Abstract: 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.

Abstract: The invention relates to a method for producing a non-developable surface printed circuit and to the thus obtained printed circuit. According to the invention, each electrically conductive pattern of a printed circuit includes at least one base, which is arranged on the non-developable surface and obtained by projecting an electrically conductive varnish, and a coating, which is arranged on the base and made of an electrically well conductive material by buffer electrolysis.

Abstract: A method for controlling an attitude control system (30) for a space vehicle (10), the attitude of the space vehicle being controlled during at least one preparation phase followed by an observation phase during which an image capture is performed. In an attitude control system that includes a maneuvering subsystem (300) which includes at least one reaction wheel, the method includes, during the at least one preparation phase, a preparation step (50), during which commands are issued to the maneuvering subsystem in order to control the attitude of the space vehicle, followed by a step (55) of stopping the at least one reaction wheel prior to the observation phase. In addition, during the observation phase, a fine control subsystem (310) having a lower vibration signature than that of the maneuvering subsystem, is sent commands in order to control the space vehicle's attitude. An attitude control system for a space vehicle is also described.

Abstract: The subject of the invention is a device for driving a pump of a rocket engine of a space vehicle that comprises an air-breathing internal combustion engine running on an oxidizer/fuel mixture of the air/hydrocarbon type, wherein the supply of oxidant and fuel is provided by tanks and a circuit that are separate from the propellant tanks of the rocket engine. The invention applies to a device for fueling a rocket engine that includes at least two pumps, each driven by the device of the invention, and means for controlling the internal combustion engines for driving the pumps, adapted for independently varying the operating parameters of these engines so as to independently adjust the rotation speeds of the pumps.

Abstract: 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.

Abstract: An electric motor (1) with permanent magnets includes a rotor (4), on which permanent magnets are fastened (6), and a stator (2). The stator includes a stator structure and coils (5) installed on the stator structure. The stator structure is realized by an assembly of at least three independent stator elements (21), assembled on a baseplate (3) with no direct mechanical linkage between them. Each stator element (21) is fastened onto the baseplate (3) of the motor by an adjusted fastener (31) and at least one anti-rotation element (32). Preferably, the stator elements (21) are made of a material that is a good heat conductor and electrical insulator, such as a ceramic.

Abstract: 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.

Abstract: A device for generating impacts on a structure has a projectile head. The head includes a main body on which an impact element is mounted so it projects. The device includes a mechanical propulsion element to set the projectile head in motion, and the propulsion element can move between an initial resting position where the propulsion element is immobile and the projectile head is held against the propulsion element by at least one retaining element, and a second position where after the propulsion element comes to a stop against stop elements, the projectile head moves alone in translation toward the structure guided by guidance elements. The device also includes an anti-rebound system to prevent any rebound by the projectile head after impact on the structure.

Abstract: The invention relates to a process for improving the adhesion of carbon fibers by coating a surface of the carbon fibers with a polymer film containing functional groups capable of acting as chain transfer agents during a chain transfer polymerization of a resin curable by chain transfer polymerization to obtain coated carbon fibers. The coated carbon fibers are then contacted with the curable resin, and the chain transfer polymerization of the curable resin is induced to produce an organic matrix and forming a composite material. The functional groups of the polymer film act as chain transfer agents during the chain transfer polymerization of the curable resin and thereby improve adhesion of the carbon fibers to the organic matrix. Applications of this invention include aeronautical, aerospatial, shipbuilding, railway and motor vehicle industries, armaments industry, sports and leisure articles, and the like.

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

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

Abstract: 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.

Abstract: 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.

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

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

Abstract: 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 (TB1, TB2), ramjets (ST1, ST2) and a rocket motor which can be made streamlined to reduce the drag of the base during the cruise phase, and where the vehicle has a gothic delta wing (A) fitted with moving fins (a1, a2) at both outer ends of the trailing edge of the delta wing (A).

Abstract: Reconfigurable fault-tolerant inverter for powering a multi-phase synchronous permanent-magnet motor, and assembly of the said inverter and motor. The inverter includes: N switching cells (B1, B2, B3) including switching devices (B11 to B32) and isolating 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) to detect an operating anomaly of the inverter, leading to a stoppage of the motor (14), resulting from a failure of one of the N cells and causing a fault of one of the phases of the motor. Each switching device informs the supervisor of a short circuit affecting this device, and the supervisor supervises the integral value of the absolute value of the current in the defective phase.

Abstract: The invention relates to a process for improving the adhesion of carbon fibres with regard to an organic matrix forming a composite material with these fibres, this composite material being obtained by bringing the fibres into contact with a resin which can be cured by chain polymerization and then polymerizing the resin, which process is characterized in that it comprises the grafting, to the surface of the fibres, before they are brought into contact with the resin, of groups capable of acting as chain transfer agents during the polymerization of said resin. Fields of application: aeronautical, aerospatial, railway, ship building and automobile industries but also the armaments industry, the industry of sports and leisure articles, and the like.

Abstract: 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.

Abstract: 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: a plurality of transmitting/receiving surface terminals, each associated to a user, one or more geostationary element installed on board satellites placed in geostationary orbit around the celestial body, these geostationary elements being able to transmit data from and to a predefined coverage area on the surface of the celestial body with a line of sight to the geostationary satellite, and one or more signal repetition element for the signals transmitted and/or received from the geostationary elements to the surface terminals these traveling repetition elements being on board satellites moving in a traveling orbit; the same frequency band is used for communications between the surface terminals and the traveling elements and for communications between the traveling elements and the geostationary elements.