Abstract: An optical transceiver assembly comprises a transmission system, a reception system and a coupling system which directs a part of the signals produced by the transmission system to the reception system. Said part of the transmission signals is detected by a photodetector matrix of the reception system, outside an useful zone of the matrix which is dedicated to the detection of the received signals. A transmission direction may therefore be determined in real time while the received signals are detected. A difference between the transmission direction and a reception direction of the transceiver assembly may then be precisely compensated for at each moment during a tracking step. The transceiver assembly may be a free space laser optical communication terminal.

Abstract: The invention relates to a device for controlling the deployment of an inflatable structure including, in the non-deployed state, a flexible tube (12) which is folded in zigzags and fixed to one end of a plug (13) provided with a buoyant gas admission (15), the other end of the tube being closed; means (25 to 29) for controlling the change of state of the tube from the folded state (12a) to the deployed state (30), the means being arranged inside the tube (12) and consisting of a set of interconnected flexible blades (25) which are radially arranged around the strut (16) in the form of petals, in such a way that the set can be displayed along the strut; and means (28, 29) for bringing the set of petals (25) towards the plug (13) in such a way as to press the folded part (12a) of the tube, each petal (25) being applied to a series of superimposed folds (21 to 24) of the folded part of the tube.

Abstract: The invention concerns a method which consists in coating uniformly the non-developable surface (6) with an electrically conductive material (9), which is in turn coated, by spraying, with a pattern (10) of polymerizable protective material, said pattern being polymerized as it is being formed, and then selectively eliminating, through the openings (10.8) of said pattern (10), the portions of said electrically conductive material (9) which do not over said electrically conductive patterns.

Abstract: The invention concerns a method for producing electrically conductive patterns on a non-developable surface of an insulating substrate, and the resulting device. The invention is characterized in that it consists in: coating the non-developable surface (6) uniformly with a layer of electrically conductive material (9), which is in turn coated with a layer of protective material (10), and then, using a mobile laser head, eliminating by laser ablation the portions of said protective substance layer (10) which do not cover said electrically conductive patterns, then eliminating the portions of said electrically conductive material (9) exposed by the elimination of said portions of said protective material layer (10).

Abstract: The present invention relates to a process which makes it possible to improve the adhesion of carbon fibres with regard to an organic matrix forming, with these fibres, a composite material, this composite material being obtained by bringing the fibres into contact with a resin which can be cured by chain polymerization, followed by polymerization of the resin, which process consists in coating the surface of the carbon fibres, before these fibres are brought into contact with the resin, with a polymer film which comprises functional groups capable of acting as chain transfer agents during the polymerization of said resin. Applications: aeronautical, aerospatial, shipbuilding, railway and motor vehicle industries, armaments industry, sports and leisure articles, and the like.

Abstract: The invention concerns a structure comprising a rigging (1-2) consisting of at least one flexible rope (1, 2) impregnated with a hardening substance, with controllable hardening, designed to rigidify at least one rope after it has been deployed and extended. The structure may comprise at least one rigging mesh, whereof at least one flexible rope (1, 2) is impregnated with the hardening substance and bound to itself and/or to another rope of the rigging by at least one bond (6). Said structure is independent of any means of deployment, but may also comprise a deploying device (3) independent of the rigging and extending the ropes (1, 2) of the structure and maintaining them taut while the hardening material is cured. The invention is in particular applicable to deployable structures capable of being rigidified on board space crafts.

Abstract: Gyrodyne comprising an inertial wheel mounted, via a wheel support, on the moving part or rotor of a cardan assembly also comprising a stator and means of setting the rotor in rotation with respect to the stator about a first axis of rotation, it being possible for the spinner of said inertial wheel to be set in rotation about a second axis of rotation not aligned with said first axis of rotation, characterized in that said stator of said cardan is mounted on a block and fixed to said block via vibration-damping means, and in that said means of setting said rotor in rotation are at least partially housed in the interior volume of said block.

Abstract: A device for controlling heat flow in a spacecraft which always has the same face facing towards the earth, a pair of mutually parallel opposed North and South faces perpendicular to the North-South axis of the earth and two pairs of mutually parallel opposed East/West and Earth/Anti-earth faces, heat-dissipating or -transmitting equipment being provided on the internal walls of the North and South faces, this device comprising a plurality of heat pipes connecting the North and South faces of said craft to another pair of opposed faces of said craft and forming a heat-pipe loop in thermal-conduction contact with one another.

Abstract: A method is disclosed for placing a satellite in an operational orbit The satellite is equipped with its own satellite propulsion system as well as a detachable separate propulsion device The satellite and separate propulsion device are launched into a transfer orbit by means of a space launcher The separate propulsion device is controlled by a satellite. The satellite is transferred from the transfer orbit to an intermediate orbit by means of the separate propulsion device. The separate propulsion device is separated from the satellite in the intermediate orbit.

Abstract: A deployable wing structure for air-braking a satellite and which, once deployed, at least one wing structure element that forms a three-dimensional structure and includes at least two panels lying in secant planes and forming a dihedron.

Abstract: The invention relates to a device for controlling the deployment of an inflatable structure including, in the non-deployed state, a flexible tube (12) which is folded in zigzags and fixed to one end of a plug (13) provided with a buoyant gas admission (15), the other end of the tube being closed; means (25 to 29) for controlling the change of state of the tube from the folded state (12a) to the deployed state (30), the means being arranged inside the tube (12) and consisting of a set of interconnected flexible blades (25) which are radially arranged around the strut (16) in the form of petals, in such a way that the set can be displayed along the strut; and means (28, 29) for bringing the set of petals (25) towards the plug (13) in such a way as to press the folded part (12a) of the tube, each petal (25) being applied to a series of superimposed folds (21 to 24) of the folded part of the tube.

Abstract: A method of determining angles of sight between a receiver device having at least two reception antennas and at least one transmitter device having at least one transmission antenna for the transmission of radioelectric signals including at least two wavelengths. The determining method is based on angular phase measurements of the radioelectric signals, which are measured modulo 2? and are therefore ambiguous since they are known to within an integer number of times 2?. The ambiguity in the phase measurements is resolved in the case of an application of the determining method to a receiver device dimensioned by applying a method of design of a system for determining angles of sight. A receiver device implements the determining method and a system for determining angles of sight includes the receiver device and at least one transmitter device.

Abstract: A spectrophotometer incorporating an interferometer and a dispersive system is adapted to have an enlarged inlet field without degrading its spatial resolution. To this end, spectral data deduced horn measurements performed by means of the interferometer are transferred into spectral data deduced from measurements per formed by means of the dispersive system. Such spectrophotometer makes it possible to scan an observation field quickly, and is compatible with use on board a satellite.

Abstract: The invention relates to a material with high fracture toughness based on a vinyl ester resin and/or on an epoxide resin and to its process of manufacture. This material comprises at least one polymerized resin chosen from vinyl ester resins and epoxide resins which can be polymerized at a temperature of less than 70° C. and their blends, and a thermoplastic adjuvant present in this resin in the form of particles, and exhibits a fracture toughness (KIc) of greater than or equal to 1.2 MPa·m1/2 as determined according to Standard ISO 13586:2000. It also relates to a composite material comprising a matrix composed of said material and a reinforcement. Applications: automobile, railway, ship-building, aeronautical, aerospatial and other industries.

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: The invention relates to a process that makes it possible to improve the mechanical strength of bonds between substrates when these bonds are produced by means of an adhesive that comprises a resin that can be cured by chain polymerization, and in particular a resin that can be cured under the effect of ionizing or light radiation. This process is characterized in that it comprises the grafting of groups capable of acting as chain transfer agents during the polymerization of said resin to the surface of the substrates, before the latter are brought into contact with the adhesive. Applications: assembling of structural, engine, passenger compartment or bodywork parts in the aeronautical, space, railway, ship-building and automotive industries.

Abstract: The aim of the method of controlling at least one mechanical system exhibiting at least one flexible structure element and at least one actuator or group of actuators is to reduce the level of vibrations of said element while controlling the actuator or group of actuators in such a way as to achieve at least one objective assigned to the mechanical system. The control consists of increments having to be carried out at a sampling period T, each of the increments being constant in amplitude in a sampling time interval extending between two successive sampling instants and each of the increments being applied during a duration which is less than or equal to the sampling period T. In each sampling interval, at least one of the initial and final instants of application of the increment is modified by adding a variable, random or pseudo-random, temporal deviation dT.

Abstract: The invention relates to the stiffening of inflatably deployable structures, in particular for space use. More specifically, the invention relates to a flexible membrane for inflatably deployable structures, that comprises one layer of a composite and at least one polymer film that is permeable to visible radiation covering one of the faces of this layer, said composite being formed from a fibrous material impregnated with a composition incorporating an epoxide or epoxy/acrylate resin and a photoinitiator, and which is characterized in that the photoinitiator is an iron-arene complex salt of general formula (I): where A is an arene group, while X is a non-nucleophilic anion. Applications; manufacture of devices of the following types: radars, solar panels, reflectors, solar shields, antennas, solar mirrors or sails, intended to equip orbital vehicles or vehicles for space or planetary exploration.