Search Images Maps Play YouTube News Gmail Drive More »
Sign in
Screen reader users: click this link for accessible mode. Accessible mode has the same essential features but works better with your reader.

Patents

  1. Advanced Patent Search
Publication numberUS3550501 A
Publication typeGrant
Publication dateDec 29, 1970
Filing dateMay 29, 1968
Priority dateMay 29, 1968
Publication numberUS 3550501 A, US 3550501A, US-A-3550501, US3550501 A, US3550501A
InventorsMunger John R, Tate Sherman E
Original AssigneeUs Army
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Rocket launcher for launching rockets with high initial acceleration
US 3550501 A
Abstract  available in
Images(1)
Previous page
Next page
Claims  available in
Description  (OCR text may contain errors)

United States Patent [56] References Cited UNITED STATES PATENTS 1,347,125 7/1920 Schneider.......

[72] Inventors John R. Munger Huntsville;

, Sherman E. Tate, l-lartselle, Ala. ['21] Appl.No. 733,193

et al 2,867,153 1/1959 Hirsch............ 3,071,073 1/1963 Ammann........ 3,134,330 5/1964 Batou.......

3,282,161 11/1966 MacDonald, Jr

[22] Filed May 29, 1968 {45] Patented Dec. 29, 1970 [73] Assignee The United States of America as represented by the Secretary of the Army Primary Examiner-Samuel W. Engle Attorneysl-1arry M. Sarag ovitz, Edward J. Kelly, Herbert Earl and J. Keith Fowler ROCKET LAUNCHER FOR LAUNCHING ROCKETS WITH HIGH INITIAL ACCELERATION DEDICATORY CLAUSE The invention described herein may be manufactured, used, and licensed by or for the Government for governmental purposes without the payment to us of any royalty thereon.

BACKGROUND OF THE INVENTION The present invention relates to rocket launchers and recoil type guns wherein a reverse gun action is effected.

Prior art mechanisms of this type rely primarily on closed breech boost or gun boost. While these mechanisms are efficient, they require a very heavy, bulky barrel or tube. These are more difficult to transport and are inherently more expensive than is desired.

SUMMARY OF THE INVENTION An improved rocket launcher, which functions on a reversegun" concept, is provided. Thus, high initial acceleration is effected due to the pressure created between the solid propellant and the face of the mandrel, this pressure being applied prior to the effective propelling force created at the rocket nozzle and, thus, being complementary thereto.

BRIEF DESCRIPTION OF THE DRAWING FIG. 1 is an axial cross-sectional view, with portions broken away, of a loaded rocket launcher according to the present invention; and

FIG. 2 is a view similar to that of FIG. 1, but showing a modified form of the invention.

DESCRIPTION OF THE PREFERRED EMBODIMENTS In the drawing, FIG. 1, reference numeral 1 indicates generally a rocket launcher according to the present invention including a launch tube or firing tube 2 supported within a tubular housing 4 carried by launcher support member 6. Support member 6 is pivotally secured at 8 to the launcher base I and is supported in elevation at its other end at I2 by the upper end of the bipod mount 14. Rocket 20, shown in the loaded position within the launch tube, includes a cylindrical motor casing 22, a nose section 24 on the fore end of the casing, and an exhaust nozzle 25 on the aft end of the casing. A removable end plate 26 closes the aftend of the nozzle and is provided with an axial bore 28. A solid propellant grain 30 is disposed within the motor casing in a conventional manner. The grain is formed with a burning surface defined by an axial bore 32 extending from its aft end to a predetermined point short of the fore end thereof. A mandrel 36 is removably secured as at 38 to the launcher base and extends coaxially through end plate bore 28 and coaxially within grain bore 32. The mandrel may be of any design which permits rigid attachment to the launcher base. In addition, the mandrel used in casting the motor grain may be left therein and utilized. For igniting the propellant, an igniter 40 is placed at the fore end of the mandrel. While the igniter is shown in its preferred location secured to the fore end of the mandrel, the same may also be supported within the space 42 between the fore end of mandrel and the end of the grain bore; or the igniter may be secured to the propellant grain at the end of the grain bore. The igniter may be activated electrically by external means (not shown) connected thereto as by conductors 43.

Referring now to FIG. 2, wherein a modified form of the invention is illustrated, mandrel 50 is arranged for telescoping action. Thus, tubular mandrel 50 is formed with a piston 52 on its fore end for sliding engagement within outer cylinder 56.

Spring-loaded balls or detent means 54 provided in the peripheral wall of the piston are adapted for interlocking engagement within the annular mating groove 58 provided in the inner wall of cylinder 56.

OPERATION OF THE PREFERRED EMBODIMENTS OF THE INVENTION In the embodiment of FIG. I when the igniter is activated, the propellant will burn initially in a substantially closed system thereby producing a high pressure for forcing the missile away from the mandrel. Hence, the firing of the device according to this invention is similar to a gun boost wherein the pressure volume work of the gases imparts energy to the rocket at a rate comparable to that of a projectile in a gun until the rocket has traveled the length of that portion of the mandrel which extends within the rocket motor grain. When the aft end of the propellant grain passes the upper end of the mandrel, i.e., when the mandrel has been withdrawn from the grain bore, the rocket motor operates with its nozzle in conventional fashion.

The operation of the embodiment of FIG. 2 is similar to that of FIG. 1 with the sole difference being in the telescoping action of the mandrel. Thus, upon activation of the igniter means, as pressure builds up in chamber 42, the missile moves toward the fore end of the launch tube carrying cylinder 56 therewith. Thus, the telescoping mandrel moves from its collapsed condition (as depicted in FIG. 2) to an extended condition wherein the detent balls 54 are engaged matingly within groove 58. Increased pressure in the chamber 42 then causes the missile to move coaxially along the outer cylinder 56 until the same has traveled the entire length of the cylinder. Accordingly, this arrangement provides for a longer time period during which the missile grain engages the mandrel, the telescoping arrangement operating to extend the effective length of the mandrel.

Since certain changes may be made in the structure described without departing from the scope of the invention, it is intended that all matter contained in the above description, or shown in the accompanying drawings, shall be interpreted as generally illustrative and not in a strictly limiting sense.

We claim:

I. In a rocket launcher for launching a rocket, said rocket being defined by a motor having an exhaust nozzle on its aft end, a body portion, and a nose portion; a solid propellant grain disposed within said body portion, said propellant grain being formed with an axial bore opening into the motor exhaust nozzle and extending forwardly a predetermined distance short of the forward end of the grain, an end closure removably secured on the aft end of the motor exhaust nozzle, said end closure having a central aperture formed therein, said launcher comprising: a rigid mount; a firing tube secured at its aft end to said mount; support structure secured to said tube adjacent the fore end thereof for maintaining the tube in elevated disposition; a telescoping mandrel removably secured at its aft end to said mount and extending through the aperture in the end closure, said mandrel extending into the grain bore a predetermined distance short of the fore end of said bore so as to define a space between the end of said mandrel and the end of said bore; said mandrel including an inner cylindrical member and an outer cylindrical member, said inner cylindrical member having a piston on its fore end, detent means carried by said piston, said outer cylindrical member having an annular groove within its aft end, said detent means being adapted for interlocking engagement in said groove when said mandrel is in an extended condition; and igniter means disposed within said space for igniting said propellant.

Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US3981225 *Mar 24, 1975Sep 21, 1976Smith Matthew SLauncher arrangement for rocket powered round
US6379207 *Jun 12, 1998Apr 30, 2002S.E.I.B. SarlInflatable life buoy launcher gun
US8967046Nov 30, 2012Mar 3, 2015Alliant Techsystems Inc.Gas generators, launch tubes including gas generators and related systems and methods
US20090308274 *Jun 11, 2008Dec 17, 2009Lockheed Martin CorporationIntegrated Pusher Plate for a Canister- or Gun-Launched Projectile and System Incorporating Same
US20110162247 *Dec 22, 2010Jul 7, 2011Diehl Bgt Defence Gmbh & Co. KgGrenade and grenade launching apparatus
DE102009060658A1 *Dec 22, 2009Jun 30, 2011Diehl BGT Defence GmbH & Co. KG, 88662Granate und Granatabschussvorrichtung
DE102009060658B4 *Dec 22, 2009Nov 15, 2012Diehl Bgt Defence Gmbh & Co. KgGranate und Granatabschussvorrichtung
Classifications
U.S. Classification89/1.816, 89/1.3, 89/1.814, 89/1.819
International ClassificationF41F3/04, F41F3/00
Cooperative ClassificationF41F3/04
European ClassificationF41F3/04