Abstract: A sizing composition for reinforcing fibres is provided which makes it possible to improve the adhesion of these fibres with respect to an organic matrix that forms, with them, a part made of a composite material and that results from the chain transfer polymerization of a curable resin. The sizing composition includes a polybutadiene prepolymer comprising at least two epoxide functions, a cross-linking agent comprising at least two reactive functions, at least one of which is a thiol function; and a catalyst comprising at least one tertiary amine function.

Abstract: A process for obtaining borazane (NH3—BH3) includes introducing anhydrous liquid ammonia (NH3(l)) into a reactor thermostatically regulated to between a temperature ?1 and 40° C.; introducing, with stirring, into the reactor an amine borane complex (Am.BH3), the corresponding amine (Am) of which is soluble in anhydrous liquid ammonia only to a proportion of less than 10 g in 100 g of ammonia at 20° C., being introduced in an amount such that the mole ratio R=(NH3(l))/(Am.BH3) is greater than or equal to 5; stirring the mixture; stopping the stirring to obtain two demixed phases: a light phase constituted essentially of a solution of anhydrous liquid ammonia (NH3(l)) containing borazane; and a heavy phase constituted essentially of the amine corresponding to the amine borane complex introduced; isolating the borazane and drying under vacuum thereof; the temperature ?1 being greater than or equal to the melting point of the amine borane complex.

Abstract: The invention relates to a combustion gas discharge nozzle for a rocket engine including a stationary part and a moving part extending from the stationary part, the moving part made using flaps positioned downstream from the stationary part and forming an extension of the nozzle, the nozzle including a sealing device extending between the fixed part and the moving part in the form of a flexible membrane withstanding a local temperature of the combustion gases at the nozzle outlet and connecting the end of the stationary part to a border of the flaps or petals forming the moving part, the flexible membrane forming an annular tubing, the sealing device being provided with a duct for injecting gas at the flexible membrane between the stationary part and the moving part extending the nozzle.

Abstract: A containment device including a dry curtain, adapted to be deployed for the containment or re-containment of a discharge area, such as an opening, e.g. a door, in response to an explosion. The device includes a ballast bar in the lower portion of the curtain, the ballast bar including cylinders of high-density foam alternated with cylinders of compressible low-density foam.

Abstract: The subject of the invention is an assembly and clamping bolt to be employed under tension, having a shank and a head, wherein the head, situated at a first end of the shank, is provided with a clamping tensioning means with a hydraulic cylinder mounted permanently on the bolt, clamping taking place between a rear shoulder device and the hydraulic cylinder, the rear shoulder device being disposed at a second end of the shank.

Abstract: A containment device including a curtain that can be deployed from a first wound or folded position into a second unwound position, and a case for storing the curtain in the first position. The case is formed by a plurality of adjacent modules, the plurality of modules including active modules that are equipped with means for retaining and releasing the curtain and passive modules that are not equipped with means for retaining and releasing the curtain.

Abstract: A composite pyrotechnic product containing energetic charges in a plasticized binder includes a cured energetic polymer and at least one energetic plasticizer, wherein: the cured energetic polymer consists of a glycidyl azide polymer (GAP) having a number average molecular weight (Mn) lying in the range 700 g/mol to 3000 g/mol and cured via its hydroxyl terminal functions with at least one curing agent of polyisocyanate type; and the energetic charges present at a content in the range 50% to 70% by weight consisting, for at least 95% of their weight, of large crystals of ammonium dinitramide (ADN) and of small crystals of hexogen (RDX): the large crystals of ammonium dinitramide (ADN) being present at a content in the range 8% to 65% by weight; and the small crystals of hexogen (RDX) being present at a content in the range 5% to 55% by weight.

Abstract: A method of generating electricity with a fuel cell includes a phase in which the cell is primed; and a phase in which the cell functions at a stable rate, during which the cell, fed with a hydrogenated gas, generates electricity and heat. In order to prime the cell, it is fed with a hydrogenated gas including at least 70 vol. % hydrogen, generated by self-sustaining combustion of at least one hydrogenated gas-generating solid pyrotechnic charge; and while it is operating at a stable rate, the cell is fed with a hydrogenated gas containing at least 85 vol. % hydrogen, generated by thermal decomposition of at least one hydrogenated gas-generating solid pyrotechnic charge; a portion of the heat produced by the operating cell being transferred to the at least one solid charge in order to start and maintain the thermal decomposition thereof.

Abstract: A support tooling for supporting at least one metal part that is to be subjected to heat treatment or shaped while hot, the tooling including: a stationary support structure presenting a determined shape that corresponds to the general shape of each metal part that is to be supported; first holder elements arranged on one side of each part; second holder elements arranged on the other side of each part; and at least one spring type resilient element placed between the support structure and each first or second holder element so as to hold the part throughout the duration of heat treatment. The support structure, the first and second holder elements and the resilient element(s) are made of thermostructural composite material.

Abstract: A system for blocking a plug valve, the system comprising: a plug (1) movable in rotation about an axis (Y-Y); and a blocker part (5); the system being characterized in that: the plug (1) presents an index portion having a first ramp (3) and a second ramp (4) that are arranged around the shaft (2) with oppositely-handed slopes; and the blocker part (5) presents first and second index portions (8, 9) adapted to come selectively into contact with the first and second ramps (3, 4) respectively; the first ramp (3) and the first index portion (8) serving to prevent the plug (1) from turning about the longitudinal axis (Y-Y) in a first direction of rotation, and the second ramp (4) and the second index portion (9) serving to prevent the plug (1) from turning about the longitudinal axis (Y-Y) in a second direction of rotation.

Abstract: A substantially cylindrical gas-generating pyrotechnical monolithic block has a thickness no lower than 10 mm, an equivalent diameter no lower than 10 mm, and a porosity lower than 5%; and a composition, given as weight percentages, which contains, for at least 94% of the weight thereof: +77.5% to 92.5% of guanidine nitrate, +5% to 10% of basic copper nitrate, and +2.5% to 12.5% of at least one inorganic titanate with a melting temperature higher than 2100 K.

Abstract: A method of starting combustion of a space vehicle engine, the method comprising igniting a propellant tank heater (25); once the heater (25) has reached stable conditions, pressurizing a first tank (23) containing the first propellant and a second tank (24) containing a second propellant, and in parallel filling respectively a first igniter tank (13) with the first propellant in gaseous form and a second igniter tank (14) with the second propellant in gaseous form until ignition thresholds values of temperature (T13, T14) and of pressure (P13, P14) have been reached; and injecting the first and second propellants in gaseous form contained in the first and second igniter tanks (13 and 14) into an igniter (12) of the engine, so as to initiate combustion.

Abstract: A nozzle (1) for a space vehicle engine (M), the nozzle comprising a stationary portion (2) and a movable portion (3), the nozzle (1) including a pneumatic deployment system (4) comprising: a deployment actuator (5) for deploying the movable portion (3) of the nozzle (1); a high unlocking actuator (6); a low unlocking actuator (7); and an ejector (41); the deployment system (4) including a feed system (8) configured so as to, sequentially: move the deployment actuator (5) from its support position towards its deployment position; move the high and low unlocking actuators (6, 7) into their high and low unlocking positions; and actuate the ejector so as to eject the deployment system (4) from the nozzle (1).

Abstract: The invention relates to the field of feeding devices, in particular for feeding rockets on the ground. A feeding device (4) of the invention comprises at least two mutually complementary feeding connectors (5, 6), a breakable connection member (15) connecting these two feeding connectors (5, 6) together and presenting a breakable section (15c) between these two feeding connectors (5, 6), and a force transmission member (16) connected to said breakable section (15c) in such a manner as to transmit a breaking load thereto in order to unlock the connection between the two feeding connectors (5, 6). During unlocking, a breaking load transmitted by the force transmission member (16) thus serves to break the breakable section (15c).

Abstract: A pyrotechnic circuit breaker (1), comprising a body (2), an igniter (4), a piston (5) and a bus bar (6), wherein wherein the piston (5) comprises a cutting edge (51) and is adapted to move along a normal direction (Z-Z) from a raised position to a lowered position to cut a portion of the bus bar (6), thereby separating the bus bar (6) into two distinct portions in order to break the electrical conduction of the bus bar (6), wherein the body (2) comprises a longitudinal slot (21) arranged through a longitudinal direction (X-X) of the body (2), perpendicular to the normal direction (Z-Z), wherein the bus bar (6) and the longitudinal slot (21) are configured so that the bus bar (6) can be slidably inserted within the insertion slot (21), characterized in that the pyrotechnic circuit breaker (1) further comprises a drawer (7) adapted to be slidably inserted within the longitudinal slot (21) of the body (2), so that once inserted in the body (2), the drawer (7) and the body (2) define an insertion slot through th

Abstract: A pyrotechnic circuit breaker (1), comprising a body (2), an igniter (4), a piston (5) and a bus bar (6), wherein the igniter (4), the piston (5) and the bus bar (6) are adapted to be accommodated within the body (2), and wherein the piston (5) comprises a cutting edge (51) and is adapted move along a normal direction (Z-Z) to cut a portion (61) of the bus bar (6), thereby separating the bus bar (6) into a proximal portion and a distal portion in order to break a circuit, wherein the cutting edge (51) of the piston (5) is stepped so that the portion of the bus bar (6) is cut sequentially, in at least two successive cutting operations along the movement of the piston (5) from a raised position to a lowered position, characterized in that the bus blade (6) comprises a breakable portion (61) configured to be cut by the cutting edge (51) of the piston (5), wherein said breakable portion (61) comprises slots (62) in order to divide the breakable portion (61) into multiple sub-portions (61a, 61b, 61c) that are adap

Abstract: A method of regulating pressure within a first propellant tank of a rocket engine having a first propellant tank containing a first propellant and a second propellant tank containing a second propellant, and a regulator device for regulating pressure within the first tank, the regulator device comprising a gas generator and a heat exchanger co-operating with the gas generator so as to vaporize at least part of the first propellant prior to reintroducing it into the first tank (16), the gas generator and the heat exchanger both being fed with the first propellant by a single first motor-driven pump, while the gas generator is fed with the second propellant by a single second motor-driven pump, wherein the flow rate of the first motor-driven pump is controlled as a function of a first parameter, while the flow rate of the second motor-driven pump is controlled as a function of a second parameter.

Abstract: A rocket engine having a rocket engine combustion chamber (116) and an ignition torch (10). The rocket engine combustion chamber (116) is a main combustion chamber, or a combustion chamber of a gas generator, or a combustion chamber of a preburner of the rocket engine. The ignition torch (10) comprises a body (20) in which a combustion chamber (21) is arranged and an ejection tube (40) for discharging combustion gas leaving the combustion chamber. The body (20) of the torch is configured to enable the combustion chamber to be fed with fuel and oxidizer via respective fuel and oxidizer feed ducts. The ignition torch (10) also has an oxidizer reinjection duct (60) configured to enable oxidizer to be injected substantially at the outlet of the ejection tube (40).

Abstract: The invention relates to the field of rocket engine propulsion chambers, and more specifically to a propulsion chamber (2) for a liquid propellant rocket engine, the propulsion chamber comprising at least an inside wall (10) made of metal, an outside covering (11) made of organic matrix composite material, and a cooling circuit (12) arranged between the outside covering and the inside wall (10). The propulsion chamber (2) further comprises at least a first axial endpiece (17, 18) secured to the metal inside wall and presenting at least one radial protrusion (19, 20) received in a concave recess in an inside face of the outside covering (11). This concave recess is situated axially between first and second belts (21, 22; 23, 24) of reinforcing fibers oriented substantially circumferentially in said outside covering (11) in such a manner as to take up forces associated with inside pressure and thrust.

Abstract: The invention relates to the field of rocket engines, and in particular to a method and a circuit for regulating a rocket engine (1) comprising at least one combustion chamber (3) and a first liquid propellant feed circuit (10) with a first pump (12) for pumping a first liquid propellant and a first turbine (14) for actuating the first pump (12), a first feed valve (15), and a regulator device for regulating the first turbine (14). In the regulation method and circuit, an opening command (DVCH) for opening the first feed valve (15) is calculated from an external command (Cext) in application of an open loop control relationship; a command for the regulator device of the first turbine (14) is calculated on the basis of said external command (Cext) and at least one feedback value, in application of a closed loop control relationship; and the first feed valve (15) and the regulator device of the first turbine (14) are controlled in application of the respective commands.