| ASTRIUM SAS Patent applications |
| Patent application number | Title | Published |
|---|
| 20120111218 | DEVICE FOR TEMPORARILY CONNECTING AND PYROTECHNICALLY SEPARATING TWO ASSEMBLIES - Temporary connection and pyrotechnic separation device with a longitudinal axis (X) comprising a pyrotechnic expansion tube ( | 05-10-2012 |
| 20120110823 | SMOOTH LINEAR SEPARATION DEVICE BETWEEN A FIRST PART AND A SECOND PART - A device for smooth linear separation between a first part and a second part. The first part is linearly connected to the second part. The device includes a heat source applied onto the first part that applies a heat stimulus to the first part so as to separate the first part from the second part by thermal deformation of the first part. | 05-10-2012 |
| 20120080562 | LANDING DEVICE FOR A SPACE PROBE, AND LANDING METHOD FOR A PROBE PROVIDED WITH SUCH A DEVICE - A space probe including a descent module with a mobile exploration vehicle, wherein the descent module is a landing module inside which the mobile exploration vehicle is fastened, the landing module being provided with landing legs which can be deployed under the lower level of the mobile exploration vehicle. | 04-05-2012 |
| 20120071587 | USE OF CURABLE RESINS CONTAINING A PREPOLYMER BASED ON GLYCIDYL (METH)ACRYLATE FOR MAKING MATERIALS FOR USE IN SPACE - It relates to the use of curable resins containing a prepolymer based on glycidyl (meth)acrylate for making composite materials for use in space and, more particularly to composite materials entering the composition of structures intended to be deployed in space and to be stiffened after deployment. | 03-22-2012 |
| 20120070037 | Method for estimating the motion of a carrier relative to an environment and computing device for navigation system | 03-22-2012 |
| 20120043427 | ABSORBENT DOME FOR A RADIATING COLLECTOR TUBE - The device for thermal monitoring for a piece of equipment, whereby said piece of equipment is integrated on a craft placed in a forced vacuum environment, an outside part ( | 02-23-2012 |
| 20120033712 | Device for Measuring the Temperature of a Substrate - A device for measuring the temperature of a substrate comprising a thermocouple comprising electric wires joined to each other at least one junction; a fixing element suitable for fixing said junction to said substrate in order to measure its temperature; characterized in that the fixing element comprises a thermally conductive element suitable for bearing a portion of electric wires adjacent to said junction; said thermally conductive element being capable of thermally coupling said portion of electric wires to said substrate. | 02-09-2012 |
| 20120026056 | RADIO ANTENNA WITH IMPROVED DECOUPLING ANGLES - A radio antenna, particularly for a spacecraft, including a reflector and means of support of this reflector, where the reflector includes a body able to reflect radio waves, and a rigid rear structure supported by the means of support and connected to the body by decoupling angles, wherein each of said decoupling angles includes, at one at least of its ends, a layer of elastic material able to dampen at least one axial component of vibrations of the body. | 02-02-2012 |
| 20120026055 | RADIO ANTENNA - The invention concerns a radio antenna for a space satellite, including a reflector and means of support of this reflector. The reflector includes a front skin able to reflect radio waves, a rigid rear structure supported by the means of support, and a layer of elastic material interposed between said front skin and said rigid rear structure, able to dampen the vibrations of the front skin. | 02-02-2012 |
| 20120019430 | RADIO ANTENNA INCLUDING IMPROVED MEANS OF RIGIDIFICATION - A radio antenna, in particular for a spacecraft, including a reflector and a rear structure supporting said reflector, and also a rigidification membrane added on to the reflector so as to limit the displacement of a peripheral portion of the reflector in a direction parallel to a central axis of this reflector, where said rigidification membrane is separate from the rear supporting structure. | 01-26-2012 |
| 20110315546 | APPARATUS FOR PRODUCING AND DISPENSING HYDROGEN - The present disclosure relates to an altitude-adjustable apparatus comprising: a platform; a device for controllably raising the altitude of the platform; a water supply combined with said platform; a device for converting water into the components thereof through solar power; and means for liquefying and storing the resulting liquefied hydrogen in tanks, the latter being built into flying bodies that are designed to arrive at a target area and dispense the liquefied hydrogen. | 12-29-2011 |
| 20110297793 | REUSABLE MODULE FOR LAUNCHER - A propulsion module configured to launch a craft into space including a recoverable module and a non-recovered part, which is secured to the recoverable module at launch. The recoverable module includes a propulsive system to launch the craft, systems for command and control of the propulsive system, a subsonic flight propulsion motor, airfoils for the subsonic flight, a landing gear, and a braking parachute. The recoverable module is installed in a lower position of the craft when the craft is in the launch position. The non-recovered part includes at least one tank to feed the propulsive system. The recoverable module and the non-recovered part are configured to be separated when the propulsion module reaches a given altitude, and the recoverable module is capable of landing in a controlled fashion after a coasting flight, for example for a return to the launch site. | 12-08-2011 |
| 20110229710 | METHOD FOR PROTECTING COMPOSITE STRUCTURES AGAINST IMPACTS - An impact-resistant protective coating includes a material consisting of an outer metal adhesive layer having a sub-layer of compressible cellular material. | 09-22-2011 |
| 20110209864 | THERMAL CONTROL DEVICE WITH NETWORK OF INTERCONNECTED CAPILLARY HEAT PIPES - The thermal control device comprises at least one network of capillary heat pipes, in which each heat pipe comprises a tube enclosing an essentially annular longitudinal capillary structure, for the circulation of a two-phase heat-transfer fluid in the liquid phase, and surrounding a central channel for the circulation of said two-phase fluid in the vapor phase. The tubes of at least two heat pipes of the network intersect and are interconnected in such a way that at each intersection of heat pipes forming a node of the network, an exchange of fluid in the liquid phase can take place by capillary action between the capillary structures of said two or more heat pipes, and such that, simultaneously, an exchange of fluid in the vapor phase can take place by free circulation between the central channels of said two or more heat pipes. | 09-01-2011 |
| 20110207378 | USE OF POLYMERISABLE RESINS WITH LOW VACUUM OUTGASSING FOR THE MANUFACTURE OF COMPOSITE MATERIALS FOR USE IN SPACE - A method of using at least one polymerisable resin R1 is disclosed. According to some aspects, the resin R1 is selected from the group consisting of epoxidised polybutadiene resins, epoxidised polyisoprene resins, epoxidised polysiloxane resins, epoxidised triglyceride resins and epoxidised polyether resins. The resin R1 having at the non-polymerised state a total mass loss (TML) value lower than about 10%, a recovered mass loss (RML) value lower than about 10%, and a collected volatile condensable material (CVCM) value lower than about 1%, as determined in accordance with standard ECSS-Q-70-02A of the European Space Agency. The resin R1 also characterized by an epoxide equivalent weight of about 100 to 600 g/mole. The resin is configured for the manufacture of a composite material for use in space, and more specifically, a composite material of a Gossamer structure. Polymerisable resin compositions are also disclosed which are useful in the manufacture of composite materials for use in space. | 08-25-2011 |
| 20110192575 | Passive Device with Micro Capillary Pumped Fluid Loop - 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 ( | 08-11-2011 |
| 20110155858 | METHOD FOR CONTROLLING SATELLITE ATTITUDE, AND ATTITUDE-CONTROLLED SATELLITE - 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. | 06-30-2011 |
| 20110132069 | DEVICE FOR GENERATING IMPACTS WITH A STRUCTURE - The invention concerns a device for generating impacts on a structure, and this device has a projectile head. | 06-09-2011 |
| 20110129177 | SPACERS FOR ROLLING BEARINGS WITH ADJUSTED LENGTHS - A rolling bearing device, of the type including a central shaft and a hub ( | 06-02-2011 |
| 20110076956 | MULTI-BEAM SATELLITE TELECOMMUNICATIONS SYSTEM AND METHOD FOR FORMING BEAMS - 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. | 03-31-2011 |
| 20110067380 | ELECTRIC THRUSTER FOR A SPACECRAFT - The invention relates to an electric thruster for a spacecraft. According to the invention, the thruster (II) comprises a jet generating portion (G | 03-24-2011 |
| 20110049328 | Device for measuring the line of sight jitter of an optical instrument - Device for measuring the line of sight jitter of an optical instrument mounted on an optical platform, includes:
| 03-03-2011 |
| 20110024572 | DEVICE FOR REDUCING AERODYNAMIC DRAG - 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. | 02-03-2011 |
| 20110006162 | ACTUATOR DEVICE FOR VARYING THE ATTITUDE OF A SPACECRAFT - 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. | 01-13-2011 |
| 20100327108 | SPACECRAFT AFTERBODY DEVICE - 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. | 12-30-2010 |
| 20100314499 | ACTUATOR WITH TRANSFER OF ANGULAR MOMENTUM FOR THE ATTITUDE CONTROL OF A SPACECRAFT - 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 ω1 of the first momentum wheel and a rotation speed ω2 of the second momentum wheel a ratio R=ω2/ω1, 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. | 12-16-2010 |
| 20100313670 | DEVICE FOR TESTING STRUCTURAL PANELS - 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. | 12-16-2010 |
| 20100309045 | SYSTEM FOR POSITIONING IN A LOCATION OPAQUE TO THE SIGNALS OF A SATELLITE NAVIGATION SYSTEM - According to the invention, the system comprises: at least three position beacons ( | 12-09-2010 |
| 20100308175 | SPACE VEHICLE SEAT AND SPACE VEHICLE PROVIDED WITH THIS SEAT - 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. | 12-09-2010 |
| 20100264290 | Modular Device for Multi-Axial Insulation Against Vibration and Impacts, Based on Elastomer - 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 ( | 10-21-2010 |
| 20100263836 | Thermal Regulation Passive Device with Micro Capillary Pumped Fluid Loop - 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. | 10-21-2010 |
| 20100182192 | System for Positioning a Terrestrial User - According to the invention, navigation satellites ( | 07-22-2010 |
| 20100166988 | ASSEMBLY OF PREPREGS FOR PRODUCING STRUCTURES, FOR EXAMPLE ONES WHICH DEPLOY THROUGH INFLATION - The invention relates to a method of assembling pre-impregnated plies by local isolated polymerization of the assembly region ( | 07-01-2010 |
| 20100158536 | Optical Transceiver Assembly with Transmission-Direction Control - 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. | 06-24-2010 |
| 20100092695 | PROCESS FOR IMPROVING THE ADHESION OF CARBON FIBRES WITH REGARD TO AN ORGANIC MATRIX - 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. | 04-15-2010 |
| 20100077693 | Deployable light structure capable of being rigidified after deployment, its production process and its application to equipping a spacecraft - The invention concerns a structure comprising a rigging ( | 04-01-2010 |
| 20100006705 | Control Moment Gyro and Device for Assembly Thereof - 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. | 01-14-2010 |
| 20100001141 | Device for Controlling the Heat Flows in a Spacecraft and Spacecraft Equipped with Such a Device - 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. | 01-07-2010 |
| 20090288801 | Capillary Pumped Diphasic Fluid Loop Passive Thermal Control Device with Thermal Capacitor - The thermal control device comprises at least one capillary pumped diphasic fluid loop, comprising, in a known manner, an evaporator extracting the heat from a so-called hot source and connected via a vapour pipe to a condenser in which the condensation of the fluid vapour releases thermal energy transmitted to a so-called cold source, the condenser being connected via a liquid pipe to the evaporator, and the device moreover comprises at least one thermal capacitor in permanent heat exchange relationship with liquid phase fluid in said at least one diphasic fluid loop. Use in particular with space vehicles such as satellites. | 11-26-2009 |
| 20090230249 | Method of Launching into Operational Orbit an Artificial Satellite and Associated Propulsion Device - 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. The satellite then enters and operational orbit from the intermediate orbit by means of its own satellite propulsion system The intermediate orbit is disposed between the transfer and operational orbits, and is in relatively close proximity to the operational orbit but is far enough away from the operational orbit to prevent possible interferences | 09-17-2009 |
| 20090218448 | SATELLITE AIR BRAKE WING STRUCTURE - 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. | 09-03-2009 |
| 20090200427 | CONTROL DEVICE FOR DEPLOYMENT OF INFLATABLE STRUCTURES - The invention relates to a device for controlling the deployment of an inflatable structure including, in the non-deployed state, a flexible tube ( | 08-13-2009 |
| 20090195457 | METHODS AND SYSTEM FOR DETERMINING ANGLES OF SIGHT BETWEEN TWO DEVICES - 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 2π and are therefore ambiguous since they are known to within an integer number of times 2π. 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. | 08-06-2009 |
| 20090160397 | ELECTRICAL POWER SUPPLY SYSTEM FOR A SATELLITE - 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. | 06-25-2009 |
| 20090133823 | METHOD FOR IMPROVING MECHANICAL STRENGTH OF BONDINGS MADE WITH AN ADHESIVE BASED ON CURABLE RESIN BY CHAIN POLYMERIZATION - 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. | 05-28-2009 |
| 20090132102 | ACTUATOR CONTROL REDUCING THE LEVEL OF VIBRATION OF AN ASSOCIATED FLEXIBLE STRUCTURE - 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. | 05-21-2009 |
| 20090075091 | RIGIDIFICATION OF STRUCTURES TO BE DEPLOYED BY INFLATING, PARTICULARLY FOR USE IN SPACE - The invention relates to the stiffening of inflatably deployable structures, in particular for space use. | 03-19-2009 |
| 20090008504 | Elastomer-Based Modular Multi-Axis Vibration/Shock Isolation Device - The device comprises at least three isolating modules each having two rigid pieces, one of which is fastened to the carrier structure and the other of which is fastened to the support for the vibrating equipment, these pieces being linked by at least one isolating stud made of an elastomer, which attenuates the transmission of low-amplitude vibrations from the equipment to the structure, the deformation of at least one stud in tension-compression and in shear being limited by three flexible stops each mounted on only one of the pieces and the free end of which is facing the other of said pieces and not in contact with it, at rest. Each stop comprises an elastomer element coming into contact with the facing other piece during deformations of sufficient amplitude of the isolating stud, the stiffness of the elastomer of the stop being greater than that of the stud. Application to the isolation of vibrating equipment on a satellite carrier structure. | 01-08-2009 |
| 20080284644 | SATELLITE POSITIONING METHOD AND SYSTEM - According to the present invention, each navigation satellite ( | 11-20-2008 |
| 20080272983 | Method for Producing a Non-Developable Surface Printed Circuit and the Thus Obtained Printed Circuit - The invention relates to a method for producing a non-developable surface printed circuit and to the thus obtained printed circuit. According to said invention, each electrically conductive pattern ( | 11-06-2008 |
| 20080220262 | Coating for External Device for Thermo-Optical Control of Space Vehicles, Method for Forming Same by Micro-Arcs in Ionized Environment, and Device Coated with Same - The invention concerns a coating produced by conversion treatment of an outer surface of a semiconductor metal support component ( | 09-11-2008 |
| 20080210456 | Method For Producing Electrically Conductive Patterns on a Non-Developable Surface of an Insulating Substrate, and Resulting Device - 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 ( | 09-04-2008 |
