U.S. patent application number 10/483302 was filed with the patent office on 2004-12-09 for projectile for radially deploying sub-projectiles.
Invention is credited to O'Dwyer, James Michael, O'Dwyer, Sean Michael.
Application Number | 20040244628 10/483302 |
Document ID | / |
Family ID | 3830258 |
Filed Date | 2004-12-09 |
United States Patent
Application |
20040244628 |
Kind Code |
A1 |
O'Dwyer, James Michael ; et
al. |
December 9, 2004 |
Projectile for radially deploying sub-projectiles
Abstract
A projectile (10) for firing from a barrel, said projectile
including a multiplicity of barrel assemblies (12, 13, 14) radially
disposed from the centre of mass of the projectile, wherein each of
said multiplicity of barrel assemblies includes a plurality of
sub-projectiles (16) axially disposed within a barrel; each of said
sub-projectiles associated with a discrete propellent charge (17)
for propelling a respective sub-projectile from the barrel, wherein
said projectile is capable of selectively firing sub-projectiles
(16), suitably with the aid of primers (18) each coupled to an
electronic controller (15). to provide a predetermined pattern of
deployed sub-projectiles. A defence system employing projectiles of
the type described is also disclosed, together with a method for
disguising the launch location of a projectile utilising divert
propulsion.
Inventors: |
O'Dwyer, James Michael;
(Queensland, AU) ; O'Dwyer, Sean Michael;
(Queensland, AU) |
Correspondence
Address: |
FINNEGAN, HENDERSON, FARABOW, GARRETT & DUNNER
LLP
1300 I STREET, NW
WASHINGTON
DC
20005
US
|
Family ID: |
3830258 |
Appl. No.: |
10/483302 |
Filed: |
July 23, 2004 |
PCT Filed: |
July 8, 2002 |
PCT NO: |
PCT/AU02/00909 |
Current U.S.
Class: |
102/480 |
Current CPC
Class: |
F42B 12/60 20130101;
F41H 11/02 20130101; F41A 19/68 20130101; F41A 19/58 20130101; F42B
12/70 20130101 |
Class at
Publication: |
102/480 |
International
Class: |
F42B 012/08 |
Foreign Application Data
Date |
Code |
Application Number |
Jul 11, 2001 |
AU |
PR 6294 |
Claims
1. A projectile for launching at a target, said projectile
including: a multiplicity of barrel assemblies radially disposed
from the centre of mass of the projectile, wherein each of said
multiplicity of barrel assemblies includes a plurality of
sub-projectiles axially disposed within a barrel; each of said
sub-projectiles associated with a discrete propellent charge for
propelling a respective sub-projectile from the barrel, wherein
said projectile is capable of selectively firing sub-projectiles to
provide a predetermined pattern of deployed sub-projectiles.
2. The projectile of claim 1 wherein the projectile is adapted to
be fired from a barrel.
3. The projectile of claim 2 wherein the plurality of
sub-projectiles is axially disposed within the barrel for operative
sealing engagement with the bore of the barrel.
4. The projectile of any one of claims 1 to 3 that is generally
spherical in shape and have the multiplicity of barrel assemblies
radially disposed from the centre of the sphere.
5. The projectile of claim 4 having a variety of different barrel
diameters in order that sub-projectiles of a variety of calibres
may be utilised.
6. The projectile of either claim 4 or claim 5 wherein relatively
large diameter barrels are disposed from the centre of the
spherical projectile and relatively small diameter barrels are
positioned between the larger diameter barrels to maximise
sub-projectile density in the projectile.
7. The projectile of any one of claims 1 to 6 wherein the
projectile includes a sabot.
8. The projectile of any one of claims 1 to 7 further including an
electronic controller for controlling ignition of the propellant
charges.
9. The projectile of claim 8 wherein a number of sub-projectiles
can be fired simultaneously or in quick succession.
10. The projectile of either claim 8 or claim 9 wherein the
multiplicity of barrel assemblies are arranged such that the
sub-projectiles may be deployed with minimal resultant reactive
force on the projectile, allowing the projectile to maintain a
desired trajectory.
11. The projectile of claim 8 further including sensors for
tracking a threat or intruder.
12. The projectile of claim 8 wherein said electronic controller
receives firing instructions from a remote tracking station via a
communications link.
13. The projectile of any one of claims 1 to 12 wherein
sub-projectiles are deployed in order to alter or control the
trajectory of the projectile.
14. A method of intercepting a missile, said method including the
steps of determining the path of the missile; firing a projectile
as claimed in any one of claims 1 to 13 into the path of said
missile; and firing selected sub-projectiles to form a
predetermined pattern of sub-projectiles in and adjacent to the
determined path of the missile.
15. A self defence method for a vehicle from an attacking force
including the steps of determining the location of the attacking
force; firing a projectile as claimed in any one of claims 1 to 13
adjacent to the determined location of the attacking force; and
firing selected sub-projectiles to form a predetermined pattern of
sub-projectiles in and adjacent to the determined location of the
attacking force.
16. A method of repelling an infantry including the steps of
determining the location of the infantry; firing at least one
projectile as claimed in any one of claims 1 to 13 adjacent to the
determined location of the infantry; and firing selected
sub-projectiles to form a predetermined pattern of sub-projectiles
in and adjacent to the determined location of the infantry.
17. A method of forming airborne images including the steps of
firing a projectile as claimed in any one of claims 1 to 13 into
the air; and firing selected sub-projectiles including image
forming matter to form a predetermined pattern of image forming
matter in the air.
18. A method of fire fighting including the steps of determining
the location of the fire; firing at least one projectile as claimed
in any one of claims 1 to 13 adjacent to the determined location of
the fire; firing selected sub-projectiles to form a predetermined
pattern of sub-projectiles in and adjacent to the determined
location of the fire; and deploying from the fired sub-projectiles
a fire retardant.
19. A method of generating a fuel-air explosion including the steps
of selecting the desired. location of the fuel-air explosion;
firing at least one projectile as claimed in any one of claims 1 to
13 adjacent to the desired location of the fuel-air explosion;
firing selected sub-projectiles including a fuel to form a
predetermined pattern of sub-projectiles; deploying the fuel from
the fired sub-projectiles; firing selected sub-projectiles
including detonators to form a predetermined pattern of
sub-projectiles; detonating said detonators to generate a fuel-air
explosion.
20. A method of deploying a payload including the steps of
selecting a desired location for the delivery of a payload; firing
at least one projectile as claimed in any one of claims 1 to 13
adjacent to the desired location of the payload; firing selected
sub-projectiles including said payload to form a predetermined
pattem of sub-projectiles; and deploying said payload from the
fired sub-projectiles.
21. A defence system for defending a designated area, said defence
system including: at least one monitor for monitoring the
designated area to detect any zone therein in which a new presence
appears; defence means capable of debilitating an intruder present
anywhere in a remote designated area wherein said defence means
includes a weapon capable of firing projectiles, wherein the
projectiles include: an array of barrel assemblies disposed
radially from the centre of mass of the projectile, each barrel
assembly having a plurality of secondary or sub-projectiles axially
disposed within a barrel, which sub-projectiles are associated with
discrete propellant charges for propelling said sub-projectiles
sequentially from the barrel, and said array of barrel assemblies
is capable of selectively firing the sub-projectiles from selected
barrels whereby said projectile may deploy a predetermined pattern
of sub-projectiles; and communication means providing communication
between the monitor and the defence for triggering selective
activation of the defence for delivering a debilitating attack to
the detected zone.
22. The defence system of claim 21 wherein the monitors include one
or more on-site sensors deployed in the designated area or
remote-sensing means deployed remote from the designated area.
23. The defence system of either claim 21 or claim 22 wherein the
monitoring means provide a visual display of the monitored
designated zone so that manual override means may be actuated, if
desired, to enable manual control of the weapon.
24. The defence system of any of claims 21 to 23 wherein a number
of sub-projectiles be fired simultaneously from a plurality of
barrels or in quick succession from the one barrel.
25. The defence system of claim 24 wherein an electrical firing
signal is carried through a circuit externally of the barrel.
26. The defence system of claim 24 wherein an electrical firing
signal is carried through superimposed sub-projectiles.
27. The defence system of claim 26 wherein the sub-projectiles clip
on to one another to continue an electrical circuit through the
barrel.
28. The defence system of claim 26 wherein the sub-projectiles abut
in electrical contact with one another.
29. The defence system of claim 24 wherein the sub-projectiles each
carry a control circuit.
30. The defence system of any one of claims 21 to 29 wherein the
array of barrel assemblies includes barrels arranged adjacent an
end of the projectile for effecting changes in attitude of the
projectile.
31. The defence system of any one of claims 21 to 30 wherein the
array of barrel assemblies includes barrels arranged medially for
laterally displacing the projectile.
32. The defence system of any one of claims 21 to 31 wherein each
array of barrel assemblies may fire a sub-projectile in a direction
having a longitudinal component in order to provide a consequent
addition to the kinetic energy of the projectile.
33. The defence system of any one of claims 21 to 31 wherein each
array of barrel assemblies may fire a sub-projectile in a direction
having a component in a direction tangential to the longitudinal
axis of the projectile in order to impart or change projectile
rotation about its longitudinal axis.
34. The defence system of any one of claims 21 to 33 wherein at
least some of the barrel assemblies may fire secondary projectiles
across flight surfaces such as a wing to induce a further steering
effect to the projectile.
35. The defence system of any one of claims 21 to 33 wherein at
least some of the barrel assemblies extend through aerofoil
surfaces so as to fire in both directions.
36. The defence system of any one of claims 21 to 33 wherein a
separate array or opposing arrays of barrel assemblies are provided
to control projectile rotation about the longitudinal axis of the
projectile.
37. The defence system of claim 36 wherein the configuration of
said arrays include opposing pairs of barrel assemblies that are
fired simultaneously to effect changes in rotation about the
longitudinal axis of the projectile only.
38. The defence system of any one of claims 21 to 37 wherein energy
required to change attitude and trajectory of the projectiles is
provided by the firing of sub-projectiles from selected barrel
assemblies.
39. A method of masking the launch location of a projectile
launching apparatus, said method including the steps of: (a)
discharging at least one projectile from a barrel assembly, said
barrel assembly having a barrel, a plurality of projectiles axially
disposed within the barrel for operative sealing engagement with
the bore of the barrel, and discrete propellant charges for
propelling respective projectiles sequentially through the muzzle
of the barrel; and (b) whilst said at least one projectile is in
flight firing at least one sub-projectile from an array of divert
propulsion assemblies incorporated therein, each divert propulsion
assembly having a plurality of sub-projectiles axially disposed
within a divert propulsion barrel, which sub-projectiles are
associated with secondary discrete propellant charges for
propelling said sub-projectiles sequentially from the divert
propulsion barrel; wherein (c) said array of divert propulsion
barrel assemblies is capable of selectively firing the
sub-projectiles from selected divert propulsion barrels whereby
said projectile is accelerated by the reactionary force generated
by said firing of sub-projectiles.
Description
BACKGROUND OF THE INVENTION
[0001] 1. Field of the Invention
[0002] This present invention relates to the deployment of objects
in the nature of projectiles and in particular, although not
exclusively, to the formation of a predetermined pattern of
deployed sub-projectiles by a parent projectile and to a projectile
launching method for masking the launch location of a
projectile.
[0003] 2. Discussion of the Background Art
[0004] Projectiles that incorporate explosive charges have been
used as fragmentation devices to deploy a plurality of fragments.
In a simple form the casing of such a projectile fragments on
detonation of the explosive charge such that individual fragments
of the casing are deployed radially to form a fragmentation pattern
roughly in the shape of the surface of a sphere.
[0005] In other configurations, the shape of the charge and the
configuration of the casing may be varied to control the
fragmentation pattern. However, such fragmenting projectiles
produce a relatively thin, shell like fragment casing pattern. It
is desirable that the depth of the fragmentation be able to be
increased or controlled.
[0006] Such projectiles may be particularly suited to defending a
designated area whilst avoiding rending the area dangerous after a
threat situation has diminished, such as occurs with conventional
minefields.
[0007] Existing defences to attacks typically include systems for
acquiring and monitoring the trajectory of objects, including
flying objects such as rockets and missiles. Examples of trajectory
acquisition and monitoring systems are described in U.S. Pat. No.
4,622,458 to Boeck et al and U.S. Pat. No. 5,960,097 to Pfeiffer et
al.
[0008] More recently, sophisticated defences to threats which
include rounds launched at relatively high angles so as to be
thrown or hurled at a target, such as characteristic of mortars,
are capable of calculating the source of an attack by deriving the
location of a projectile launching apparatus from the trajectory of
the projectiles.
SUMMARY OF THE INVENTION
OBJECT OF THE INVENTION
[0009] It is an object of certain embodiments of the invention to
provide a projectile that may be used to deploy sub-projectiles in
a predetermined pattern that addresses the problems of the prior
art, by providing increased or controlled fragmentation, or at
least provides a useful choice for defence purposes.
[0010] It is a further object of certain embodiments of the
invention to provide a defence system that has improved control
over deployment of projectiles and does not render the defended
area unsafe for later civilian use.
[0011] It is an object of other embodiments of the invention to
provide a defence system capable of masking the location of a
projectile launching apparatus by diverting projectile in flight
whereby the location of the projectile launching apparatus is
unable, or at least more difficult, to derive.
DISCLOSURE OF THE INVENTION
[0012] According to a first form of the present invention, there is
provided a projectile including a multiplicity of barrel assemblies
radially disposed from the centre of mass of the projectile,
wherein each of said multiplicity of barrel assemblies includes a
plurality of sub-projectiles axially disposed within a barrel,
wherein each of said sub-projectiles are associated with a discrete
propellent charges for propelling a respective sub-projectile from
the barrel, and wherein said projectile is capable of selectively
firing sub-projectiles to provide a predetermined pattern of
deployed sub-projectiles.
[0013] Preferably the projectiles of the present invention are
particularly adapted for deployment by firing from the barrel of a
gun, rather than self-propelled missiles or rockets that are
launched from a tube or gantry. In other embodiments the
projectiles of the invention may be deployed by dropping from a
mobile platform, such as an aircraft or ship, utilising gravity for
delivery or, alternatively, adapted for throwing by a soldier or
protective services officer in a similar fashion to a conventional
manually delivered grenade.
[0014] The projectiles of the invention suited to firing from a
barrel may, in a first aspect, be used for intercepting and
destroying incoming missiles, particularly of the high altitude
ballistic type. In a second aspect, the present invention provides
a method of intercepting a missile including the steps of
determining the path of the missile, firing a projectile of the
type herein described into the path of said missile, and firing
selected sub-projectiles to form a predetermined pattern of
sub-projectiles in and adjacent to the determined path of the
missile.
[0015] The projectiles of the present invention may be used for
vehicle self defence. A vehicle coming under attack, in particular
from close range, may fire a projectile of the type herein
described towards the attackers and deploy the sub-projectiles in a
predetermined pattern amongst the attackers. In a third aspect, the
present invention provides a self defence method for a vehicle from
an attacking force including the steps of determining the location
of the attacking force, firing a projectile of the type herein
described adjacent to the determined location of the attacking
force, and firing selected sub-projectiles to form a predetermined
pattern of sub-projectiles in and adjacent to the determined
location of the attacking force.
[0016] The projectiles of the present invention may be used for
repelling an infantry advance. In a fourth aspect, the present
invention provides a method of repelling an infantry including the
steps of determining the location of the infantry, firing at least
one projectile of the type herein described adjacent to the
determined location of the infantry, and- firing selected
sub-projectiles to form a predetermined pattern of sub-projectiles
in and adjacent to the determined location of the infantry.
[0017] The projectiles of the present invention may be used for
forming airborne images, such as fireworks. In a fifth aspect, the
present invention provides a method of forming airborne images
including the steps of firing a projectile of the type herein
described into the air, and firing selected sub-projectiles
including image forming matter to form a predetermined pattern of
image forming matter in the air.
[0018] The projectiles of the present invention may be used for
fire fighting. In a sixth aspect, the present invention provides a
method of fire fighting including the steps of determining the
location of the fire, firing at least one projectile of the type
herein described adjacent to the determined location of the fire,
firing selected sub-projectiles to form a predetermined pattern of
sub-projectiles in and adjacent to the determined location of the
fire, and deploying from the fired sub-projectiles a fire
retardant.
[0019] The projectiles of the present invention may be used for
generating a fuel-air explosion. In a seventh aspect, the present
invention provides a method of generating a fuel-air explosion
including the steps of selecting the desired location of the
fuel-air explosion, firing at least one projectile of the type
herein described adjacent to the desired location of the fuel-air
explosion, firing selected sub-projectiles including a fuel to form
a predetermined pattern of sub-projectiles, deploying the fuel from
the fired sub-projectiles, firing selected sub-projectiles
including detonators to form a predetermined pattern of
sub-projectiles, detonating said detonators to generate a fuel-air
explosion.
[0020] The projectiles of the present invention may be used for
deploying a variety of payloads. In a eighth aspect, the present
invention provides a method of deploying a payload including the
steps of selecting a desired location for the delivery of a
payload, firing at least one projectile of the type herein
described adjacent to the desired location of the payload, firing
selected sub-projectiles including said payload to form a
predetermined pattern of sub-projectiles, and deploying said
payload from the fired sub-projectiles.
[0021] The projectiles of the present invention may be used for
defending a designated area. In a ninth aspect, the invention
resides broadly in defence system for defending a designated area,
said defence system including:
[0022] at least one monitor for monitoring the designated area to
detect any zone therein in which a new presence appears;
[0023] defence means capable of debilitating personnel present
anywhere in a remote designated area wherein said defence means
includes a weapon capable of firing projectiles wherein the
projectiles include an array of barrel assemblies disposed radially
from the centre of mass of the projectile, each barrel assembly
having a plurality of secondary or sub-projectiles axially disposed
within a barrel, which sub-projectiles are associated with discrete
propellant charges for propelling said sub-projectiles sequentially
from the barrel, wherein said array of barrel assemblies is capable
of selectively firing the sub-projectiles from selected barrels
whereby said projectile may deploy a predetermined pattern of
sub-projectiles; and
[0024] communication means providing communication between the
monitor and the defence for triggering selective activation of the
defence for delivering a debilitating attack to the detected
zone.
[0025] The monitors include one or more on-site sensors deployed in
the designated area or remote-sensing means deployed remote from
the designated area. Alternatively the monitoring means may include
both on-site and remote sensing means.
[0026] The monitoring means may also provide a visual display of
the monitored designated zone so that manual override means may be
actuated, if desired, to enable manual control of the set defence
means.
[0027] A number of secondary or sub-projectiles can be fired
simultaneously from a plurality of barrels or in quick succession
from the one barrel. In such arrangements the electrical signal may
be carried externally of the barrel or it may be carried through
the superimposed secondary projectiles which may clip on to one
another to continue the electrical circuit through the barrel, or
abut in electrical contact with one another. The sub-projectiles
may carry the control circuit or they may form a circuit with the
barrel.
[0028] The array of barrel assemblies may be arranged adjacent the
leading end or the trailing end of the projectile for effecting
changes in attitude of the projectile or medially for displacing
laterally displacing the projectile. Alternatively the directional
control system may include an array of barrel assemblies adjacent
both leading and trailing ends of the projectile.
[0029] The or each array of barrel assemblies may fire a
sub-projectile in a direction having a longitudinal component in
order to provide a consequent addition to the kinetic energy of the
projectile or a component in a direction tangential to the
longitudinal axis of the missile in order to impart or change
projectile rotation about its longitudinal axis. The barrel
assembly may fire secondary projectiles across flight surfaces such
as a wing to induce a further steering effect to the projectile.
Alternatively barrel assemblies may extend through the aerofoil
surfaces so as to fire in both directions. This may add structural
strength to the aerodynamic design.
[0030] If desired, a separate array or opposing arrays of barrel
assemblies may be provided to control projectile rotation about the
longitudinal axis of the projectile. The configuration of the
arrays may include opposing pairs of barrel assemblies that are
fired simultaneously to effect changes in rotation about the
longitudinal axis of the projectile only. The sub-projectiles may
be selectively actuated before and/or after firing secondary
projectiles form the directional control system to negate or
utilise the effects on the projectile of such rotation about its
longitudinal axis.
[0031] In certain embodiments of the present invention energy
required to change attitude and/or the flight direction of the
parent projectile may be provided by the firing of sub-projectiles
from one or more selected barrel assemblies.
[0032] According to a second form of the present invention, there
is provided a method of masking the launch location of a projectile
launching apparatus is provided. The method includes the steps of
discharging at least one projectile from a barrel assembly, said
barrel assembly having a barrel, a plurality of projectiles axially
disposed within the barrel for operative sealing engagement with
the bore of the barrel, and discrete propellant charges for
propelling respective projectiles sequentially through the muzzle
of the barrel and, whilst said at least one projectile is in
flight, firing at least one sub-projectile from an array of divert
propulsion assemblies incorporated therein, each divert propulsion
assembly having a plurality of sub-projectiles axially disposed
within a divert propulsion barrel, which sub-projectiles are
associated with secondary discrete propellant charges for
propelling said sub-projectiles sequentially from the divert
propulsion barrel, wherein said array of divert propulsion barrel
assemblies is capable of selectively firing the sub-projectiles
from selected divert propulsion barrels whereby said projectile is
accelerated by the reactionary force generated by said firing of
sub-projectiles.
[0033] The overall shape of the sub-projectile is not narrowly
critical as the sub-projectile is a mass against which the
secondary propellant acts and exerts a reactionary force on the
breech of the divert propulsion barrel. In the context of the
present form of the invention, the breech may be formed by
subsequent sub-projectiles remaining in the barrel in sealing
engagement with the bore of the divert propulsion barrel. The
reactionary force is transferred from the breech of the secondary
or divert propulsion barrel to the projectile and results in an
acceleration of the projectile.
[0034] The array of barrel assemblies may be disposed radially from
the centre of mass of the projectile. Such configurations of barrel
assemblies are particularly suited to objects that do not
incorporate an in flight propulsion system, ie. rockets and
missiles. The firing of sub-projectiles simply displaces the
projectile and the projectile continues upon its trajectory, save
for the displacement, the apparent trajectory.
[0035] The present invention has particular application to area
denial systems wherein the area is subject to shelling by
projectiles launched from a pod, such as a mortar box. It will of
course be understood that the present invention also has
application to disguising the firing location of other projectile
launching or firing systems.
[0036] In a preferred embodiment the apparent trajectory may be
selected to draw fire from the launch apparatus to other enemy
positions.
[0037] The projectiles of the present invention advantageously
employ barrel assemblies of the type described in International
Patent Application Nos. PCT/AU94/00124 and PCT/AU96/00459. Such
barrel assemblies include a barrel;
[0038] a plurality of sub-projectiles axially disposed within the
barrel for operative sealing engagement with the bore of the
barrel, and discrete propellant charges for propelling respective
sub-projectiles sequentially through the muzzle of the barrel.
[0039] The sub-projectiles 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. If required, the projectiles carrying the
sub-projectiles may be substantially cylindrical, ovoid or
spherical in shape.
[0040] The propellant charge may be form as a solid block to
operatively space the sub-projectiles in the barrel or the
propellant charge may be encased in metal or other rigid case which
may include an embedded primer having external contact means
adapted for contacting an pre-positioned electrical contact
associated with the barrel. For example the primer could be
provided with a sprung contact which may be retracted to enable
insertion of the cased charge into the barrel and to spring out
into a barrel aperture upon alignment with that aperture for
operative contact with its mating barrel contact. If desired the
outer case may be consumable or may chemically assist the
propellant burn. Furthermore an assembly of stacked and bonded or
separate cased charges and sub-projectiles may be provided for
reloading a barrel.
[0041] Each sub-projectile may include a head and extension means
for at least partly defining a propellant space. The extension
means may include a spacer assembly that extends rearwardly from
the head and abuts an adjacent sub-projectiles assembly.
[0042] The spacer assembly may extend through the propellant space
and the head whereby compressive loads are transmitted directly
through abutting adjacent spacer assemblies. In such
configurations, the spacer assembly may add support to the
extension means that may be a thin cylindrical rear portion of the
head. Furthermore the extension means may form an operative sealing
contact with the bore of the barrel to prevent burn leakage past
the sub-projectile.
[0043] The spacer assembly may include a rigid collar which extends
outwardly to engage a thin cylindrical rear portion of a malleable
head inoperative sealing contact with the bore of the barrel such
that axially compressive loads are transmitted directly between
spacer assemblies thereby avoiding deformation of the malleable
head. Complementary wedging surfaces may be disposed on the spacer
assembly and head respectively whereby the head is urged into
engagement with the bore of the barrel in response to relative
axial compression between the spacer means and the head. In such
arrangement the head and spacer assembly may be loaded into the
barrel and there after an axial displacement is caused to ensure
good sealing between the sub-projectile and barrel. Suitably the
extension means is urged into engagement with the bore of the
barrel.
[0044] The head may define 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 head and the complementary tapered spigot
causes a radially expanding force to be applied to the
sub-projectile.
[0045] The barrel may be non-metallic and the bore of the barrel
may include recesses that may fully or partly accommodate the
ignition means. In this configuration the barrel houses electrical
conductors that facilitate electrical communication between the
control means and ignition means. This configuration may be
utilised for disposable barrel assemblies that have a limited
firing life and the ignition means and control wire or wires
therefore can be integrally manufactured with the barrel.
[0046] A barrel assembly may alternatively include ignition
apertures in the barrel and the ignition means are disposed outside
the barrel and adjacent the apertures. A non-metallic outer barrel
that may include recesses adapted to accommodate the ignition means
may surround the barrel. The outer barrel may also house electrical
conductors that facilitate electrical communication between the
control means and ignition means. The outer barrel may be formed as
a laminated plastics barrel that may include a printed circuit
laminate for the ignition means.
[0047] The barrel assembly may have adjacent sub-projectiles that
are separated from one another and maintained in spaced apart
relationship by locating means separate from the sub-projectiles,
and each sub-projectile may include an expandable sealing means for
forming an operative seal with the bore of the barrel. The locating
means may be the propellant charge between adjacent sub-projectiles
and the sealing means suitably includes a skirt portion on each
sub-projectile that expands outwardly when subject to an in-barrel
load. The in-barrel load may be applied during installation of the
sub-projectiles or after loading such as by tamping to consolidate
the column of sub-projectiles and propellant charges or may result
from the firing of an outer sub-projectile and particularly the
adjacent outer sub-projectile.
[0048] The rear end of the sub-projectile may include a skirt about
an inwardly reducing recess such as a conical recess or a
part-spherical recess or the like into which the propellant charge
portion extends and about which rearward movement of the
sub-projectile will result in radial expansion of the
sub-projectile skirt. This rearward movement may occur by way of
compression resulting from a rearward wedging movement of the
sub-projectile along the leading portion of the propellant charge
it may occur as a result of metal flow from the relatively massive
leading part of the sub-projectile to its less massive skirt
portion.
[0049] Alternatively the sub-projectile may be provided with a
rearwardly divergent peripheral sealing flange or collar which is
deflected outwardly into sealing engagement with the bore upon
rearward movement of the sub-projectile. Furthermore the sealing
may be affected by inserting the sub-projectiles into a heated
barrel that shrinks onto respective sealing portions of the
sub-projectiles. The sub-projectile may comprise a relatively hard
mandrel portion located by the propellant charge and which
cooperates with a deformable annular portion may be moulded about
the mandrel to form a unitary sub-projectile which relies on metal
flow between the nose of the sub-projectile and its tail for
outward expansion about the mandrel portion into sealing engagement
with the bore of the barrel.
[0050] The sub-projectile assembly may include a rearwardly
expanding anvil surface supporting a sealing collar thereabout and
adapted to be radially expanded into sealing engagement with the
barrel bore upon forward movement of the sub-projectile through the
barrel. In such a configuration it is preferred that the propellant
charge have a cylindrical leading portion that abuts the flat end
face of the sub-projectile.
[0051] The sub-projectiles may be adapted for seating and/or
location within circumferential grooves or by annular ribs in the
bore or in rifling grooves in the bore and may include a metal
jacket encasing at least the outer end portion of the
sub-projectile. The sub-projectile may be provided with
contractible peripheral locating rings which extend outwardly into
annular grooves in the barrel and which retract into the
sub-projectile upon firing to permit its free passage through the
barrel.
[0052] The electrical ignition for sequentially igniting the
propellant charges of a barrel assembly may preferably include the
steps of igniting the leading propellant charge by sending an
ignition signal through the stacked sub-projectiles, and causing
ignition of the leading propellant charge to arm the next
propellant charge for actuation by the next ignition signal.
Suitably all propellant charges inwardly from the end of a loaded
barrel are disarmed by the insertion of respective insulating fuses
disposed between normally closed electrical contacts.
[0053] Ignition of the propellant may be achieved electrically or
ignition may utilise conventional firing pin type methods such as
by using a centre-fire primer igniting the outermost sub-projectile
and controlled consequent ignition causing sequential ignition of
the propellant charge of subsequent rounds. Controlled rearward
leakage of combustion gases or controlled burning of fuse columns
extending through the sub-projectiles may achieve this.
[0054] In other embodiments, the ignition is electronically
controlled with respective propellant charges being associated with
primers that are triggered by distinctive ignition signals. For
example the primers in the stacked propellant charges may be
sequenced for increasing pulse width ignition requirements whereby
electronic controls may selectively send ignition pulses of
increasing pulse widths to ignite the propellant charges
sequentially in a selected time order. Preferably however the
propellant charges are ignited by a set pulse width signal and
burning of the leading propellant charge arms the next propellant
charge for actuation by the next emitted pulse.
[0055] Suitably in such embodiments all propellant charges inwardly
from the end of a loaded barrel are disarmed by the insertion of
respective insulating fuses disposed between insertion of
respective insulating fuses disposed between normally closed
electrical contacts, the fuses being set to burn to enable the
contacts to close upon transmission of a suitable triggering signal
and each insulating fuse being open to a respective leading
propellant charge for ignition thereby.
[0056] In certain embodiments the barrel assemblies may be of the
low-pressure type, which fire grenade-like sub-projectiles although
high muzzle pressure barrel assemblies may be used. Respective
barrel assemblies may be loaded with different sub-projectiles and
the barrel assemblies may have different size bores for
accommodating different size sub-projectiles.
[0057] Suitably each sub-projectile includes a trailing collar
captively mounted to the sub-projectile body and when stored in the
barrel, extends rearwardly to wedge against the nose portion of a
trailing sub-projectile body. Suitably a shallow wedge provides the
wedging action whereby, in use, the trailing end of the collar is
expanded into operative sealing engagement with the barrel.
[0058] The trailing collar may be mounted for limited axial
movement relative to the sub-projectile body and the leading end of
the collar formed with an annular sealing face engageable with a
complementary face formed on the sub-projectile body whereby
rearward movement of the sub-projectile body resulting from the
reaction of propellant gases thereon forces the its complementary
face into sealing engagement with the annular sealing face at the
leading end of the collar.
[0059] The complementary face and the annular sealing face may
extend substantially radially and be formed with complementary
sealing features thereon. However it is preferred that these faces
are complementary part-conical sealing faces which wedge into tight
sealing engagement with one another. The leading end part may also
be expandable into operative sealing engagement with the barrel.
Suitably however the wedging between the part-conical faces are
relatively steep faces whereby the leading end of the collar is not
expanded into operative sealing engagement with the barrel by the
wedging action.
[0060] In low pressure applications, preferably each sub-projectile
is associated with a high-pressure propellant chamber that exhausts
to respective low-pressure propulsion chambers formed between the
adjacent sub-projectiles for efficient low muzzle velocity
operation. The high-pressure propellant chambers may be formed
integrally with the sub-projectile body or the trailing collar or
be provided at the exterior of the barrel to communicate therewith
through ports provided through the barrel wall.
[0061] Suitably the configuration of the space into which the
ignited propellant propagates and the propellant properties are
such that only low barrel pressures occur in use, such as in the
order of 2,000 psi to 5,000 psi. Typically the collar is such that
in its relaxed attitude it does not prevent free movement of the
projectile through the barrel either for loading purposes or during
firing.
[0062] A pressure pad is mounted on the housing inwardly of the
open trailing end. The collar is relocated from the engaged
condition upon ignition of the propellant and is retained in a
relaxed condition by the pressure pad for passage through the
barrel and out the muzzle of the barrel.
[0063] The projectile may be of the conventional type and be
conventionally fired or preferably be adapted to be fired from a
barrel assembly that includes a plurality of projectiles axially
disposed within a barrel wherein each of said projectiles are
associated with a discrete propellant charges for propelling said
projectiles from the barrel.
[0064] The projectile, in a preferred form, may be generally
spherical in shape and have the multiplicity of barrel assemblies
radially disposed from the centre of the sphere. The barrel
assemblies may be the same or different. For example whilst large
diameter barrels may be disposed from the centre of the spherical
projectile. Smaller diameter barrels may be positioned between the
larger diameter barrels to provide the maximum sub-projectile
density in the projectile. It may be desirable to provide the
projectile with the maximum barrel packing density and hence
firepower. Alternatively it may be desirable to provide the
projectile with a variety of barrel bores in order that
sub-projectiles of a variety of calibres may be utilised.
[0065] The projectile may be a saboted projectile for advantageous
deployment. A spherical projectile may be saboted into a more
convenient shape for firing from a conventional deployment system
such as in the form of a conventional munition. Alternatively if it
is desirable to provide increased muzzle velocity a saboted
projectile can accommodate an increased propellant charge without
require a prohibitive barrel length.
[0066] Barrel assemblies that are radially disposed from the centre
of mass of the projectile allow the projectiles to deploy the
sub-projectiles in a regular and readily controlled manner. Barrel
assemblies that are radially disposed from the centre of mass of
the projectile allow the projectile to maintain its attitude. By
deploying sub-projectiles in a manner that results in zero
resultant reactive force on the projectile the projectile may be
maintained on its desired trajectory
[0067] A number of sub-projectiles can be fired simultaneously, or
in quick succession. In such arrangements the electrical signal may
be carried externally of the barrel or it may be carried through
the superimposed sub-projectiles that may clip on to one another to
continue the electrical circuit through the barrel, or abut in
electrical contact with one another. The sub-projectiles may carry
the control circuit or they may form a circuit with the barrel.
[0068] The projectile of the present invention may deploy the
sub-projectiles in a predetermined pattern that may be selected for
particular applications. For example, in order to intercept and
destroy an incoming missile, it is desirable to deploy the
sub-projectiles in a manner that maximises the likelihood of the
missile impacting with one or more of the sub-projectiles.
Fragmentation systems have been employed to scatter fragments of a
projectile in the path of an incoming missile. However, systems
such as this that explode the projectile generally produce a band
of fragments that disperse and form an expanding spherical shell.
The projectiles may deploy the sub-projectiles of the invention in
a more homogeneous manner throughout the space occupied by the
predetermined pattern. By controlling the timing of the firing of
the sub-projectiles it is possible to establish a three dimensional
"frag" pattern having a substantially homogeneous distribution of
sub-projectiles. Alternatively, the sub-projectiles may be
concentrated in areas where the missile is more likely to be
intercepted so as to increase the effectiveness of the deployed
sub-projectiles.
[0069] The sub-projectile may contain material for forming
air-borne images. The image forming material may include, for
example, explosive matter, incendiary matter, incandescent or
luminous matter or other matter to provide a highly visible
temporary image. Alternatively, the image forming matter may
include smoke, gas, particles or sheets or strips, such as in the
nature of chaff, or other material capable of being dispersed to
form, an image. Accordingly, the projectile of the invention may be
advantageously employed to launch counter-measures from military
aircraft. The image forming matter may also include means for
slowing its descent from its dispersed position, such as a
parachute and the like.
[0070] The sub-projectiles may be arranged in the barrel assemblies
such that once fired and the image forming matter deployed, the
desired temporary airborne image is formed. Sub-projectiles
containing different image forming matter, either differing in
colour or form, may be sequentially loaded into each barrel
assembly.
[0071] The image forming matter may be deployed, for example, by
explosive means, by stored energy or by separation of separable
parts of the sub-projectile to expose the image forming matter or
by any other suitable dispersing means.
[0072] The image forming matter may be contained within a housing
that may be of any suitable configuration that provides for the
containment of the image forming matter and is suitably configured
for engagement with the trailing end of the expandable collar of
the preceding projectile. Preferably the housing is of the type
employed with grenade-like projectiles, having relatively squat
shape although projectiles having elongate housings could also be
employed.
[0073] The housing may suitably be formed from biodegradable
material and/or combustible material. This material may be based on
a natural product such as woodchip or a synthetic material, such as
a biodegradable polymer.
[0074] Advantageously the projectiles of the present invention may
deploy selected sub-projectiles in order to control the course of
the projectile. Such deployment may be understood as a divert
propulsion system and may be used to affect limited corrections to
the position of the projectile for the deployment of the remainder
of the sub-projectiles in the desired pattern.
[0075] The projectiles of the present invention may suitably be
employed in a defence system of the type described in the present
applicant's International Patent Application No.
PCT/AU00/01351.
BRIEF DETAILS OF THE DRAWINGS
[0076] 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 illustrate preferred embodiments of the
invention and wherein:
[0077] FIG. 1 is a cross sectional illustration of a projectile
according to a preferred embodiment of the present invention;
[0078] FIG. 2 is a cross sectional illustration of a saboted
projectile for use in a barrel assembly having a plurality of
axially disposed saboted projectiles;
[0079] FIG. 3 is a cross sectional illustration of the firing of
saboted projectiles as shown in FIG. 2;
[0080] FIG. 4 is a side elevational diagram of a defence system
according to a further embodiment of the invention; and
[0081] FIG. 5 is a perspective diagram of the defence system of the
further embodiment.
DESCRIPTION OF PREFERRED EMBODIMENTS
[0082] FIG. 1 shows a projectile 10 having six (6) large bore
barrels 12 of a convenient calibre, although only four (4) are
shown in this cross sectional representation. The remaining two (2)
large bore barrels (extending perpendicularly to the page) are
depicted at 11. The cross sectional representation also shows four
(4) medium bore barrels 13 of medium calibre, and forty-eight (48)
small bore barrels 14 of relatively small calibre. The large bore
12, medium bore 13 and small bore 14 barrels each contain a
plurality of axially disposed sub-projectiles 16, as represented on
the drawing. The sub-projectiles are associated with propellant
charges 17 and ignition means 18, which ignition means may be
sequentially fired under the control of an electronic controller
15. In some embodiments, the projectile 10 may also contain an
explosive charge for terminal detonation.
[0083] The electronic controller 15, which is disposed in the
centre of the projectile 10 behind the barrels 11, 12 in this
embodiment, may include sensors for tracking an incoming missile
when in-flight. Alternatively, the electronic controller 15 may
receive firing instructions from a remote tracking station via a
communications link. The sequenced firing of a number of the
sub-projectiles may thus be coordinated to provide an improved
likelihood of impacting with the targeted incoming missile or
similar threat.
[0084] FIG. 2 shows a projectile of the type shown in FIG. 1 with a
sabot 20, wherein the sub-projectiles are omitted for reasons of
clarity. The projectile 10 is retained in a barrel within the sabot
20. The sabot includes a forward sabot portion 21, a rearward sabot
portion 22 and an expanding sleeve 23 disposed about a chamfered
rear surface 24 of the rearward sabot portion. The detonation and
firing of a propellant charge in front of the forward sabot portion
21 forces the rearward sabot portion 22 against the expandable
sleeve 23 and causes the expandable sleeve to sealably engage with
the bore of a parent barrel.
[0085] FIG. 3 shows a series of projectiles 10 being fired from a
parent barrel assembly 30, having a plurality of parent barrels 31,
32 and 33. Projectile 10A has been fired from barrel 33 and has
discarded its sabot (not shown). Projectile 10B has been fired from
barrel 32 and the sabot 20 is shown in the process of being
discarded. The expandable sleeve 23 has detached from the rearward
sabot 22 and the rearward sabot 22 has also detached from
projectile 10B. Forward sabot 21 has similarly detached from the
projectile 10B. Projectile 10C has been more recently fired from
barrel 31 and the sabot 20 has commenced detachment from projectile
10C.
[0086] Referring to FIGS. 4 and 5, it will be seen that a
designated area 40 to be defended is monitored by an array of field
sensors 41 distributed over the designated area and which may be of
any suitable type such as pressure, acoustic or seismic type
sensors.
[0087] The illustrated defence system 42 employs a weapon taking
the form of a pair of grenade boxes 43 each using the barrel
assemblies 30 and coupled to a remote sensing means 44 and to a
receiver unit 49 associated with the field sensors 41. The remote
sensing means 44, which in the embodiment is tower mounted, is
adapted to sweep the designated area 40 using electro-optical or
microwave techniques to monitor any intrusion into the designated
area by a personnel, vehicles or other intruder.
[0088] The receiver unit 49 is adapted to receive signals from the
array of field sensors 41, using a radio frequency (RF)
communications link in the embodiment (although a cable link may be
employed in the alternative). Upon any sensed intrusion in the area
40, the zone of the intrusion will be isolated for targeting by
projectiles 10 fired from the grenade boxes 43. Thus the designated
area 40 is monitored by either or both of the array of field
sensors 41 or by the remote sensing means 44.
[0089] It is desirable that each grenade box 43 is located in a
substantially concealed position, such as a hole in the ground.
Once set up, the hole in which the grenade box 43 is placed may be
back filled without causing any detrimental effects to the
operation of the barrel assemblies 30 therein. In other
arrangements, the grenade box 43 may be conveniently concealed in
foliage and adjusted by screw jacks 48 associated with a support
base 47 for the grenade box.
[0090] A subsidiary control circuit 43a (see FIG. 5), provided as a
plug-in connection to the grenade box 43, is fitted on-site but not
during transport so as to maintain safety of the weapon during
transport. Once fitted with the control circuit 43a, the weapon is
armed and ready to fire in accordance with controls provided by the
sensor unit 44 and/or the receiver unit 49. The control circuit is
suitably able to communicate with the electronic controller 15 in a
respective projectile, as required.
[0091] A central remote sensor 44 in FIG. 2 is linked to multiple
grenade boxes 43 via respective control circuits 43a. In use, if an
intrusion into the detected area is detected at a zone, such as any
one of the zones indicated as 50 to 59, the selected grenade box 43
can be activated to fire one or more projectiles 45 into that
particular zone. The sub-projectiles may be subsequently fired a
respective projectile 45, either in accordance with a pre-selected
sequence or under remote control, to produce a predetermined
pattern of deployed sub-projectiles. The pattern of sub-projectiles
is desirably chosen in accordance with the nature of the
intruder.
[0092] An intruder coming into the designated area 40 may be in any
of a number of forms and may include a plurality of intruders. An
intruder may be military personnel, in the form of an infantryman
or foot soldier. Alternatively, the intruder may be a manned or
unmanned vehicle such as an armoured car or tank. The intruder may
have sophisticated defence systems that may track the trajectory of
an incoming round and calculate the location of the launch
apparatus, thereby enabling an attack on the previously hidden
launch apparatus. The defence system of the embodiment allows the
trajectory of the projectile to be diverted in flight by launching
sub-projectiles, thereby enabling an apparent trajectory to be
tracked and the true location of the launch apparatus to be masked.
If feasible, the apparent trajectory may be selected to draw enemy
fire directed at the defence system 42 to other enemy
positions.
[0093] Whilst the above defence system is land based, another
aspect of the invention concerns projectiles that might be termed
water mines. These water mines may be launched from a ship and
remain floating in the water and activated for either remote
control or autonomous operation using on-board sensor systems,
including radar, sonar or infra-red sensors. A line of such mines,
incorporating stabilising or anchoring means such as a suspended
weight, could be laid to provide a marine defence perimeter capable
or being activated or deactivated as required.
[0094] In another mode of deployment, projectiles of the invention
may be dropped from an aircraft such as a helicopter. Stabilising
or anchoring means, such as spikes, could be provided to fix retain
projectiles in one position on the ground. A first layer of
sub-projectiles could include sensor systems for launching to
detect the presence of enemy troops or vehicles, which could be
engaged as required by grenades in subsequent layers in individual
barrels of the projectile. Further sensors may be provided in other
layers for surveying the result of an engagement.
[0095] A further mode of deployment is to provide a projectile of a
size that can be conveniently hand-held and deployed by throwing,
similar to a conventional grenade. However, the incorporation of
sub-projectiles in barrels in the hand-delivered projectile enables
it to be used in a repeating mode using a pre-set time delay or a
remote control facility. This may provide certain advantages in
engagements that occur in closed spaces, such as in urban warfare
or topography including caves. The sub-projectiles may incorporate
non-lethal rounds and an audio annunciation system for warning,
perhaps in a siege situation, that additional rounds are capable of
being fired if the miscreants involved fail to surrender
immediately.
[0096] Projectiles of the invention may be carried into space and
delivered into orbit around a planet or moon as required,
effectively comprising a satellite. Since the barrel assemblies can
be radially dispersed within a generally spherical body, they
function very effectively to correct the position of the satellite
in orbit, protect a zone around a valuable satellite from space
junk, meteorites and the like, or to engage an enemy space vehicle
or satellite. A change of position can be undertaken much more
rapidly in the low gravity environment because of the energy
liberated by firing a solid sub-projectile, rather than a burst of
gas as in conventional satellites. The satellite projectiles are
suitably constructed so as to be consumed by combustion upon
re-entry into the atmosphere subsequent to orbital decay.
[0097] In one particular form, the satellite may comprise a
super-projectile which in turn may deploy projectiles of the
present invention from radially disposed barrel assemblies therein,
and those deployed projectiles may themselves be equipped with
sub-projectiles, thus providing a two tiered defence system. This
two tiered system of course may be employed in other applications
of suitable scale.
[0098] 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 thereto as would be apparent to
persons skilled in the art are deemed to fall within the broad
scope and ambit of the invention as is herein set forth in the
following claims.
* * * * *