Abstract: The present invention relates to an injector of tricoaxial structure comprising a body that is circularly symmetrical about an axis of symmetry, said body being provided with a plurality of injection elements having axes parallel to said axis of symmetry and passing through an injection wall fixed to said body and separating said injector from a combustion member to which it is coupled. According to the invention, each of said injection elements comprises a central injection channel fed with a second propellant and an annular injection slot surrounding said central channel and fed with a first propellant, an additional annular injection channel for the second propellant being formed by a space that exists around each injection element between its side wall and said injection wall, such that the sheet of first propellant flowing from said annular slot is engaged between the central jet and the outer sheet, each of which delivers the second propellant.

Abstract: The present invention relates to an injector of tricoaxial structure comprising a body that is circularly symmetrical about an axis of symmetry, said body being provided with a plurality of injection elements having axes parallel to said axis of symmetry and passing through an injection wall fixed to said body and separating said injector from a combustion member to which it is coupled. According to the invention, each of said injection elements comprises a central injection channel fed with a second propellant and an annular injection slot surrounding said central channel and fed with a first propellant, an additional annular injection channel for the second propellant being formed by a space that exists around each injection element between its side wall and said injection wall, such that the sheet of first propellant flowing from said annular slot is engaged between the central jet and the outer sheet, each of which delivers the second propellant.

Abstract: The present invention relates to a parallel-sheet injector provided with a body about an axis to which there is coaxially connected at least one annular injection element comprising a central annular injection slit surrounded by two other annular injection slits. The central annular slit is fed with a second propellant which enters at the top of the injection element level with said central slit and the other annular slits are fed with a first propellant which enters at the base of the injection element, on either side of the central slit, and passes through an annular homogenization cavity from which it flows towards the annular slits surrounding the central injection slit. The invention also relates to injection elements which may be used within the scope of this injector.

Abstract: The downstream portion of the diverging part of the nozzle of the rocket engine is extended by an ejectable diffuser which, downstream from the zone where it is connected to the diverging part, presents a zone of smaller cross-section that acts during a first stage of flight in the presence of significant outside pressure to recompress the flow of hot gases and to prevent a flow separation from appearing along with the wall of the diverging part. The ejectable diffuser may have a streamlined throat which constitutes the zone of smaller cross-section.

Abstract: In a rocket engine nozzle with a selectively smaller outlet cross-section, the nozzle comprising a converging portion which receives the gases produced in a combustion chamber, a nozzle throat of small cross-section and a diverging part connected to the nozzle throat and terminating at its downstream portion in a gas jet outlet cross-section defining a high cross-section ratio, a releasable annular obstacle is connected to the downstream end of the diverging part so as to define at the outlet of the diverging part a zone of selectively smaller cross-section which ensures stability of the separation of the flow of hot gases relative to the wall of the diverging part during a first phase of flight.

Abstract: The rocket engine is fitted with an injection device comprising a single injection plate having a central portion that defines the end of the burn zone of the combustion chamber and that contains first propellant injectors having a high mixing ratio adapted to the conditions under which hot gases are produced in the burn zone, and a peripheral portion in the form of a ring that defines the end of an annular cavity of a gas generator and that contain second propellant injectors having a low mixing ratio and adapted to the conditions under which hot gases are produced in the gas generator. The gas generator is thus integral with the combustion chamber and the annular cavity of the gas generator is separated from the burn zone of the combustion chamber by a cylindrical wall that extends axially perpendicularly to the injection plate and that is fixed thereto in sealed manner.

Abstract: The deployment mechanism comprises three identical operative assemblies mounted on a fixed main frame. Each operative assembly comprises a linear actuator and first and second links disposed in such a manner as to ensure self-locking in a deployed position by causing the axes of the following three hinges to pass to or slightly beyond a dead point where they are in alignment: the hinge between the main frame and a first zone of the first link; the hinge between the upstream end of the second link and a second zone of the first link; and the hinge between the downstream end of the second link and a link support mounted on the deployable portion of the nozzle. The actuator is secured and anchored to a non-deployable portion of the nozzle and it includes a drive member whose free end is hinged to a third zone of the first link, and it is deactivated in both of the final positions, i.e. when the deployable portion is deployed and when it is retracted.