The elastomer element is made from elastomer material with loss angle ? greater than ten degrees and is arranged such that the transmission of forces between one of the wings of the flat angle bracket and the connectors is achieved entirely via the elastomer element.

Abstract: A segmented structure includes a principal panel and a secondary panel, as well as at least one deployment device configured to move the secondary panel into a storage position or into a deployed position. The deployment device includes a translation system having a movable trolley, guided in translation and provided with a connection arm which is connected to the rear face of the secondary panel. The translation system is configured to generate a translation movement of said secondary panel with respect to the principal panel. The deployment device further includes a rotation system is configured to generate at least one rotation of the connection arm to generate a rotational movement of said secondary panel with respect to the principal panel.

Abstract: A device for expelling/containing a predetermined liquid. The device configured to be built into a liquid tank operable at low or zero gravity and comprising a unitary three-dimensional sponge structure. The sponge structure comprises a set of substantially wire-like elements that extend between a peripheral area of the sponge structure and an area for expelling/containing liquid. The wire-like elements are substantially oriented in the direction of flow of the fluid within the device. The wire-like elements are connected together by crosspieces and are arranged such that the capillary gradient is positive or zero in the direction of flow of the fluid from the peripheral area to the area for expelling/containing liquid.

Abstract: A method for managing the service policy applied to a black network comprising a radio link and to a red network connected to this black network managed by a predetermined set of profiles is proposed. The congestion of the radio link is detected by any means by the black domain. The congestion of the radio link is detected by a method for detecting congestion which operates by means of exchanges within the red domain. A service policy profile then established matches for each domain to a detected congestion level.