Rocket armament launchable from a tubular launcher with an outside launcher non-ignition securing and motor separation during flight

A gas dispersion assembly of a pyrotechnic assembly that can be fitted in a rocket-based armament that is launchable from a tubular launcher, wherein said gas dispersion assembly comprises:

• a dispersing openings array that is connected to a flow of gas mass-produced by an actuation of said pyrotechnic assembly, and is encaseable by an interior surface of said tubular launcher in a manner that prevents dispersion of gas through the gas dispersion assembly;
• and
• a bushing member that is formed as a piston, one end of which is located inside an ejection nozzle of said rocket motor, in a manner that prevents the ignition of the rocket motor by the force of the gas mass-produced by the actuation of said pyrotechnic assembly, if said dispersing openings array is not encased, and therefore enables the dispersion of gases through said array;
• wherein the gas dispersion assembly is configured to prevent the ignition of the rocket motor of said armament when the rocket armament is not encased in the tubular launcher, even if said pyrotechnic assembly is actuated.

A cutting and separation assembly, comprising:

• a cutting piston located at an end of a rocket motor of a rocket armament and stressed on a side by gas pressure that forms from an ignition of said rocket motor to a linear motion towards a structural connection between the rocket motor and an effective payload of the rocket armament to mechanically cut the structural connection;
• a springy means that rests on said structural connection and stresses said cutting piston on another side opposite said linear motion, and once the structural connection is cut, the cutting and separation assembly helps to thrust said rocket motor and separate the rocket motor from the effective payload;
• a dispersing openings array that is connected to a flow of gas and is encaseable by an interior surface of a tubular launcher;
• and
• a bushing member that is formed as a piston, one end of which is located inside an ejection nozzle of said rocket motor, in a manner that prevents the ignition of the rocket motor by the flow of gas if the dispersing openings array is not encased;
• wherein the cutting and separation assembly is actuated by gas pressure from the rocket motor to mechanically cut the structural connection between the rocket motor and the effective payload and separate the rocket motor and the effective payload during flight.