Abstract: A ram jet engine including a combustion chamber ending in a gas injection nozzle, a cruising propulsion unit fee ding liquid propellant into the combustion chamber, and at least one air duct for feeding air intended for combustion of the fuel in the combustion chamber. A rigid tubular element is incorporated into the ramjet engine, with an interior volume of the rigid tubular element being divided into two spaces by an intermediate transverse partition. One of the spaces houses the cruising propulsion unit while the other space houses the combustion chamber. Passages are cut into the intermediate transverse partition to allow feeding of liquid fuel into the combustion chamber, and the air duct is mounted on the tubular element to feed the combustion air through the tubular wall of the tubular element.

Abstract: A propulsion unit for the acceleration of a self-propelled vehicle, such as a missile or a rocket, is loaded with a propellant block secured laterally to the body of the propulsion unit by means of a combustion inhibitor and has an aspect ratio of between 2.5 and 6. The propellant block has one axial duct and at least 6 peripheral ducts and, on its upstream face, is equipped with a fitting secured to the body of the propulsion unit. This fitting provides a free space between the upstream face of the propellant block and the bottom of the body of the propulsion unit, the axial duct and the peripheral ducts opening into this free space via orifices made in the fitting. The combustion gases are ejected rearward without being fed through a nozzle. Sonic velocity is achieved downstream of the ducts.

Abstract: A missile for dropping a batch of armaments having a housing containing propulsion, guidance and control devices and a container having a device therein for holding and ejecting at least one armament group connected to the housing to form the missile. The container has an upper, reinforced flank, two side flanks integral with the upper flank with each having pyrotechnic cords for cutting windows therein, a lower pallet integral with the two side flanks and a pyrotechnic cord for cutting a window therein, and two end frames, the holding and ejecting device being supported on the lower pallet.

Abstract: A procedure for steering a missile launched at low speed from a tube, with the missile being equipped with a propulsion unit system of the type with a propellant fuel charge. The procedure is characterized by the fact that the above-mentioned propulsion unit system is determined and arranged in such a way that it can simultaneously impart to the missile axial propulsive thrust and maneuver forces for steering by force and that the variation of the position of the center of gravity of the missile on its axis as a function of the burn-up of the propellant charge is such that, when the missile leaves the tube, the center of gravity passes through the line of action of the above-mentioned maneuver forces and that, during its flight, makes it possible for torques to develop which generate aerodynamic angles of attack and which produce maneuver forces which are added to those of steering by force.

Abstract: A steering system for a missile provided with aerodynamic surfaces such as fins comprises a gas generator and lateral nozzles through which the gas generated by the gas generator emerges. The nozzles are arranged to lie between adjacent pairs of the aerodynamic surfaces, to project beyond the fuselage of the missile and to have an oblong cross-section, the largest dimension of which lies substantially parallel to the longitudinal axis of the missile. The gas flow through the nozzles is controlled by complete or partial closing of the nozzles. The shape and placement of the nozzles minimizes changes in the aerodynamic characteristics of the missile caused by interaction between the gas jets emerging from the nozzles and the flow of air over the aerodynamic surface of the missile.