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 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 thrust device comprises a valve body (20) having a chamber (24) surrounding part of the needle, at least one gas admission opening (27) opening out into the chamber, and a gas outlet opening (25) opening out into the chamber and defined by a wall portion which co-operates with a nose portion (14) of a moving needle (10) to define an outlet section for gas leaving the chamber. Actuator means (40, 41, 43) control the position of the needle in the valve body by acting on a rear end portion of the needle. The nose (14) of the moving needle (10) has an aerodynamic concave profile (15) and the wall portion (29) which defines the outlet (25) from the chamber is shaped in such a manner as to be capable of directing the exiting gases essentially against the concave side of the nose of the needle, which needle acts as the main member for taking up thrust.

Abstract: The control system comprises a plurality of nozzles pointing in different directions, a plurality of gas generators, and pipework connecting the gas generators to the nozzles via gates for allowing or preventing gas being ejected therethrough. Each gas generator is fitted with a shutter disposed in an outlet passage connecting the generator to the pipework, the shutter having a closed position in which it closes the outlet passage by bearing against a seat formed in the passage and against which it is pressed when the generator is not ignited so as to isolate the gas generator in sealed manner from gas contained in the pipework and coming from other generators, the shutter being automatically lifted off its seat to move from the closed position to an open position under the effect of the pressure produced in the generator in response to being ignited, thereby enabling control to be performed with gas generators being ignited independently of one another.

Abstract: A device for controlling a spacecraft by gating gas, the device comprising a nozzle, a gas feed duct, a gate having a seat and a plunger interposed between the feed duct and the nozzle, and control means for opening and closing the gate in order to put the feed duct selectively into communication with the nozzle. The seat of the gate is secured to the nozzle and the nozzle is movable such that the gate is opened and closed by displacement of the nozzle, which displacement is driven directly by the hot gas, without calling on an auxiliary fluid.