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 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.

The device of the present disclosure is a weapon. The weapon having a CO.sub.2 powered projectile which is fired from the weapon, used principally for self-defense. The projectile is generally rocket shaped wherein the front end of the rocket can be formed by a rounded shape of a front of a CO.sub.2 cylinder. The impact of the rocket projectile on a human could cause some pain, depending upon exactly what part of the body it hits. The impact could also cause some loss of balance to a human, due to the impact.

The device of the present disclosure is a weapon. The weapon having a CO.sub.2 powered projectile which is fired from the weapon, used principally for self-defense. The projectile is generally rocket shaped wherein the front end of the rocket can be formed by a rounded shape of a front of a CO.sub.2 cylinder. The impact of the rocket projectile on a human could cause some pain, depending upon exactly what part of the body it hits. The impact could also cause some loss of balance to a human, due to the impact.

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.

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 canister for storing and launching a self-propelled projectile comprises: a) an inner layer comprising an aluminum foil; b) a top layer consisting of an injected thermoplastic polymer; and c) optionally, a primer and/or a topcoat.

A canister for storing and launching a self-propelled projectile comprises: a) an inner layer comprising an aluminum foil; b) a top layer consisting of an injected thermoplastic polymer; and c) optionally, a primer and/or a topcoat.

A multi-aiming point reticle for use in an optical scope is described including both range-finding and aiming points. The reticle, and scope incorporating the same, finds special utility for combination with a rocket propelled grenade (RPG) launcher to hit targets at extended distances. A method of operation is also described.

A multi-aiming point reticle for use in an optical scope is described including both range-finding and aiming points. The reticle, and scope incorporating the same, finds special utility for combination with a rocket propelled grenade (RPG) launcher to hit targets at extended distances. A method of operation is also described.