Abstract: A pogo effect corrector system for a liquid propellant feed system of a rocket engine includes a liquid propellant feed pipe portion, and a hydraulic accumulator including a tank connected firstly to the feed pipe portion firstly via at least one take-off passage opening out into a take-off segment of the feed pipe portion, and secondly via at least one rejection passage opening out into the tank at an intermediate level lying between the at least one take-off passage and the top of the tank, wherein the feed pipe portion possesses a constriction segment where the flow section of the feed pipeline portion is less than the flow section of the take-off segment, and wherein at least one rejection passage opens out into the feed pipeline portion in the constriction segment.

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).

Abstract: A nozzle presents a longitudinal axis, includes both a combustion chamber made of metal material and presenting a downstream end, and a diverging portion made of composite material formed by a wall of conical shape extending between an upstream and a downstream end. The upstream end of the composite material diverging portion is connected to the downstream end of the combustion chamber. The nozzle further includes an annular mount made of metal material including a first portion secured to the combustion chamber and a second portion extending beyond the downstream end of the combustion chamber along the longitudinal axis. The upstream end of the composite material diverging portion is fastened to the second portion of the annular mount by a plurality of fastener members, each including a fastener bolt, each fastener bolt passing through the conically-shaped wall of the composite material diverging portion near the upstream end of the wall.

Abstract: An injector element for injecting a mixture of at least a first propellant and a second propellant into a combustion chamber. The injector element includes a first tubular wall defining a first duct for injecting the first propellant, and a second wall surrounding the first wall and defining, between the first and second walls, a second duct for injecting the second propellant. The first wall includes a first electrode for igniting the mixture by electric discharge.

Abstract: A pogo effect corrector system for a liquid propellant feed system of a rocket engine includes a liquid propellant feed pipe portion, and a hydraulic accumulator including a tank connected firstly to the feed pipe portion firstly via at least one take-off passage opening out into a take-off segment of the feed pipe portion, and secondly via at least one rejection passage opening out into the tank at an intermediate level lying between the at least one take-off passage and the top of the tank, wherein the feed pipe portion possesses a constriction segment where the flow section of the feed pipeline portion is less than the flow section of the take-off segment, and wherein at least one rejection passage opens out into the feed pipeline portion in the constriction segment.

Abstract: A valve includes a valve body provided with a plug, connected to an actuation system, an upstream duct, a downstream duct, and a purge duct provided with a shutter. The plug is movable in rotation about a longitudinal axis in the valve body, so that the rotation of the plug according to a first angular sector defines a flow between the upstream duct and the downstream duct, the rotation of the plug according to a second angular sector separate from the first angular sector shuts off the connection between the upstream duct and the downstream duct, and the rotation of the plug according to a third angular sector included in the second angular sector actuates the shutter so as to allow a flow from the upstream duct to the purge duct.

Abstract: The invention relates to a pressure sensor (10) comprising a cavity (12) containing a liquid, said cavity (12) being closed at a first end by a first diaphragm (20a) and at a second end by a second diaphragm (20b), and a measuring body (30) which comprises a strain gauge (31) positioned inside said cavity (12), characterized in that the measuring body (30) is mechanically connected only to one diaphragm among the first diaphragm (20a) and the second diaphragm (20b) by a connection member (50), the measuring body (30) comprising a shape having central symmetry and the connection member (50) being fastened to the center of symmetry of said measuring body (30).

Abstract: A method of controlling a multi-engine bay in which the following steps are performed: a) controlling the bay so that it delivers desired thrust and each engine is operated in compliance with a set of operating limits for the engine; b) periodically evaluating a level of damage for each of the engines, the level of damage of an engine being information representative of a probability of the engine failing; c) for each engine, periodically evaluating whether its level of damage exceeds a predetermined value; and d) if the level of damage of an engine, referred to as a “damaged” engine, exceeds a predetermined value, modifying at least one operating limit of the damaged engine so that the rate of damage of the damaged engine is less than a predetermined maximum rate of engine damage.

Abstract: According to the present invention, the device, which is provided with a male element secured to one of the parts and a female element secured to the other of said parts, comprises a plurality of resilient fastening strips forming a flared receptacle for said male element inside said female element. This receptacle is slidably movable so as to capture, pull and hold said male element inside said female element.

Abstract: A system for positioning at least one satellite in working orbit, characterized in that the system for positioning satellites in working orbit comprises: a first attachment device configured to attach a first satellite to the system for positioning satellites in working orbit; a main propulsion device with solid propulsion comprising a plurality of parallel solid-propellant cartridges; a secondary propulsion device which is re-ignitable; at least one position sensor configured to measure the position of said system; a monitoring unit connected to said at least one position sensor and which is configured to control a firing of the cartridges of the main propulsion device to move said system from a transfer orbit to a working orbit of the first satellite, said monitoring unit being further configured to control an opening of the first attachment device to separate said system from the first satellite.

Abstract: A field of vehicles propelled by reaction, and more specifically to a method of suppressing the pogo effect in such a vehicle. A feed system for feeding a reaction engine of the vehicle includes a hydraulic accumulator enabling a selection to be made from among a plurality of predetermined operating levels, each corresponding to a different volume of gas. In the method, if a first reference criterion is not satisfied by the current level, the hydraulic accumulator is ordered to make a transition, preferably to an alternative level selected from among alternative levels for which the first reference criterion is satisfied and for which no hydraulic resonant frequency crosses any current mechanical resonant frequency during the transition.

Abstract: An in-flight side force steering and attitude control system for a vehicle includes a thruster body and a plurality of valves distributed in first and second valve sets. The system further includes a first tank defined by a first cylindrical enclosure present at the center of the thruster body, the first tank containing a first solid propellant charge having at least one combustion face exposed at one end of the first tank, the first tank being in communication with the first valve set; and a second tank defined between the first cylindrical enclosure and a second cylindrical enclosure present around the first enclosure, the second tank containing a second solid propellant charge having at least one combustion face exposed at one end of the second tank, the second tank being in communication with the second valve set.

Abstract: A process for manufacturing a composite part includes introducing an adhesion promoter into the pores of a fibrous preform formed by threads covered with a coating having —OH groups on its surface, the adhesion promoter including an electron-withdrawing group G1 that is reactive according to a reaction of substitution or of nucleophilic addition with the —OH groups, and a reactive group G2; grafting the adhesion promoter to the surface of the coating by a reaction of substitution or nucleophilic addition of the —OH groups on the group G1; introducing a ceramic precursor resin into the pores of the fibrous preform; polymerizing the resin introduced and bonding the grafted adhesion promoter to the resin by chemical reaction between these two compounds at the level of the group G2, and forming a ceramic matrix phase in the pores of the fibrous preform by pyrolysis of the polymerized resin.

Abstract: A supply system for supplying a rocket engine with at least one propellant, the supply system comprising at least one supply circuit able to circulate the propellant, and at least one reservoir in fluid communication with the supply circuit via at least one communication pipe, so that a fluid contained in the reservoir can flow from the latter up to the supply circuit, and vice versa, via said at least one communication pipe, the reservoir being able to contain a volume of gas, and heating means able to vary the volume of gas in the reservoir, the heating means being configured to vaporize the propellant in the reservoir.

Abstract: A rotor for a turbomachine includes a disc and a plurality of blades fixed to the disc. Each blade of the plurality of blades is fixed to the disc via a lattice structure configured so that a tensile force applied to the lattice structure induces a change in the angle of incidence of the blade. The blades and the lattice structures are configured so that: (i) when the rotor is stationary, the distribution of the angles of incidence of the blades around the disc is aperiodic, and (ii) when the rotor is rotating at a predetermined rotational speed, the angles of incidence of the blades are identical.

Abstract: A system for producing gaseous hydrogen, includes an enclosure formed by a side wall, a front end wall, and a rear end wall, the enclosure containing unit charge(s) of a material for generating gaseous hydrogen when heated, wherein each unit charge includes a cylindrical body including a closed rear end wall and a front end wall having an opening, at least one block of material for generating gaseous hydrogen, each block presenting an annular shape defining a central channel leading to the opening in the front end wall of the body and an initiator present in the vicinity of the rear end wall of the body; the opening facing the front end wall of the enclosure so that the hot gas coming from the block of material for generating gaseous hydrogen when heated is directed directly against the inside surface of the front end wall of the enclosure.

Abstract: An installation for fabricating a thermal protection covering of a body or of a rear assembly for a thruster, includes an extruder presenting a die having an outlet orifice through which a strip of elastomer material is to be extruded, the extruder having a die control system to vary the size of the outlet orifice; a mandrel to be set into rotation about its axis; a deposition head to deposit the strip on the mandrel; a conveyor system to convey the strip from the outlet orifice of the die of the deposition head; and a thickness monitoring system to measure the thickness of the strip on the deposition head and on the mandrel and to compare each measured thickness value with a predetermined value, the thickness monitoring system to control the die control system so as to cause the size of the outlet orifice of the die to vary.

Abstract: A patch antenna intended to equip a spacecraft, the antenna comprising a dielectric substrate, a radiating antenna element present on the dielectric substrate, the radiating antenna element having a center of symmetry and an area devoid of material, the center of symmetry being present in the area devoid of material, and a protective layer covering the radiating antenna element.

Abstract: The invention relates to a curable resin that represents an excellent substitute for phenolic resins and is therefore able to replace phenolic resins in all applications in which they are used. Said resin is characterised in that it comprises: (1) at least one prepolymer resulting from the prepolymerisation of a compound A comprising at least one aromatic or heteroaromatic ring, a first group —O—CH2-C?CH and at least one second group selected from the groups —O—CH2-C?CH2 and —CH2-CH?CH2, said groups being carried by the at least one aromatic or heteroaromatic ring; and (2) a compound B comprising at least two thiol groups (—SH). The invention also relates to a material obtained by curing said curable resin, and in particular to an ablative composite material. The invention further relates to a material obtained by curing said curable resin.

Abstract: A loading tooling for thermochemical treatment of parts includes at least first and second loading stages stacked one on the other in separable manner, each loading stage including a rack extending in a horizontal plane. The rack is supported by four legs extending in a vertical direction with the legs of the second loading stage standing on the legs of the first loading stage. The rack has a plurality of support arms secured thereto, with the plurality of support arms of the first loading stage presenting an arrangement that is different from the arrangement of the plurality of support arms of the second loading stage.