The present disclosure provides a propulsion system with a retardant set between two sections of propellant for delaying the combustion and reducing the generated smoke or heat while launching the propulsion system.

The present disclosure provides a propulsion system with a retardant set between two sections of propellant for delaying the combustion and reducing the generated smoke or heat while launching the propulsion system.

The present disclosure provides a throwing device with a launcher and a propulsion system. The propulsion system comprises a retardant set between two sections of propellant for delaying the combustion and reducing the generated smoke or heat while launching the propulsion system. The launcher comprises: a tube for containing the propulsion system; and a trigger for triggering the ignition cartridge. A screw hole is in center of a bottom of the first chamber; nozzles are located around the screw hole; and a collar with a hole fixed in the bottom of the first chamber, wherein the ignition cartridge is fixed in the screw hole by the collar. The ignition cartridge comprises an explosive primer, and the launcher further comprises a firing pin triggered by the trigger to hit the explosive primer.

The present disclosure provides a throwing device with a launcher and a propulsion system. The propulsion system comprises a retardant set between two sections of propellant for delaying the combustion and reducing the generated smoke or heat while launching the propulsion system. The launcher comprises: a tube for containing the propulsion system; and a trigger for triggering the ignition cartridge. A screw hole is in center of a bottom of the first chamber; nozzles are located around the screw hole; and a collar with a hole fixed in the bottom of the first chamber, wherein the ignition cartridge is fixed in the screw hole by the collar. The ignition cartridge comprises an explosive primer, and the launcher further comprises a firing pin triggered by the trigger to hit the explosive primer.

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 rocket motor ignitor assembly that may be used in a shoulder-fired rocket system. The rocket motor ignitor assembly may include a delay ignitor operable to ignite a rocket motor propellant, a stab firing pin operable to activate the delay ignitor by contacting the delay ignitor, and a biasing element coupled with the stab firing pin. The stab firing pin may have a length to diameter ratio greater than two, as well as relief grooves allowing air to vent past the stab firing pin as it travels toward the delay ignitor to activate it. The rocket motor ignitor assembly may also include a guide stop to limit penetration of the stab firing pin into the delay ignitor.

A rocket motor ignitor assembly that may be used in a shoulder-fired rocket system. The rocket motor ignitor assembly may include a delay ignitor operable to ignite a rocket motor propellant, a stab firing pin operable to activate the delay ignitor by contacting the delay ignitor, and a biasing element coupled with the stab firing pin. The stab firing pin may have a length to diameter ratio greater than two, as well as relief grooves allowing air to vent past the stab firing pin as it travels toward the delay ignitor to activate it. The rocket motor ignitor assembly may also include a guide stop to limit penetration of the stab firing pin into the delay ignitor.

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 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.