Abstract: The invention relates to an armored ventilation grille for an opening, the grille including an outer side to be exposed to a projectile shot and an inner side to be applied to the opening, the grille including a plurality of parallel bars, the bars having a V-shaped cross-section, each limb of the V being made of of a blade, the blades being arranged in chevrons in order to form baffles such that at least one blade is located in the trajectory of the projectile shot whatever the incidence may be. The grille according to the invention wherein the outer blades is made an armored material while the inner blades made of a ductile material, the blades all being fixed to transverse members in the bearing ranges in such a way that they can be disassembled.

Abstract: The invention relates to an armoured ventilation grille for an opening, the grille including an outer side to be exposed to a projectile shot and an inner side to be applied to the opening, the grille including a plurality of parallel bars, the bars having a V-shaped cross-section, each limb of the V being made of of a blade, the blades being arranged in chevrons in order to form baffles such that at least one blade is located in the trajectory of the projectile shot whatever the incidence may be. The grille according to the invention wherein the outer blades is made an armoured material while the inner blades made of a ductile material, the blades all being fixed to transverse members in the bearing ranges in such a way that they can be disassembled.

Abstract: This invention relates to a fuel injection system for a ramjet engine of the type comprising a swirling combustion chamber, wherein said system comprises:at least one first injector arranged in the inner part of the corresponding air duct to send, in common with said first injectors of the other individual injection devices, fuel into a common zone of said combustion chamber adjacent said closed end and peripherally defined by said air ducts; as well asat least one second injector arranged in the outer part of the corresponding air duct, to send fuel into a specific zone of said combustion chamber located near the wall thereof, downstream of the opening of the corresponding air duct. The invention is more particularly applicable to the propulsion of missiles.