Abstract: The invention pertains to a system and method for transmitting temporal data relating to the starting of a device placed in a missile launched from a carrier system. The command to fire the missile is transmitted to the missile from the carrier system by means of a firing control wire. The method consists in using the control wire to also transmit the temporal data to the device specifying when to start up the device after the missile has been launched.

Abstract: Disclosed is a device used to bend the end of the trajectory of a rocket in the desired plane without making costly and complicated servo-control mechanisms necessary. A cardan type assembly is formed by a section of the projectile and an internal frame, a gyrostat being mounted in the internal frame. The section carries the control instrument. The device can thus be used to keep the control instrument in a stable roll position throughout the trajectory. It is thus possible to bend the trajectory in a defined direction so as to attack targets from the top with high precision. The device can be adapted to infantry rockets, aeronautical rockets and in general, to short-range projectiles.

Abstract: Disclosed is a system for the holding of multiple warheads, placed in a missile rotating on its longitudinal axis and dropped in trajectory through an end of the missile. Each stage of the warhead includes at least two distinct parts which have to be separated laterally at the moment of dropping, the missile including a casing inside which the warhead is placed. For each stage, mechanisms to fix the parts at the said stage are arranged so that each stage forms a compact unit so as not to cause major radial stresses against the casing due to the centrifugal force created by the rotating missile. The fixing mechanisms are retractable at the moment when the parts are dropped, by means of inertia blocks that are subjected to the centrifugal force. The invention can be applied to sub-munitions and mortar shells.

Abstract: A system is provided for guidance, by laser beam and pyrotechnic thrusters, of one or a number of carriers such as missiles which are intended to intercept maneuvering targets such as aircraft, helicopters or tanks. Guidance of the carrier is performed partly from the ground by means of a laser beam (beam-rider guidance) which tracks the target and partly by means of pyrotechnic thrusters placed on board the carrier. At each instant, the carrier thus "knows" its position with respect to the ideal flight path provided by the laser beam. The carrier corrects its flight path by triggering a pyrotechnic thruster when its distance with respect to the ideal flight path is greater than a predefined threshold value and when its radial velocity to the ideal path is lower than a predefined threshold.

Abstract: A wind power or hydraulic power machine with axial feed, radial outflow and variable geometry vanes is disclosed. This machine has a support that channels the flow, in limiting the escape flows to the maximum, and provides protection in giving to this wind power or hydraulic power machine excellent resistance to axial stresses, and plays the role of an inertia wheel.

Abstract: Disclosed is a device designed to close a munitions compartment of a rocket and to be ejected just before the munitions so as to open the compartment. This device has a lid locked with a key and an inflatable balloon used to release the lid from the key and to dismantle the device without breaking it, by completely expelling the lid.

Abstract: The invention relates to bombs intended to be released at a very low altitude so as to damage high mechanical resistance surfaces and more particularly antirunway bombs equipped with a downward or acceleration propulsive unit. Each bomb comprises means for braking and orienting it during its initial fall, so as to position the bomb in a plane activating an upward propulsive unit. These means are formed of at least one parachute placed at the head of the bomb. With the activation position reached, the upward propulsive unit causes the bomb to rise and, during the final fall of said bomb, a downward propulsive unit, placed in front of the upward propulsive unit, accelerates the final fall of the bomb so as to accumulate high kinetic energy at the time of impact on the ground.

Abstract: A charge releasable from a carrier, such as a charge having to be activated at the moment of release, is provided with an activating device with a safety system to prevent its untimely activation. The triggering means are activated by means of the activating device comprising a cable connected to the carrier. At the moment of release, the cable controls the activating device which initiates the triggering means by means of an internal mechanical link. All the elements are placed inside the charge. Moreover, the activating device constitutes a safety device to prevent the activation of the charge so long as it is not released.

Abstract: The device of the invention provides for the substantially constant unfolding of unfoldable fins on a guided missile without damaging the bearing structure or the fin itself. The device comprises a deformation part placed around a bearing neck that is joined to the fin. Means are used to convert the rotational kinetic energy due to the unfolding of the fin into translational energy. These means comprise, in particular, a compression ring which is displaced and compresses the deformation part in conjunction with the rotation of the bearing neck due to the unfolding of the fin. The invention can be used in missiles, self-propelled rockets and similar devices.

Abstract: A projectile forming the head of a carrier has a defined balllistic trajectory and contains sub-munitions ejected, at a given moment in the trajectory of the projectile, in a controlled direction. In the projectile, the sub-munitions are arranged so as to have a single direction, namely with the head of the sub-munition facing the front of the projectile, in one or more rows. In each row, the shells of the sub-munitions are tangential to one another and their fin systems ar placed in one another in a self-locking way. The projectile further comprises securing means among the sub-munitions and between these interstitial spaces are further filled with a powdery material.

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 multi-head military charge for dispersing multiple warheads from a vehicle has a carrier structure for carrying the projectiles. The carrying structure includes an ejectable casing and a central tube which is substantially coaxial with the longitudinal axis of the carrying vehicle. The central tube holds an annular support upon which the projectiles rest. A plurality of resilient securing devices hold the projectiles onto the annular support member. Each securing device has a bolt for clamping the securing device to the associated projectile. Ejector pistons are disposed within the carrier structure to propel each of the projectiles outside of the vehicle. Each ejector piston simultaneously releases the bolt clamping the securing device to the associated projectile and projects the projectile outside of the carrying vehicle.

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: The invention provides a lateral gas jet piloting device comprising at least one pair of diametrically opposite nozzles and a sliding bar comprising bistable pneumatic means ensuring reciprocal movement thereof so that the ends of said bar close alternately coupling ducts disposed between the nozzles and an external gas generator.

Abstract: A guided projectile comprising an energy source supplying a gas flow which feeds two pairs of exhaust nozzles, each pair of nozzles being disposed in the corresponding steering plane. Each of these nozzles is provided with a valve for regulating the relative flowrates of the throughflowing gases; this valve being formed essentially by a pivoting vane hinged about an axis; these vanes are interlocked in pairs and positioned by means of two independent mechanisms formed by a deformable parallelogram, the element 40 being the drive element. According to the invention, the directions of the thrust forces created by the nozzles converge at a point P situated on the axis of the projectile and this point P may merge with the center of gravity G of the projectile.