US3677179A

US3677179A - Telescoping ordnance device

Info

Publication number: US3677179A
Application number: US583498A
Authority: US
Inventors: Lester A Potteiger; Navy Usa
Original assignee: Individual
Current assignee: US Department of Navy
Priority date: 1966-09-29
Filing date: 1966-09-29
Publication date: 1972-07-18
Anticipated expiration: 1989-07-18

Abstract

1. An ordnance device adapted for flight through the air comprising: A PLURALITY OF INDIVIDUAL WARHEADS IN TELESCOPED RELATION; MEANS FOR EXTENDING THE LENGTH OF THE ORDNANCE DEVICE FROM A COLLAPSED POSITION FOR STORAGE TO AN EXTENDED POSITION IN FLIGHT; AND STOP MEANS ON EACH OF SAID WARHEADS FOR PREVENTING SEPARATION OF ADJACENT WARHEADS WHEN SAID DEVICE IS IN ITS EXTENDED POSITION.

Description

States Potteiger et al.

[45] July 18, 1972 [54] TELESCOPING ORJDNANCE DEVICE [72] Inventors: Lester A. Potteiger, Fredericksburgh, Va.; The United States of America as represented by the Secretary of the Navy 22 Filed: Sept. 29, 1966 21 App1.No.: 583,498

[52] US. Cl ..l02/56, 102/58, 102/67 [51] Int. I F42b 13/32 [58] Field of Search 102/5, 7.2 XR, 7.4, 34.1, 56 XR,

[56] References Cited UNITED STATES PATENTS 1,464,192 8/1923 Willson ..l02/63 2,293,817 8/1942 Gruver ..l02/7.4 2,368,587 1/1945 Wise ..102/63 Primary Examiner-Verlin R. Pendegrass Attorney-G. J. Rubens, Arthur L. Branning and Lawrence R. Radanovic EXEMPLARY CLAIM 1. An ordnance device adapted for flight through the air comprising:

a plurality of individual warheads in telescoped relation; means for extending the length of the ordnance device from a collapsed position for storage to an extended position in flight; and stop means on each of said warheads for preventing separation of adjacent warheads when said device is in its extended position.

12 Clains, 5 Drawing figures Patented July 18, 1972 2 Sheets-Sheet l INVENTOR LESTER ,4. Pom/6m A XaM W R BY Patent July 1, 1972 2 Sheets-Sheet 3 y MN TELESCOPING ORDNANCE DEVICE 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.

The present invention relates generally to an ordnance device whose design is applicable to a wide variety of high explosive devices, including bombs, missile warheads and gunfired projectiles. The invention involves particularly an ordnance device constructed of a series of individual hollow concentric right circular cylinder warheads in telescoping relationship with each other such that upon deployment, the device is extended, thereby providing for a greater amount of effective kill mechanism, for a greater target area by the kill mechanism, and a more effective use of a given volume for purposes of delivering kill mechanisms to the target.

Currently present in the ordnance art are ordnance devices having a basic cylindrical shape fixed both in diameter and length, i.e., at least until detonation of the high explosive and subsequent expansion of the high explosive case. The dimensions of these devices must be fixed for many reasonseconomy, efficiency, handling, aircraft capabilities, propulsion capabilities, etc. Because the volume and mass of a missile warhead, for example, are so fixed, the amount of kill mechanism that can be delivered to the target, the target area covered by the kill mechanism and the efiective use of the given volume for a particular kill mechanism are restricted to some extent. Naturally, the greater the amount of effective kill mechanism and area covered by that kill mechanism, the greater the probability of target kill. On the other hand, if the kill mechanism cannot be adequately distributed at the target, the probability of a hit is decreased, hence, also the probability of a kill. Regarding adequacy of the kill mechanism distribution, sometimes the complete volume allowed for the ordnance device is not required to efiectively propel the kill mechanism, or the length-to-diameter ratio of the volume is such that effective and efficient kill mechanism propulsion is not possible. For example, several continuous rod warheads have a central cavity free of high explosive. Filling the cavity with explosive in order to increase adequacy of the kill mechanism distribution would necessitate complete redesign of the warhead. The preformed fragmentation warhead is an example of a possibly improper length-todiameter ratio. Unless this ratio is carefully designed, the multi-layers of metal cube fragments may not be an effective nor efiicient way to propel fragments due to their interaction and breakup. Ordnance devices are designed for a particular job or for a specific target. The method of delivery, size, type of kill mechanism, etc., must be considered in their design. A particular fragmentation, for example, requires a particular metal-mass to explosive-mass ratio. The telescoping ordnance device of the present invention can adequately solve the above-mentioned problems since the device can be applied to most ordnance devices and kill mechanisms.

Accordingly, it is an object of the present invention to provide an ordnance device for producing a greater amount of effective kill mechanism, i.e., fragmentation blast, shaped charge, fire, etc., from a given volume.

Another object of the present invention is to provide an ordnance device for producing a greater target coverage by the kill mechanism by providing a means for increaing the effective length of the device.

A further object of the present invention is to provide a telescoping ordnance device in order to achieve a more efiective use of a given volume for purposes of delivering kill mechanisms to a target.

A still further object of the present invention is to provide a telescoping ordnance device comprised of a series of individual, hollow, concentric, right circular cylinder warheads which, after the device is deployed expands to thereby increase the surface area over which the kill mechanism may be distributed.

A still further object of the present invention is to provide a telescoping ordnance device constructed of individual warheads each having a common axis and being of different diameters, such that extension of the device is made possible by retardation means such as fins afiixed to the device by hinges.

Other objects, advantages and novel features of the present invention will become apparent from the following detailed description of the invention when considered in conjunction with the accompanying drawings wherein:

FIG. 1 is a side elevation view of a three-stage telescoping ordnance device of the instant invention shown in its collapsed position;

FIG. 2 is a top view of the device shown in FIG. 1 with the extendable fins shown extended in phantom;

FIG. 3 is an enlarged quarter section longitudinal view of the device shown in FIG. 1;

FIG. 4 is a longitudinal side elevation, partly broken away, showing the instant device in its fully extended position; and

FIG. 5 is a side elevation view of the device according to FIG. 1 difiering thereover only by an attached nose, the nose ended device also shown partially extended in phantom in the direction of the arrow.

Referring now to the drawings wherein like characters designate like or corresponding parts throughout the several views, there is shown a telescoping ordnance device 10 which, as its name applies, resembles and functions like a telescope. To describe the device and illustrate its operation a fragmenting missile warhead has been selected. The telescoping warhead 10 is constructed of a series of individual, hollow, concentric right

circular cylinder warheads

11, 21, and 31 with or without end enclosures, each having a common axis and of different diameters such that they fit one within the other, as is clearly shown in FIG. 1 with the device in its collapsed position. Cylinders ll, 21, and 31, any number and size of which can be used within the limitations of the dimensions of the particular volume, are fabricated such that when the innermost cylinder 11, for example, is fully extended by holding the opposite or outermost cylinder 31 fixed and pulling along the common axis, the entire device resembles an extended or fully opened telescope as illustrated in FIG. 4.

Directing attention to FIG. 3, the innermost cylinder 11 comprises an outer cylindrical casing wall 12, which, in this case is a fragmentation type casing, having at its aft end a collar or end stop 15, forward and aft end plates and in the forward end plate a high explosive plugged loading port 14. A high explosive of any conventional type occupies the space between the forward and aft end plates and side wall 12. The length of cylinder 11 is such that a ring extension 17 is provided for nose attachment to be hereinafter described. Also, near the aft portion of cylinder 1 1 is provided a laterally disposed tube 16 for a mechanical locking device to be hereinafter described. Qlinder 11 may be completely hollow as shown or may have an axially disposed spaced tube therewithin such that a double wall cylinder would result.

Central cylinder 21 is similar to cylinder 11 in that an outer cylindrical wall or casing 22 is provided having an end stop or collar 25 at its aft portion and end plates, forward and aft, with the latter having a high explosive loading plugged port 24 therein. An inner cylindrical casing 23 is also provided and has at its forward outer end an end stop or collar 28 such that an air space 27 is formed between cylinders 11 and 21 and between end stops l5 and 28. Any desirable high explosive fills the space between walls 22, 23 and the forward and aft end plates. A laterally disposed hollow tube ,26 is also provided in co-axial relationship with tube 16.

Outerrnost tube 31 is similar to cylinder 21 in that an outer cylindrical casing or fragmentation wall 32 is provided, an inner cylindrical wall 39 spaced from the outer casing, and forward and aft end plates with the aft plate having therein a high explosive plugged loading port 34. Wall 32 is recessed along its aft end as at 35. In order to accommodate a foldable retardation fin 40, hinged thereto as at 41, inner wall 39 has along its forward end an end stop 37 secured thereto by an end stop fastener 38, which stop is similar to end stop 28 of the center cylinder 21. An air space 29 is formed between

walls

22 and 39 and between

end stops

25 and 37. As in cylinders 11 and 21, a laterally disposed pin cylinder 36 is provided in axial alignment with

tubes

16 and 26.

In operation, cylinder 31 is effectively held fixed by-retardation fins 40, which, just prior to target contact and warhead detonation, are extended to a position as shown in FIG. 4. Extension is effected as aerodynamic force on fin stop 45 lifts the fins away from cylinder 31 after a strap 44, which may be frangible or weakened in sections, breaks away. Fin stop 45 limits the movement of retardation fins 40 away from cylinder 31. Strap 44 is for the purpose of holding the fins against the device and also for maintaining pin 42 within aligned

tubes

16, 26 and 36. Air drag caused by the fins is sufficient to slow the outermost cylinder 31 and allow the device to deploy and extend by virtue of the forward velocity of the missile. As the fins are deployed, a mechanical locking device which prevents the warhead from telescoping is released. The mechanical locking device may be a spring loaded pin 42 which is ejected as the fins are deployed. A spring 43 disposed in tube 16 will facilitate pin ejection as strap 44 breaks away and fins 40 extend. The above-described end stops cooperate to prevent separation of the individual cylinders along their axis as they are deployed.

As shown in FIG. 5, the innermost cylinder 11 may have an aerodynamic nose 18 which may also function to propel fragmentation. Nose 18 may be threaded onto extension 17 by means of external (as shown) or internal threads. Each

cylinder

11, 21, 31 is cast loaded with high explosive through their respective loading ports and each is provided with some means of explosive initiation. One means of inltiation would be to provide each cylinder with its own fuse. Until release and subsequent missile-to-target contact, the telescoping warhead is unextended as shown in FIG. 1. Upon missile contact with the target, the warhead is extended as shown in FIG. 4 without the aid of electronic or complex or mechanical means.

From the above description, it is obvious that the telescoping ordnance device of the present invention will provide for a greater amount, over and above that from a conventional device, of effective kill mechanism from a given volume. This has been accomplished by providing a greater surface area over which the kill mechanism may be distributed more efiectively for propulsion. The present telescoping ordnance device will provide for a greater target area coverage by the kill mechanism over and above that of a conventional device. This is accomplished by providing a means for increasing the effective length of the ordnance device. The telescoping ordnance device will also enable more effective and efiicient use of a given volume and launching of kill mechanism over and above that of a conventional device for purposes of delivering effective kill mechanism to the target. This is achieved by providing essentially unrestricted dimensions of the ordnance device, i.e., size, thickness and number of hollow cylinders may be varied to suit the kill mechanism within imposed restrictions. The telescoping ordnance device of the present invention also provides for a more efficient and more economical storage of potential kill mechanism because it is stored and launched in its compact, unextended configuration and is capable of carrying a greater amount of the kill mechanism. Many alternative materials, methods and constructions of the invention are possible. The choice of the general term kill mechanism" rather than a specific term such as blast illustrates the possibilities in this area. The individual cylinders may be fabricated of any one or more materials both metallic and non-metallic. The cylinders need not have true cylindrical surfaces, for example, a shaped charge kill mechanism may be used in which case the outer surface of the cylinders may be dimpled. The cylinders may or may not have one end fully closed by a circular plate. The innermost cylinder may be retarded rather than the outermost. A retardation parachute could be used instead of the fins especially with a free-fall weapon. A blunt nose may be used rather than an aerodynamic one as shown in FIG. 5. Of course, the telescoping ordnance device of the present design may be applied to any basically cylindrical ordnance device including free-fall and retarded bombs, missile warheads and gun fire projectiles. Fusing of the individual cylinder missile warheads may be accomplished or one may be fused and the other detonated successively or by means on an explosive train. As already noted, .the size, thickness and number of cylinders may be varied.

The invention has been described in an illustrative manner and it is to be understood that the terminology which has been used herein is intended to be in the nature of words of description rather than of limitation.

Obviously many modifications and variations of .the present invention are possible in the light of the above teachings. It is therefore to be understood that within the scope of the appended claims the invention may be practiced otherwise than as specifically described.

What is claimed is: 1. An ordnance device adapted for flight through the air comprising:

a plurality of individual warheads in telescoped relation; means for extending the length of the ordnance device from a collapsed position for storage to an extended position in flight; and

stop means on each of said warheads for preventing separation of adjacent warheads when said device is in its extended position. i

2. The device of claim 1 further comprising:

locking means for preventing extension of the device when in the stored position; and

means for releasing the locking means during flight of the ordnance device.

3. The device of claim 2 wherein the means for extending the effective length comprises retardation means fixed to one of the individual warheads for slowing the device sufficiently to allow the remaining warheads to deploy and extend by virtue of their forward momentum after the locking means is released.

4. The device of claim 3 wherein said warheads comprise hollow, concentric, right-circular cylinders.

5. The device of claim 3 wherein said retardation means comprises hingedly fixed fins.

6. The device of claim 4 wherein said retardation means comprises hingedly fixed fins.

7. The device of claim 4 wherein said warheads are filled with a high explosive.

8. The device of claim 7 wherein all but the innermost of said warheads are double walled with said explosive occupying the space between said double walls.

9. The device of claim 3 wherein said locking means comprises a spring released pin laterally disposed to and interlocking said warheads.

10. The device of claim 3 wherein said locking means comprises a spring released pin laterally disposed to and interlocking said cylinders.

11. The device of claim 4 and further including an aerodynamic nose afiixed to the innermost of said cylinders.

12. The device of claim 5 wherein:

the fins are hingedly fixed so as to be folded in the storage position to lie generally parallel to the longitudinal axis of the ordnance device and further comprising:

a fin stop attached to each fin near the hinge point and extending outwardly at an angle therefrom;

whereby pressure of the air on the fin stop as the device travels through the air will extend the fins; and

whereby the amount of extension of the fins will be limited by pressure of the fin stop against the body of the device.

Claims

2. The device of claim 1 further comprising: locking means for preventing extension of the device when in the stored position; and means for releasing the locking means during flight of the ordnance device.

11. The device of claim 4 and further including an aerodynamic nose affixed to the innermost of said cylinders.

12. The device of claim 5 wherein: the fins are hingedly fixed so as to be folded in the storage position to lie generally parallel to the longitudinal axis of the ordnance device and further comprising: a fin stop attached to each fin near the hinge point and extending outwardly at an angle therefrom; whereby pressure of the air on the fin stop as the device travels through the air will extend the fins; and whereby the amount of extension of the fins will be limited by pressure of the fin stop against the body of the device.