Abstract: A guided projectile, especially a propelled or ballistic missile, has its trajectory corrected by gas jets from pulse thrusters disposed in at least on axial plane of the missile symmetrically on opposite sides of the center of gravity thereof and whose thrusts are countered, when no longer needed, by the operation of diametrically opposite pulse thrusters in the same plane and at the same side of the center of gravity. The pulse thrusters are formed as gas generators which can be triggered to feed respective nozzles. The projectile is also roll stabilized, e.g. by a rotatable empennage. The transverse thrusts produced by the pulse thrusters are controlled by a sensor which responds to deviations from the correct orientation of the missile. The invention is particularly applicable to self-guided or homing tactical weapons.

Abstract: In this homing device, the side nozzles of the gas propulsion unit can be opened independently of one another. The device comprises a gas generator, preferably using solid propellant, and means to control the shutting and opening of nozzles, these means comprising, for each nozzle, an electromagnetic device controlled independently of the electromagnetic devices of the other nozzles. Provision can be made for a spring giving the power needed to close a nozzle, the electromagnetic device being actuated only to open the nozzle. Among the control means, the invention also provides for a control piston actuated by the electromagnetic device which brings a pressure chamber, within which there is a sliding piston, into contact either with the open air or with the gases coming from the gas generator. The control means are also arranged in such a way as to act as safety valves, in order to avoid the untimely explosion of the gas generator in the event that none of the nozzles is open.

Abstract: A gas propellor having at least one pair of diametrically opposed lateral nozzles for supplying a thrust force directed towards the rear of the missile or projectile includes a cake of solid propellant relatively insensitive to the combustion pressure, and opening-closing valves for each of the nozzles. These valves have sliding elements provided with pneumatic flip-flop actuators that are controlled by control circuits including a logic operator which prevents the simultaneous closing of the two nozzles of a same pair. The sliding elements of the valves are provided with mechanical safety means in order to limit the relative displacement of these sliding elements.

Abstract: A guidance method is provided for the terminal portion of the trajectory of a guided missile having a sensor and comprising two sections coupled together by a central shaft and free to rotate with respect to one another about the longitudinal axis of the missile; one section comprises a drive means for controlling the roll attitude of this section and a gas generator which feeds a nozzle for providing a transverse throat force and the other section has a stabilizing tail unit formed by a set of fins able to be opened out.

Abstract: A control device using gas jets makes it possible to modify the flight direction of a guided missile. This device comprises an energy source supplying a gas flow to a set of fixed nozzles arranged in an annular member within which are coaxially placed movable sleeves, respectively provided with gas passage openings or ports. Means are provided for positioning these openings so as face the inlets of the nozzles, in order to divert the gas flow towards one of the nozzles.

Abstract: A steering device comprising an annular element having N exhaust nozzles and a rotary element disposed coaxially inside said annular element; the rotary element comprising M gas passageways may be positioned in MN discrete directions so as to provide a transverse thrust force orientated in one of the steering planes.

Abstract: A process for piloting and guiding a projectile in the terminal phase in which the correction is obtained by means of a barrel of (n) impellers with lateral nozzles. Combustion of the first is triggered off when the rotational speed of the sight line reaches a triggering threshold. The mean thrust of each of the impellers which discharge successively and completely during a single revolution of the projectile is directed in the same direction located with respect to an absolute system of reference axes tied to the target.

Abstract: A system for controlling the attitude of a cylindrical body moving in a fluid, including controlling the attitude of this body in roll, which is applicable to controlling the roll of projectiles, rockets and missiles.The system includes a finned rotary empennage concentric with the body, a torque-transmitting means connecting the body and the empennage, and an attitude detector means mounted integral with the body. The attitude detector means produces an electrical signal which is proportional to the divergence of the actual and desired attitude of the body. This signal is amplified and applied to the torque-converting means which changes the rotation of the empennage relative to the body, to thereby correct the attitude of the body by such relative rotation and the dynamic force exerted on the fins of the empennage by the fluid in which the body is moving.