A recoilless, slideless repeating magazine-fed (19) weapon, comprising a hammer (9), a hammer pull rod (7), a trigger spring (8) and a safety (28). The open breech (15) connects directly to the open, expanding cross-section funnel (18), and furthermore the funnel (18) has an extractor (24) on the side which connects to the forend (21) through a funnel pull rod (20), and furthermore the magazine (19) is connected to the magazine well (19/1) at the bottom of the open breech (15) with a magazine holding pin (19/6). The weapon is compatible with a variety of magazines (19), including box magazines (with one or more rows of cartridges), drum magazines, or helical magazines.

An optical scope mounting system is disclosed including a back-sloped base mount and a pair of rings, to cooperate with the base mount, for positioning an optical scope laterally of the weapon on which it is mounted. The optical mounting system finds utility on rocket propelled grenade (RPG) launchers. The back-sloped base mount creates a divergence between the centerline of the bore of the RPG launcher and the line of sight through the optical scope.

The present embodiment relates to a guided missile launch system comprising a launch tube with a guided missile space for receiving a guided missile and with a cartridge space for receiving a blank cartridge, further comprising a handle piece mountable on the launch tube and separable from the launch tube, the handle piece having a striking pin system for firing the blank cartridge.

Rocket armament launchable from a tubular launcher with an outside launcher non-ignition securing and motor separation during flight and a method to prevent the ignition of the armaments rocket even in the event of actuation of the armaments pyrotechnic assembly, which normally serves to eject the armament from the launcher and to ignite its rocket motor, wherein the armament comprises a gas dispersion assembly, which when the armament is not encased in the tubular launcher, prevents the ignition of the rocket motor even if the armaments pyrotechnic assembly is actuated; and a cutting and separation assembly that is actuated by the pressure of the rocket motor gases for mechanically cutting a structural connection between the rocket motor and the armaments effective payload and separate them during their flight.

A recoilless, slideless repeating magazine-fed (19) weapon, comprising a hammer (9), a hammer pull rod (7), a trigger spring (8) and a safety (28). The open breech (15) connects directly to the open, expanding cross-section funnel (18), and furthermore the funnel (18) has an extractor (24) on the side which connects to the forend (21) through a funnel pull rod (20), and furthermore the magazine (19) is connected to the magazine well (19/1) at the bottom of the open breech (15) with a magazine holding pin (19/6). The weapon is compatible with a variety of magazines (19), including box magazines (with one or more rows of cartridges), drum magazines, or helical magazines.

A breech for noise reduction in a recoil-less weapon is described. The breech is adapted to be arranged in fluid communication with a launcher of the weapon to release exhaust gas. The breech comprises a venturi tube. The venturi tube has an inlet at a first end adapted to be connected to the launcher, and an outlet for releasing the exhaust gas at a second end, wherein the area of the outlet is larger than the area of the inlet. The venturi tube further comprises an exhaust gas controlling element formed at the venturi tube structure. The exhaust gas controlling element is arranged to control the release of exhaust gas so as to decrease a sound pressure peak at the weapon. The inner envelope surface of the venturi tube is configured, such that the inner envelope surface does not alter or at least has a very small influence on recoil characteristics of the weapon.

A projectile launch system includes a longitudinally extending launch tube having an inner bore formed therethrough. The launch tube having a metal liner and a composite overwrap, and a firing pin aperture formed in the longitudinally extending launch tube. A firing pin sleeve can be coupled with the metal liner and extend through at least a portion of the firing pin aperture, and a receiver including a launch control system.

A missile includes a rocket motor that has a flow deflector in an expansion region of the rocket motor's nozzle. The flow deflector diverts flow of combustion products away from a safe region that is aft of the missile. The safe region protects an operator of a launcher used to fire the missile, such as a shoulder-fired launcher, from harm caused by the combustion products. The flow deflector may be small enough such that it does not significantly adversely affect the performance of the rocket motor. The presence of the flow diverter may allow for the rocket motor to be started sooner in the flight of the missile, or at a distance closer to the operator, while still keeping the operator safe. The flow deflector and supporting structure, such as struts, may be additively manufactured with at least an aft part of the nozzle, as a continuous single-piece part.

A breech for noise reduction in a recoil-less weapon is described. The breech is adapted to be arranged in fluid communication with a launcher of the weapon to release exhaust gas. The breech comprises a venturi tube. The venturi tube has an inlet at a first end adapted to be connected to the launcher, and an outlet for releasing the exhaust gas at a second end, wherein the area of the outlet is larger than the area of the inlet. The venturi tube further comprises an exhaust gas controlling element formed at the venturi tube structure. The exhaust gas controlling element is arranged to control the release of exhaust gas so as to decrease a sound pressure peak at the weapon. The inner envelope surface of the venturi tube is configured, such that the inner envelope surface does not alter or at least has a very small influence on recoil characteristics of the weapon.

A missile includes a rocket motor that has a flow deflector in an expansion region of the rocket motor's nozzle. The flow deflector diverts flow of combustion products away from a safe region that is aft of the missile. The safe region protects an operator of a launcher used to fire the missile, such as a shoulder-fired launcher, from harm caused by the combustion products. The flow deflector may be small enough such that it does not significantly adversely affect the performance of the rocket motor. The presence of the flow diverter may allow for the rocket motor to be started sooner in the flight of the missile, or at a distance closer to the operator, while still keeping the operator safe. The flow deflector and supporting structure, such as struts, may be additively manufactured with at least an aft part of the nozzle, as a continuous single-piece part.