Thomson-brandt Armements

Rene Thouron

Jean-Francois Denis

Marc Bernard

Pascal Herrero

Philippe Arnaud

Herve Boubault

This device concerns missiles and in particular those made up of a payload stage in the form of a sub-munitions cargo-container and a propulsion stage. It is intended for the separation and aerodynamic braking of the propulsion stage at the end of its operation so that the sub-munitions can be released without the risk of hitting it. It includes attachment by fitting and locking by shear screws of the two parts of the missile, an inflatable bag arranged in an annular housing, a mobile piston used to separate the two parts of the missile, an initiatable gas generator driving the mobile piston then inflating the bag, means of initiating the gas generator consisting of a primer and firing pin and sensitive to a drop in pressure of the gases in the propulsion stage.

Separation and aerodynamic braking device for the propulsion stage of a

The invention concerns a guided munition, fired from a launching system with a cannon effect. This munition comprising sub-assemblies is supported, during acceleration in the cannon, by a peripheral casing which rests on the first sub-assembly of the munition placed at the front of the munition and is fixed to an ejectable sub-assembly placed at the rear of the munition. The weight of this casing is necessary to withstand the forces due to acceleration and it enables the range of the munition to be increased during the ballistic phase. During the transition from the ballistic phase to the guided phase, the ejectable sub-assembly is ejected, taking with it the casing which thus frees the airfoil surfaces to open out. The casing thus positioned also provides sealing and protection of the sensitive parts and rigidity of the whole of the munition.

Peripheral casing for a guided munition fired with a cannon effect

Disclosed is a gas jet device within at least one movable nozzle in rotation, enabling the creation of one or more thrust forces providing for the guidance-control of a carrier. The guidance-control device has a nozzle unit to which a nozzle is fixed. The nozzle, through the movable nozzle unit, is put into rotation by a rotation-driving device which may be, for example, a rotation-driving device. This pneumatic control device has a control piston provided with a rack device and cylindrical chambers. Through a gas distribution system, these cylindrical chambers undergo pressure variations which give the piston a translational motion. This piston transmits a rotational motion, through a toothed wheel, to the nozzle unit and, hence, to the nozzle. With a gas generator feeding the nozzle or nozzles, and with the guidance-control mode being chosen, all that remains is to position the nozzle or nozzles according to the desired aperture angle to obtain the desired direction.

Guidance/control device for a carrier comprising a movable nozzle

Disclosed is a protective casing for ejectable munitions, having means enabling it to be broken through, this being a necessary operation for the sub-munitions to be ejected, in the next stage, without any difficulty of breaking through and ejection. The fracture lines are obtained by means of screens of high temperature resistant fibers arranged in a plane perpendicular to the internal and external surfaces of the casing. This casing is a part obtained, for example, by fusion and molding. The screen is integrated so that, during the casting of the metal, this metal links up all the fibers forming the screen together. The invention can be applied to protective casings, notably for rockets and munitions carriers.

Protective casing for munitions having means enabling it to be broken

A device for the impervious sealing of a structure, for example a munitions compartment of a rocket, is disclosed. This device comprises an elastic shaped section inside which the edge of the structure and rim of a lid are imperviously embedded. This device further has means for thrusting the lid outwards from the structure. This thrust pushes the rim and/or the edge out of the shaped section through the deformation of this elastic shaped section, and causes the total expulsion of lid. When the device is fitted into a rocket, the moving away of the rim modifies the aerodynamic drag coefficient (Cx) of the rocket. This difference in Cx causes the total expulsion of the lid and thus causes the structure to be opened.

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La Ferte St Aubin, France

Rene Thouron