Abstract: A mobile craft is guided with respect to a trajectory. To guide the craft, the distance xtk is determined between the mobile craft and the point of orthogonal projection of the mobile craft on a segment of the trajectory. The angle tkae is determined between the direction of travel of the mobile craft and the direction at the point of orthogonal projection. A control value is computed for the lateral attitude from the distance and angle, two characteristic coefficients and a nominal control value. This control value is applied to the craft.

Abstract: The present invention relates to a method and to a system for producing a reinforcement for a composite component, formed by said reinforcement embedded in a cured matrix, said reinforcement comprising superposed plies of thread. According to the invention, the system comprises means (5) for the memory storage and processing of data, in which means the mathematical model of the reinforcement (A) to be produced may be created and stored in memory and which are capable of controlling means (3) for steering the tool (1) for laying down and/or stitching thread (F).

Abstract: A system for controlling the tab (6) of an aircraft control surface (3) having a pair of position sensors (12 and 15) that supply information regarding the turning of the control surface (3) and the position of a jack (13), respectively, on the basis of signals generated by the sensors (12 and 15) as well as possibly on the basis of at least one parameter (p) originating from the aircraft, such as airspeed, positions of lift-augmenting devices, forces exerted by the pilot on a control, etc., and which formulates a command for the jack (13).

Abstract: In order to ensure transmission of low amplitude back-and-forth movements between, for example, the non-aligned control member (46) of an actuator (42) and the sealing flap (34) of a valve, a lever (30) mounted on a body (10) by means of a flexible strip (32) is used. Said flexible strip lies in the longitudinal axis of the lever (30) and is fastened inside a tubular section (22) of the body (10) at two diametrically opposed points. The sealing flap (34) is fitted to one end of the lever (30) and the control member (46) actuates the other end of the lever.

Abstract: A fuel injection stub (6) for a ramjet is intended to operate at a high Mach number. According to the invention, the nose of the stub is formed by a thermally conductive thin wall (11) having at least approximately the shape of a dihedron, the angle of said dihedron being at most equal to 15.degree. and the radius of the leading edge (11A) of said nose being at most equal to 2 mm, and said stub includes means (23, 27) for injecting a coolant into the sealed chamber (18), said injection means producing a number of jets of pressurized coolant striking the concave face of said thin wall.

Abstract: The present invention relates to a system for coupling at least two control columns (2A, 2B) of a control device (DC) of a machine, especially an aircraft. The coupling system includes for each of the columns (2A, 2B), at least one operating member (13A, 13B, 14A, 14B) capable of making the column (2A, 2B) tilt about an axis, and a calculation unit (CAL) receiving information relating to the position of tilt of the columns (2A, 2B) and generating, when at least one of the columns (2A, 2B) is operated, tilt commands which are transmitted to the operating member (13A, 13B, 14A, 14B) of the other column (2A, 2B).

Abstract: A ramjet for supersonic and/or hypersonic aircraft, designed to operate over a wide range of speeds, includes an inlet for a combustion supporting gas; a fuel injection device; and a ramjet body. The ramjet body has a combustion chamber in which the combustion supporting gas is mixed with a fuel to be burned and an exhaust nozzle to channel gases leaving the combustion chamber and which has, at least in a transition area between the combustion chamber and the exhaust nozzle, a variable geometry enabling its longitudinal section to be progressively modified. The ramjet body has at least one controllable opening adapted to establish communication between the combustion chamber and the exterior to enable the introduction of an exterior air stream into the transition area.

Abstract: A process for the production of a panel, of the honeycomb support type clad on opposite sides with a skin of carbon/carbon or carbon/ceramic composite. A honeycomb support is produced by pyrolysis of a carbon cloth pre-impregnated with a thermosetting resin. Skins are produced from carbon cloth pre-impregnated with a thermosetting resin. The support and the skins are assembled with a carbon cloth pre-impregnated with a thermosetting resin between them. The assembly is polymerized and then pyrolyzed. Finally, a chemical infiltration in vapor phase is carried out for densification and reinforcement of the bonding of the assembly. Used in the production of structures requiring very high dimensional stability, such as those used in outer space.

Abstract: A process and device for damping vibrations or preventing their appearance in aircraft airframes in transonic flight. The aircraft has a fuselage carrying on each side a fixed wing (7) provided with at least one propulsion motor. At least one wing (7) is provided with an additional fixed weight (12-14) so arranged that there is more added weight on one side of the aircraft than on the other, the weight being disposed within the volume delimited by the wing (7). Different weights can be added to opposite sides of the aircraft, or all the added weight can be concentrated in one wing, the weight is as close to the end of the wing as possible, beyond the motor or outermost motor of the aircraft.

Abstract: A method for producing a sandwich-type panel with structural and acoustic properties and formed of a core with an open cellular structure. The method includes the steps of forming first and second skins by superimposing and hot-pressing at least two fabric plies of mineral or synthetic fibers impregnated with a thermoplastic resin, of forming in one of the skins perforations with a diameter of between about 0.5 and 1.5 mm, with a vacuum proportion of empty spaces on the surface of the skin of between about 10 and 25%, of after preparation of the skins applying on one face of the skins an epoxy adhesive coating, of forming a sandwich including the open cellular structure with the two skins on its opposing faces, and then of hot-pressing the sandwich at an appropriate temperature so as to polymerize the adhesive. During hot-pressing the pressure and duration are set so as to avoid any full or partial obstruction of the perforations of the perforated skin.

Abstract: An automatic device for maintaining an aircraft at an authorized speed compatible with the technical capabilities of the aircraft includes:a system for comparing the effective speed of the aircraft with reference speeds defined in accordance with the technical capabilities of the aircraft,a system for calculating, on the basis of such comparison, modified control values to align the effective speed with these reference speeds, anda system for imposing one of these calculated values on the aircraft, if this is necessary to maintain the aircraft at an authorized speed.

Abstract: The invention relates to compositions of ionization-setting maleic resins and their use for manufacture of composite materials with a fibrous reinforcement. These compositions comprise a maleic resin and a reactive diluent made up of at lest one compound chosen from among dipentaerythritol pentacrylate and hydroxyethyl methacrylate, the total quantity of reactive diluent being between 10 and 70 parts by weight per 100 parts by weight of maleic resin. They may also comprise a plasticizer such as bis-allylic resin. With these compositions it is possible to obtain composite materials set by ionization without additional post heat treatment.

Abstract: An element made of a reinforced low density heat protective material including an elastomer and/or a silicon resin matrix loaded with organic and/or inorganic components, wherein the reinforcement is formed of glass or ceramic thread sections or the like or organic materials fitted in the mass of the matrix along directions approximately orthogonal to at least one of the faces of the element and being flush, at least at one of their extremities, with at least one of the faces. The method for obtaining this element, includes, after molding to the general dimensions and shapes of the element with the aid of a loaded silicon matrix, placing the thread sections by stitching.

Abstract: A device and a process for detecting the movement of a target observed in the field of view of an optical detector in which a differential image is determined from two successive pictures of the field of view, a binary image is formed from the differential image and from a binary conversion threshold, moving zones in the binary image are individualized, individual envelopes surrounding the zones are determined, an overall envelope surrounding the individual envelopes is determined, and it is determined whether there is movement of the target from the individual envelopes and the overall envelope.

Abstract: A method and apparatus for real time control of the dose rate of particles or ionizing radiation, especially X-ray radiation, generated from an electron linear gun and applied to objects for various purposes. The method involves sampling continuously, using an appropriate ionization chamber having planar electrodes, placed in the field of particles or ionizing radiation, the current for collecting the load between the electrodes. Thus, the instantaneous does rate of the radiation is represented by the collecting current. Using an appropriate shielded conducting system, the collecting current is directed to an amplification and measurement circuit arranged outside of the irradiation zone. The intensities of the current are translated into dose rate values. The does rate values are then processed and/or displayed and/or recorded. The invention can be applied to the polymerization of resins of composite materials.

Abstract: A magnetic actuator, for example a magnetic bearing, embodies a fixed part and a mobile part. These parts are ferromagnetic and form an airgap between them extending parallel to a predetermined first direction. The magnetic actuator further embodies a nonmagnetic wall interposed in the airgap. The wall is that of a confinement chamber, for example. In this magnetic actuator one of the fixed and mobile parts embodies fingers penetrating the nonmagnetic wall and directed towards the other of the fixed and mobile parts.

Abstract: An instrumented device for the study of airflow over a structure (10), comprises a support (16) forming a thin plate (24) adapted to be applied and shaped to the contour of a predetermined region of the structure. Connection structure (22) cements a portion of an inner surface of the support to that predetermined region, leaving a space (36) of low height between an inner surface of the plate (24) of the support and that predetermined region. This height is substantially equal to the thickness of said cementing structure. Instrumentation (18) is connected to the support, a portion (28) of this instrumentation and wire connections (20) therefor being disposed in that space (36), whereby the device is adapted to form a skin on the structure.

Abstract: A fuel injection stub (6) for a ramjet is designed to operate at a high Mach number. According to the invention, said stub includes a carbon-carbon composite body (10), in which a rail of elementary injectors is arranged, and a nose piece (11) consisting of a thin skin of carbon-carbon composite in at least approximately the shape of a dihedron, the edge (11A) of which has a radius of curvature (r) at most equal to 2 mm and the angle of which is at most equal to 15.degree.. Means (23, 27) for injecting a coolant into the sealed chamber (18) are arranged in said body (10), said injection means producing a number of jets of pressurized coolant striking the concave face of said skin (11).

Abstract: Portions of a sound and thermic insulation mattress are modified so as to retain the water imperviousness of the mattress and its insulation characteristics when it is secured to a support. The mattress is provided with an opening therein and a foam insert arranged in the opening and provided with an orifice. The insert is held in the opening by an adhesive strip which is glued to the foam insert and the mattress.

Abstract: In order to be able to install in juxtaposed manner several satellites beneath the nose cone of the same launcher without any collision risk at the time of their separation, between each satellite and the support plate is positioned an adaptor. During launch, the adaptors occupy a size-limiting carriage position. When it is wished to control the separation of a satellite, its adaptor passes into a separation position, in which the satellite is tilted or swung away from the neighbouring satellite or satellites.