The subject matter of the invention is a wing or blade in at least two sections (1a, b) facing each other, said sections each comprising a longitudinal bearing structure (2a, 2b, 22) provided with at least one sole (2a, 2b) of which the link between the sections comprises at least one first link plate (3a, 3b) linking the end of the soles of said sections facing each other. The invention further concerns the method of producing the wing or blade of the invention.
The subject matter of the invention is a method for draping on a form, which includes a step of deposition on the form of a first fold support in the form of one or more polymer nonwoven fabrics. The invention further relates to a thermoplastic nonwoven material manufactured with a nonwoven fabric of polymer fibers.
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
D04H 3/08 - Non woven fabrics formed wholly or mainly of yarns or like filamentary material of substantial length characterised by the method of strengthening or consolidating
D04H 3/11 - Non woven fabrics formed wholly or mainly of yarns or like filamentary material of substantial length characterised by the method of strengthening or consolidating with bonds between yarns or filaments made mechanically by fluid jet
D04H 3/105 - Non woven fabrics formed wholly or mainly of yarns or like filamentary material of substantial length characterised by the method of strengthening or consolidating with bonds between yarns or filaments made mechanically by needling
3.
CALIBRATION METHOD AND SYSTEM FOR ESTIMATING A PATH DIFFERENCE OF A TARGET SIGNAL TRANSMITTED BY A SPACECRAFT OR AIRCRAFT
The present invention relates to a method (50) for estimating a path difference between two paths followed by a target signal transmitted by a spacecraft or aircraft (20) in order to reach a first receiving antenna (32a) and a second receiving antenna (32b) of a receiving base, respectively. The method (50) comprises: a step (500) of measuring a useful-phase difference between signals corresponding to the target signal received on the first receiving antenna (32a) and second receiving antenna (32b); and a step (502) of estimating the path difference on the basis of the measurements of the useful-phase difference. Said method (50) further comprises: a step (504) of transmitting a calibration signal to the receiving base; a step (506) of measuring a calibration-phase difference between signals corresponding to the calibration signal received on the first receiving antenna (32a) and second receiving antenna (32b); and a step (508) of compensating for variations in the measurements of the calibration-phase difference relative to the measurements of the useful-phase difference. The present invention also relates to a system (30) for estimating a path difference.
The present invention relates to a method (50) for estimating a path-length difference between two paths followed by a target signal transmitted by a spacecraft or aircraft (21) in order to arrive at a first receiving antenna (32a) and a second receiving antenna (32b) of a receiving base, respectively. The method (50) comprises a step (500) of measuring a useful-phase difference between signals that correspond to the target signal received by the first receiving antenna (32a) and second receiving antenna (32b), and a step (502) of estimating the path-length difference in accordance with the useful-phase difference measurements. In addition, the step (500) of measuring the useful-phase difference comprises either correlating the signals received by the first receiving antenna (32a) and second receiving antenna (32b), respectively, with a reference target signal, or analysing said signals received by the first receiving antenna (32a) and second receiving antenna (32b), respectively, using an FFT or a PLL. The present invention also relates to a system (30) for estimating path-length differences.
The invention relates to a device for cooling at least two distinct heat sources, characterized in that it comprises: - a closed circuit in which a diphasic fluid flows, - at least one capillary evaporator (10) designed to be placed in thermo contact with one of the heat sources, referred to as the primary heat source (41), - for each other heat source, referred to as a secondary heat source (15, 20) that is to be cooled, at least one exchanger (14, 19) designed to be placed in thermal contact with said secondary heat source, - at least one condenser, referred to as the first condenser (12), positioned downstream (according to the theoretical direction of the path of the fluid through the circuit) of the evaporator (10), and upstream of the at least one exchanger (14, 19), - at least one condenser, referred to as the last condenser (22), positioned upstream (according to the theoretical direction of the path of the fluid through the circuit) of the evaporator (10) and downstream of the at least one exchanger (14, 19).
F28D 15/04 - Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls in which the medium condenses and evaporates, e.g. heat-pipes with tubes having a capillary structure
6.
DEVICE AND METHOD FOR OPTICAL COMMUNICATIONS BETWEEN A SMALL AUTONOMOUS GROUND TERMINAL AND A SATELLITE
The invention relates to a system for communicating by optical link between a terminal arranged at a point that is stationary relative to the surface of the earth, referred to as "ground terminal," having a directional optical transmitter and a remote relay that is movable relative to the ground terminal, the ground terminal comprising means for the automatic orientation in terms of elevation and azimuth of the directional optical transmitter to the remote relay, with a precision that is compatible with the establishment of an optical communication between the stationary terminal and the remote relay. The ground terminal preferably also comprises autonomous power supply means.
According to the invention, the component to be ruptured comprises an alternation of oblong pre-cut zones and of non-pre-cut zones and the pyrotechnique rupture device (1) with detonating cord (2) comprises an alternation of sections (1.1) for rupturing said non-pre-cut zones and of inflatable sections (1.2) for parting the broken parts of said component.
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
Inventor
Coqueret, Xavier
Krzeminski, Mickael
Defoort, Brigitte
Abstract
The invention relates to a curable composition containing a vinyl ester polymerisable resin, together with a sulfonated poly-aromatic thermoplastic polymer and an N-vinyl lactame. The composition is characterised in that it also comprises: a first non-vinyl-ester polymerisable compound comprising at least one isocyanurate group bearing two (meth)acrylate groups, and a second non-vinyl-ester polymerisable compound comprising at least one carbopolycyclic or heteropolycyclic group bearing at least two (meth)acrylate groups. The invention also relates to a material obtained by curing said composition. The invention is suitable for composite materials and adhesives.
C09J 4/06 - Adhesives based on organic non-macromolecular compounds having at least one polymerisable carbon-to-carbon unsaturated bond in combination with a macromolecular compound other than an unsaturated polymer of groups
9.
ELECTRIC JACK COMPRISING STRESS-LIMITING MEANS AND SPACE LAUNCHER COMPRISING A NOZZLE SUPPORTED BY SUCH A JACK
The invention relates to an electro-mechanical jack (10) comprising: a movable member (14) provided with linking means (20) and capable of moving in translation in relation to a chassis (12); and an energy-absorption/dissipation structure (28, 30) located on a force path between the linking means (20) and the chassis (12), said structure comprising a porous capillary matrix (40) having open porosity and an associated liquid (42) which has a wetting angle greater than 90 degrees in relation to the matrix (40) and which is selected such that part of the liquid (42) enters the pores of the matrix (40) when the structure is subjected to a pressure above a first pressure level P1 and is spontaneously discharged from the pores of the matrix (40) by capillary action when the structure is subjected to a pressure below a second pressure level P2 which is lower than the first pressure level P1.
The invention relates to a device for expelling/containing a predetermined liquid, said device being capable of being built into a liquid tank that is to operate at low or zero gravity, and including a unitary three-dimensional so-called sponge structure (32) comprising a set of substantially wire-like elements (70) that extend between a peripheral area of the sponge and an area for expelling/containing liquid, wherein said wire-like elements are substantially oriented in the direction of flow of the fluid within the device, said wire-like elements being connected together by crosspieces and are arranged such that the capillary gradient is positive or zero in the direction of flow of the fluid from said peripheral area to said area for expelling/containing liquid.
The present invention relates to a method (50) for identifying uplink multiplexing resources of a multibeam satellite (20) that are usable in a land-based telecommunications system, i.e. by a transmitting station for transmitting radio signals to a receiving station, said transmitting station or said receiving station being a base station (30) having a range defining a coverage area. For a given uplink multiplexing resource, the method comprises: a step (51) of estimating a maximum allowable interference level, with respect to the satellite, for radioelectric signals transmitted from the coverage area; a step (52) of estimating a potential interference level of the transmitting station; and a step (53) of determining whether or not said uplink multiplexing resource is usable by the transmitting station by comparing the potential interference level with the maximum allowed interference level for said uplink multiplexing resource. The present invention also relates to a telecommunications system.
The subject matter of the invention is a device for the connection of sections of wings such as wind turbine blades which include, at the ends of the facing sections, central boxes arranged end to end and clamped against each other by clamping rods, and a method of producing sections of wings such as wind turbine blades which includes a step of producing devices for the connection of said sections in the form of central junction boxes.
The present invention concerns a method of controlling the attitude of a satellite in orbit around a celestial body, the attitude of the satellite being controlled by means of a momentum storage device and by means of controllable surfaces of the satellite capable of creating desaturation torques in the storage device by using solar pressure, said controllable surfaces being arranged on solar panels mobile in rotation around an axis Y. The attitude of the satellite is also controlled by means of at least one electric thruster also implemented to control the orbit of the satellite, the orientation of the at least one electric thruster being controlled in such a way as to activate said at least one electric thruster with a thrust direction deliberately not aligned with a centre of mass of the satellite in order to create desaturation torques in the storage device along axis Y, the controllable surfaces being controlled to create desaturation torques of said storage device in a plane orthogonal to the Y axis. The present invention also concerns an attitude-controlled satellite (10).
The present invention concerns a method for correcting a digital image stored by a client device by geometric adjustment of this image onto a reference image stored by a server device connected to the client device by a communication network. The method is characterised in that it includes the following steps: - obtaining, by the server device, at least one area of interest of the reference image, - sending, to each client device, each area of interest, - obtaining, by the client device, part of the image delimited by each received area of interest, said image part being either a part of the image to be corrected or a part of an image resulting from the image to be corrected, - sending, to the server device, each image part thus obtained, - determining, by the server device, parameters of the correction to apply to the image to be corrected, said parameters being determined by geometric adjustment of said received at least one image part onto the reference image, - sending, to the client device, the parameters thus determined, and - applying, by the client device, the correction of the image to be corrected, said correction using firstly the received parameters and secondly a ground elevation model corresponding to this image to be corrected.
The subject matter of the invention is a flame resistant shield. According to the invention, this shield comprises two opposing walls between which are positioned at least: - a first insulating layer (4), said first layer (4) being capable of distributing heat in the plane formed by said layer and being insulating across its thickness, - a second insulating layer (5), - one (2) of said opposing walls which covers said first layer (4) 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 (3) being a support.
The invention relates to a telecommunication system for the intermittent transfer of data from and to at least one user on the ground, including at least one surface terminal associated with the user, at least one signal-repeating means for signals transmitted and/or received from surface terminals (REC), said repeating means moving above the surface of the celestial body, each moving repeating means comprising at least one antenna directed towards the surface of the celestial body, the path of which at the surface of the celestial body forms the ground path, and the progressive scanning of the surface by said ground path determining a so-called swath band. The system comprises a means for reducing the length of the active path such that, at each point of the swath on the ground of the moving repeating means and during each pass thereof, the total duration of coverage by at least one active antenna of the moving repeating means defines a so-called active communication length that is substantially smaller than the width of said swath.
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
The present invention relates to a payload (10) for a repeater satellite (LEO) of a communication system, said repeater satellite being placed into drift orbit above the surface of a celestial body, and said payload (10) being configured to repeat data received from a stationary satellite (GEO) above the surface of the celestial body towards a terminal (REC) substantially at the surface of the celestial body, and to repeat data received from the terminal towards the stationary satellite. The payload (10) is further configured to use a single frequency band for repeating data towards the stationary satellite (GEO), referred to as uplink transmission, and for repeating data towards the terminal (REC), referred to as downlink transmission, as well as to time-division multiplex the uplink transmissions and the downlink transmissions. The present invention also relates to a telecommunication system comprising a repeater satellite provided with a payload (10) according to the invention, as well as to a satellite communication method.
The invention relates to a method for producing a composite (10) comprising two skins (14) made of a composite material adhered onto either side of a core (12) provided in the form of a honeycomb panel, wherein the method comprises a step of firing the skins (14) on the core (12) in order to simultaneously achieve the curing of the skins (14) and the adhesion of the skins (14) to the core (12), characterized in that it involves placing a stiffening layer (22) between the core (12) and at least one skin (14).
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B32B 3/12 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
B32B 37/26 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers with at least one layer which influences the bonding during the laminating process, e.g. release layers or pressure equalising layers
B32B 5/28 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer impregnated with or embedded in a plastic substance
19.
METHOD FOR TEMPORARILY CONNECTING TWO PARTS TOGETHER, SUCH AS TWO STAGES OF A SPACE LAUNCHER, AND ASSEMBLY INCLUDING TWO TEMPORARILY CONNECTED PARTS
The invention relates to a method for temporarily connecting two parts (10, 12) together, comprising the following consecutive steps: providing a connection member (40, 40') in a service position in which said connection member surrounds the assembly formed by said parts and is subjected to an internal deformation stress; locking the position of said connection member using a stress-maintaining means (52') with controlled release; and connecting said connection member (40, 40') to each of the parts (10, 12) using attachment means (36, 38), wherein said internal deformation stress is sufficient for disconnecting the connection member (40, 40') from said parts (10, 12) by being deployed into a rest position upon a control for releasing said stress-maintaining means (52').
An expansion tube (15) of a detonating pyrotechnic rupture piece is open next to pre-established rupture zones (12, 13) and, inside said open expansion tube (15) there is disposed a sealed bladder (17) which contains a pyrotechnic fuse (14).
According to the invention, a link is established between the fixed part (4A) and the removable part (4B) of an enclosure (4) in which the second satellite is previously enclosed, said link being such that said removable part (4B) remains attached to said fixed part (4A) when said removable part (4B), initially in a first position for which said enclosure (4) is closed and encloses said second satellite, lies in a second position for which said enclosure (4) is open and able to release said satellite.
The subject of the invention relates to a mandrel (10) for winding fibres which is made at least partially by means of a cellular concrete and to a method of producing a winding tool comprising a mandrel which is produced at least in part using cellular concrete, characterized in that it comprises a step of casting a mandrel (10) or parts of a mandrel which are provided with a housing to accept a winding spindle (11).
The invention relates to a method for triggering at least one detonator provided in the inner space of a plant for the destroying explosive waste from a power source located outside said plant by means of an explosion. According to the invention, the method comprises the following steps: coupling the explosive waste to pyrotechnic elements (5, 6) including at least one electrical detonator (6), the minimum operating voltage of which is no lower than 200 V; electrically connecting the detonator (6) to a power supply circuit of said plant, the detonator (6) being coupled to a grounding member (10) contacting said wall with a resistance of no lower than 50 kOhms; electrically connecting said power supply circuit to a circuit for distributing electric pulses provided by the energy source (11, 13); and said energy source (11, 13) generating an electric ignition signal in the form of electric pulses having a strength of at least 5 A in order to initiate the explosion.
The present invention relates to a device for monitoring the attitude of a satellite (10) using solar pressure, comprising at least two solar generators (14a, 14b) to be arranged on either side of a central body (12) of the satellite (10), and each having one so-called front surface (140) that is exposed to the sun, said device further comprising at least three surfaces (16), the optical properties of which are controllable. The surfaces (16) having controllable optical properties are arranged on vanes (18) connected to the solar generators (14a, 14b), each vane being stationary relative to the solar generator to which it is connected, and such that, when in the operating position, at least two of said surfaces (16) are not parallel when the front surfaces (140) of the solar generators are optimally oriented relative to the sun. The device further comprises a module for controlling the optical properties of each surface (16) having controllable properties. The invention also relates to a satellite (10) comprising said device, and to a method for controlling such a satellite.
- Method and system for piloting a rear-propulsion unit craft - According to the invention, in accordance with a slaving loop, the attitude (θм) of the craft (1) is measured in the vicinity of the rear end (1R) of said craft, then, the orientation (β) of propulsion means (2), orientable with respect to said rear end (1R), is adjusted as a function of said measurement of attitude (θм) in such a way that said craft (1) is stabilized on its flight trajectory.
According to the invention, this piece comprises: a base section piece (1) provided with a projecting longitudinal heel (4) delimiting a longitudinal groove (7); a longitudinal pyrotechnic cord laid in said groove; and a plurality of consecutive section piece portions (2) fixed one after the other to said base section piece (1) by first fixing means (9). Between the consecutive section piece portions (2) are second fixing means (18), distributed along said base section piece (1) and independent of said first fixing means (9), enabling said pyrotechnic cord to be fixed and positioned relative to said base section piece (1).
The invention relates to a method for managing the service policy applied to a black network including a radio link, and to a red network connected to said black network managed by a predetermined set of profiles. 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 corresponds to each level of detected congestion for each domain, wherein said service policy profile is then implemented.
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 (5), each with a footpad (6) at the end thereof, intended for braking the landing impact of the body when coming into contact with the ground and for supporting the body on the ground after landing. The footpads (6) are not coplanar.
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 shifting are restricted to windows which are at least in part contained in a main window of the observation images. Furthermore, said images dedicated to the detection of shifting are captured at a frequency greater than a frequency of the observation images.
H04N 5/232 - Devices for controlling television cameras, e.g. remote control
H04N 5/343 - Extracting pixel data from an image sensor by controlling scanning circuits, e.g. by modifying the number of pixels having been sampled or to be sampled by switching between different modes of operation using different resolutions or aspect ratios, e.g. between still and video mode or between interlaced and non-interlaced mode
31.
NETWORK OF SWITCHES AND PAYLOAD OF TELECOMMUNICATIONS SATELLITE COMPRISING A NETWORK OF SWITCHES
The present invention relates to a network (1) of switches comprising N input accesses and M output accesses, each of said switches comprising four ports and the input and output accesses of the network being ports of connection switches. The network (1) comprises at least one stage (E1,E2) of switches, each stage comprising: - a pair of lines (L1,L2) of switches whose ports are not used as input access or output access of the network, termed "interconnection switches", a line being a series of interconnection switches connected together, - at least two transverse arms linking interconnection switches of different lines, a transverse arm being made up of elements different from those of the other transverse arms, a transverse arm comprising at least two links and a switch, termed the "transverse switch" (ct1,ct2), the connection switches being transverse switches. Furthermore, at least two transverse switches (ct1,ct2) of different transverse arms of each stage (E1,E2) are connection switches of the network (1), and at least one interconnection switch of a line (L1,L2) of a stage (E1,E2) of the network is connected to an interconnection switch of the other line of the same stage or of a line of another stage of the network (1), by a link not comprising any switch, termed an "inter-line link" (IL1, ILx).
The invention relates to a method and equipment for producing a metal liner especially for a composite tank. Said equipment comprises a mandrel embodied as a plurality of mandrel elements (1a, 1b, 1c) for supporting primary parts (2a, 2b, 2c) forming the metal liner.
The invention relates to a vibration isolating device that can be positioned between a structure (10) and a mounting plate (11) carrying equipment, said device comprising a lattice made up of bars, each bar comprising at least one axial actuator (25), the lattice being an active hexapod comprising six identical bars (12) arranged with a regular geometry, the six bars (12) being arranged in such a way that control over the tension-compression forces in each of the six bars (12) provides control over six independent degrees of freedom in terms of forces and moments at the interface between the structure and the equipment so as to achieve effective isolation in all the degrees of freedom of the system. At least one end-fitting of each bar consists of an element (16) made of an elastomeric material (and called an elastomeric element).
F16F 15/08 - Suppression of vibrations of non-rotating, e.g. reciprocating, systemsSuppression of vibrations of rotating systems by use of members not moving with the rotating system using elastic means with rubber springs
34.
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 communication network transmits an identifier of subscription to this service during a phase of registration (3.1; 3.2) in the network. With each service subscription identifier is associated a call identifier for making it possible to call the terminal registered via the network. A system (1.2, 1.3) intended to register at least one terminal (1.4) from among a plurality of terminals (1.3; 1.4) in a telephony network comprises means of dynamic changing of service subscription identifier (3.11, 3.12, 3.13) and of associated call identifier (3.4, 3.5, 3.6), for at least one of said terminals, and means for reregistration (3.15) in said network of each terminal for which the service subscription identifier and the associated call identifier have been dynamically changed.
Detection of the congestion of a link based on an exchange of messages between a sender and a receiver, a sender and several receivers or several senders and a receiver. These items of equipment are connected to the ends of a transmission channel. One of the items of equipment is designated master and the other slaves. These exchanges are aimed at allowing the master to calculate and to compare the bit rate of the data sent and the bit rate of the data received. A divergence in the bit rates calculated is evidence of a congestion of the link. All the exchanges are made within the application layer and therefore do not involve the underlying layers.
According to the invention, a transmitting beacon (4) comprises at least two transmitting current loops (6.1, 6.2, 6.3) which are mutually orthogonal and capable of transmitting electromagnetic waves (5.1, 5.2, 5.3), as well as means (7) for supplying power to said transmitting current loops (6.1, 6.2, 6.3) in series.
G01S 1/10 - Systems for determining direction or position line using amplitude comparison of signals transmitted sequentially from antennas or antenna systems having differently-oriented overlapping directivity-characteristics, e.g. equi-signal A-N type
G01S 3/30 - Systems for determining direction or deviation from predetermined direction using amplitude comparison of signals derived simultaneously from receiving antennas or antenna systems having differently-oriented directivity characteristics derived directly from separate directional systems
G01S 5/02 - Position-fixing by co-ordinating two or more direction or position-line determinationsPosition-fixing by co-ordinating two or more distance determinations using radio waves
The invention relates to a metal friction-fit member for assembling two parts, which comprises, on at least one surface thereof to be placed in contact with one of the parts, a coating of an oxide of said metal produced by treating the member by means of an electrolytic-plasma oxidation process. Said coating has sufficient degrees of roughness and hardness such that, when the member is arranged so as to be clamped between the assembled parts, the shear-force transmission capability is significantly increased without the resulting assembly sliding.
The invention relates to a heat transfer system (34) comprising one main capillary pumped diphasic fluid loop (40) and a secondary capillary pumped diphasic fluid loop (50) suitable for cooling at least one hot source (6), the main fluid loop (40) and the secondary fluid loop (50) comprising one evaporator (404, 504), a vapour pipe (412, 512) capable of conveying the cooling fluid in the vapour state from the evaporator (404, 504) to a condenser (408, 508), a condenser (408, 508) and a liquid pipe (418, 518) capable of conveying the cooling fluid in the liquid state from the condenser (408, 508) to the evaporator (404, 504); characterized in that the cooling fluid of the main fluid loop (40) is in heat exchange with the cooling fluid of the secondary fluid loop (50).
F28D 15/04 - Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls in which the medium condenses and evaporates, e.g. heat-pipes with tubes having a capillary structure
F28D 15/02 - Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls in which the medium condenses and evaporates, e.g. heat-pipes
39.
METHOD AND DEVICE FOR NON-DESTRUCTIVE TESTING OF WIND TURBINE BLADES
The method CND (200) of non-destructive testing of a wind turbine blade (10), comprises a step (201) of stressing the structure of the blade through a modification of a physical characteristic of a fluid filling the hollow interior volume (18) of the blade, a step (202) of observing zones to be tested of the exterior surface (19) of the blade, with the contactless measurement of a physical parameter on points of the exterior surface (19) of the blade and a step (203) of comparing the map of the values of the physical parameter measured with a reference map. A system CND for checking the structural integrity of a wind turbine blade (10) according to the method CND comprises an aerothermic device (40) for modifying the physical conditions, temperature or pressure, of a fluid filling the hollow interior volume (18) of the blade, a device for contactless measurement (50) of a physical parameter, temperature or dimensions, of the exterior surface (19) of the blade, and a device for processing the measurements.
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.
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
Inventor
Aanesland, Ane
Chabert, Pascal
Irzyk, Michael
Mazouffre, Stéphane
Abstract
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 12 and/or 13); and the alternating polarisation potentials of the extraction and acceleration grid (4) are adjusted such that the plasma beam (PB) is at least approximately electrically neutral.
A method (10) for estimating a carrier's movement relative to an environment (20) with respect to which the carrier moves, the carrier having at least one navigation sensor and one vision sensor producing 2D images of the environment installed, The method (10) includes the following steps: i) (12) identifying, in images acquired by the vision sensor, characteristic elements of the images representing characteristic elements of the environment, ii) (14) calculating, based on characteristic elements of a triplet of images acquired at different times, at least one condensed measurement representative of characteristics of the carrier's movement during the acquisition of the triplet's images, iii) (16) estimating the movement by a navigation filter, based on navigation measurements made by the navigation sensor and on the at least one condensed measurement. A computing device for a navigation system of a carrier is also described.
According to the invention, the device (1) comprises a bolt (6) including a locking member (9) which is mounted such that it can slide with respect to a first component (2) and can adopt a locked position in which the locking member (9) retains the second component (3) and an unlocked position in which the locking member (9) releases the second component (2), the transition from the locked position to the unlocked position taking place under the action of pyrotechnic means (5). In addition, a branch (4) that is at least partially deformable under the action of the pyrotechnic means (5) is arranged with respect to the bolt (6) in such a way that the transition from the locked position to the unlocked position takes place by means of the deformation of said branch (4).
The subject of the invention is a tank comprising a tank body (1), a liner (2) and a composite body (3) spooled onto the liner, and at least one mounting (4), wherein the liner (2) and the composite body (3) are adhesively bonded together apart from in an annular joining region (5) between the body of the tank and the mounting, surrounding the mounting.
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.
G01K 7/02 - Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat using thermoelectric elements, e.g. thermocouples
G01K 7/16 - Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat using resistive elements
G01K 1/14 - SupportsFastening devicesArrangements for mounting thermometers in particular locations
G01D 11/30 - Supports specially adapted for an instrumentSupports specially adapted for a set of instruments
46.
SPACE SITUATIONAL AWARENESS SYSTEM FOR NEAR SPACE MONITORING
The invention relates to a space situational awareness system including optical watch systems which are arranged as a network and are suitable for scanning areas of the Earth orbit, in particular the LEO layer, and which are arranged in the form of a mesh at the surface of a planet, characterized in that said system comprises means suitable for acquiring images of objects passing through the areas that are scanned by the optical systems, and calculation means suitable for carrying out a measurement of the position time series of the objects passing through the scanned areas by short fixed-field integration.
The invention relates to an optical system for a watch system for a space watch system, characterized in that said optical system comprises at least one telescope having a field no lower than 5°, and preferably no lower than 10°, which is mounted on a mount that is movable along two axes, wherein said telescope is coupled to an image sensor having a sensitivity suitable for an integration time having an order of magnitude of a hundred milliseconds.
B64G 1/68 - Arrangements or adaptations of apparatus or instruments, not otherwise provided for of meteoroid or space debris detectors
G02B 23/06 - Telescopes, e.g. binocularsPeriscopesInstruments for viewing the inside of hollow bodiesViewfindersOptical aiming or sighting devices involving prisms or mirrors having a focusing action, e.g. parabolic mirror
G02B 17/00 - Systems with reflecting surfaces, with or without refracting elements
48.
METHOD FOR MAKING A SPACE WATCH SYSTEM FOR NEAR SPACE MONITORING
The invention relates to a method for making a space watch system for the LEO areas of the Earth orbit, characterized in that said method comprises a step of providing and arraying stations of optical watch systems on the surface of the planet according to a mesh suitable for providing an efficient daily cycle of the system close to 24h and a selected revisit duration of the observed LEO area.
Recoverable module for propulsion module intended to launch a craft into space, said recoverable module of longitudinal axis (X1), said recoverable module (14) comprising a central body, a propulsive system (8) intended for launching the craft, systems for control and command of the propulsive system, at least one propulsion motor (20) for subsonic flight, lifting surfaces for subsonic flight and a landing gear (30), the lifting surface comprising two substantially plane wings (19a1, 19b1) fixed with respect to the central body, and arranged on either side of the central body of the module and a stabilizer (19a2, 19b2) mounted articulated in rotation on a downstream end of each wing (19a1, 9b1), each stabilizer comprising at least one pair of intrados flaps and extrados flaps mounted articulated on said stabilizer (19a2, 19b2) or any other flap affording a dynamic function.
The invention relates to a polychromatic imaging method, using a picture-taking instrument (1), 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.
The invention relates to an imaging method, including reconstructing a final image (IF) from intensity values inputted by a limited selection of photodetectors (2). One out of every two photodetectors is selected along columns (CDET) and rows (LDET). The final image has a resolution that is double that of a picture within the plane of the photodetectors. With identical resolution, the modulation transfer function is improved relative to an image that would be inputted while using all the photodetectors. Additionally, an image-sensing optical system that is used for an imaging method according to the invention can be of reduced size and weight, having constant resolution and constant modulation transfer functions.
H04N 5/345 - Extracting pixel data from an image sensor by controlling scanning circuits, e.g. by modifying the number of pixels having been sampled or to be sampled by partially reading an SSIS array
H04N 5/372 - Charge-coupled device [CCD] sensors; Time delay and integration [TDI] registers or shift registers specially adapted for SSIS
52.
LASER CAVITY WITH CENTRAL EXTRACTION BY POLARISATION FOR COHERENT COUPLING OF INTENSE INTRA-CAVITY BEAMS
The invention relates to a laser cavity with central extraction by polarisation for coherent coupling of intense intra-cavity beams. The laser cavity (1) according to the invention comprises an extraction unit (7) with central extraction, which divides the laser cavity (1) longitudinally into two functional portions (P1, P2), namely a first portion (P1) including the active components (3), which amplifies the laser beams (4), and a second portion (P2) which performs coherent coupling of the laser beams (4).
H01S 3/23 - Arrangement of two or more lasers not provided for in groups , e.g. tandem arrangement of separate active media
H01S 3/07 - Construction or shape of active medium consisting of a plurality of parts, e.g. segments
H01S 3/106 - Controlling the intensity, frequency, phase, polarisation or direction of the emitted radiation, e.g. switching, gating, modulating or demodulating by controlling devices placed within the cavity
H01S 3/11 - Mode lockingQ-switchingOther giant-pulse techniques, e.g. cavity dumping
H01S 3/08 - Construction or shape of optical resonators or components thereof
H01S 3/082 - Construction or shape of optical resonators or components thereof comprising three or more reflectors defining a plurality of resonators, e.g. for mode selection or suppression
An altimetric measurement device (100) incorporates a LIDAR System (10) and a stereoscopic imaging system (20), which share a single radiation collector (5). Altimetric measurements which are produced by the stereoscopic imaging system may be calibrated by measurements which are produced simultaneously by the LIDAR system. This device makes it possible to propagate the precision of the LIDAR to the measurement span of the stereoscopic imager. In an enhancement of the device, impacts of a radiation implemented by the LIDAR system may appear in additional images which are captured. In this way, sites corresponding to the altimetric measurements of the LIDAR system appear directly in relief maps which are produced by the stereoscopic imaging system.
The invention relates to a satellite having a structure that includes a circular launching interface ring (1) and at least two main planar apparatus-holding walls (5) that are substantially parallel to the axis (A) of the ring (1) and rigidly connected to one another and to the ring (1). Each wall (5) directly bears on the ring (1) by a base (6) of the wall (5), and each wall (5) is rigidly and directly attached to the ring (1) by at least one somewhat point-by-point connection (7) on at least one point or area of tangency or intersection with the base (6) of the wall (5) and the ring (1).
The subject of the invention is a thermal protection material for a surface, which material is made from a mixture comprising a resin, granules of cork and refractory fibres, characterized in that the proportion of granules of cork in the mixture corresponds to a mass percentage of 50 to 80%.
The subject of the invention is a thermal protection material for a surface, which material is made from a mixture comprising granules of cork and a resin forming a binder which furthermore comprises short fibres of a heat resistant material. Preferably the material comprises a phenolic resin or an epoxy resin.
The subject of the invention is a thermal protection material for a surface, which material is made from a mixture comprising a resin, granules of cork and refractory fibres, the proportion of granules of cork in the mixture corresponding to a mass percentage of 50 to 80%, characterized in that the proportion of refractory fibres corresponds to a mass percentage in the mixture of 1 to 11%.
EUROPEAN AERONAUTIC DEFENCE AND SPACE COMPANY EADS FRANCE (France)
ASTRIUM SAS (France)
Inventor
Moliere, Florian
Morand, Sébastien
Douin, Alexandre
Salvaterra, Gérard
Binois, Christian
Peyre, Daniel
Abstract
The subject of the present invention is in particular a device (2) for stressing an integrated circuit (1) comprising an electronic chip (10) mounted in a package (12), said device comprising a source (20) of thermal stress. The device (2) also comprises a thermally conductive coupling member (22) intended to be thermally coupled to the source (20) of thermal stress during the stressing operation. The coupling member (22) comprises an end (220) having a geometry suited to introduction into an aperture having a preset geometry, which is to be produced in the package (12) of the integrated circuit (1) so as to thermally couple a coupling face (222) of this end (220) with a face (102) of the electronic chip (10).
The invention relates to a method of commanding an attitude control system (30) of a space vehicle (10), the attitude of said space vehicle having to be controlled in the course of at least one preparation phase followed by an observation phase in the course of which a picture must be taken. In an attitude control system (30) comprising a manoeuvring subsystem (300) comprising at least one reaction wheel, the method comprises, in the course of the at least one preparation phase, a preparation step (50), in the course of which the manoeuvring subsystem (300) is commanded so as to control the attitude of the space vehicle (10), followed by a step (55) of stopping the at least one reaction wheel prior to the said observation phase. Furthermore, in the course of the observation phase, a fine control subsystem (310), of smaller vibratory signature than that of the manoeuvring subsystem (300), is commanded so as to control the attitude of the space vehicle (10). The invention also relates to an attitude control system (30) of a space vehicle (10).
The thermal control device for radiative dissipation equipment comprises: first means, for capturing at least some of the radiation emitted by the dissipative equipment within at least one predetermined wavelength range of the infrared spectrum; second means, for emitting radiation in at least one wavelength range; means for transporting heat over a distance between the first and second means. Application in particular to thermal control for a travelling wave tube of the type with a radiating collector, said tube having a collector extending to the outside of the walls of a vehicle intended to operate in a high-vacuum environment, the collector being fastened to a finned cooler. The invention also relates to a method of operating the device.
The invention relates to a device for controlling the temperature of an apparatus for dissipating heat by means of radiation, comprising means for reversibly filtering a portion, included between two predetermined end values, of the radiation emitted or received by the dissipating apparatus in at least one wavelength range, and means for controlling said selective filtering means. The dissipating apparatus is typically a travelling-wave tube (5) including a radiating collector, said tube (5) comprising a collector (6) projecting outside of the walls (2, 3) of equipment placed in a high-vacuum environment, the collector (6) being rigidly connected to a cooler (7) radiating toward the outside of the vehicle, while the filtering means comprises a screen (13) arranged around at least a portion of the solid angle of radiation of the cooler (7) radiating toward the outside of the equipment. The invention also relates to a method for driving the device.
A permanent-magnet electric motor (1) comprises a rotor (4) to which permanent magnets (6) and a stator (2) are fixed. The stator comprises a stator structure and windings (5) arranged on the stator structure. The stator structure is formed by a set of at least three independent stator elements (21) assembled on a base (3) with no direct mechanical connection between them. Each stator element (21) is fixed to the base (3) of the motor by an adjusted fastening element (31) and at least one antirotation element (32). Preferably the stator elements (21) are made of an electrically insulating material that is a good heat conductor, such as a ceramic.
H02K 21/22 - Synchronous motors having permanent magnetsSynchronous generators having permanent magnets with stationary armatures and rotating magnets with magnets rotating around the armatures, e.g. flywheel magnetos
H02K 21/14 - Synchronous motors having permanent magnetsSynchronous generators having permanent magnets with stationary armatures and rotating magnets with magnets rotating within the armatures
H02K 3/47 - Air-gap windings, i.e. iron-free windings
H02K 16/02 - Machines with one stator and two rotors
63.
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 reception characteristic (S1) 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 (S2) to be taken into account in real time when said laser signals pass through part of the earth's atmosphere (AT).
The invention relates to a travelling-wave tube (5) of the type including a radiating collector, in which the tube (5) comprises a collector (6) that extends externally beyond the walls (2, 3) of a device placed in a high-vacuum environment and is solidly connected to a radiant cooler (7) outside the device. According to the invention, the tube includes a removable emissive screen (8') attached to the radiant cooler (7) of the collector substantially at the part thereof intended to be positioned closest to the wall of the device following the installation of the tube inside the device. The external face of the aforementioned screen comprises a coating having a sufficiently high emissivity ratio in the infrared/solar absorptivity range in order to contribute to the cooling of the radiator by a value above a pre-determined threshold.
According to the invention, said device (1) comprises two substantially parallel flanges (4, 5) which are provided with rupture areas (16, 17), respectively, located in the same element (2) of the elements (2, 3) to be connected. In said device, the rupture areas (16, 17) and the portions (18, 19, 21) of the flanges outside the rupture area are arranged so as to prevent the connected elements (2, 3) from catching after the separation thereof, and to limit the vibrations induced in the element (2) in said rupture areas (16, 17).
a) of a microporous mass provided in the outer tube and pumping by capillarity a liquid-phase heat-carrier fluid flowing in the insulating sleeve of the condenser towards the evaporator, while the gaseous-phase fluid flows from a vapor-collecting central duct in a second portion of the mass of the evaporator towards the condenser in a duct inside said outer tube. The invention can be used for the thermal energy transfer from an electronic component or circuit defining a heat source in relation with the evaporator to a cold source in relation with the condenser.
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; 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.
The invention relates to a method for producing a composite mirror. Said method comprises the steps of providing a glass blank having a low expansion coefficient, machining a convex shape (4) into the glass blank, draping a front skin (6) impregnated with resin over the convex shape (4) of the glass blank (2), machining a concave shape matching the convex shape machined into glass blank (2) into a rear supporting structure (8), adhering the concave shape (10) of the supporting structure (8) to the convex shape of the glass blank (2), machining a convex shape on the supporting structure, draping a rear skin (14) impregnated with resin onto a mold, adhering the rear skin (14) to the convex shape of the supporting structure (8), turning over the assembly such that the blank (2) is situated at the upper portion of the assembly, and machining and polishing a mirror in the glass blank (2).
G02B 7/183 - Mountings, adjusting means, or light-tight connections, for optical elements for prismsMountings, adjusting means, or light-tight connections, for optical elements for mirrors for mirrors specially adapted for very large mirrors, e.g. for astronomy
The system (1) comprises terminals (2) that are mounted onto a predetermined number of feeder vessels, comprises means (6, 7) for detecting identification signals sent by surrounding ships, and moreover comprises means (10, 13) for recording identification information that include the detected identification signals and the current position of the feeder vessel. Said system also comprises a system (3) for transmitting data via satellites (4), said data transmitting system making it possible to transmit data between the terminals (2) and a monitoring center (5), said monitoring center (5) including a means (21) for generating requests intended for the terminals (2) in order to ask said terminals to provide the recorded identification information. Said monitoring center also includes a means (23) for analyzing the received identification information.
G01S 5/00 - Position-fixing by co-ordinating two or more direction or position-line determinationsPosition-fixing by co-ordinating two or more distance determinations
70.
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.
EUROPEAN AERONAUTIC DEFENCE AND SPACE COMPANY - EADS FRANCE (France)
Inventor
Prampolini, Marco
Coraboeuf, Yohann
Abstract
The invention relates to an ultra-rapid air vehicle and to a method for aerial locomotion provided by an ultra-rapid air vehicle. The air vehicle is propelled by an engine system consisting of jet engines (TB1, TB2), ramjet engines (ST1, ST2), and a streamlinable rocket engine for reducing the base drag in cruise phase. The air vehicle has a gothic delta wing (A) provided with winglets (a1, a2) that are movable to the two outer ends of the trailing edge of the delta wing (A).
RECONFIGURABLE INVERTER HAVING FAILURE TOLERANCE FOR POWERING A SYNCHRONOUS POLY-PHASE MOTOR HAVING PERMANENT MAGNETS, AND ASSEMBLY INCLUDING SAID INVERTER AND MOTOR
The invention relates to a reconfigurable inverter having failure tolerance for powering a synchronous poly-phase motor having permanent magnets, and to an assembly including said inverter and said motor. The inverter includes: N switching cells (B1, B2, B3) including switching devices (B11 to B 32) and insulating devices (S11 to S33) where N is the number of phases of the motor (N≥3); at least one redundancy cell (R); a supervisor (12) for detecting an operation dysfunction of the inverter leading to the motor stop (14), resulting from a failure of one of the N cells and leading to a defect in one of the phases of the motor. Each switching device notifies the supervisor of a short-circuit affecting the device, and the supervisor monitors the integral value of the absolute value of the current in the faulty phase.
H02M 7/48 - Conversion of DC power input into AC power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode
H02H 7/122 - Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for convertersEmergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from normal working conditions for rectifiers for static converters or rectifiers for inverters, i.e. DC/AC converters
73.
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 who are substantially located on the surface of a celestial body, includes: a plurality of transmitting/receiving surface terminals that each correspond to a user; one or more geostationary means located onboard satellites that are placed in geostationary orbit around said celestial body, said geostationary means being capable of transmitting data from and to a predetermined coverage area on the surface of the celestial body with a view to the geostationary satellite; and one or more signal repetition means for the signals transmitted and/or received from the geostationary means to the surface terminals. Said traveling repetition means are located onboard satellites that move in a traveling orbit, a single frequency band being used for the communications between the surface terminals and the traveling means as for the communications between the traveling means and the geostationary means.
The present invention relates to a method for calibrating a transmission format selection threshold, from a plurality of transmission formats, in order to exchange data packets over a radiofrequency propagation channel, referred to as the "channel" (L1,L2,L3), between a transmitting device and a receiving device of a satellite telecommunications system, said method being characterized in that it comprises: a step (30) of calculating a calibration table for the threshold which associates transmission statistics, representative of an amount of estimated errors for a plurality of data packets received by the receiving device, with a plurality of values of the instantaneous quality of the channel, and a step (40) of updating the threshold, which, according to the calibration table, is a value of the instantaneous quality of the channel enabling a predefined value of the transmission statistics to be provided. The present invention also relates to a threshold calibration module which can be included in a terrestrial terminal (2), and/or a satellite (3), and/or more generally speaking in a satellite telecommunications system.
The invention relates to a method for estimating the movement of an observation instrument (10) on-board a vehicle flying over a celestial body, the observation instrument (10) comprising at least two bars (b1, b2) the lines of sight of which are different, each bar acquiring consecutive line images forming a composite image, portions of the composite images representing substantially a single scene of the celestial body. The estimated movement is determined by means of optimizing an image resemblance function which associates a resemblance between matching pixel values of at least one pair of composite images with a given movement hypothesis, and, for each movement hypothesis considered during optimization of the image resemblance function, the method comprises the steps (200) of determining at least one space-time transformation for the at least one pair of composite images on the basis of the movement hypothesis in question and a geometric model of the observation instrument (10), and (201) matching the pixels of at least one pair of composite images by means of the at least one space-time transformation.
The flying vehicle comprises a means (4) that is capable of moving the jet nozzle (1) in the absence of propulsion so as to generate inertial forces for stabilizing the vehicle.
B64G 1/28 - Guiding or controlling apparatus, e.g. for attitude control using inertia or gyro effect
B64G 1/38 - Guiding or controlling apparatus, e.g. for attitude control damping of oscillations, e.g. nutation dampers
B64G 1/10 - Artificial satellitesSystems of such satellitesInterplanetary vehicles
F02K 9/84 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof characterised by thrust or thrust vector control using movable nozzles
77.
INCREASE IN THE TOUGHNESS OF A MATERIAL ACHIEVED BY MEANS OF A CURABLE COMPOSITION INCLUDING AT LEAST ONE VINYL ESTER MONOMER
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
Inventor
Krzeminski, Mickael
Defoort, Brigitte
Coqueret, Xavier
Abstract
The invention relates to a method for increasing the toughness of a material achieved by means of curing a composition including at least one vinyl ester monomer. Said method includes incorporating a sulfonated polyaromatic thermoplastic polymer into said composition, carried out by dissolving the vinyl ester monomer and the thermoplastic polymer in a reactive diluent in which both are soluble. The invention also relates to a curable compound including at least one vinyl ester monomer and enabling the production of materials having a very high toughness, as well as to a material obtained by curing said composition. The invention can be used in the aeronautical, space, railroad, naval, automobile, and arms industries, etc.
C09J 4/06 - Adhesives based on organic non-macromolecular compounds having at least one polymerisable carbon-to-carbon unsaturated bond in combination with a macromolecular compound other than an unsaturated polymer of groups
C09J 163/10 - Epoxy resins modified by unsaturated compounds
The invention relates to a system for measuring the traveling speed of a mobile element (10), including means for forming an interference between two portions of a radiation beam. Each beam portion (F1, F2) is reflected by a separate mirror (1, 2), at least one of which is connected to the mobile element. A modulation is further applied to an initial intensity (A0) of the radiation beam during the movement of the mobile element. A spectral analysis of an interference detection signal then provides a direct measurement of the traveling speed of the mobile element.
The invention relates to a method for detecting shifts in line images obtained by a sensor that is airborne or moving in space. 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 different portions of a scene on the surface (S) of a celestial body, sequentially acquired by a row of sensitive cells of a sensor (10) on-board a vehicle flying over said celestial body. The shifts in the line images are induced by sighting errors of the sensor (10) during the acquisition of the line image Lj. According to the invention, the lateral and/or longitudinal shift of a line image Lj, relative to a line image Li, where j is different from i, is determined according to a local model of lateral and/or longitudinal variation of the similarity between different line images. The invention also relates to a method for forming composite images using line images with shifts.
G01C 21/16 - NavigationNavigational instruments not provided for in groups by using measurement of speed or acceleration executed aboard the object being navigatedDead reckoning by integrating acceleration or speed, i.e. inertial navigation
80.
DEVICE FOR ASSEMBLING SECTIONS OF WIND-TURBINE BLADES AND METHOD FOR LINKING SECTIONS OF WIND-TURBINE BLADES
The invention relates to a device for assembling sections (1) of wind-turbine blades provided with casings (2), including at least one tie (3, 30) comprising a first portion (3a, 30a) and a second portion (3b, 30b), the first portion being a portion for assembly with a casing (2) 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, characterised in that the first portion (3a) includes at least one composite/metal shear link provided with a continuous fitting element (4) on at least one surface (2a) of the casing (2) which receives one end of said surface of the casing, provided with attachment pins (6) 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 (5), the end of said surface of the casing being received between the fitting and the back fitting, the attachment pins (6) passing through the fitting, the end of the surface and the back fitting, the link also being provided with a means (7, 8, 9, 10, 11) for attaching the back fitting to the fitting.
F16B 17/00 - Fastening means without screw-thread for connecting constructional elements or machine parts by a part of or on one member entering a hole in the other
L'objet de l'invention est un procédé de dimensionnement d'une liaison mécanique à multi-cisaillements caractérisé en ce qu'on réalise une liaison à multi-cisaillements, on décompose le système constitué par la liaison en autant de sous ensembles qu'il y a d'interfaces de cisaillement simples, on définit les sous ensembles autour de chaque interface de cisaillement, on applique la méthode de Huth à chaque interface de cisaillement et on calcule en chaque point l'état de contrainte de chaque cisaillement en fonction de ses spécificités matériau, module, épaisseur.
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.
B64G 1/28 - Guiding or controlling apparatus, e.g. for attitude control using inertia or gyro effect
83.
VIRTUAL POLAR SATELLITE GROUND STATION FOR LOW ORBIT EARTH OBSERVATION SATELLITES BASED ON A GEOSTATIONARY SATELLITE POINTING AN ANTENNA OVER AN EARTH POLE
The invention relates to a satellite system comprising a satellite operating in an orbit around the Earth and a satellite operating in another orbit around the Earth; where the satellite points a fixed beam at least temporarily to a zone above the Earth's surface through which the satellite passes.
The invention relates to a system and to a method for testing devices using powders such as propellants. The system is suitable for performing tests on functional subunits and includes a confining chamber (1) provided with a means for sealing said chamber and a gas-treatment unit (6), the chamber and the gas-treatment unit being connected by a controllable gas-conveying means (5, 7, 8) in the form of a controlled leak so as to extract a gauged flow of gas from the tests of the chamber (1) to the treatment unit (6).
F02K 9/96 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof characterised by specially adapted arrangements for testing or measuring
85.
DEVICE FOR GENTLE LINEAR SEPARATION OF A FIRST PART AND A SECOND PART
The invention relates to a device (12) for linear separation of a first part (2) and a second part (4). The first part is linearly connected to the second part (4). The device comprises a heat source (12) applied to the first part (2), which applies a heat stimulus to the first part (2) such as to separate the first part (2) from the second part (4) by thermal deformation of the first part (2).
According to the invention, the system (1) includes a plurality of liquid-hydrogen-producing balloon stations (2A, 2B, 2C, , 2n) that form a total network for distributing liquid hydrogen to target areas (Z) using said liquid hydrogen, and said balloon stations (2A, 2B, 2C, ..., 2n) in the network are positioned at the nearest of said target areas (Z) of use, substantially above the latter, such that the transfer of the liquid hydrogen between said production balloon stations and said target areas of use is minimal.
C01B 3/06 - Production of hydrogen or of gaseous mixtures containing hydrogen by reaction of inorganic compounds containing electro-positively bound hydrogen, e.g. water, acids, bases, ammonia, with inorganic reducing agents
87.
LANDING SYSTEM FOR A BODY AND SPACE PROBE PROVIDED WITH SUCH A SYSTEM
The invention relates to a landing system of a body and a space probe provided with such a system for landing on a bearing ground. Said landing system includes landing legs (5), each with a footpad (6) at the end thereof, intended for braking the landing impact of said body when coming into contact with the ground and for supporting said body on the ground after landing. According to the invention, said footpads (6) are not coplanar.
The invention relates to a device for temporary connection with a longitudinal axis (X) and for pyrotechnic separation, including a pyrotechnic expansion tube (14) mounted in a space (11) arranged in a connection area between a first (2) and a second (4) assembly to be separated, the second assembly (4) consisting of a stack of layers (12.1, 12.2) adhered to one another, the two assemblies (2, 4) being connected together by two metal parts (10.1, 10.2), said metal parts being attached to the first assembly and adhered to the outer layers (12.1) of the second assembly (4), wherein the adhesion surface between said outer layer (12.1) and the adjacent inner layer (12.2) is smaller than the adhesion surface between two inner layers (12.2) forming a fusible layer, such that, when the pyrotechnic expansion tube (14) is used, the outer layer (12.1) separates from the adjacent inner layer.
The invention relates to a system comprising a mother probe forming a carrier space vehicle (1) and a plurality of daughter probes (2a, 2b, 2c) aligned in a longitudinal axis (A) of the mother probe, in which the attachment of the daughter probes to the mother probe is carried out by means of a plurality of probe-supporting annular segments (5a, 5b, 5c) each provided with an annular collar (3a, 3b, 3c) for attaching a daughter probe.
The invention relates to a radio antenna (20, 52), especially for a spacecraft, comprising a reflector (22), a rear structure (24) supporting said reflector, and a rigidifying membrane (48) attached to the reflector (22) in such a way as to limit the displacement of a peripheral portion (38) of the reflector in a direction parallel to a central axis (28) of said reflector (22), said rigidifying membrane (48) being separate from the rear supporting structure.
H01Q 15/16 - Reflecting surfacesEquivalent structures curved in two dimensions, e.g. paraboloidal
H01Q 19/12 - Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces wherein the surfaces are concave
The invention relates to a radio antenna (20) for a spatial satellite, comprising a reflector and means for supporting said reflector. The reflector comprises a front skin (22) for reflecting radio waves, a rigid rear structure (24) carried by the supporting means, and an elastic material layer (28) inserted between said front skin (22) and said rigid rear structure (24), for absorbing the vibrations of the front skin (22).
The invention relates to a radio antenna, especially for a spacecraft, comprising a reflector (20) and means for supporting said reflector. The reflector (5) comprises a shell (22) for reflecting the radio waves, and a rigid rear structure (28) carried by the supporting means and connected to the shell (22) by decoupling angles (24). Said antenna is characterised in that each decoupling angle (24) comprises, on at least one of its ends, a layer of plastic material (38) that can absorb at least one axial vibration component of the shell (22).
F16F 15/08 - Suppression of vibrations of non-rotating, e.g. reciprocating, systemsSuppression of vibrations of rotating systems by use of members not moving with the rotating system using elastic means with rubber springs
According to the invention, said apparatus is altitude-adjustable and comprises: a platform (2); a device (3) for controllably raising the altitude of the platform; a water supply (4) combined with said platform (2); a device (5) for converting water into the components thereof through solar power; and a means (6) for liquefying and storing the resulting liquefied hydrogen in tanks (16), the latter being built into flying bodies (20) that are designed to arrive at a target area and dispense the liquefied hydrogen.
The invention relates to a space probe (1) that comprises a descent module with a mobile exploration vehicle (3), characterised in that the descent module is a landing module (2) 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.
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
Inventor
Defoort, Brigitte
Coqueret, Xavier
Mille, Marion
Abstract
The present invention relates to the use of curable resins containing a glycidyl (meth)acrylate prepolymer for the production of composite materials for use in space and, more particularly, composite materials used to form structures intended to be deployed in space and to become rigid after deployment.
The invention relates to a method for detachably gluing at least one porous substrate to another material using at least one layer of a detachable adhesive comprising an ungluing admixture adapted for generating gases which, by gas expansion or gas migration towards at least one of the interfaces of the detachable adhesive layer, weakens the adhesive bond when heated by a detaching control, said method comprising, before gluing, applying a metal sealing coating onto at least one of the substrates.
C09J 5/02 - Adhesive processes in generalAdhesive processes not provided for elsewhere, e.g. relating to primers involving pretreatment of the surfaces to be joined
C09J 5/06 - Adhesive processes in generalAdhesive processes not provided for elsewhere, e.g. relating to primers involving heating of the applied adhesive
The invention relates to a propulsion module for launching a vehicle into space comprising a reusable module (14), as well as an expendable portion (16) rigidly connected to the reusable module (16) during the launch, said reusable module (14) comprising a propulsion system (8) for launching the vehicle, said reusable module (14) and said expendable portion (16) being intended to separate when the propulsion module reaches a given altitude, the reusable module (14) being suitable for landing in a controlled fashion following a conventional flight, for example for a return to the launch site.
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.
H04B 10/00 - Transmission systems employing electromagnetic waves other than radio-waves, e.g. infrared, visible or ultraviolet light, or employing corpuscular radiation, e.g. quantum communication
99.
SYSTEM IN SPACE FOR REINFORCING PHOTOSYNTHESIS AND METHOD
The invention relates to a system in space for reinforcing photosynthesis on earth, comprising a satellite (2) with at least one first optical assembly (3) intended for collecting sunlight, the position of which is stationary; a second optical assembly (6), smaller in size and with less inertia than the first optical element (3), intended for retransmitting the collected light with higher density of the retransmitted flux density than the collected flux density, and with an adjustable orientation; a remotely controllable means capable of adjusting the orientation of the second optical assembly (6); and a light-transmitting means (10) which transmits the collected light from the first optical assembly (3) to the second optical assembly (6). The second optical assembly retransmits light only in specified frequency bands around 450nm and 660nm.
The thermal control device comprises at least one network (30) of capillary heat pipes (31), in which each heat pipe (31) 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 vapour phase. The tubes of at least two heat pipes (31) of the network (30) intersect and are interconnected in such a way that at each intersection of heat pipes (31) forming a node (36, 37, 38) of the network (30), 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 (31), and such that, simultaneously, an exchange of fluid in the vapour phase can take place by free circulation between the central channels of said two or more heat pipes (31).
F28D 15/02 - Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls in which the medium condenses and evaporates, e.g. heat-pipes
F28D 15/04 - Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls in which the medium condenses and evaporates, e.g. heat-pipes with tubes having a capillary structure
