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: A satellite, intended to be placed in a station in orbit about a celestial body, including a first electrical thruster of orientatable thrust direction, a second electrical thruster of orientatable thrust direction, and an electrical thruster of fixed orientation that is fixed with respect to the satellite and of line of thrust passing through the center of gravity of the satellite. The satellite includes two electrical-thruster power units and an electrically interconnecting network connecting a first power unit to the first thruster of orientatable thrust direction and to the thruster of fixed orientation, and connecting a second power unit to the second thruster of orientatable thrust direction and to the thruster of fixed orientation. Each of the power units is configured to power either the associated thruster of orientatable thrust direction or the thruster of fixed orientation.

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 segmented structure comprising at least two panels, one panel referred to as a main panel and at least one panel referred to as a secondary panel, together with at least one unfurling device able to bring a secondary panel into a storage position or into an unfurled position, the unfurling device comprising at least one strip fixed to the secondary panel and connected to the main panel, the strip being elastically preloaded into the storage position thereof so as to unfurl automatically and autonomously when relative movement between the secondary panel and the main panel becomes possible, so as to move the secondary panel.

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: Space craft comprising a body, at least one pair of supporting arms, a first device mounted on a first supporting arm and a second device mounted on a second supporting arm. The first arm is rotatably mounted on the body of the craft about an axis of rotation. The second arm is fixed to the body, and in which craft of the first device and the second device at least one is offset from the axis of rotation of the first arm. The pair of supporting arms further comprises a hollow module for the rotatable mounting of the first arm on the body. The mounting module comprising an opening through which the axis of rotation and the second supporting arm pass.

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: An isolation module between a vibration generating device, such as a satellite launcher, and a structure to be isolated, such as the structure carrying a satellite, comprising: at least two fastening parts, and a connecting means. The first fastening part, called the frame, comprises at least two parallel radial branches, and the second fastening part, called the support, comprises at least one radial branch extending between the two branches of the frame. The connecting means is made from an elastomer material and includes at least one pair of identical elastomer pads, being mounted in series between the frame and the support.

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: Disclosed is a method (70) for monitoring a phase for transferring a satellite (20) from one earth orbit, called “initial orbit”, to another earth orbit, called “mission orbit”, in particular a transfer using electric propulsion unit. The monitoring method includes a step for estimating the direction of the satellite during the transfer phase by way of an earth array antenna (30) including a plurality of elementary antennas (31), each elementary antenna having a primary radiation lobe with a width greater than or equal to 20°, the elementary antennas (31) being oriented such that their respective fields of vision overlap, the direction of the satellite being estimated based on at least one useful phase difference measurement between signals corresponding to a target signal, transmitted by the satellite and received on a pair of elementary antennas (31).

Abstract: The invention relates to a heat transfer system with one main capillary pumped diphasic fluid loop and a secondary capillary pumped diphasic fluid loop suitable for cooling at least one hot source. The main fluid loop and the secondary fluid loop have one evaporator, a vapor pipe capable of conveying the cooling fluid in the vapor state from the evaporator to a condenser, a condenser and a liquid pipe capable of conveying the cooling fluid in the liquid state from the condenser to the evaporator-so that the cooling fluid of the main fluid loop is in heat exchange with the cooling fluid of the secondary fluid loop.

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.