US3433437A - Rocket projectile - Google Patents

Description

March 18, 1969 1.. E. BATES ROCKET PROJECTILE Sheet Filed Jan. 18, 1967 U .w s

INVENTOR LEONARD E. BATES A TTORNE Y March 18, 1969 1.. E. BATES 3,433,437

ROCKET PROJECTILE Filed Jan. 18, 1967 Sheet 2 of 2 INVENTOR. LEONARD E. BATES ATTORNEY United States Patent 3,433,437 ROCKET PROJECTILE Leonard E. Bates, Aurora, Colo., assignor to John E. Reilly Filed Jan. 18, 1967, Ser. No. 610,094 US. Cl. 244-3.23 Int. Cl. F42b 25/14, 13/14, 13/32 13 Claims ABSTRACT OF THE DISCLOSURE wire area.

The present invention relates to new and useful rocket projectiles and more particularly relates to a projectile containing a pyrophoric gel composition which upon impact with a target and exposure to air is self-igniting and, according to the properties of the composition, will undergo highly intense burning over a predetermined time interval.

Various flame-producing weapons are currently in use in modern warfare, such as for instance, flame-throwers or napalm bombs. A definite need exists for a flame-producing missile or projectile which can be fired or launched accurately by hand-held weapons over intermediate ranges. Accordingly the present invention concerns itself with the design and construction of a missile or rockettype projectile which is particularly adapted for use in launching flame-producing substances by means of handheld weapons whereby the projectile can be accurately propelled and delivered on target in ranges on the order of one thousand yards while being completely safe to handle by the operator.

As designed and constructed, the projectile of the present invention is readily comformable for use with various payloads, but is especially adaptable for use in launching flame-producing materials including but not limited to pyrophoric materials as well as oxidizing chemicals, such as chlorine trifiuoride, or white phosphorous or finely divided sodium. Alternate payloads are high explosives, smoke, illuminating flares and chemical agents, such as, titanium tetrachloride. Moreover, the payload may contain both fragmentation and armor-piercing configurations much the same as conventional rifle grenades, but with improved range and accuracy; and in this connection the projectile can be launched or otherwise delivered in single or repeated bursts by hand-held weapons, artillery or vehicle-mounted weapon systems.

In the selection and choice of flame-producing materials, by far the most effective are pyrophoric substances, especially those of the tri-alkyl aluminum family. These compositions are characterized in that they are selfigniting upon exposure to air and will burn intensely in virtually any environment, such as, in the presence of organic materials and any non-porous, non-flammable material. Still further, these compositions possess the characteristic of reacting vigorously with moisture and with lush vegetation and thus are particularly effective in jungle warfare. On the other hand, because of the properties of certain pyrophoric substances, such as tri-ethyl aluminum, extreme caution must be exercised in the handling, unloading and storage of the materials. In this connection it must be rendered completely safe for handling and storage when packing as a payload in a weapon system and be controlled to ignite only when delivered to the target area. For optimum performance, the burning rate of the pyrophoric substance must be controlled without reducing its heat intensity, and optimum dispersion of the substance upon impact with a target must be promoted in order to cover the widest possible target area in relation to the size of the payload.

Accordingly, desirable characteristics of the projectiles of the class described are that they can be safely handled, loaded and stored; yet when launched will upon impact be self-igniting and dispersed over a wide area while burning at a controlled rate and with a high heat intensity. Moreover that the projectile will lend itself to short or long range firing either in single or multiple shot rounds and be capable of causing maximum destruction over the widest possible area in relation to the size of the payload. It is therefore a principal object of the present invention to achieve the above and other desirable characteristics in a projectile containing a flame-producing payload which can be packaged in any selected size for launching by hand-held Weapons, remote controlled weapon systems or artillery.

It is another object of the present invention to provide for a projectile which is so constructed and arranged that it can be accurately launched without danger of misfiring either in single shots or multiple shot rounds and is readily conformable for use in short, intermediate or long-range weapon systems; and more specifically to provide a projectile which can be activated to deliver a payload composed of pyrophoric gel compositions accurately on a target in a safe, dependable manner.

It is a further object of the present invention to provide in a projectile for a rocket or thrust producing system that can be selectively activated to accurately propel a payload over considerable distances and to maintain the projectile in proper alignment for detonation and dispersion of the payload upon impact at the target area.

It is a still further object of the present invention to incorporate a payload in a projectile which is composed of a gelled or thickened pyrophoric composition which will afford maximum fire power and destruction for the size of the payload and is capable of dispersion and ignition immediately upon impact at the target area and of burning with a high heat intensity and at a controlled rate; and in addition to provide a rocket projectile containing payloads of the type herein described which is safe to handle and load without danger of misfiring and can be accurately launched and propelled with maximum stability over considerable distances.

The above and other objects, advantages and features of the present invention will become more readily understood and appreciated from a consideration of the following preferred and alternate forms of the present invention when taken together with the accompanying drawings, in which:

FIGURE 1 is a view partially in section of a preferred form of rocket projectile, in accordance with the present invention.

FIGURE 2 is an enlarged sectional view in detail of one form of arming device for the rocket projectile of the present invention.

FIGURE 3 is a sectional view taken on line 3-3 of FIGURE 1.

FIGURE 4 is an enlarged view in section of the aft portion of the rocket or thrust section of the preferred form of invention shown in FIGURE 1.

FIGURE 5 is a sectional view taken about line 5-5 of FIGURE 1.

FIGURE 6 is an end view of the aft portion of the thrust section of the projectile shown in FIGURE 1.

FIGURE 7 is a view partially in section of a modified form of rocket projectile in accordance with the present invention; and

FIGURE 8 is an enlarged view in section of the ignition system for the modified form of invention shown in FIGURE 7.

The present invention is best exemplified by illustrating preferred and alternate rocket projectiles which are designed for firing by hand-held weapons or launcher systems. Nevertheless, for purposes of the present invention, this weapon system is merely representative and it will be apparent from the following that preferred and alternate forms of projectiles herein described are readily conformable for manufacture and use in different sizes for launching in other weapon systems.

In the preferred form of invention shown in FIGURES 1 to 6, a projectile 10 comprises an outer shell 12 containing a payload designated at 13. A rear thrust section 14 of the reaction type includes an outer case 15 for an ignition system 16, a solid rocket propellant 18 and circumferentially spaced reaction nozzles 19.

The outer shell 12 is in the form of a thin-walled tube and is preferably composed of a lightweight material, such as, aluminum. The shell is internally threaded at opposite ends as designated at 21 and 22 and is further provided with external, longitudinally extending grooves 23 at equally spaced, circumferential intervals. The front end of the shell is closed by a bullet-nosed cap 24 containing a conventional arming device 25, and the cap 24 has an externally threaded extension 26 to threadedly engage the end 21 of the shell. The opposite end of the shell is closed by a disk 27 which makes threaded engagement with the end portion 22 and together with the nose forms a hermetically sealed container for the payload composition. Linear, flexible, shaped charges 28 are inserted in each of the external grooves 23 as best seen from FIGURE 3 and which charges run the entire length of the shell and continue forwardly through limited bores 29 in the cap 24 and terminate in a detonator 30, the latter forming part of the arming device. The shaped charges are suitably covered with an outer lead sheath 32 for the purpose of sealing in place and preventing exposure to the elements. The charge employed may be of any suitable composition and for example may be of the type manufactured and sold by Du Pont de Nemours Company designated A67. It is important that the charges be set deeply enough within the body of the shell whereupon detonation by the arming device the charges will simultaneously explode with sufficient force to sever the shell along the grooves and to separate the shell from the nose thereby exposing the payload composition to air.

Various means may be devised or utilized for detonating the shaped charges, such as, conventional point detonating or super-quick fuses. In the preferred form, the arming device 25 is a setback device which is broadly comprised of a central chamber 35 being formed in the cap 24 for placement of the detonator 30 and of a firing pin 37, the latter including an enlarged tapered end 38 and a rearwardly directed stem 39. The device is normally disarmed by retaining the pin in spaced relation behind the detonator through use of a sleeve 40 vented at 40' which is slidably disposed in the chamber and has a stop 41 insertable in external grooves at the leading end of diametrically opposed keepers 42. The keepers 42 are spring-loaded to be biased inwardly into the chamber through laterally extending bores 44 formed in the nose cap section. Similarly, the sleeve element 40 is normally biased forwardly to make connection between the stop 41 and keepers 42 by an outer concentric, coiled spring 46, and an inner spring 47 is coiled about the trailing end of the stem 39 between the sleeve 40 and a backing ring 49 mounted on the stem. A safety wire 50 extends through the cap and through a lateral bore 52 in one of the keepers 42 whereby to normally lock one of the keepers in position and prevent accidental forward release of the firing pin toward the percussion cap.

Immediately prior to firing in a manner to be described, the safety wire is released to arm the projectile. Upon firing, the keeps are movable in response to spinning 0r centrifugal force of the projectile laterally and away from the central chamber; at the same time the forward momentum of the projectile is sufiicient to overcome the force of the spring 46 to retract the firing pin rearwardly through the chamber. In response to impact or sudden deceleration of the projectile the pin is thrown forwardly to strike the detonator 30 and to detonate the charges 28.

The payload 13 is preferably composed of a liquid pyrophoric substance combined with a combustible thickening agent and solid particles 17 uniformly distributed throughout the mixture. Preferably, the pyrophoric substance is composed of triethyl aluminum in its liquid state. The thickener may comprise a mixture of natural or synthetic rubber in a suitable solvent together with a magnesium powder, the rubber solution acting as a combustible thickener to inhibit or retard the burning rate of the aluminum substance and encourage the gel to stick to objects upon striking, and the magnesium powder serving to raise the temperature or heat intensity of the mixture. The solid particles 17 may be incorporated as part of the gel and may take the form of chunks of rubber or rubber-like particles, such as, latex or gum rubber which have the capacity of absorbing the liquid aluminum material and upon impact will form burning chunks of incendiary material. Further the particles will cooperate in reducing the burning rate and affording wider dispersion upon impact. The solvent also encourages the rubber particles to absorb the tri-ethyl aluminum thereby to cause the particles to swell or expand. In determining the relative proportions of the ingredients, the tri-ethyl aluminum is present in the optimum range of seventy-five to ninety-five percent and the balance being comprised of the thickener made up of equal parts by weight of magnesium and of the rubber solution. In mixing, the objective is to provide a controlled burning rate at the highest possible temperature as well as to provide optimum dis persion upon impact in the form of tiny particles, as opposed to a vapor, and further wherein the gelled or thickened mixture has the characteristic of being sticky or glue-like in consistency so as to adhere on contacting an object until each of the particles is entirely burned. In this connection, it is essential that the ingredients be mixed and loaded into the shell in an oxygen-free chamber to prevent combustion of the pyrophoric material and that the payload be hermetically sealed within the shell. Accordingly, in loading the gel into the shell, both the nose portion 24 and disk 27 should be threaded into sealed relation at opposite ends of the shell with the aid of sealant compounds.

The thrust or rocket section 14 is so constructed as to achieve maximum acceleration and to the extent that the propellant will have completely expended itself while providing the necessary momentum by the time the projectile is released from the end of the launcher barrel thereby eliminating flash-back when fired. Of course the size and thrust of the motor section will vary according to size of payload and maximum range desired. In the preferred form, the motor case 15 is of reduced diameter and relatively thick-walled in relation to the thickness of the shell 12 with the leading end of the case being externally threaded for threaded connection to the trailing end 22 of the shell 12. As shown in FIGURE 4, the motor section is armed with a mechanical firing pin 60 which is centered in a chamber 61 within the nozzle section 19 and has a tapered leading end 62 and a trailing end 63 biased by spring element 64 to project into a cupshaped recess area 65 at the aft end of the motor section. A central tube 68 defines a forward continuation of the chamber 61 to extend the length of the motor section and terminate at its leading end within a cavity 70 filled with a secondary ignitor material 72. The tube may be loosely filled with a finely ground black powder or other suitable primary ignitor 73, and a percussion cap 74 at the trailing end or entrance to the tube 68 is positioned in the path of travel of the firing pin 60. A cloth screen 76 may serve as a temporary retainer for the ignitor 72, and a series of fuse trains 78 leads outwardly from the ignitor and rearwardly through central openings formed in solid propellant sticks 18, the fuse trains extending through the entire length of the propellant sticks. In turn the sticks 18 are placed circumferentially in contacting relation to one another around the inner surface of the case as shown in FIGURE 5 and are interposed between a cap 80 at the forward end of the case and a wire screen or disk 82 located just forwardly of the reaction nozzles; a spacer sleeve 83 retains the screen in spaced relation away from the reaction nozzles. In this manner, when the firing pin is engaged and driven forwardly through its chamber to detonate the cap 74 the primary ignitor in the tube 68 will provide the necessary spark for the ignitor 72 to simultaneously activate each of the fuse trains 78 and to ignite the external surfaces of the solid propellant thereby to initiate simultaneous burning of the propellant sticks both internally and externally; and, although burning of the propellant is to some extent progressive in nature it occurs almost instantaneously. Furthermore the screen 82 will temporarily contain the fire and gases formed within the propellant section for a sufiicient time interval to permit complete burning and conversion into gas under high pressure prior to release and discharge through the reaction nozzle section 19.

A series of four reaction thrust nozzles, as shown in FIGURE 6, are formed out of a solid cylinder 84 and are arranged at equally spaced circumferential intervals about the aft end of the motor section each including a venturi throat and rearwardly divergent exhaust to develop maximum thrust in response to high pressure ignition and release of the propellant gases. Further the nozzles are canted at a low angle to the longitudinal axis of the projectile or line of flight, as shown in FIGURE 6, to impart a spin to the projectile as it is discharged from the barrel thereby affording maximum stability and accuracy in flight. The spin moment imparted will further aid in releasing the keepers 42 in the arming device whereby to free the firing pin for forward travel through its chamber to strike the detonating member 30. In addition, flexible or collapsible fin members 85 are tangentially connected to the external surface of the case, there being a series of three fins mounted at equally spaced circumferential intervals about the aft end of the projectile or case. Most desirably, the fins are composed of spring steel or other resilient material so that when inserted into a launcher will be free to collapse against the case, and it will be noted that the fins are each formed with rearwardly divergent edges 86 which when propelled through the barrel will cooperate with the reaction nozzles to lend an increased spin force to the projectile; and when released from the barrel will spring out to materially increase the stability and greatly minimize any tendency of the projectile in flight to tumble or deviate from its course. The fins are located toward the aft end in order to displace the center of pressure of the rocket motor rearwardly of the center of gravity of the projectile and contribute to greatly increased stability in flight.

As described in said co-pending application, the projectiles may be loaded in a magazine and successively advanced into alignment with the barrel of the launcher, in which position the firing pin is aligned with the hammer of a cocking mechanism. Prior to loading, or just prior to firing, the safety Wire 50 is removed to prepare the arming device for detonation of the shell. When fired, the energy of propulsion developed by the solid propellant sticks will have expended itself in accelerating and spinning the projectile through the barrel for discharge at a high rate of speed. The spin is initiated by the reaction nozzles and, once released from the barrel, the fin members are free to spring away from the case to increase both the accuracy and stability of the projectile in flight. Again the forward momentum of the projectile will retract the firing pin 38, and the spin force developed will urge the keepers 42 outwardly and away from the chamber 25. Under sudden deceleration or impact the detonator will ignite the explosive charges in the shell. Resultant sectioning or severance of the shell is almost instantaneous upon impact thereby causing the pyrophoric gel composition, or payload 13, to be dispersed and scattered over a wide area. Again, the use of solid particles in the gel composition serves to increase dispersion and to inhibit the burning rate of the gel.

In the modified form of invention shown in FIGURES 7 and 8, like or similar parts are correspondingly designated with prime numerals. Broadly it will be seen that the projectile 10' is comprised of a shell 12' encasing a pyrophoric gel composition or payload 13, and the necessary thrust is again developed by a solid rocket motor section 14 including an electrical ignition system 16'. In the modified form, however, the arming device is eliminated; instead the shell 12 is in the form of a frangible, bullet-nosed container of one-piece construction and, for example, may be composed of a thin-walled glass or brittle plastic material which will readily rupture or break upon impact so as to expose the pyrophoric gel composition to air for self-combustion. In this relation, the gel composition is sealed in a separate glass container 90 having a front stopper portion 91; in turn, the outer frangible shell may be formed by pouring or casting a curable synthetic resinous material in surrounding relation to the container. The rearward end of the container 90 is enclosed by an aluminum sleeve 92 forming a rearward continuation of the shell 12, and a fast curing synthetic resin material, such as, polysulfide rubber is cast around and behind the container to define a cushion or impact absorbing member 93.

In the motor section, the basic construction and arrangement of parts is the same as that of the preferred form but is activated by an electrical ignition system 16. In assembly, the leading end of the motor case is connected to the shell portion by a threaded connector sleeve 94 with a spacer ring 95 interposed between adjacent ends of the motor case 15 and sleeve 93, the spacer ring together with the leading end of the motor case defining a cavity in front of the propellant section for insertion of the electrical ignition system.

In the ignition system, a contact wire 98 leads from the sleeve 93 into an ignitor cup 100 filled with primary and secondary ignitor substances with a combustible cloth screen 102 retaining the ignitor in the cup portion. The ignition or contact wire 98 will when energized cause sparking across the ignitor cup and ignition of the primary then secondary ignitor materials to burn the ignitor fuses 78' for the propellant sticks 18. In firing the projectile, it will be apparent that the launcher requires a modified trigger system which for example may take the form of a battery-powered capacitor-transformer spark system which can operate off the primary trigger to selectively energize the contact wire 98. In this relation, one side of the contact sleeve would be positive and the opposite side negative, or at ground, to develop the necessary spark in the gap or space across the ignitor cup.

In practice, a six-ounce charge of a gel composition composed of tri-ethyl aluminum, rubber solution, magnesium powder and latex rubber particles in the proportions described developed a flame ranging from ten feet by ten feet on ninety degree impact to three feet by thirty feet at less than five degree impact. Terrain and target conditions will obviously influence the flame size and pattern. However on a non-porous, non-flammable surface the duration of the flame is twenty-five to thirtyfive seconds and would of course increase with more porous surfaces. Each individual round weighed on the order of one pound and accuracy was demonstrated to be within eight mils in bench rest tests. Ignition was by spark gap in a primary ignitor composed of one-half gram of black powder which in turn ignited two grams of secondary ignitor mix and thirteen rapid fuse trains leading to the propellant sticks. A disk or screen bearing one-tenth gram of ignitor mix was located at the aft end of the propeller charge to assist in complete ignition. In each case, the size and Weight of the projectile will vary with different sized payloads as will the size and capacity of the various component elements of the projectile.

It will be apparent that component parts of the preferred and modified forms of invention may be readily interchanged, such as, the shell and payload construction or the ignition systems described. Moreover, by virtue of the safety afforded in handling, accuracy and reliability in launching and firing, projectiles devised according to the present invention are adaptable for use with virtually any type of payload or warhead. Accordingly, while preferred and alternate forms of the present invention are herein set forth, illustrated and described it is to be understood that various other modifications and changes may be made in the particular construction and arrangement of parts without departing from the spirit of the present invention.

What is claimed is:

1. A projectile comprising thrust producing means for launching and propelling said projectile, an outer thinwalled shell, and a payload composed of an admixture of a major amount of a liquid pyrophoric substance, and minor amounts of a combustible thickening agent to modify the burning rate of said pyrophoric substance hermetically sealed within said shell, said payload being capable of self-combustion upon release from said shell and exposure to air.

2. A projectile according to claim 1, said payload further including solid particles distributed throughout the mixture.

3. A projectile according to claim 1, said payload being composed of a major proportion of tri-ethyl aluminum in the liquid state and minor amounts of a rubber solution and magnesium powder.

4. A projectile according to claim 1, said outer shell having a generally cylindrical container and a nose cap closing one end thereof, explosive charges in said shell, and an arming device in said nose portion being operative upon launching to detonate said charges and sever said shell for release of said payload.

5. A projectile according to claim 4, said explosive charges being in the form of linear, shaped charges extending through longitudinal grooves at spaced circumferential intervals about said shell, and said arming device being operative upon impact to detonate said charges.

6. A projectile according to claim 1, said outer shell being composed of a frangible material defining a generally cylindrical container and a nose portion closing one end of said shell, said thrust producing means being connected to the opposite end of said shell with an interface isolating said payload from said thrust producing means.

7. A projectile having an outer shell containing a payload composed of an admixture of a major amount of a liquid pyrophoric substance, and minor amounts of a combustible thickening agent to modify the burning rate of said pyrophoric substance; a reaction motor connected to the rearward end of said shell comprising an outer casing, a propellant enclosed within said casing, an ignition system within said casing being operative to ignite said propellant, a series of reaction nozzles at uniformly spaced circumferential intervals about the trailing end of said casing rearwardly of said propellant, said reaction motor further including a series of collapsible fins tan. gentially mounted at equally spaced circumferential intervals about the external surface of the casing.

8. In a projectile according to claim 7, said reaction nozzles being canted about axes in relation to the longitudinal axis of said projectile to impart a spinning moment of force to said projectile about its longitudinal axis upon ignition and discharge of the propellant gases through said reaction nozzles.

9. A projectile according to claim 7, said propellant mixture being in the form of solid propellant sticks arranged about the inner wall of said case and in parallel to the longitudinal axis of said case, and said ignition system being located forwardly of said case including a fuse train extending rearwardly from the ignition system with a fuse extending longitudinally through each of said elongated propellant sticks, and a screen interposed between said propellant sticks and said reaction nozzles.

10. In a projectile according to claim 7, said ignition system further including a tubular member extending rearwardly through said casing and terminating at the trailing end thereof, a primary ignitor within said tubular member including a percussion cap at the trailing end thereof, and a firing pin at the rearward end of said case being selectively engageable to strike said percussion cap.

11. In a projectile according to claim 7, said ignition system comprising electrical contact elements, ignition material contained within a recess forwardly of said propellant section and ignition wires leading from said electrical contacts into the recess being energized to discharge a spark across the recess to ignite the ignition material, and a fuse leading from said ignition material into said propellant section.

12. A projectile adapted for launching from a handheld weapon comprising in combination a stream-lined frangible shell, a pyrophoric gel composition hermetically sealed within said shell, said pyrophoric gel being composed of a major amount of a triethyl aluminum and minor amounts of a combustible thickener to modify the burning rate of the triethyl aluminum upon exposure to air, and solid rubber or rubber-like particles interspersed throughout said gel; and a thrust reaction motor connected to the trailing end of said shell including rearwardly disposed thrust reaction nozzles canted in a direction to promote spinning of said projectile through the barrel upon energizing said motor, and a series of tangentially extending, collapsible stabilizers arranged at equally spaced circumferential intervals about the external surface of said motor case.

13. A projectile adapted for launching from a handheld weapon comprising in combination a streamlined frangible shell, a pyrophoric gel composition hermetically sealed within said shell, said pyrophoric gel composition being disposed in a liner, and said frangible shell being composed of a curable synthetic resin material cast into surrounding relation to said liner; a thrust reaction motor connected to the trailing end of said shell including rear wardly disposed thrust reaction nozzles canted in a direction to promote spinning of said projectile through the barrel upon energizing said motor, and a series of tangentially extending, collapsible stabilizers arranged at equally spaced circumferential intervals about the external surface of said motor case.

(References on following page) References Cited UNITED STATES PATENTS Van Loenen.

Barker 1029O Brandt 2443.23 Wade 102 90 X Viasmensky 102--79 Greene 10290 X Smelling 1029O X Kratzer 1027.2 Davis et a1. 10270 ODonnell 60255 US. Cl. X.R.

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