Abstract: An electrical power supply system for a satellite with continuously controlled DC-voltage is suitable for recharging batteries without requiring any specific charge module. To this purpose, at least one solar generator section, so-called charge section, is connected directly to a battery output terminal (B). Simultaneously, at least one battery discharge module is dedicated to the control of a residual current that is not used for recharging the batteries. A first regulator is added to the system in order to control said residual current on the basis of a current produced by the charge section and a charge target for the batteries. Optionally, a second regulator may also be added, in order to directly control the current produced by the charge section when equipment that is electrically powered has a low consumption.

Abstract: Each loop of the device includes an evaporator and a condenser connected by an outer tube in a portion of which extends a thermally insulating sleeve having one end that can lead into the condenser and another end that surrounds a first portion (8a) of a microporous mass provided in the outer tube and pumping by capillarity a liquid-phase heat-carrier fluid flowing in the insulating sleeve of the condenser towards the evaporator, while the gaseous-phase fluid flows from a vapour-collecting central duct in a second portion of the mass of the evaporator towards the condenser in a duct inside said outer tube. The invention can be used for the thermal energy transfer from an electronic component or circuit defining a heat source in relation with the evaporator to a cold source in relation with the condenser.

Abstract: A method for controlling the attitude of a satellite in orbit around a celestial object, the satellite including an observation instrument, a solar panel, a radiator and a star sensor which are arranged on the satellite such that, in a reference frame associated with the satellite and defined by three orthogonal axes X, Y, and Z, the observation instrument has its observation axis parallel to the Z-axis, the solar panel is parallel to the Y-axis, the radiator is arranged on one of the sides ?X, +Y, or ?Y of the satellite, and the star sensor points to the negative X values side. The roll and pitch attitudes of the satellite are controlled during an activity period to direct the observation instrument towards areas of the celestial object to be observed, and the yaw attitude of the satellite is controlled to keep the sun on the positive X values side and ensure that a solar panel minimum insolation constraint is satisfied during observation phases of the activity period.

Abstract: The invention concerns a device for generating impacts on a structure, and this device has a projectile head. According to the invention, this head includes a main body (1) on which an impact element (2) is mounted so it projects. The device includes a mechanical propulsion element (8) to set this projectile head in motion, and the propulsion element is capable of moving between an initial so-called resting position where that propulsion element is immobile and the projectile head is held against it by at least one retaining element (10), and a second position where this propulsion element comes to a stop against stop elements (11, 12), and the projectile head moves in translation toward the structure guided by guidance elements (4). The device also includes an anti-rebound system (6, 7) to prevent any rebound by the projectile head after impact on the structure.

Abstract: A rolling bearing device, of the type including a central shaft and a hub (10) mobile in rotation relative to each other, the bearing including at least two rolling bearings (12, 13), one designated “lower” and the other designated “upper”, arranged between the central shaft (11) and the hub (10) in two positions spaced in the axial direction Z, these rolling bearings being fitted with inner (14, 16) and outer (15, 17) rings and with balls (18, 19), the rolling bearings being assembled back-to-back or face-to-face, a rigid preload being applied to these bearings along the axial direction Z, internal (22) and external (23) spacers being arranged between these rolling bearings, the inner (22) and outer (23) spacers have lengths adjusted to limit variations in rigid preload caused by temperature gradients from one point of the bearing to another to less than 30%, particularly thermal gradients in the radial direction.

Abstract: A satellite terrestrial positioning system is disclosed in which navigation satellites verify, in an autonomous manner, essential information that is transmitted to users using unidirectional links received from reference beacons.

Abstract: A multi-beam telecommunications satellite, intended to be placed in orbit around the earth, and adapted to relay data between terrestrial terminals and at least one ground station and to form beams on a user link between the satellite and terrestrial terminals, includes a module for forming beams on board in the satellite, a module for processing beams in the ground station, and a module for routing signals received from the ground station and/or from terrestrial terminals, signals of beams formed on board being routed towards the on-board beam forming module, and signals of ground-formed beams being routed towards the ground-formed beam processing module. A telecommunications system including the multi-beam satellite, a ground station and a beam management center adapted to divide the beams into one group of ground-formed beams and one group of beams formed on board, as well as a method for forming beams are disclosed.

Abstract: The invention relates to an electric thruster for a spacecraft. According to the invention, the thruster (II) comprises a jet generating portion (G1) and a jet accelerating portion (A2), pivotably connected (H1) such that the jet accelerating portion (A2) can rotate in relation to the jet generating portion (G1).

Abstract: Device for measuring the line of sight jitter of an optical instrument mounted on an optical platform, includes: an optical measurement path primarily common with the observation path of the optical instrument, a light measurement source arranged essentially at one end of the optical observation path, a detector for measuring the optical beam coming from the light measurement source, arranged such that this beam has passed through the optical observation path at least once, at least one collimation mirror designed for the reflection of the optical beam, arranged essentially on the optical observation path, essentially at the other end of the optical observation path, relative to the light measurement source, whereby this mirror is isolated by at least one passive isolator of lateral vibrations (i.e., inducing a rotation of the perpendicular line of the mirror) generated by the optical platform in a predetermined frequency range.

Abstract: A device for reducing the aerodynamic drag of a vehicle includes at least one masking element for at least one part of a nozzle of the vehicle's engine, the masking element having a resorbable material designed to be eliminated in the nozzle's flow once the engine is ignited. A space craft includes the nozzle attached to the fuselage of the space craft.

Abstract: An actuator device for varying the attitude of a spacecraft includes a reversible conversion chain of electrical energy to mechanical rotation energy of a flywheel. The electrical energy is stored in a capacitive element that may be a supercapacitor. The actuator device also includes an electrical power converter, connected, on one hand, to the capacitive element and intended to be connected, on the other hand, to the spacecraft power bus. The converter makes it possible to compensate for losses to keep a total energy of the actuator device constant.

Abstract: An afterbody device for a spacecraft fitted with at least one rocket engine at the rear of the craft includes at least one movable cover element designed to take a first position, masking and reducing the vehicle's rear drag, where it prolongs the vehicle's fuselage around at least one part of a rocket engine nozzle of the vehicle and extends beyond the rear of the vehicle's fuselage, and to take a second position fully deployed, increasing the vehicle's aerodynamic drag.

Abstract: An attitude control actuator of a spacecraft includes a first momentum wheel driven in rotation by a motor and a second momentum wheel. Both momentum wheels are movable in rotation about an axis and are mechanically coupled by coupling means imposing between a rotation speed ?1 of the first momentum wheel and a rotation speed ?2 of the second momentum wheel a ratio R=?2/?1, negative on the one hand and continuously modifiable by the coupling means in response to a command on the other hand so as to modify the total angular momentum of the actuator while the total kinetic energy of the wheels are kept constant. In one embodiment, both momentum wheels have the same inertia and are coupled through a toroidal variator, where ratio R varies between ?3 and ?1/3. The motor drives the momentum wheels and operates as a generator for braking the momentum wheels.

Abstract: A testing device for structural panels is characterised in that it includes passive apparatus in the form of a mount and interface apparatus between the mount and the panel to geometrically apply stresses representing the stresses caused by the parts surrounding the panel during a normal utilisation thereof.

Abstract: The seat specially designed for space vehicles and in particular space planes comprises a rigid hull and parts of axis of which the direction of alignment passes in front of the occupant of the seat and along him; the seat rotates freely around parts of axis according to the direction of the acceleration in order to always place the occupant in the orientation perpendicular to the forces of acceleration.

Abstract: According to the invention, the system comprises: at least three position beacons (3) arranged about said location (2) and emitting in the long-wave range, and an apparatus associated with the user (1) and including means for receiving, processing and displaying the information transmitted by said beacons (3).

Abstract: The invention relates to control of a battery, permitting a reduction in the number of components of the battery. The battery comprises several modules (2a, . . . , 2n), each module comprising a charge limiting circuit (4). When a module is detected as defective, the charge limiting circuit (4) carries out a command for the discharge of said defective module, by formation of a short-circuit path. The battery can subsequently be used without functional hindrance by the defective module.

Abstract: The invention related to a device comprising at least three insulation modules distributed around vibration equipment. Each module comprises at least two rigid parts, at least one of said parts being an outer part fixed to the carrier structure and at least one of said parts being an inner part fixed to the equipment or the stand (3) thereof. At least one elastomer insulating plug connects an inner part and an outer part and at least one of said parts carries two longitudinal flexible abutments and two tangential flexible abutments which each have a free end facing another respectively outer or inner rigid part, said free end being at a distance from the inner part in an idle position. The invention can be applied to satellite equipment.

Abstract: The device includes an evaporator and a condenser connected by an outer tube in which extends at least one inner tube having one end leading into the condenser and another end connected to an end of a central duct for collecting the vapours of a heat-carrier fluid, in a microporous mass provided in the outer tube and pumping by capillarity the liquid-phase fluid flowing in at least one outer duct between the outer and inner tubes from the condenser to the evaporator, while the vapour-phase fluid flows from the evaporator to the condenser in at least one inner duct inside said at least one inner tube. The invention can be used for the thermal energy transfer from an electronic component or circuit in relation with the evaporator to a cold source in relation with the condenser.

Abstract: According to the invention, navigation satellites (1) are at least partially managed by at least three management satellites (3.1 to 3.3) positioned on high orbits inclined in relation to the equator (E). Said high orbits intersect the equatorial plane along intersecting diametrical straight lines (5.1 to 5.3), such that the two outer intersecting diametrical lines (5.2, 5.3) form therebetween an angle of longitude (2?) that is at least equal to 90°.