AU742659B2 - A barrel assembly - Google Patents

Description

i BACKGOUNDO THEIVENT A BARREL ASSEMBLY iii:I i' i' i 15 t s.:

XXX.::

The invention relates to firearms.

The invention has utility as an automatic, high rate of fire, firearm whereby it may be used for example, as a close-in ship-board defense against bombs, missiles or attack aircraft for launching large numbers of projectiles within a short period of time. The invention also has utility in handguns such as a rapid fire pistol or rifle ||whirch*4i sr av e v be i di e osabl l to a barrel. Such firearms have numerous moving parts, tend to be heavy and complex, may jamb or be unreliable, and require elaborate delivery and loading systems to support the rate of fire. The rate of fire of automatic firearms of this type is limited by the time required to load the catridge,seal the barrel, unseal the barrel and eject the empty case.

firearms retain many of the problems of conventional firearms.

SUMMARY OFTHE INVENTION U M AR The present inventioeaims to provide an alternative system which will alleviate at least one of the disadvantages of the prior art.

operative sealing engagement with the bore of the barrel; sequentially through the muzzle of the barrel; ignition means for igniting the discrete propellant charges; and control means for selectively and sequentially actuating the ignition means.

The ignition means may be electrical, chemical, mechanical or any other conventional primer. Conveniently, the ignition means is electrical and the control m.eans .isanelectrical control adapted to provide electrical ignition pulse to the respective ignition means. Suitably the control means is configured to enable a user to selectively control the rate, number, and frequency of the pulses to provide a ::desredfiring pattern. The control means may fire the projectile assembliessingly, in pairs, or in any other combinations.

The projectile assembly may be round, conventionally shaped or dart-like and the fins thereof may be off-set to generate a stabilising spin as the dart is propelled from a barrel which may be a smooth-bored barrel. In addition the barrel assembly may find utility as a removable/replaceable barrel of a rifle or pistol.

Alternatively the barrel assembly constitutes one of a plurality of barrel assemblies and the control means may actuate the ignition means of each of the :barrel assemblies in such manner that a sequential plurality of arrays f projectile assemblies are propelled in following relationship. Aiming and firing of the arrays of Sprojectile assemblies may be controlled by a conventional radar fire control system or ~other.known fire control systems. The individual barrel assemblies may be aimed 15 such that the array of projectile assemblies converges at a particular range to give a maximum density of projectile assemblies at that range.

Alternatively, the array of projectile assemblies may diverge to maximise coverage of an area. Thus, the average separation distance at the target between the projectile assemblies in an array can be predetermined and adjusted to suit the nature and range of the target. Of course, the individual barrel assemblies may be fired randomly or independently of the ther barrel assemblies.: abutting reltionship throughout the barrel either by the projectilassemblies abutting one another or abutting column means intermediate the projectile assemblies to form a compression resistant column able to resist compression of the projectile assemblies or propelling charges associated therewith due to pressure generated by the f iring fthe leadin ig projectile assemblies.

The propelling charges may be either solid or granular and compression of either may be an undesirable, moreover, movement of the projectile assemblies relative to the barrel may cause misalignment of the ignition means with their respective propellant charges.

It is preferred that the ignition means be disposed at the leading end of the propellant charge so as to minimise possible energy loss in accelerating the front portion of the propellant charge.

It is preferred that each projectile assembly includes a projectile head and extension means for at least partly defining a propellant space. Preferably, the extension means includes a spacer assembly which extends rearwardly from the projectile head and abuts an adjacent projectile assembly.

In one embodiment, the spacer assembly extends through the propellant space and the projectile head whereby compressive loads are transmitted directly S 10 through abutting adjacent spacer assemblies. In such embodiment the spacer assembly may add support to the extension means which may be a thin cylindrical rear portion of the projectile head. Furthermore the extension means may form an operative sealing contact with the bore of the barrel to prevent burn leakage past the projectile head.

l..ii l i n. cl u a id o l l a r w h icll i i d 5 It is preferred that the spacer assembly includes a rigid collar which ::extends outwardly to engage a thin cylindrical rear portion of the malleable projectile head inoperative sealing contact with the bore of the barrel such hat axially compressive loads are transmitted directly between spacer assemblies thereby avoiding deformation of the malleable projectile head.

In another embodiment, complementary wedging surfaces are disposed on the spacer assembly and projectile head respectively whereby the projectile head is urgedinto engagement with the bore of the barrel in response to relative axial compression between the spacer means and the projectile head. In such arrangement the projectile head and spacer assembly may be loaded into the barrel and thereafter an axial displacement is caused to ensure good sealing between the projectile head and barrel. Suitably the extension means is urged into engagement with the bore of the barrel.

Preferably, the projectile head defines a tapered aperture at its rearward end into which is received a complementary tapered spigot disposed on the leading end of the spacer assembly, wherein relative axial movement between the projectile head and the complementary tapered spigot causes a radially expanding force to be applied to the projectile head.

4 The barrel may be non-metallic and the bore of the barrel may include recesses which may fully or partly accommodate the ignition means. In this situation the barrel houses electrical conductors which facilitate electrical communication arre m:iy:: ion: between the control means and ignition means. This arrangement may be utilised for disposable barrel assemblies which have a limited firing life and the ignition means and control wire or wires therefor can be integrally manufactured with the barrel.

In an alternative arrangement, a barrel assembly includes ignition apertures in the barrel and the ignition means are disposed outside the barrel and adjacent the apertures. The barrel may be surrounded by a non-metallic outer barrel which may.

i ~:10 ii ii I: in:c i: I a t a i h.yie. t i i a i e t.gn 0 include recesses adapted to accommodate the ignition means. The outer barrel may :.:ialso house electrical conductors which facilitate electrical communication between the control means and ignition means. The outer barrel may be formed as a laminated plastics barrel which may include a printed circuit laminate for the ignition means.

Both of the above arrangements lend themselves to a modular or disposable construction. The barrel assemblies may be adapted for firing as is, or may be for mounting within a housing.

For safety, the barrel assembly may include an arming switch associated with e each ignition means which is closed inresponse to the preceding projectile assembl being discharged. Preferably, the armin"g switch is closed by biasing means which..'.

are normally resisted by the preceding projectile assembly. In a preferred.

irsembod.mentl ui diment the projectile head and spacer asseb each constitute switch....

contacts which are normally electrically isolated from each other and wherein an whisuccession eleto propical contact with theof projectile head, is also into the airspace.

sequentially igniting propellant in the barrel assemblies in rapid succession to propel sequential arrays of projectile assemblies into the airspace.

BRIEF DECITO.F.H.

In order that this invention may be more readily understood and put into practical effect, reference will now be made to the accompanying drawings which illust.irate:I typical e!mbiiments of the invention ::and ein: n whren FIG. 1 is a sectional and schematic view of an embodiment of a barrel assembly according to the invention; FIG. 2 schematically illustrates the concept of a plurality of barrel assemblies according to the invention being massed in pods; FIG. 3 is a schematic view of arrays of projectile assemblies being fired from the pods of FIG. 2; assembly according to the invention wherein the projectile assembly is.. .form ofa dart;.

FIG. 5 is a sectional and schematic view of another embodiment of a barre I assembly according to the invention; 105 .FIG. 7 is a sectional and schematic view of another embodiment of a barrel assembly according to the invention; i assembly according to the invention; FIG. 1 is a sectional and schematic view of another embodiment of a barrel assembly according to the invention; the present invention, and DESCRIPTION OF THE PREFERRED EMBODIMENT Referring to FIG. 1 there is illustrated a barrel assembly 10 including a barrel 12, a plurality of spherical projectiles 14 axially disposed within barrel 12 for operative sealing engagement with the bore of barrel 12,discrete propellant charges 16 disposed between adjacent projectile assemblies 14 for propelling the respective ojectileG. assemblies 14 ind vidualy and sequentiallythrough the muzzleemb of barrel 2, bhb"d .t th e J iven ti o'n 9:eis: axtIonal and scheaticvied of another embodimenclud a barrel plraiyosperical rojectiles h atic viewo e anotheriembod b ert d o b e d n riassemble 14 for tl pective 1 a plurality of spherical projectiles 14 axially disposed within barrel 12 for operative Ii ii i seali:i::iii1lng engagement with the bore of barrel 12,discrete propellant charges l'i:I::i:::iliiiiiiii:;i iiii~ i disposed between adjacent rojectile assemblies 14 fo propelling the respectiv

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6 ignition means 18 for igniting discrete propellant charges 16, and control means for selectively and sequentially actuating ignition means 18.

In use, the lead i i ng projectile assembly 14 is propelled in response to ignition of the leading propellant charge 16by the leading ignition means 18. Thereafter the following projectile assemblies are sequentially propelled in like fashion. There is no ammunition delivery system or moving parts, and the firing rate is practically limited only by the time taken for each projectile assembly to exit the barrel.

The control means may have time delay means to control the rapidity of fire and or timing means permitting a selected numberof sequential ignitions in response to each manual actuation of the ignition means, such as by squeezing a trigger. A mode switch may be associated with the control means to enable a user to select the form of firing, i.e. full barrel discharge, short bursts of rapid fire, sequential fire .of a selected number of projectiles, single shot firing per actuation etc. Integrated circuit electronic control means are preferably utilised as the control means and may be manufactured as part of the barrel assembly.

.eferring to FIG. 2 the barrel assembly constitutes one of a pluralityof barrel.

assemblies andthecontrol means actuates thenition meansof eachofthe barrel assemblies in such ianner that a sequential plurality of arrays of projectile assemblies are-propelled in following relationship as shown in FIG. 3. The plurality of S20 r bahrrel assemblies forms a pd 22 ad a pluality of ps aren ound ti a trainable mount 24. The aiming and firing of the barrel assemblies is controlled by a radar fire control system 25 or other conventional system.

associated propellant charges can be preloaded into the barrel. The pod has a cross-sectional dimension of 0.75 metres by 0.75 metres for example and therefore accommodates approximately 1200 barrel assemblies. Thus, a pod can be pre- 2 m:.:nbmloaded with 48000 projectile assemblies. I This enables significant fire-power to be associated with a relatively small weapon and a very high discharge rate to be achieved, bearing in mind the firing rate of each individual barrel assembly may be significantly in excess of the rate achievable by conventional automatic firearms. The barrel assemblies may be formed as a relatively lightweight honeycomb structure which will be very stiff and if desired the barrels may be arranged to focus at a point relatively close to the :weapon with a vwo counteractingthe spreadingteencies produce e expansion of the hot explosion gases radiating in an outwards direction. Alternatively a box-like baffle could be used to prevent the immediate outward spread of the gases. This baffle may be slidably supported about the outer barrel section for extension past the end of the barrels during firing. A further manner of alleviating this perceived effect would be to slightly stagger the firing of the projectiles.

Referring to the embodiments of FIGS. 4 to 10, projectile assemblies 14 are disposed in axial abutting relationship to form a compression resistant column.

Axially compressive loads are created by the pressures generated in the barrel by "ii I: i: iii i i i ii !:ii: :I.

the propulsion of preceding projectile assemblies. Compression can result in an alteration of the burn rate of a propelling charge, misalignment of ignition means with respective propelling charges or even premature ignition of propelling charge.

Each projectile assembly 14 includes a projectile head26 and means for defining a propellant space in the form of spacer assembly 28 which extends axially .and rearwardly from projectile head 26 and abuts an adjacent prwjectile assembly14.

S'l Projectile head 26 is formed from a heavy malleable material such as lead to facilitate operative sealing with barrel 12, and spacer assembly 28 is formed of a rigid material such as steel.

the embodiment of FIG. 5, the spacer assembly 28takes the form of a 2cyinclder ax radially outwarly extending collar flange 32which suports thin through projectile head 26 tothe leading end of projectile head 26 whereby compressive loads are transmitted directly between adjacent spacer assemblies 28.

Spacer assembly 28 supports a thin cylindrical rear portion30 of projectile head 26 in operative sealing contact with the bore of barrel 12. Specifically, spacer assembly 28includes a radially outwardly extending collar flange 32which supports thin cylindrical rear portion 30 of projectile head 26 in operative sealing contact with the .b o re o f: b a rre l 1 2 8 Referring to the embodiments of FIGS. 9 and 1 0,complementary wedging surfaces 34, 36 are disposed on spacer assembly 28 and projectile head 26 respectively whereby thin cylindrical reaportion 30 projectil ad 2 rg to engagement with the bore of barrel 12 in response to an axially compressive load being applied to projectile assemblyl 4. Projectile head 26 defines a tapered aperture 38 at its rearward end into which is received a complementary tapered spigot 40 disposed on the leading end of spacer assembly 28.

Relative axial movement between tapered aperture 38 and complementary tapered spigot 40 causes a radially expanding force to be applied to thin cylindrical.

rear portion 30 of projectile head 26.

In the embodiment of FIG. 7, barrel 12 is non-metalli and the bore of the barrel includes recesses 42 which at east partly accommodate e ignition means 18.

means and ignition means.

:Inthe embodiments of FIGS.8 and 9,barrel 12 includes ignition apertures 46 and ignition means 18 are disposed outside the barrel and adjacent the apertures.

Barrel 12 is surrounded by a non-metallic outer barrel 48, the bore of the outer barrel includingrecesses adapted to at least partly accommodate the ignition means. The barrel assembly may be slidably received in sheath 50. Outer barrel 48. houses Referring to FIG. 10, arming switch 52 associated with i gnition means 18 is ii2 clsed in response to the preceding projectile assembly being d ged.

each constitute switch contacts which are normally electrically isolated from each other by insulating layer 56. An electrical circuit between barrel 12and spacer assembly 28 is completed when arming switch 52closes in response to the preceding projectile assembly being discharged. The ignition means 18 is thus armed only when the preceding projectile assembly has been discharged.

i'iliiiii'ii i iii:iiliiiiiiiiiiir:iiiiiiiii:i:i'iii ::i:iiil;iiiiii:iiiiii:iiilll\ :i'ii';j:i.i'li::1 ii .,..:liiiiiiii:iiiiii'i::iiiii:iiiii il~:iiiliiZ :i liil :i-i is 9 A four barrel hand gun 60 is illustrated in FIG. 11. The barrels of the four barrel set 61, are arranged in as square formation, and are fed by a matching replaceable four barrel magazine block 62 which slots into a cutout 63 at the base of the barrel set 61. The barrel set 61 is formed integrally with the handgrip 64 which contains the electronic controls for the ignition means.

The four barrel magazine block 62 is loaded with 5rounds per barrel, which number may of course be varied depending on the size of the block and the size of the round. In this embodiment the magazine block 62 contains twenty rounds.

A variable fire rate and pattern switch 66, is provided for selectively electrically with the circuits in the hand gun via contacts which meet when the magazine block 62 is slid into position. The switch 66 maybe adjusted for electronic control to enable a user to fire individual rounds with each action of the trigger 65, up to four rounds simultaneously, or all rounds automatically on all barrels. A safety catch 68 may also be provided for electrically disabling the weapon. Preferably the 0* cartridges are disposable and may be provided in different formats so that a user provided with external flights orspiral ridges as illustrated in FIGS. 12 and 13. The ridges 70 are provided on the nose ofthe projectile to impart spin during flight. In the form illustrated a 7.62mm bullet 71 has four spiralling ridges 70 radiating from the .axis for every meter travelled.

Of course two or more spiralling ridges, spaced evenly around the bullet nose may be utilised if desired. Furthermore the height of the ridges, the length of the ridges, the pitch or degree of spiralling, the geometric curve form of the spiral, may be varied to suit the desired flight characteristics. The ridges may also extend along the side of the bullet. The cross section profile of the spiral ridges may be relatively flat, or steep according to the intended use of the ammunition, and the desired degree of reaction to the airflow.

i l 0eo C p S 9 35550 As illustrated in FIG. 13, the ridges 70 may have a steep leading face 72, which offers resistance to the airflow over the bullet, and causes the bullet to rotate a flat top portion 73 and trailing faces 74 which slope gently to the surface of the bullet.

Such ammunition may also be used in rifled barrel weapons to advantage.

Also as the spirals on the bullet would assist in producing the spin during firing, the normal pressure applied by the edge of the rifling lands against the soft metal of the bullet would be reduced. Therefore the bullet would not require the rifling to cut as long a track along the side of the bullet. Rather, the small expanding band of the Minie' gas sealing system would then be adequate to assist with spin acceleration.

On impact with soft targets, the spiral bullet of the present invention would tend to react to the increased pressure on the ridges by maintaining a high rate of twist, as it progresses through the target material.

It will of course be realised that the above has been given only by way of illustrative example of the invention, and that all such modifications and variations 15 thereto as would be apparent to persons skilled in the art are deemed tofall within the broad ambit and scope of the invention as is herein set forth.

Claims (7)

1. A barrel assembly including: a barrel; a plurality of projectile assemblies axially disposed within the barrel for operative sealing engagement with the bore of the barrel; discrete propellant charges for propelling respective projectile assemblies sequentially through the muzzle of the barrel; ignition means for igniting the discrete propellant charges; and control means for selectively and sequentially actuating the ignition means.

2. A barrel assembly as defined in claim 1, wherein the barrel assembly constitutes one of a plurality of barrel assemblies and the control means actuates the ignition means of each of the barrel assemblies in such manner that a sequential plurality of arrays of projectile assemblies are propelled in following relationship.

3. A barrel assembly as defined in claim 1, wherein the head of the projectile is formed from a heavy malleable material.

4. A barrel assembly as defined in claim 1, wherein complementary wedging surfaces are disposed on the projectile. ooooo A barrel assembly as defined in claim 4, wherein the head of the projectile defines a tapered aperture at its rearward end into which is received a complementary tapered spigot wherein relative axial movement between the tapered aperture and the complementary tapered spigot causes a radially expanding force to be applied to the projectile head. A method of defending an airspace, including:- providing a plurality of barrel assemblies as defined in any one of the preceding claims, and sequentially igniting propellant charges in the barrel assemblies in rapid succession to propel sequential arrays of projectile assemblies into the airspace.

7. In a barrel assembly of the type having a column of projectiles arranged in- line within the barrel with associated selectively ignitable propellant charges for propelling the projectiles sequentially through the muzzle of the barrel, a method of forming a seal between the projectiles and the barrel so as to prevent an ignited leading propellant charge travelling rearward past the following projectile so as to ignite the propellant charge associated with that following projectile, the method including:- providing each projectile with a radially expandable sealing part having a forwardly-reducing part-conical inner surface; providing a complementary mandrel capable of interacting with the part- conical inner surface so as to expand the sealing part into operative sealing engagement with the bore of the barrel; supporting each complementary mandrel from the column of trailing projectiles, and 20 arranging the sealing part for movement in a rearward direction over its complementary mandrel and into sealing engagement with the bore of the barrel.

8. A method as claimed in claim 21 wherein each mandrel is constituted by the nose part of each following projectile. 13

9. A method as claimed in any one of claims 6 to 8, wherein movement of the sealing part occurs as a consequence of ignition of the preceding propellant charge. DATED THIS THIRTIETH DAY OF AUGUST 2001 METAL STORM LIMITED BY PIZZEYS PATENT TRADE MARK ATTORNEYS *o 0 0 o* oo go *oo ••go* o*