Abstract: A holding system (101, 102, 103) for holding at least one pipe, comprising a comb including a bar and parallel teeth perpendicular to the bar. A blocking device (30) consisting essentially of a pin, serves to prevent a pipe passing between two of the teeth from moving away from the bar. The holding system further comprises two supports (40A, 40B), positioned at the ends of the comb, and which hold the comb so as to allow rotation thereof around the axis of the bar. A method for mounting a heat exchanger (100) comprising such a holding system.

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 holding system (101, 102, 103) for holding at least one pipe, comprising a comb including a bar and parallel teeth perpendicular to the bar. A blocking device (30) consisting essentially of a pin, serves to prevent a pipe passing between two of the teeth from moving away from the bar. The holding system further comprises two supports (40A, 40B), positioned at the ends of the comb, and which hold the comb so as to allow rotation thereof around the axis of the bar. A method for mounting a heat exchanger (100) comprising such a holding system.

Abstract: An assembly including a cryogenic fluid tank for a space vehicle and a thermal protection system for a cryogenic fluid tank of the space vehicle, the system including: a shell adapted to surround the cryogenic fluid tank, the shell being dimensioned to define an inside space between the shell and the tank; and an injector for injecting a cooling fluid spray into the inside space; the cooling fluid being injected into the inside space in the liquid state at a temperature that is adapted to ensure that the cooling fluid picks up the heat flux reaching the cryogenic fluid tank, thereby causing the cooling fluid to vaporize, the shell having a plurality of orifices adapted to allow the cooling fluid in gaseous form to leave inside space through the shell.

Abstract: A propulsion assembly (1, 201) for a rocket, comprising a tank (2) configured to contain a propellant, an engine having a combustion chamber (9), a propellant feed pipe (11) extending between the tank (2) and the combustion chamber (9) and having an isolation valve (24) arranged therein, and a heater (15) having an inlet connected to the feed pipe (11) and an outlet connected to the tank (2). The inlet of the heater comprises an inlet pipe (13a) connected firstly to the feed pipe (11) downstream from the isolation valve (24) and secondly to a neutral fluid feed (31).

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 rocket engine with an extendible exit cone including an exhaust nozzle for gas from a combustion chamber, the nozzle presenting a longitudinal axis having a first portion defining a nozzle throat and a stationary first exit cone segment, at least one extendible second exit cone segment of section greater than the section of the stationary first exit cone segment, and an extension mechanism for extending the extendible second exit cone segment, the mechanism being located outside the first and second exit cone segments. A rigid thermal protection shield is interposed between the extension mechanism and the stationary first exit cone segment. The thermal protection shield presents a convex wall on its face facing towards the stationary first exit cone segment.

Abstract: A test bench for a reaction engine including a nozzle having a divergent. The bench includes a mechanism for holding the divergent in position, capable of holding the divergent so that its axis is vertical, and capable of interacting with a downstream portion of the divergent located in the downstream half thereof to limit distortion and/or displacement of this downstream portion. The test bench enables the divergent to remain undamaged even if lateral forces are applied to it during testing.

Abstract: A rocket engine with an extendible exit cone including an exhaust nozzle for gas from a combustion chamber, the nozzle presenting a longitudinal axis having a first portion defining a nozzle throat and a stationary first exit cone segment, at least one extendible second exit cone segment of section greater than the section of the stationary first exit cone segment, and an extension mechanism for extending the extendible second exit cone segment, the mechanism being located outside the first and second exit cone segments. A rigid thermal protection shield is interposed between the extension mechanism and the stationary first exit cone segment. The thermal protection shield presents a convex wall on its face facing towards the stationary first exit cone segment.