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

Patent metadata

Field	Value
Publication number	US-12018913-B2
Application number	US-201917262607-A
Country	US
Kind code	B2
Filing date	Jul 28, 2019
Priority date	Jul 30, 2018
Publication date	Jun 25, 2024
Grant date	Jun 25, 2024

Abstract

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.

First claim

The invention claimed is:

1. A rocket-based armament launchable from a tubular launcher that comprises:
an effective payload;
a rocket motor that is structurally connected to the effective payload and is adapted from the time of an ignition of the rocket motor to propel the effective payload; and
a pyrotechnic assembly that has been adapted, once actuated, to eject the rocket motor and said effective payload from said tubular launcher and to ignite said rocket motor;
wherein said armament is characterized in that said armament also comprises:
a. a gas dispersion assembly which, when said rocket armament is not encased in the tubular launcher, prevents the ignition of said rocket motor even if said pyrotechnic assembly is actuated, said dispersion assembly comprising:
a dispersing openings array that is connected to a flow of gas mass-produced by the 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 the gas dispersion assembly; and

b. a cutting and separation assembly that is actuated by gas pressure from said rocket motor for mechanically cutting a structural connection between the rocket motor and the effective payload and separate the rocket motor and the effective payload during flight.

2. The rocket armament of claim 1 , wherein said cutting and separation assembly comprises:
a cutting piston located at an end of said rocket motor and stressed on a side by gas pressure that is formed by the ignition of said rocket motor in a linear motion towards said structural connection between the rocket motor and the effective payload to mechanically cut the structural connection; and
a springy means that rests on said structural connection and stresses said cutting piston on another side opposite the 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.

3. The rocket armament of claim 1 , wherein said armament is a 40 mm armament that is launchable from said tubular launcher, wherein the tubular launcher is a grenade launcher or a single-use disposable canister.

4. 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.

5. 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.

Assignees

• Rafael Advanced Defense Systems Ltd

Inventors

• Tal Nadav
• Teper Yossi
• Guller Evgeny
• Ziv Jakov

Classifications

• F42B3/006

  Explosive bolts; Explosive actuators (explosive valves F16K13/06; explosive cutting B23D15/145; explosive switches H01H39/00; pyrotechnical actuators F15B15/19) · CPC title

• F42B39/20

  Packages or ammunition having valves for pressure-equalising; Packages or ammunition having plugs for pressure release, e.g. meltable {; Blow-out panels; Venting arrangements (ventilating arrangements on packages formed from foldable or erectable blanks B65D5/4295; packages with pressure-relief valves incorporated in a container wall B65D77/225)} · CPC title

• F42C15/31

  generated by the combustion of a pyrotechnic or explosive charge within the fuze · CPC title

• F42C15/28

  operated by flow of fluent material, e.g. shot, fluids (F42C15/26 takes precedence) · CPC title

• F42B30/04 Primary

  Rifle grenades · CPC title