Abstract: The terminal portion of a prefabricated skirt is connected to a casing of a thruster body in the vicinity of an end wall thereof using a method including positioning the terminal portion of the skirt with circumferential clearance around the casing of the thruster body in the vicinity of the end wall; keeping the skirt in position relative to the casing of the thruster body; closing both ends of an annular space between the terminal portion of the skirt and the casing of the thruster body; injecting elastomer into the annular space; and curing the elastomer.

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: A modulator device for modulating a gas ejection section, which device is for placing in a nozzle upstream from the throat of the nozzle and includes a plunger. The plunger has both a proximal portion connected to a control guide and also a distal portion in the form of a body of revolution, the plunger being movable between a retracted position and an extended position. The plunger presents, in its distal portion, a first section of concave shape and a second section of concave shape situated downstream from the first section.

Abstract: A pogo effect corrector system for a feed system for feeding a rocket engine with liquid propellant, the corrector system comprising: a feed pipe part for feeding liquid propellant that is configured to be connected both upstream and downstream to a liquid propellant feed pipe of the feed system; and a hydraulic accumulator comprising a tank connected to the feed pipe part via at least one communication orifice; the corrector system being characterized in that: at least a portion of the feed pipe part is at least partly surrounded by the inner volume of the tank; with each cross-section of said portion relative to its central axis being at least partly surrounded by the corresponding cross-section of the inner volume of the tank, in such a manner that the corresponding cross-section of the inner volume of the tank is off-center relative to said cross-section of said portion.

Abstract: The device comprises two heat exchangers (74, 90) suitable respectively for vaporizing first and second propellants before they are reintroduced in gaseous form into their tanks (16, 18). The heat exchangers co-operate respectively with first and second gas generators (60, 84) suitable for being fed with a mixture of propellants in order to produce combustion, the second gas generator (84) being suitable for being fed at least in part by the exhaust from the first gas generator (60).

Abstract: A device for destroying dangerous objects such as shells, munitions or other charges that are to be destroyed by detonating them, which device includes a packaging produced from a flat blank folded on itself along three folds, four folds or more in order to form at least three sides and two half, four sides or four sides and a flap for closing the packaging which is produced in the form of a tubular package of polygonal and notably square or rectangular cross section once the flat blank has been folded up, with explosive charges placed on the sides that are to be folded, the flat blank being of dimensions suited to being able to house, in the middle of the tubular package in contact with the explosive charges, one or more of the dangerous objects that are to be destroyed.

Abstract: An emission/reception device is configured for communication between a ground station and a mobile craft which is provided with a retro-reflector configured to modulate a laser beam received along a direction and to return it along the direction, the mobile craft being situated above a backscattering zone, the emission/reception device generating at least two temporally offset emission/reception sequences, each being associated with a laser beam and comprising successive pairs of associated emission and reception phases, the emission phase including emitting a laser beam from the ground station towards the mobile craft, and the reception phase including receiving a laser beam returned by the retro-reflector, each reception phase being deactivated during the transit through the backscattering zone of the laser beam emitted during the associated emission phase.

Abstract: The system (S) to separate at least two mechanical elements (E1, E2), comprises a holding device comprising a connecting screw integral with a mechanical element (E1) and held by a nut segmented in portions (4n) arranged between the connecting screw and an outer envelope integral with the other mechanical element (E2), the system (S) comprising a force generator generating a thrust force (F) in a longitudinal direction (X-X) and comprising an energy accumulator comprising a sealed chamber with a colloid of a porous matrix and liquid, the chamber deforming in the longitudinal direction (X-X) to adapt to the change from a compressed to a decompressed state in order to generate the force (F), and an activatable actuating element to, either apply a predetermined pressure to the chamber to keep the colloid in the compressed state, or not apply the predetermined pressure to allow the change in state of the colloid.

Abstract: A device for protecting from lightning (30) is intended to form at least a portion of an external surface of a structure to be protected and comprises a ground plane (32), a dielectric substrate (34) arranged on the ground plane, and an array of first metal elements (36) arranged on the dielectric substrate (34) and extending substantially parallel to the ground plane (32) in such a way that any pair of consecutive elements from said first metal elements (36) is separated by a distance comprised between 0.01 millimetres and 10 millimetres, said first metal elements being distributed in juxtaposed similar patterns, each of said patterns including first metal elements of different dimensions corresponding respectively to different electromagnetic resonant frequencies the juxtaposition of which defines an electromagnetic absorption band of the pattern.

Abstract: The subject of the invention is a device for the in-flight conditioning of equipment of cryogenic circuits of an aircraft, which device includes means for bleeding air from outside the aircraft, means for extracting nitrogen from this air using a nitrogen separator of the OBIGGS type and means for distributing this nitrogen around the equipment. The device notably includes means for distributing nitrogen around the various pieces of equipment of cryogenic circuits using a system of piping provided with calibrated orifices.

Abstract: A pyrotechnic circuit breaker, comprising a body, an igniter, a bus bar, and a piston which comprises a cutting edge and is movable along a normal direction to cut a portion of the bus bar, thereby separating the bus bar to break a circuit, wherein the cutting edge of the piston is stepped so that the portion of the bus bar is cut sequentially, in at least two successive cutting operations, characterized in that the bus bar comprises a breakable portion configured to be cut by the cutting edge of the piston, wherein said breakable portion comprises slots in order to divide the breakable portion into multiple sub-portions that are adapted to be cut sequentially by the stepped cutting edge of the piston.

Abstract: A method and a device for securing a space crossed by a high-power laser beam. A security laser beam is produced in the form of an envelope surrounding said high-power laser beam and the emission of the latter is forbidden when an object comes into contact with said envelope.

Abstract: A propulsion chamber for a liquid propellant rocket engine is provided. The propulsion chamber includes an inside wall made of metal, an outside covering made of organic matrix composite material, and a cooling circuit arranged between the outside covering and the inside wall. The propulsion chamber further includes at least a first axial endpiece secured to the metal inside wall and presenting at least one radial protrusion received in a concave recess in an inside face of the outside covering. The concave recess is situated axially between first and second belts of reinforcing fibers oriented substantially circumferentially in the outside covering in such a manner as to take up forces associated with inside pressure and thrust.

Abstract: A rocket engine combustion chamber (1) extending along a longitudinal axis A may have a longitudinal envelope, the longitudinal envelope having a longitudinal inner wall (10) made of a first alloy, which is a copper alloy, and that is extended over its radially outer face (15) by a plurality of fins (20) extending radially outwards, each of the fins presenting a proximal portion (22), a middle portion (25), and a distal portion (28), and having an outer shell (30) surrounding the inner wall (10) and the fins (20), the shell (30) being made of a third alloy distinct from the first alloy. The proximal portion (22) is made of the first alloy, and the distal portion (28) is made of a second alloy that is an alloy distinct from the first alloy.

Abstract: The invention relates to a space wing, produced by means of a diaphragm forming a polygonal surface provided with an inflatable structure which includes ribs extending over the diaphragm along diagonals of the diaphragm and passing through a central point of the diaphragm. The inflatable structure includes at least one film strip, the perimeter of which adheres onto the diaphragm such as to form an inflatable space with the diaphragm.

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: The device comprises a primary heater (58) suitable for heating the propellant coming from the tank (16) prior to it being reintroduced into its tank. The primary heater uses the heat of combustion from the engine (10) and the device further comprises a secondary heater (66) having its source of heat independent from the operation of the engine, the secondary heater being arranged downstream from the primary heater (58) in order to heat the propellant between its outlet from the primary heater and being reintroduced into the tank. The device also has means (62) between the feed to the primary heater (58) and the return of the propellant to the tank for putting the propellant under pressure.

Abstract: An assembly comprising at least two reflectors in the form of a thin shell, which are individually attached to a common tubular structure by means of strut lugs. The reflectors, the tubular structure and the strut lugs are made of a fibre-resin composite material. The reflectors can operate in different frequency bands.

Abstract: A method for producing a propulsion nozzle, wherein the nozzle is produced from an ablative resin, the method including a step of pre-polymerization wherein an innovative aldehyde compound is used.

Abstract: A rocket engine benefiting from better behavior during its starting stage, the rocket engine (1) including a diverging section (13) and a lashing system (40) configured to hold the diverging section (13) while starting the rocket engine (1), the lashing system (40) comprising: a plurality of radial cables (42) connected at respective first ends to a plurality of points of the diverging section (13), and a peripheral cable (41) connected to the second ends of the radial cables (42) and configured to co-operate with attachment points (43) of a launch platform (3).