US3267810A

US3267810A - Grenade carrying rocket

Info

Publication number: US3267810A
Application number: US377429A
Authority: US
Inventors: Thomas G Lancaster
Original assignee: Individual
Current assignee: Individual
Priority date: 1964-06-23
Filing date: 1964-06-23
Publication date: 1966-08-23
Anticipated expiration: 1983-08-23

Description

1966 T. G. LANCASTER 3,

GRENADE CARRYING ROCKET Filed June 23, 1964 INVENTOR Thomas 6. Lancaster W G ATTORNEYS 3,267,810 GRENADE CARRYING ROCKET Thomas G. Lancaster, Perry Hall, Md., assignor to the United States of America as represented by the Secretary of the Army F iied June 23, 1964, Ser. No. 377,429 6 Claims. (Cl. 891.816)

The invention described herein may be manufactured and used by or for the Government for governmental purposes without the payment of any royalty thereon.

This invention relates to apparatus for dispersing grenades of various types over a considerable distance and area.

The principal object of this invention is to provide a modified rocket warhead whereby a plurality of grenades are launched from a one man rocket launcher as a unit and then have the warhead release the grenades in flight whereby the grenades are given a much greater range and dispersion pattern than has heretofore been achieved.

The prior art of which I am aware has indicated that the only way to disperse solid shot or small explosive shells is to fire them out of a cannon encased in an elongated projectile and have the projectile casing fall apart in flight thereby releasing and scattering the solid or explosive shells on the target. This is illustrated by the patent to Cleu 15,474 dated Dec. 20, 1864.

By means of my invention, I have provided a lightweight portable weapon which achieves the above results in a much more eflicient manner since only one operator is needed to load and fire the device.

The use of rocket munitions in warfare goes back for hundreds of years. In recent years there has been developed the fixed fin stabilized rocket which can be fired by one man from a relatively simple manually held tube or rocket launcher. These fin stabilized rockets normally have a high explosive warhead and are extremely useful against tanks and vehicles.

The present invention is essentially directed towards converting these rockets to antipersonnel use. In my invention, the high explosive rocket War-head is replaced with a split tube which is adapted to contain a plurality of high explosive grenades, smoke grenades, white phosphorus grenades, tear gas grenades and the like. Thus, in my invention the rocket shoots or carries the grenades high in the air whereupon the tube splits apart and tumbles back to earth along with the rocket motor due to their great wind resistance while the momentum imparted to the grenades carries them a much greater distance to the desired target where they per-form their normal function. Thus, in my invention the grenades are given a much greater range and dispersion than has been previously obtained.

It is common in the art to adapt single grenades to be shot from rifles or mortars. This is illustrated by the patents to Post 1,311,006 and Farrell 1,309,280. My invention provides means to shoot a plurality of grenades a distance equal to or greater than the prior art devices and therefore is considered to be a substantial improvement since more grenades are'delivered at or near the target.

The specific nature of the invention as well as other advantages thereof will clearly appear from a description of a preferred embodiment as shown in the accompanying drawings in which:

FIGURE 1 is a view of the standard US. Army manual rocket launcher;

FIGURE 2 is a view of a loaded split tube warhead mounted on a finned rocket with the top half separated and partially broken away;

FIGURE 3 is a partial isometric view of the same warhead showing how the firing lever opens the split tube after the pull rings are removed. The pull rings are shown in place for illustrative purposes;

FIGURE 4 is a cross-sectional View showing the placement of the spacing blocks;

FIGURE 5 is a view of a disposable rocket launcher which shoots non-finned rockets;

FIGURE 6 is a view of a loaded split tube warhead mounted on a non-finned rocket with the top half separated and only partially shown;

FIGURE 7 illustrates how the split tube rocket warhead is loaded into the rear of a launcher;

FIGURE 8 is a partial cross-section through the area where the split tube warhead of FIGURE 2 joins the rocket. The warhead of FIGURE 6 is built in the same manner.

As shown in the drawings, my invention consists of a finned rocket 32 having attached to it a split tube warhead made up of

half sections

14 and 16 by means of a threaded plug 31 on the forward end of the rocket 32. The plug 31 is diagrammatically illustrated in FIGURE 8 and consists of a threaded male portion 33 which screws into the pusher or end plate 30 and a threaded male portion (not shown) of a larger diameter which screws into the forward end of the rocket motor 32 .or 42. It is to be understood that the threaded plug 31 is merely illustrative and that any equivalent fastening means such as welding or riveting may be used at this point.

The

split tube warhead

14 and 16 is divided up into a plurality of compartments by the separators or circular disks 22 and the

end plates

23 and 30. The spacing of the separators 22 is so chosen that the longest grenade will easily fit into each compartment. For shorter grenades a spacer 28 is used to take up the space. Block spacers 18 are provided in this type of my grenade rocket so that the

split tube

14 and 16 is held together when the warhead is loaded into the launcher 10 since the diameter of the split tube is substantially less than the internal diameter of the launcher 10.

I have also provided a split tube warhead having

half sections

38 and 40 which is attached to a non-finned or definned rocket 42. This device is essentially the same as the above device except that the diameter of the assembled

split tube rocket

38 and 40 is substantially the same as the internal diameter of the expendible rocket launcher 32.

In loading this device, the grenades 20 are placed in the

half sections

16 and 40 so that the pull rings 24 of the munition fall through the slots 26 which is in each

half section

16 or 40 adjacent to and to the rear of each separator disk 22. It is to be understood that the slots 26 can be eliminated if desired by assembling the grenades so that the pull ring 24 extends out of the gap between each

half section

14 and 16 in FIGURE 2 or 38 and 40 in FIGURE 6.

In loading the split tube warhead into the launcher, I proceed as indicated in FIGURE 7. As the warhead is pushed into the rear end or the forward end of the launcher, each pull ring is extracted until the entire warhead is in the launcher.

In operation, the operator squeezes the combination trigger and handle 12 or 34. This activates a small magneto built into the handle. The current generated is carried by conventional wires and contacts to ignite the rocket motor in

rocket

32 or 42. Shortly, after the warhead is in flight, the

sub-sections

14 and 16 or 38 and 40 are pushed apart by the firing levers 27 of the grenades 20. The current generated is carried by an insulated wire (not shown) to the yieldable contact pins located in housing units 46 and 48 whereby contact is made with the insulated

contact strips

50 and 52. The other side of the magneto is, of course, grounded to the launcher and rocket.

Therefore, when the warhead is positioned by the contact pins of housing unit 46 and 48 and electrical energy is fed into the

strips

50 and 52 from the trigger, the igniter, and propellant (both not shown for purposes of clarity) of the

rocket motor

32 or 42 are touched oil? and the hot gases roar out of the venturi 44 to launch the warhead and rocket.

The materials used in my device are not critical. The

split tube warhead

14 and 16 or 38 and 40 can be constructed from aluminum or plastics such as polymethylmethacrylates. The expendible launcher 32 can be made of a fiberglass reinforced plastic or aluminum tube. The separators 22, the spacers 28, and the end plates are preferably made from plastics such as polymethylmethacrylates.

Since the foregoing is a full and complete disclosure of my invention, I claim:

1. A rocket device for dispersing grenades with a rocket launcher comprising in combination:

(a) split tube means of predetermined length having a diameter substantially less than the diameter of said rocket launcher, said split tube means comprising a first and second half section, said first half section having a plurality of circular disk means mounted transversely to the axis of said tube means and spaced a predetermined distance apart throughout the length of said section, said section being mounted on end plate means having attaching means therein, said first and second sections being provided with a plurality of spacing means on the exterior thereof whereby said tube means is substantially centered in said rocket launcher;

(b) rocket means comprising a finned casing having propellant means,'nozzle means, and igniter means therein, said rocket casing having attaching means on the forward end thereof adapted to be secured to the end plate attaching means.

2. A rocket device as set forth in claim 1 in which said first half section is provided with a hole immediately to the rear of said disk means.

3. A rocket device for dispersing grenades with a rocket launcher comprising in combination:

(a) split tube means of predetermined length having a diameter substantially less than the diameter of said rocket launcher, said split tube comprising a first and second half section, said first half section having a plurality of circular disks mounted transversely to the axis of said tube and spaced a predetermined distance apart throughout the length of said first half section; said section being mounted on a circular end plate having attaching means therein, said first and second sections being provided with a plurality of spacers on the exterior thereof whereby said tube means is substantially centered in said rocket launcher;

(b) rocket means comprising a finned casing having propellant means, nozzle means, and igniter means therein, said rocket casing having attaching means on the forward end thereof adapted to be secured to the end plate attaching means.

4. A rocket device as set forth in claim 3 in which said first half section is provided with a hole immediately to the rear of each of said disks.

5. A rocket device for dispersing grenades having pull rings with a rocket launcher comprising in combination:

(a) split tube means of predetermined length having a diameter substantially equal to the diameter of said rocket launcher, split tube means comprising a first and second half section, said first half section having a plurality of circular disk means mounted transversely to the axis of said tube means and spaced a predetermined distance apart throughout the length of said first half section, said first half section being mounted on end plate means having attaching means therein, said first half section further having a hole immediately to the rear of each of said disk means, whereby said grenade pull rings are extracted through said hole during the loading procedure;

(b) a rocket motor comprising a casing having propellant means, nozzle means, and igniter means therein, said casing having attaching mean on the for- Ward end thereof, adapted to be secured to said end plate attaching means.

6. A rocket device for dispersing grenades having pull rings with a rocket launcher comprising in combination:

(a) a split tube of a predetermined length having a diameter substantially equal to the diameter of said rocket launcher, said split tube comprising a first and second half section, said first half section having a plurality of circular disks mounted transversely to the axis of said tube and spaced a-predetermined distance apart throughout the length of first half section, said section being mounted on a circular end plate having attaching means therein, said first half section further having a hole immediately to the rear of each of said disk means, whereby said grenade pull rings are extracted through said hole during the loading procedure;

(b) a rocket motor comprising a casing having propellant means, nozzle means, and igniter means therein, said casing having attaching means on the forward end thereof adapted to be secured to said end plate.

References Cited by the Examiner UNITED STATES PATENTS 1,311,006 7/1919 Post 10265.2 2,809,583 10/1957 Ortynsky et al 1027.2 3,093,072 6/1963 Pigman 1027.2 3,143,965 8/1964 La Pointe 102-344 3,180,265 4/1965 Rybak 102-42 X BENJAMIN A. BORCHELT, Primary Examiner.

SAMUEL W. ENGLE, Examiner.

Claims

1. A ROCKET DEVICE FOR DISPERSING GRENADES WITH A ROCKET LAUNCHER COMPRISING IN COMBINATION: (A) SPLIT TUBE MEANS FOR PREDETERMINED LENGTH HAVING A DIAMETER SUBSTANTIALLY LESS THAN THE DIAMETER OF SAID ROCKET LAUNCHER, SAID SPLIT TUBE MEANS COMPRISING A FIRST AND SECOND HALF SECTION, SAID FIRST HALF SECTION HAVING A PLURALITY OF CIRCULAR DISK MEANS MOUNTED TRANSVERSLEY TO THE AXIS OF SAID TUBE MEANS AND SPACED A PREDETERMINED DISTANCE APART THROUGHOUT THE LENGTH OF SAID SECTION, SAID SECTION BEING MOUNTED ON END PLATE MEANS HAVING ATTACHING MEANS THEREIN, SAID FIRST AND SECOND SECTIONS BEING PROVIDED WITH A PLURALITY OF SPACING MEANS ON THE EXTERIOR THEREOF WHEREBY SAID TUBE MEANS IS SUBSTANTIALLY CENTERED IN SAID ROCKET LAUNCHER; (B) ROCKET MEANS COMPRISING A FINNED CASING HAVING PROPELLANT MEANS, NOZZLE MEANS, AND IGNITER MEANS THEREIN, SAID ROCKET CASING HAVING ATTACHING MEANS ON THE FORWARD END THEREOF ADAPTED TO BE SECURED TO THE END PLATE ATTACHING MEANS.