US3296967A - Incendiary device - Google Patents

Description

am 10, m7

Filed Jan. 29, 1965 INVENTOR.

p Billyll i been used in warfare; for manyyears.

3,296,967 IN GENDIARY DEVICE .l Bounds, Yardley, Pa., and Lowell F. Matthies, Ogden, rUtah, assignors to Thiokol Chemical Corporation,` Bristol, Pa., a corporation of `,Delaware FiledJah. 29, 1965, Ser; No. 428,987 13 Claims. (Cl. 102I.6)

This` invention relates to incendiary devices, and more l, particularly `1to incendiary devices incorporating means yfor self-propulsion thereby becoming capable of traversing the zsurface `of. the: ground while simultaneously carrying outan incendiary mission.

Incendiarydevices are well known in the art and have Examples of` devices of this character are `the torpedo used in submarine warfareand aerial missiles used against terrestrial targets.

These, devices carry explosive and/or incendiary material and are sometimes self-propelled as by means of a prol pellerw driven by an internal combustion motor or a jet device `to a pre-selected target area where the incendiary material is.initiated by some well known means to cause` i destruction by; fire in varying degrees Other devices are dropped `as by `parachute after ejection from an airplane or missile over a target area and initiated to cause incendiarydestruction thereat.

However, there are-disadvantages to` these aforementioned `deviceszlwhich are overcome by the invention hereinto be described. l A chief disadvantage of the iprior art devicesiis that their incendiary effect is necessarily directed `toward relativelyrestricted areas and specific targets; 1; In addition, such conventional devices are usually Min the tform of a bomb or `missile dropped or otherwiselaunched from a flying or ground vehicle and arelinitiated to wreak their incendiary havoc among ground ztroops, buildings `and munitions storage depots of the enemy. But because of their stationary nature,

M after@ initiation, a :relatively great many must be used to destroy the target or` otherwise carry out the objectives cendiary` gasito create a desired incendiary effect on the surrounding terrain `.While simultaneously propelling said delvice` oven a relatively great distance limited only by the amountof material contained.

It `is`another object of this invention to provide a device ofuthecharacter described wherein impact means is provided to initiate combustion of said incendiary material when dropped on a surface upon which it is intended to y operate.

A` still further object of the invention is to provide a device of the `character described wherein parachute means `is `provided to permit dropping the device from an aircraft whereby` the` area of initiation of propulsion thereof canbe `predetermined with some .precision prior to its traversing theiarea and creating its incendiary havoc.

It1is still anotherobject of this invention to provide a device oftthe` character described `wherein a safe and arm means is provided to prevent premature initiation of `combustion of the incendiary material during transportation thereof to the target area intended for its use, and

iszarmed `during the` descent after ejection from an aircraft `or other vehicle from which it is being launched.

These. and other; objects will becomemore apparent to i United States Patent O M 3,296,967 Patented Jan. 10, 1967 ICC a skilled person in the art to which the invention pertains from the description in the following specification and illustrated in the drawings in which:

FIGURE 1 is a sectional, longitudinal view of the invention illustrating its several parts when assembled;

FIGURE 2 is a section view taken along either of lines 2-2 of FIG. 1 intended to illustrate forward and aft ejection passages, and

FIGURE 3 is an enlarged view of the portion of FIG. l within the dash circle.

Referring now to FIG. l, there is shown an incendiary device 10 comprising a casing 11 defining achamber 33 and a forwardend cap assembly 12 attached by adhesive bonding or other means well known. Casing 11 is preferably fabricated in the form of an elongated cylinder of resin impregnated paper wherein the resin is selected from the phenolics, polyesters, polyurethanes and the like; however, other, substantially more durable, materials such as metals and the like are also contemplated for use herein. Forwardend cap assembly 12 comprises an impactingnose cone 13, resilient member orcushion 34 of foam rubber or plastic andcap base 14.Cap base 14 has a forward recessedportion 37 to receivecushion 34 and a rear recessed portion 37a to receive cylinder 11. Forward recessedportion 37 comprises a pair ofuid passages 38 and acentral hole 39.Base 14 further comprisesinternal passages 15 terminating in exhaust ports 35 (FIG. 2) which are radially off-set for a purpose to be later described. Mounted on the rearward end (to the right of FIG. l) is an aft end cap assembly 16, similarly fashioned with off-set passages 15 and exhaust ports 35 (FIG. 2), and apartition 40 havingpassages 41 therein and defining acompartment 17 between it and an aft end closure or-diaphragm 20. Apuncturable container 18 is mounted onpartition 40 preferably by adhesive bonding in the manner illustrated.Container 18 is fabricated of metal or plastic of a type selected for its compatibility with the fluid contained bycontainer 18, usually stainless steel, aluminum, Teflon plastic and the like. Foldably confined withincompartment 17 is aparachute 19 or other device for slowing the descent of device 10 when launched above ground in air. A rip cord withpull handle 36 or other manual actuating mechanism is attached todiaphragm 20 for a purpose later to be described. Communication betweencompartment 17 interior and the exterior of incendiary device 10 is provided by means of forwardly directed or oriented aft scoops orpassages 21.Parachute 19 or other air descent deceleration device is connected by means of wires orcords 22 to a centrally position safe and arm device or assembly 23 (shown in greater detail in FIG. 3).

Safe and arm device orassembly 23 comprises a spring urged rod end 24 engaging aprobe 25 by means of a connector 26. Rod end 24 is connected to, or integral with, alongitudinal rod 27 which is centrally positioned within device 10 and rigidly connected to, or integral with,nose cone 13 as shown in FIG. 1. Connector 26 is fabricated with a centrally perforated internal partition 28 for retaining a compression spring 29 as indicated in FIG. 3. At its forward end, connector 26 is formed with springlike jaws 30 held in open position as shown in FIG. 3 byrod 27.Rod 27 has an abrupt change in diameter and thereat forms a shoulder 31 w-here rod end 24 connects or preferably is formed as shown in FIG. 3.

Completing the assembly of incendiary device 10 is a centr-ally perforatedcharge 32 comprising combustible, high temperature gas producing incendiary material in solid form such as any of the solid propellant materials well known in the art of rocket motors. These materials usually contain fuels in solid form which are premixed with an oxidizer in a mold where solidification through means of the addition of a curing agent takes place to form a solid charge such ascharge 32 inchamber 33.Charge 32 is molded in place in casing 11 or alternatively is a separable 'body insertable inchamber 33 of casing 11. In the latter embodiment,charge 32 is held in position by adhesive bonding well known to the art. Other materials such as powdered metals and the like are often added for raising the temperature of the combustion gases after ignition; hence, the incendiary effect is thereby enhanced.

In operation of the invention, device is launched by any means well known, for example, from an airplane or missile overflying a specified target area such as where enemy troops may ybe concentrated. Device 10, as it descends, scoops air intocompartment 17 through aftscoop orair passages 21 causing it to become slightly pressurized..l1`his pressure Vcauses destruction of aft closure ordiaphragm 20, andparachute 19, being attached to diaphragm 2i) is ejected fromcompartment 17 and inates, slowing the descent of device 10. Simultaneously, with the decrease in t-he rate of descent of device 10, connector 26 is pulled aftwardly because of attachment thereof to parachute 19 'by wires orcords 22, compressing spring 29. The length and spring rate of spring 29 is selected to permit aftwardly motion of connector only to the extent that jaws 30 are permitted to engage shoulder 31 betweenrod 27 and rod end 24. In this manner,device 19 lbecomes armed sincerod 27, connector 26, rod end 24, andprobe 25 become in effect a rigid assembly. In addition,probe 25 has now assumed a position proximate topuncturable container 18 which is filled with a reactive fluid, for example, chlorine triuoride or chlorine pentailuoride, which are capable of reacting hypergolically withincendiary charge 32. In its now armed state, device 10 continues to descend until `contact is made with the target area surface.

Upon contact with the surface, impactingnose cone 13 strikes first and compresses foam rubber or otherresilient material cushion 34, and causesrod 27, rigidly attached tocone 13, to move an additional distance aft until rod end 24contacts container 33, puncturin-g it. Upon penetration of rod end 24 intocontainer 33, the hypergolic uid contained thereincontacts charge 32 and ignites it.Charge 32 thus ignited, produces high temperature -incendiary gas which is expelled from both ends of -device 10 throughpassages 15 andexhaust ports 35 thereat. As is apparent from FIG. 2 r(and FIG. 1),passages 15 are radially off-set with respect to the longitudinal axis lof device 10 and direc-ted rearwardly from the forward end and forwardly from the .aft end lto create thrust vectors which reduce to a force-couple system acting on device '10 about its central axis to cause it to roll or turn about on the surface upon which it was placed.

In addition to the if-orcecouples create-d which act about the central longitudinal axis of device 10 and render it self-propelling as above stated, gases ejected ,fromports 35 throughpassages 15 also cause incendiary destruction of objects and personnel within a broad area along its path of movement.

Additionally, it is contemplated herein to fabricate the linvention so thatnose cone 13 andresilient cushion 34 are removable. Provision therefor is indicated byfluid passages 38 andcentral lhole 39 inbase 14. Gases emanating from burningcharge 32 act against the aft surface ofcushion 34 after passing throughpassages 38 andhole 39, causingcushion 34 andnose cone 13 to become dislodged frombase 14, thereafter increasing incendiary gas ow to the surrounding terrain.

Alternatively, where air launching or descent by parachute is undesirable or otherwise impractical, provision is included in this invention .for manual arming by means ofrip cord 36, af-ter which delivery to enemy territory can be effected by any well known means, for example, by la simple catapulting device, by rifle in the manner of a rifle grenade, by mortar or other ield piece, -or even, when properly designed, by hand.

To operate the invention is this aspect,rip cord 36 is pulled destroying diaphragm '20 until a restriction is encountered, indicating spring 29 has achieved its solid height and jaws 30` of connector 26 have engaged shoulder 31 inassembly 23, thereby arming device 10. Device 10 is mounted in a launcher such as a rifle, mortar or the like or held in the hand and launched or thrown in the desired direction for impaction ofnose cone 13 on the surface in the area to be subjected to incendiary dam-age. After impaction, Ioperation of the invention is as hereinbefore described.

It is, `of course, not required in Ioperation of this invention that the ignition of charge `32 be accomplished by means of a hypergolic fluid such as above described. Many other means will occur to a skilled artisan for example,container 18 can be replaced with an ignitable charge of black powder or the like and a percussion type initiator mounted thereon so as to be contacted and detonated bypro-be 25. Detonation of the percussion initiator then ignites the ignita'ble charge which, in turn, ignitescharge 32 as above indicated.

Therefore, while the invention has been described and illustrated with reference to a preferred embodiment, it will be apparent to those skilled in the art that other embodiments, as well as modifications to that disclosed, may 4be made and practiced, without departing from the spirit or scope thereof except as pr-ovided in the subten-ded claims.

What is claimed is:

1. A self-propelled incendiary device comprising, a hollow elongated casing dening a chamber, an incendiary gas producing charge disposed within said chamber, means for initiating combustion of said charge in said chamber, a rst incendiary gas expelling means in one end of said casing communicating rwith said charge, and a second incendiary gas expelling means in the other end of said casing communicating with said charge, each said gas expelling means arranged in said casing ends in off-set tradial relation and angularly disposed with respect to the central axis of said casing so as to propel said device on the surface of the ground in a substantially rolling motion upon expulsion of incendiary gas produced by said combustion initiated incendiary charge from said expelling means.

2. A self-propelled incendiary device comprising, a cylindrical outer casing, an incendiary charge having a central, longitudinal perforation bonded to the interior of said casing, means in said casing for initiating combustion of said incendiary charge, and a plurality of incendiary -gas passage means, each in off-set radial relation and angularly disposed with respect to the central axis of said casing, in said casing proximate to the ends -of said charge for passage of incendiary gas from said casing, said gas passage from said ycasing providing a propelling force thereto for rolling and turning said incendiary device on a surface and simultaneously exposing objects in its path over said surface to said incendiary gas.

3. A self-propel1ed incendiary device comprising, a central hollow casing dening a chamber, an end cap asse-mbly attached to one end of said casing comprising an impact-ing nose cone, a cap base and a resilient member positioned therebetween, sai-d cap base comprising a plurality of -uid passages each comp-rising an exhaust port for establishing communication between said chamber and the exterior of said incendiary device, said passages radially off-set with respect to the main axis of said device and angularly disposed thereto, a longitudinal rod attached to said nose cone and extendible through said resilient member, said base cap and into said charnbe-r, a spring urged probe attached to said rod extendible to a position proximate to said puncturable container, means for connecting said probe to the end of said rod, an aft end cap assembly attached to the opposite end terior of said` incendiary device said fluid passages radially off-set `with respect to the main axis of said device and angularly disposed thereto, means for attaching said parachute to said probe connection means `for positioning said probe proximate to said container, means in said aft end: capv `for :establishing communication between said 1compartment and said incendiary device exterior, and

a charge` of incendiary material in said casing chamber `forqgroducing incendiary gas upon `combustion thereof,V

saidcombustion initiated by impacting said nose cone on a surface, whereby said probe is urged against said puncturable container to release of said chemically reactiveluid therein, said reactive fluid contacting said charge1 for combustion thereof.

4a The invention of claim 1 wherein the incendiary charge is a solid propellant;

5,; The invention of claim 1 wherein the means for initiating combustion insaid charge is a fluid hypergolically reactive with said charge.

6J The invention ofclaim 2 wherein said incendiary charge,l is a solid propellant.

7.? The invention ofclaim 2 wherein the means for initiating combustion in said charge is a fluid hypergolically reactive with said charge.

8. The device of claim 1 wherein means is provided for slowing descent of said device after air launching thereof.

9. The device of claim 8 wherein the means for slowing descent is a parachute.

10. The device ofclaim 2 wherein means is included for slowing descent of said device after air launching thereof.

11. The device ofclaim 2 wherein the means lfor slowing descent is a parachute.

12. T-he invention of claim 1 wherein the rneans -for initiating combustion of said charge is a percussion initiated ignitable charge of black powder.

13. The invention of claim-2 wherein the means `for initiating combustion is a percussion initiated ignitable charge of black powder.

References Cited by the Examiner UNITED STATES PATENTS 37,940 3/1863 Plant 102-35.4 1,771,455 7/1930 Wiley 102--4 2,489,610 11/1949 Barker 102-6 2,959,127 11/1960 Weinert 102--66 X 3,056,171 10/1962 Fite 86-1 X BENJAMIN A. BORCHELT, Primary Examiner.

SAMUEL W. ENGLE, Examiner.

Claims (1)

1. 2. A SELF-PROPELLED INCENDIARY DEVICE COMPRISING, A CYLINDRICAL OUTER CASING, AND INCENDIARY CHARGE HAVING A CENTRAL, LONGITUDINAL PERFORATION BONDED TO THE INTERIOR OF SAID CASING, MEANS IN SAID CASING FOR INITIATING COMBUSTION OF SAID INCENDIARY CHARGE, AND A PLURALITY OF INCENDIARY GAS PASSAGE MEANS, EACH IN OFF-SET RADIAL RELATION AND ANGULARLY DISPOSED WITH RESPECT TO THE CENTRAL AXIS OF SAID CASING, IN SAID CASING PROXIMATE TO THE ENDS OF SAID CHARGE FOR PASSAGE OF INCENDIARY GAS FROM SAID CASING, SAID GAS PASSAGE FROM SAID CASING PROVIDING A PROPELLING FORCE THERETO FOR ROLLING AND TURNING SAID INCENDIARY DEVICE ON A SURFACE AND SIMULTANEOUSLY EXPOSING OBJECTS IN ITS PATH OVER SAID SURFACE TO SAID INCENDIARY GAS.

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