Abstract: A method of fabricating an opto-pyrotechnic initiator, includes a) forming a body having a cavity in which a pyrotechnic charge is to be received, the body also having an internal passage extending between the cavity containing the pyrotechnic charge and an inlet opening out in an outside face of the body; b) placing a first portion of an optical fiber in the internal passage of the body, with a second portion of the optical fiber extending beyond the inlet of the body, and a glass preform being interposed between the optical fiber and the inlet of the body; and c) applying heat treatment to the glass preform to raise the glass preform to a temperature higher than the melting point of the glass preform so as to form a hermetic sealing element made of glass between the optical fiber and the inlet of the body.

Abstract: A method of fabricating an opto-pyrotechnic initiator, includes a) forming a body having a cavity in which a pyrotechnic charge is to be received, the body also having an internal passage extending between the cavity containing the pyrotechnic charge and an inlet opening out in an outside face of the body; b) placing a first portion of an optical fiber in the internal passage of the body, with a second portion of the optical fiber extending beyond the inlet of the body, and a glass preform being interposed between the optical fiber and the inlet of the body; and c) applying heat treatment to the glass preform to raise the glass preform to a temperature higher than the melting point of the glass preform so as to form a hermetic sealing element made of glass between the optical fiber and the inlet of the body.

Abstract: An adapter device for controlling a rocket engine nozzle under conditions of external pressure that can lead to the jet separating inside the nozzle, the nozzle being fitted with a diverging portion that is movably mounted relative to a stationary portion of the nozzle, thrust deflection then being achieved by swivelling the diverging portion so as to deflect the jet of combustion gas in contact with the inside wall of the diverging portion. The device includes a structure disposed inside the diverging portion in such a manner as to reduce the diverging nature of the flow section thereof and to increase the bearing area of pressure forces exerted by the jet on the diverging portion during swivelling thereof.

Abstract: An adapter device for controlling a rocket engine nozzle under conditions of external pressure that can lead to the jet separating inside the nozzle, the nozzle being fitted with a diverging portion that is movably mounted relative to a stationary portion of the nozzle, thrust deflection then being achieved by swivelling the diverging portion so as to deflect the jet of combustion gas in contact with the inside wall of the diverging portion. The device includes a structure disposed inside the diverging portion in such a manner as to reduce the diverging nature of the flow section thereof and to increase the bearing area of pressure forces exerted by the jet on the diverging portion during swivelling thereof.

Abstract: The nozzle comprises a moving diverging portion (20) and a static portion (16) secured to the rear end wall of the combustion chamber (12) of the engine. A cardan mount jointed link device connects the moving diverging portion of the nozzle to the static portion, the moving diverging portion and the static portion being in mutual contact via respective spherical surfaces (24a, 16a), and an actuator device (50a, 50b) acts on the moving diverging portion of the nozzle so as to be able to vary the direction of the thrust vector of the engine by modifying the orientation of the nozzle with sliding of the spherical surfaces one on the other. Resilient return means (62, 64) are interposed between the moving diverging portion (20) of the nozzle and the static portion (16) and act on the moving diverging portion in order to urge it towards the static portion so as to keep the spherical surfaces (24a, 16a) in mutual contact for any desired orientation of the nozzle.

Abstract: The tank for fluid under pressure comprises one or an assembled-together plurality of individual containers or modules made at least in part out of composite material. The or each individual container (20) comprises a cylindrical body (22) of composite material, two end plates (30) closing the axial ends of the cylindrical body, and at least one belt passing around the container substantially in a longitudinal direction and bearing against portions of the outside faces of the end plates.

Abstract: The nozzle comprises a moving diverging portion (20) and a static portion (16) secured to the rear end wall of the combustion chamber (12) of the engine. A cardan mount jointed link device connects the moving diverging portion of the nozzle to the static portion, the moving diverging portion and the static portion being in mutual contact via respective spherical surfaces (24a, 16a), and an actuator device (50a, 50b) acts on the moving diverging portion of the nozzle so as to be able to vary the direction of the thrust vector of the engine by modifying the orientation of the nozzle with sliding of the spherical surfaces one on the other. Resilient return means (62, 64) are interposed between the moving diverging portion (20) of the nozzle and the static portion (16) and act on the moving diverging portion in order to urge it towards the static portion so as to keep the spherical surfaces (24a, 16a) in mutual contact for any desired orientation of the nozzle.

Abstract: The tank for fluid under pressure comprises one or an assembled-together plurality of individual containers or modules made at least in part out of composite material. The or each individual container (20) comprises a cylindrical body (22) of composite material, two end plates (30) closing the axial ends of the cylindrical body, and at least one belt passing around the container substantially in a longitudinal direction and bearing against portions of the outside faces of the end plates.