US3620162A

US3620162A - Rifle launched rocket

Info

Publication number: US3620162A
Application number: US862201A
Authority: US
Inventors: Paul C King
Original assignee: US Department of Navy
Current assignee: US Department of Navy
Priority date: 1969-09-30
Filing date: 1969-09-30
Publication date: 1971-11-16
Anticipated expiration: 1988-11-16

Abstract

A RIFLE LAUNCHED ROCKET WHICH COMPRISES A ROCKET MOTOR PROVIDED WITH A BULLET CATCHER AND A WARHEAD WITH A FUSE ASSEMBLY AND MEANS FOR ATTAHCMENT OF THE ROCKET TO THE MUZZLE OF A FILID RIFLE. IN OPERATION WHEN THE RIFLE IS FIRED THE COMBINATION OF THE BULLET MOMENTUM AND THE GASES FROM THE FIRED CARTRIDGE CREATE SUFFICIENT IMPETUS TO LAUNCH THE ROCKET FROM THE BARREL OF THE RIFLE. SIMULTANEOUSLY THE BULLET IGNITES THE ROCKET MOTOR WHICH PROPELS THE ROCKET TO THE TARGET AT HIGH SPEED. WHEN THE FORWARD END OF THE ROCKET WHICH CARRIES THE WARHEAD AND FUSE ASSEMBLY HITS A TARGET, THE FUSE INITIATES DETONATION OF THE WAREHEAD. THIS DEVICE PROVIDES A MEANS FOR BOOSTING THE RANGE AND DESTRUCT CAPABILITY OF SMALL ROCKETS CARRYING HIGH EXPLOSIVES OR VARIOUS TYPES OF CHEMICALS.

Description

Nov. 16, 1971 P. c. KING RIFLE LAUNCHED nocxmw Filed Sept. 50. 1969 INVI'QN'IHR.

PAUL C. KING ROY MILLER ATTORNEY.

US. Cl. 10265.2 3 Claims ABSTRACT OF THE DISCLOSURE A rifle launched rocket which comprises a rocket motor provided with a bullet catcher and a warhead with a fuse assembly and means for attachment of the rocket to the muzzle of a field rifle. In operation when the rifle is fired the combination of the bullet momentum and the gases from the fired cartridge create suflicient impetus to launch the rocket from the barrel of the rifle. Simultaneously the bullet ignites the rocket motor which propels the rocket to the target at high speed. When the forward end of the rocket which carries the warhead and fuse assembly hits a target, the fuse initiates detonation of the warhead. This device provides a means for boosting the range and destruct capability of small rockets carrying high explosives or various types of chemicals.

GOVERNMENT INTEREST The invention described herein may be manufactured and used by or for the Government of the United States of America for governmental purposes without the payment of any royalties thereon or therefor.

BACKGROUND OF THE INVENTION The invention relates to a rifle launched rocket.

In the field of small weapons, particularly, objects designed to be thrown, dropped, projected, or propelled by a hand operated, individually carried apparatus, such as a field rifle, the need exists for greater target capability. Hand and gun tossed grenades and small launchers have been developed and used as a means of defense or offense. However, these missiles generally have limited effectiveness. The present invention will overcome some of the difliculties encountered and provide an effective means of boosting the range and destruct capability for one handling a single Weapon.

DESCRIPTION OF THE DRAWING FIG. 1 is a view of the rocket positioned on a field rifle in accordance with this invention;

FIG. 2 is a longitudinal section of the rocket attached to the muzzle end of a field rifle; and

FIG. 3 is a section of the fin assembly.

DESCRIPTION OF THE INVENTION Referring now to the drawing wherein similar numbers refer to similar parts there is shown in FIG. 1, rocket embodying this invention positioned on the muzzle end of a field rifle 11. In FIG. 2 rocket 10 is shown in section. It comprises a rocket motor 12, the rear end of which encloses a nozzle 13, a bullet assembly attached by threaded or other means to the forward end of said motor 12 at point 14; and a warhead 16 secured to the forward end of catcher assembly 15 by suitable means such as sliding over a flange or by threaded means. Rocket motor 12 comprises a combustion chamber 17 formed by a hollow metal casing 18 lined with insulation material 19, such as phenolic asbestos, and containing therein an internal perforated solid propellant grain 20. Grain 20 is cast into said chamber 17, or Wrapped with insulation material 19 and secured to the walls of said United States Patent 0 chamber. The insulation also functions as an inhibitor against ignition of the grain. Nozzle 13, an extension of casing 18 which forms the chamber, is a conventional type for exit of the thrust producing high pressure gas produced upon ignition of propellant grain 20. The gases pass through the nozzle throat 21 which is provided with insert 22 composed of graphite or phenolic asbestos bonded to casing 18 with a cement designated 23. A fin assembly 24, attached to the nozzle end of rocket 12 and the muzzle end of rifle 11, provides for stabilization of rocket 10. Pin assembly 24 comprises four fins designed generally by numeral 25, which are attached to an inner ring member 26 adapted to closely engage the outer surface of casing 18 of the end of said rocket nozzle 13 and the outer surface of the muzzle end of the rifle 11. That part of ring member 26 which engages casing 18 is secured thereto by welding or other suitable means. The outer edges of fins 25 are joined by close fit or are cemented to an outer ring member 27. Two ports designated 28 are positioned opposite each other in the nozzle section 13 near the point of attachment of inner ring 26. Ports 2-8 serve to release the overpressure caused by gases escaping from the cartridge of the rifle. Bullet catcher 15 comprises a metal plate 29, having a forward surface 30 provided with a flanged edge 31 Which fits into the forward end of rocket casing 18 and the rear surface 32 which is concave and closes the cylindrical shaped warhead 16; a cylindrical metal tube 33 which is mounted on the center of said plate and is positioned through the middle of combustion chamber 17 with the same axis as said nozzle throat 21. Tube 33 is provided with a liner 34 comprising a plurality of ceramic discs. The discs at the forward end of the tube adjacent plate 29 are solid, and each of the others are provided with a center bore of varying dimensions so that when they are stacked one on the other a single conical shaped bore 36 is formed. Liner 35 acts to stop the bullet as it passes from the gun through the rocket nozzle into bore 36 of said assembly. The warhead 16 comprises a metal cylinder 37 substantially filled with a high explosive 38 and secured by threads or other suitable means to the concave side 32 of said bullet catcher plate 29. A fuse mechanism 39 is threaded in the nose of said warhead 16 for detonation of the warhead high explosive 38.

A plastic hood 40 is shown covering the main components of said mechanism. The fuse body 41 is of steel and is secured by threaded means into the nose of warhead 16. The detonating train 42 is shown positioned through the center of the fuse and in contact with a booster charge 43 which is adjacent high explosive 38.

Many conventional impact fuses are available which initiate detonation upon impact of a target. An example of a suitable fuse is described in detail in Pat. No. 2,948,219, which issued to W. F. Sapp in August 1960, and is assigned to the United States of \America as represented by the Secretary of the Navy. A delay fuse can also be used, such as described in Pat. No. 3,162,127 which issued in December 1964, and is also assigned to the Government. The delay fuse will permit the rocket to penetrate the target before detonating the explosive carried in the warhead.

The liner for the bullet catcher comprises ceramic discs made from boron carbide. Other ceramics which are temperature and pressure resistant can be used.

In operation rocket 10 is attached to the muzzle of the gun 11. When the gun is fired the bullet passes through the nozzle throat 21 of motor 12 into bore 36 which catches the bullet. The bullet impact and gun gases launch the rocket, and ignite the propellant grain. Burning of the propellant creates suflicient thrust to propel 3 the rocket to the target. When the rocket hits or approaches the target, the fuse is initiated whereupon detonation of the high explosive carried in the warhead causes destruction.

The term rocket used herein means an aggressive missile, carrying a warhead containing a payload of high explosives or other chemicals, that is projected from a launcher (a rifle) toward a target by a rocket power plant or a solid rocket combustion unit. This rocket can be used on various types of rifles without modification of the rifle. It is easily portable and simple to use.

The solid propellant used in the rocket motor is generally of the composite type, although the homogeneous (double-base) propellant can also be used. Examples of the composite propellants are the polysulfide propellants which are a mixture of granular ammonium perchlorate suspended in a polysulfide synthetic rubber; the polyurethane propellants which are prepared by the reaction of di-isocyanate material with polyglycols containing functional hydroxyl groups and subsequent addition of ammonium perchlorate along with aluminum powder to increase performance; and plastisol perchlorate propellants which are made by dispersing an inorganic oxidizer in a fluid fuel mixture made of approximately equal parts of finely divided polyvinyl chloride and a nonsoluble plasticizer. There are many other composite grains which can be used. The double-base grain is a gelatinized colloidal mixture consisting of nitrocellulose and an explosive plasticizer usually nitroglycerin.

The casing was steel. Other suitable materials can be used such as aluminum and many of the plastics depending on shelf-life and compatibility of materials.

The warhead was filled with the high explosive, cyclotetramethylenetetranitramine (HMX), or cyclotrimethylenetrinitramine (RDX). Other high explosives such as composition C and diaminotrinitrobenzene (DATB) could be used, as Well as some of the anti-personnel agents and gelled fuels in use today.

What is claimed is:

1. A rifle launched rocket consisting essentially of a rocket motor provided with a fin assembly and means for attachment at its nozzle end to the muzzle of a rifle;

a bullet catcher assembly secured to the forward end of said motor; and

a warhead provided with a fuse and containing a high explosive mounted to the forward end of said bullet catcher assembly;

said rocket motor consisting of a combustion chamber closed at the forward end by a bullet catcher assembly and having an opening at the aft end through an exhaust nozzle and an internal perforated propellant grain bonded to the combustion chamber wall;

said bullet catcher consisting of a metal plate; a cylindrical tube closed at one end by said plate; said tube being projected into the center of said combustion chamber adjacent said nozzle and having the same axis as said nozzle; a plurality of ceramic discs stacked inside said tube to form a liner;

said discs at the base of said tube being solid and the remainder of said discs being provided with a center bore of varying dimensions whereby said stacked discs form a single conical bore which catches the bullet from the rifle as it passes through the nozzle throat whereupon the bullet impact and gun gases act to launch said rocket.

2. The rocket in accordance with claim 1 wherein said warhead comprises a metal cylinder substantially filled with a high explosive being a member selected from the group consisting of cyclotetramethylenetetranitramine, and cyclotrimethylenetrinitramine, and

an impact fuse positioned in the nose of said cylinder whereby said explosive detonates when said fuse strikes a target.

3. The rocket in accordance with claim 2 wherein said fin assembly and means for attachment of said rocket to the muzzle end of a rifle comprises a first ring member adapted to closely engage the outer surface of the end of the nozzle of said rocket and the outer surface of the muzzle end of said rifle; said member being welded to said nozzle surface;

four fins suitably attached to the outer surface of said ring member, and

a second ring member adapted to engage the outer edges of said fins.

References Cited UNITED STATES PATENTS 1,900,790 3/1933 Brandt 102-652 2,853,008 9/195& Bowles 10265.2 2,998,772 9/1961 Land 102--56 3,007,410 11/1961 Blacker 244-3.3 3,140,660 7/1964 Wyser 102-652 3,439,615 4/1969 iForman et a1. 10265.2

VERLIN R. PENDEGRASS, Primary Examiner