ASTRIUM SAS Patent applications |
Patent application number | Title | Published |
20140322479 | FLAME RESISTANT SHIELD - A flame resistant shield includes two opposing walls between which are positioned at least: a first insulating layer, the first layer being capable of distributing heat in the plane formed by the first layer and being insulating across its thickness, a second insulating layer, one of the opposing walls which covers the first layer being produced from a refractory antioxidant material or having at least the surface intended to be exposed to flames covered with a material preventing this surface from being oxidised, the other wall being a support. | 10-30-2014 |
20140293785 | METHOD FOR MANAGING SERVICE POLICY IN A TELECOMMUNICATIONS NETWORK - 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. | 10-02-2014 |
20140232416 | SYSTEM AND METHOD FOR DETECTING AND LOCATING AN INSULATION FLAW IN A SOLAR GENERATOR ON A SPACE VEHICLE - A system and method for detecting and locating an insulation flaw in a solar generator on a spacecraft. The solar generator comprises a plurality of flaps. Each flap bears at least one solar cell that is connected to an electrical distribution network and electrically insulated from the flap. Each flap is connected, by a first load and by a second load, to a first electrical line and a second electrical line, respectively. The ratio of the impedances of the first load and of the second load of a flap being denoted as an impedance ratio of the flap. The solar generator comprises at least two flaps exhibiting different respective impedance ratios. The system comprises a component for evaluating the currents flowing in the first and second electrical lines, and a detector for detecting and locating an insulation flaw in the solar generator based on the evaluations of the currents. | 08-21-2014 |
20140146694 | METHOD AND DEVICE FOR DETECTING CONGESTION ON A TRANSMISSION LINK - Detection of the congestion on a link based on an exchange of messages between a sender and a receiver, one sender and several receivers or several senders and one receiver. This equipment is connected to the ends of a transmission channel. One of the items of equipment is designated as the master and the others slaves. These exchanges are aimed at enabling the master to calculate and compare the rate of the data send and the rate of the data received. A divergence in the rates calculated reveals a congestion on the link. All these exchanges are made in the application layer and therefore do not involve the underlying layers. | 05-29-2014 |
20140144887 | TOOLSET AND METHOD FOR PRODUCING A METAL LINER - A method and a toolset for manufacturing a metal liner for a composite vessel includes a mandrel configured in several mandrel elements forming support elements of primary parts constituting the metal liner. | 05-29-2014 |
20140128059 | DEVICE AND METHOD FOR OPTIMIZING THE GROUND COVERAGE OF A HYBRID SPACE SYSTEM - A telecommunications system for intermittent data transfer from and to at least one user located substantially on the surface of a celestial body. The system comprises at least one surface transmitter/receiver terminal associated with each user, one or more signal repeater means for the signals transmitted and/or received from the surface terminals. Each moving repeater means has at least one antenna oriented toward the surface of the celestial body, and adapted to allow communications from and to surface terminals. Each antenna produces a transmission/reception beam, the track of which on the surface of the celestial body forms the ground track, the progressive sweeping of the surface by this ground track forming a strip called a swath. | 05-08-2014 |
20140123867 | DETONATING PYROTECHNIC RUPTURE PIECE - An expansion tube of a detonating pyrotechnic rupture piece is open next to pre-established rupture zones and, inside said open expansion tube there is disposed a sealed bladder which contains a pyrotechnic fuse. | 05-08-2014 |
20140113546 | Unknown | 04-24-2014 |
20140110530 | Aerodynamic and Spatial Composite Flight Aircraft, and Related Piloting Method - An aircraft having propulsion units for both conventional aircraft flight in the atmosphere and for high-altitude operation as a rocket. The aircraft is divided into a payload compartment and a compartment containing rocket propulsion unit propellant or fuel, and includes a long transverse wing with a small back-sweep to favour lift in the dense layers of the atmosphere and to thus make it possible to climb to high altitudes at a subsonic speed before using the rocket propulsion units. The return flight portion is performed by gliding or controlled as for a conventional aircraft. | 04-24-2014 |
20140110051 | METHOD FOR MAKING A SANDWICH TYPE COMPOSITE BY CO-FIRING - The invention provides a method for making a composite ( | 04-24-2014 |
20140105100 | SATELLITE COMMUNICATION SYSTEM, LEO SATELLITE RELAYING COMMUNICATIONS BETWEEN A GEO SATELLITE AND TERRESTRIAL STATIONS, THE UPLINKS AND DOWNLINKS USING THE SAME FREQUENCY BAND AND TIME-DIVISION MULTIPLEXING - 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 | 04-17-2014 |
20140044478 | Method for Temporarily Connecting Two Parts Together, such as Two Stages of a Space Launcher, and Assembly Including Two Temporarily Connected Parts - A method for making a temporary connection between two parts ( | 02-13-2014 |
20140027578 | METHOD AND DEVICE FOR THE SUCCESSIVE LAUNCHING OF TWO SATELLITES - According to the invention, a link is established between the fixed part ( | 01-30-2014 |
20140018044 | SYSTEM AND METHOD FOR MANAGING COMMUNICATIONS OF AT LEAST ONE TERMINAL IN A COMMUNICATION NETWORK - 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 ( | 01-16-2014 |
20130340644 | REVERSIBLE DETONATING PYROTECHNIC RUPTURE PIECE - According to the invention, this piece comprises: e base section piece ( | 12-26-2013 |
20130336661 | METHOD AND SYSTEM FOR FREE-FIELD OPTICAL TRANSMISSION BY MEANS OF LASER SIGNALS - The invention relates to a method and system for free-field optical transmission by means of laser signals, including setting a rate for encoding information that is useful for transmission on the basis of variations in a signal receiving characteristic belonging to a single communication session. The encoding rate is preferably dynamically adjusted during the communication session. An optimized compromise is thereby created between a useful rate that is high and a post-decoding bit error rate that is low. The method and the related system enable atmospheric conditions that can disrupt laser signal transmission to be taken into account in real time when said laser signals pass through part of the earth's atmosphere. | 12-19-2013 |
20130311010 | METHOD AND SYSTEM FOR PILOTING A FLYING CRAFT WITH REAR PROPULSION UNIT - According to the invention, in accordance with a servo loop, the attitude (θ | 11-21-2013 |
20130301639 | NETWORK OF SWITCHES AND PAYLOAD OF TELECOMMUNICATIONS SATELLITE COMPRISING A NETWORK OF SWITCHES - A network of switches includes N input accesses and M output accesses, with each of the switches including four ports and with the network input and output accesses being connection switch ports. The network includes at least one stage of switches, with each stage including: a pair of switch lines whose ports are not used as network input or output accesses, referred to as “interconnection switches”, a line being a set of interconnection switches connected to one another; and at least two transverse arms linking interconnection switches of different lines, a transverse arm consisting of elements that are separate from those of the other transverse arms, a transverse arm including at least two links and a switch, referred to as “transverse switch” with the connection switches being transverse switches. At least two transverse switches from different transverse arms of each stage are connection switches of the network. | 11-14-2013 |
20130300288 | METHOD AND DEVICE FOR FORMING A PLASMA BEAM - The invention relates to a method and device for forming a plasma beam. According to the invention: the quality of the electroneutrality of the plasma beam (PB) is detected (in | 11-14-2013 |
20130292518 | DEVICE FOR MONITORING THE ATTITUDE OF A SATELLITE, AND METHOD FOR CONTROLLING A SATELLITE PROVIDED WITH SAID DEVICE - A device for controlling the attitude of a satellite exploiting solar pressure, includes at least two solar generators destined to be arranged on either side of a central body of the satellite and each having one face to be exposed to the Sun, referred to as “front face”, the device also including at least three surfaces whose optical properties can be commanded. The surfaces whose optical properties can be commanded are arranged on flaps connected to solar generators, each flap being fixed with respect to the solar generator to which it is connected, and such that, in the operating position, at least two of the surfaces are not parallel when the front faces of the solar generators are optimally oriented with respect to the Sun. The device further includes a module for commanding the optical properties of each surface whose optical properties can be commanded. | 11-07-2013 |
20130278757 | SPACE SURVEY SYSTEM FOR MONITORING NEAR-EARTH SPACE - A space survey system includes networked optical surveying systems designed to scan areas of earth orbit, in particular the LEO layer, arranged in a grid on the surface of a planet and further includes means designed to acquire images of objects traversing the areas scanned by the optical systems and calculation means designed to realize a measurement of the position time series of objects crossing the scanned areas by short integration over a fixed field. | 10-24-2013 |
20130264463 | OPTICAL SURVEILLANCE SYSTEM FOR A SPACE SURVEY SYSTEM FOR MONITORING NEAR-EARTH SPACE - An optical system for surveillance systems for space surveillance systems includes at least one telescope with a field greater than or equal to 5° mounted on a mobile mount along two axes, and coupled with an image sensor, whose sensitivity is designed for an integration time of the order of magnitude of a hundred milliseconds. | 10-10-2013 |
20130258106 | METHOD OF USING AN IMAGE SENSOR - A method of using an image sensor onboard a satellite or an aircraft comprises two simultaneous sequences of image capture. The first sequence corresponds to a capture of observation images, and the second sequence corresponds to a capture of images dedicated to the detection of a shifting of the observation images. The images dedicated to the detection of the shifting are restricted to windows that are at least in part contained in a main window the of observation images. Furthermore, said images dedicated to the detection of shifting are captured at a frequency greater than a frequency of the observation images. | 10-03-2013 |
20130241773 | SYSTEM FOR ORIENTING AND POSITIONING AN ELECTROMAGNETIC RECEIVER - According to the invention, a transmitting beacon ( | 09-19-2013 |
20130235897 | METHOD AND DEVICE FOR NON-DESTRUCTIVE TESTING OF WIND TURBINE BLADES - The method CND of non-destructive testing of a wind turbine blade includes: stressing the structure of the blade through a modification of a physical characteristic of a fluid filling the hollow interior volume of the blade; observing zones to be tested of the exterior surface of the blade, with the contactless measurement of a physical parameter on points of the exterior surface of the blade; and comparing the map of the values of the physical parameter measured with a reference map. A corresponding system CND for checking the structural integrity of a wind turbine blade includes an aerothermic device for modifying the physical conditions, temperature or pressure, of a fluid filling the hollow interior volume of the blade, a device for contactless measurement of a physical parameter, temperature or dimensions, of the exterior surface of the blade, and a device for processing the measurements. | 09-12-2013 |
20130223209 | SERVICE ADMISSION PATH CONTROL (SAPC) - A service admission control method in a communication network comprising at least one group of at least one node per group, the method comprising the steps: Receive a service establishment attempt from one group; and admit the service in the network depending on the granularity of the network topology, the link topology and/or the partitioning of the link topology. | 08-29-2013 |
20130211778 | METHOD FOR REALIZING A SPACE SURVEY SYSTEM FOR MONITORING NEAR-EARTH SPACE - A method for realizing a space survey system for the LEO zones of the Earth orbit includes positioning and placing network stations of optical survey systems over the surface of the globe according to a grid designed to offer an effective daily cycle of the system close to 24 hours and a chosen revisit period for the LEO zone observed. | 08-15-2013 |
20130207028 | HEAT-PROTECTION MATERIAL - A heat protection material for a surface, made of a mixture comprising a resin, cork granules and refractory fibers, wherein the proportion of cork granules in the mixture is | 08-15-2013 |
20130207027 | HEAT-PROTECTION MATERIAL - A heat protection material for a surface, made of a mixture comprising a resin, cork granules and refractory fibers; the proportion of cork granules in the mixture is 50 to 80% by mass, wherein the corresponding proportion of refractory fibers in the mixture is 1 to 11% by mass. | 08-15-2013 |
20130199359 | ATTACHMENT DEVICE WITH PYROTECHNIC BOLT - According to the invention, the device ( | 08-08-2013 |
20130193366 | OPTIMIZED HEAT-PROTECTION MATERIAL - A material for protecting a surface from heat made of a mixture comprising cork granules and resin as a binding agent, which also includes short fibers of heat-resistant material, and phenolic resin or epoxy resin. | 08-01-2013 |
20130186893 | CONNECTION BETWEEN A METAL LINER AND A COMPOSITE STRUCTURE IN THE MOUNTING REGION OF A TANK - A tank includes a tank body, a liner and a composite body spooled onto the liner, and at least one mounting, wherein the liner and the composite body are adhesively bonded together apart from in an annular joining region between the body of the tank and the mounting, surrounding the mounting. | 07-25-2013 |
20130186602 | HEAT TRANSFER SYSTEM - The invention relates to a heat transfer system comprising 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 comprising one evaporator, a vapour pipe capable of conveying the cooling fluid in the vapour 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. | 07-25-2013 |
20130099059 | SATELLITE HAVING A SIMPLIFIED, STREAMLINED, AND ECONOMICAL STRUCTURE, AND METHOD FOR IMPLEMENTING SAME - The invention relates to a satellite having a structure that includes a circular launching interface ring and at least two main planar apparatus-holding walls that are substantially parallel to the axis of the ring and rigidly connected to one another and to the ring. Each wall directly bears on the ring by a base of the wall, and each wall is rigidly and directly attached to the ring by at least one somewhat point-by-point connection on at least one point or area of tangency or intersection with the base of the wall and the ring. | 04-25-2013 |
20130088115 | PERMANENT-MAGNET ELECTRIC MOTOR COMPRISING A SEGMENTED STATOR - An electric motor ( | 04-11-2013 |
20130087659 | SIMPLIFIED REUSABLE MODULE FOR LAUNCHER - A recoverable module for a propulsion module configured to launch a craft into space, the recoverable module including a central body, a propulsion system configured to launch the craft, systems for commanding and controlling the propulsion system, at least one propulsion engine in subsonic flight, lift surfaces for the subsonic flight and landing gear, the lift surface including two substantially flat wings fixed with respect to the central body, arranged on either side of the central body of the module, and a stabilizer mounted articulated for rotation on a downstream end of each wing, each stabilizer including at least one pair of lower wing surface and upper wing surface flaps mounted articulated on the stabilizer or any other flap fulfilling a dynamic function. | 04-11-2013 |
20130050494 | IMAGING METHOD - The invention relates to an imaging method, including reconstructing a final image (IF) from intensity values inputted by a limited selection of photodetectors ( | 02-28-2013 |
20130050488 | POLYCHROMATIC IMAGING METHOD - The invention relates to a polychromatic imaging method, using a picture-taking instrument, which is placed on board an aircraft or satellite, which enables a reduction of the size of the instrument without reducing resolution of a final obtained image. To this end, a pupil of the instrument is sized for intermediate images that are limited to a first spectral sub-band without any image information being completely transmitted by the instrument for at least one wavelength that is located beyond said first spectral sub-band. Merging the intermediate image, inputted for the first spectral sub-band, with at least one other intermediate image, inputted for another spectral sub-band, recreates a polychromatic visual rendering that is satisfactory for the final image. Said other intermediate image includes the wavelength located beyond the first sub-band. | 02-28-2013 |
20120325957 | ULTRA-RAPID AIR VEHICLE AND RELATED METHOD FOR AERIAL LOCOMOTION - The invention concerns an ultra-rapid air vehicle together with a method of aerial locomotion by means of an ultra-rapid air vehicle, where the air vehicle is propelled by a system of motors formed of turbojets (TB | 12-27-2012 |
20120313564 | RECONFIGURABLE INVERTER HAVING FAILURE TOLERANCE FOR POWERING A SYNCHRONOUS POLY-PHASE MOTOR HAVING PERMANENT MAGNETS, AND ASSEMBLY INCLUDING SAID INVERTER AND MOTOR - Reconfigurable fault-tolerant inverter for powering a multi-phase synchronous permanent-magnet motor, and assembly of the said inverter and motor. | 12-13-2012 |
20120308084 | METHOD FOR ESTIMATING THE MOVEMENT OF A TRAVELING OBSERVATION INSTRUMENT FLYING OVER A CELESTIAL BODY - Method for estimating the movement of an observation instrument on-board a vehicle flying over a celestial body, the instrument including at least two strips with different lines of sight, each strip realizing the acquisition of successive image lines making up a composite image, parts of the composite images representing substantially a same scene of the celestial body. The estimated movement is determined by optimization of an image similarity function that associates, to a given movement hypothesis, a similarity between values of matched pixels of at least a pair of composite images. The method includes, for each movement hypothesis considered during the optimization: determining, for the at least one pair of composite images, at least one spatio-temporal transformation using the considered movement hypothesis and a geometric model of the observation instrument, and matching the pixels of the at least one pair of composite images using the at least one spatio-temporal transformation. | 12-06-2012 |
20120301708 | Replacement part for satellite optical solar reflectors - Method for installing a thermo-optical patch on an outer satellite wall; the patch consists of a metal sheet that includes a coat of electrically conductive adhesive on one of its sides and a coat of paint with predefined thermo-optical properties on its other side. A satellite that includes a patch applied to an outer side of a wall of the satellite is also described. | 11-29-2012 |
20120300815 | HYBRID SPACE SYSTEM BASED ON A CONSTELLATION OF LOW-ORBIT SATELLITES WORKING AS SPACE REPEATERS FOR IMPROVING THE TRANSMISSION AND RECEPTION OF GEOSTATIONARY SIGNALS - The remote communications system, intended for low-throughput data transfer between at least two users located substantially on the surface of a celestial body, includes:
| 11-29-2012 |
20120295521 | METHOD FOR PRODUCING A COMPOSITE MIRROR AND COMPOSITE MIRROR OBTAINED WITH SAME - A method for producing a composite mirror. It comprises the steps of providing a glass blank with low coefficient of expansion, machining a convex shape ( | 11-22-2012 |
20120287802 | METHOD FOR CALIBRATING THRESHOLDS AND THRESHOLD CALIBRATION MODULE FOR A SATELLITE TELECOMMUNICATIONS SYSTEM - A method for calibrating a threshold for selecting a transmission format, from a plurality of transmission formats, in order to exchange data packets over a radio-frequency propagation channel, referred to as the “channel” (L, | 11-15-2012 |
20120284006 | METHOD OF DETERMINING THE PARTICLE SENSITIVITY OF ELECTRONIC COMPONENTS - To analyze an electronic component, this component is exposed to a focused laser beam. The information provided by the laser mapping relating to the position and to the depth of the sensitivity zones of the component is used as input parameter in prediction codes for quantifying the sensitivity of the mapped component to ionizing particles in the natural radioactive environment. The prediction codes are used to determine the occurrence of malfunctions in the electronic component. Determination of the risks associated with the radiative environment imposes two aspects: one, probabilistic, takes into account the particle/matter interaction and the other, electrical, takes into account the charge collection inside the electronic component. | 11-08-2012 |
20120277383 | INCREASE IN THE TOUGHNESS OF A MATERIAL OBTAINED FROM A CURABLE COMPOSITION COMPRISING AT LEAST ONE VINYL ESTER MONOMER - A method increases the toughness of a material obtained by curing a composition that includes at least one vinyl ester monomer. The method includes the incorporation into the composition of a sulfonated polyaromatic thermoplastic polymer, which is achieved by dissolving the vinyl ester monomer and the thermoplastic polymer in a reactive diluent in which they are both soluble. The resulting curable composition includes at least one vinyl ester monomer, and very high toughness materials can be made from it. A curable composition can include at least one vinyl ester monomer, a sulfonated polyaromatic thermoplastic polymer and a N-vinyl lactam. The compositions can be used in the aeronautical, space, railway, nautical, automotive industries, arms and other industries. | 11-01-2012 |
20120210808 | SYSTEM COMPRISING A SPATIAL MOTHER PROBE FORMING A SPATIAL CARRIER VEHICLE AND A PLURALITY OF SPATIAL DAUGHTER PROBES - A system includes a mother probe forming a carrier space vehicle ( | 08-23-2012 |
20120184208 | Virtual Polar Satellite Ground Station for Low Orbit Earth Observation Satellites Based on a Geostationary Satellite Pointing an Antenna Over an Earth Pole - A satellite system includes a satellite operating in an orbit around the Earth and a satellite operating in another orbit around the Earth. The satellite points a fixed beam at least temporarily to a zone above the Earth's surface through which the satellite passes. | 07-19-2012 |
20120153077 | LANDING SYSTEM FOR A BODY AND SPACE PROBE PROVIDED WITH SUCH A SYSTEM - A landing system of a body and a space probe provided with such a system for landing on a bearing ground. The landing system includes landing legs ( | 06-21-2012 |
20120148113 | METHOD FOR DETECTING SHIFTS IN LINE IMAGES OBTAINED BY A SENSOR THAT IS AIRBORNE OR MOVING IN SPACE - Method for estimating shifts of line images obtained by an airborne or spaceborne scanning sensor. The invention relates to a method for estimating shifts in line images of an image, referred to as a “composite image”, made up of the juxtaposition of J line images. The line images show portions of a scene on the surface (S) of a celestial body that are different and successively acquired by a row of sensitive cells of a sensor ( | 06-14-2012 |
20120141284 | DEVICE FOR ASSEMBLING SECTIONS OF WIND-TURBINE BLADES AND METHOD FOR LINKING SECTIONS OF WIND-TURBINE BLADES - A device for assembling sections of wind-turbine blades provided with casings, including at least one tie including a first portion and a second portion, the first portion being a portion for assembly with a casing of a first section and the second portion being a portion for mounting with a complementary tie supported by a casing of a second section, wherein the first portion includes at least one composite/metal shear link provided with a continuous fitting element on at least one surface of the casing which receives one end of the aformentioned surface of the casing, provided with attachment pins passing through the fitting and the end of the surface. According to a preferred embodiment, the composite/metal link has at least double shear and is additionally provided with a back-fitting element, the end of the aforementioned surface of the casing being received between the fitting and the back fitting, the attachment pins passing through the fitting, the end of the surface and the back fitting, the link also being provided with a means for attaching the back fitting to the fitting. | 06-07-2012 |
20120136473 | METHOD FOR MAKING MECHANICAL LINKS - A method of making a mechanical multishear link includes sizing the multishear link by breaking down a system comprised by the link into as many subassemblies as there are simple shear interfaces, defining the subassemblies around each shear interface, describing each shear by its stiffness, and applying the mechanical relationships to achieve a system of equations for a computer-assisted resolution by applying the Huth method to each shear interface. | 05-31-2012 |
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 |