U.S. patent application number 11/039836 was filed with the patent office on 2006-03-30 for anti-missile missiles.
This patent application is currently assigned to Metal Storm Limited. Invention is credited to James Michael O'Dwyer.
Application Number | 20060065150 11/039836 |
Document ID | / |
Family ID | 3819366 |
Filed Date | 2006-03-30 |
United States Patent
Application |
20060065150 |
Kind Code |
A1 |
O'Dwyer; James Michael |
March 30, 2006 |
Anti-missile missiles
Abstract
An anti-missile missile (10) includes a missile configured to
track and intercept an incoming missile travelling along path (12).
Missile (10) includes at least one barrel assembly (13) having a
multiplicity of projectiles stacked axially within barrel assembly
(13), together with discrete selectively ignitable propellant
charges for propelling the multiplicity of projectiles sequentially
through the muzzle of barrel assembly (13). The multiplicity of
projectiles produce a fragment column (20) along path (12) to
destroy the incoming missile. Alternatively, anti-missile missile
(10) can be guided to produce a direct hit at point (18) on the
incoming missile. Barrel assembly (13) can include an aiming
mechanism so that barrel assembly (13) can be rotated through
sector (15, 16) to target path (12).
Inventors: |
O'Dwyer; James Michael;
(Queensland, AU) |
Correspondence
Address: |
FINNEGAN, HENDERSON, FARABOW, GARRETT & DUNNER;LLP
901 NEW YORK AVENUE, NW
WASHINGTON
DC
20001-4413
US
|
Assignee: |
Metal Storm Limited
|
Family ID: |
3819366 |
Appl. No.: |
11/039836 |
Filed: |
January 24, 2005 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
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10181453 |
Oct 9, 2002 |
|
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PCT/AU01/00063 |
Jan 24, 2001 |
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11039836 |
Jan 24, 2005 |
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Current U.S.
Class: |
102/489 ;
102/475 |
Current CPC
Class: |
G05D 1/12 20130101; F41G
7/20 20130101; F42B 12/62 20130101 |
Class at
Publication: |
102/489 ;
102/475 |
International
Class: |
F42B 12/58 20060101
F42B012/58 |
Foreign Application Data
Date |
Code |
Application Number |
Jan 24, 2000 |
AU |
PQ 5240 |
Claims
1. An anti-missile missile including a missile configured to
intercept an incoming missile wherein said anti-missile missile
further includes at least one barrel assembly having a multiplicity
of projectiles stacked axially within the at least one barrel
assembly together with discrete selectively ignitable propellant
charges for propelling the multiplicity of projectiles sequentially
through the muzzle of the at least one barrel assembly.
2. An anti-missile missile according to claim 1 wherein the
anti-missile missile includes a guidance system for tracking the
path of the incoming missile and maintaining the anti-missile
missile on a path to intercept the incoming missile.
3. An anti-missile missile according to claim 2 wherein the
guidance system incorporates a path sensing means that is
associated with an aiming mechanism for the at least one barrel
assembly.
4. An anti-missile missile according to claim 1 wherein the at
least one barrel assembly includs a barrel; a multiplicity 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.
5. An anti-missile missile according to claim 1 wherein the
projectile is selected from the group consisting of projectiles
that are round, conventionally shaped or dart-like, optionally with
fins off-set to generate a stabilising spin as the dart is
propelled from a barrel.
6. An anti-missile missile according to claim 1 wherein the
projectiles are propelled from the at least one barrel assembly by
a propellant that is sequentially ignited by an electronic
charge.
7. An anti-missile missile according to claim 1 wherein the at
least one barrel assembly is arranged to deploy projectiles into
the path of the incoming missile both before and after the
predicted impact of the anti-missile missile and the incoming
missile.
8. An anti-missile missile according to claim 1 wherein a single
barrel assembly is arranged to deploy projectiles into path of the
incoming missile both before and after the predicted impact of the
anti-missile missile and the incoming missile.
9. An anti-missile missile according to claim 1 wherein the barrel
assembly simultaneously fires projectiles in opposite directions so
as to minimise any change of flight path of the anti-missile
missile.
10. An anti-missile missile according to claim 1 wherein the
projectile is a grenade-like projectile that is capable of
detonating in the path of the incoming missile so as to create a
column of fragments through which the incoming missile must
pass.
11. An anti-missile missile according to claim 10 wherein the
projectile uses spin count for gauging the distance/timing to the
position at which it crosses the path of the incoming missile and
detonates at that position.
12. An anti-missile missile according to claim 11 wherein multiple
projectiles fired from the at least one barrel assembly have the
spin count preset for each projectile and the time delay in the
firing sequence provides the desired separation or intermingling of
deployed fragments along the flight path of the incoming
missile.
13. An anti-missile missile according to claim 10 wherein the
timing mechanism may be adjustable in flight with input provided by
incoming missile path sensor.
14. An anti-missile missile according to claim 1 wherein aiming
corrections to the at least one barrel assembly may be effected by
a rotation on mountings on the anti-missile missile about its axis
and/or rotation of the missile axis.
15. A method of destroying or incapacitating an incoming missile
comprising the steps of launching an anti-missile missile wherein
said anti-missile missile includes a missile configured to
intercept said incoming missile and wherein said anti-missile
missile further includes at least one barrel assembly having a
multiplicity of projectiles stacked axially within the at least one
barrel assembly together with discrete selectively ignitable
propellant charges for propelling the multiplicity of projectiles
sequentially through the muzzle of the at least one barrel and
sequentially firing said multiplicity of projectiles at said
incoming missile.
Description
[0001] This invention relates to anti-missile missiles and to a
method of destroying or incapacitating an incoming missile.
[0002] Missiles generally move at high speed towards a target and
are thus extremely difficult to intercept in order to destroy or
incapacitate. Whilst it may be possible to deploy a multiplicity of
defensive rounds from the target to intercept the incoming missile,
this may not be desirable as the initial or sole response to the
threat. Such interception of the incoming missile is generally more
effective close to the target and as such does not permit secondary
responses if the initial response fails to destroy or incapacitate
the incoming missile. Further the incoming missile may still be a
significant threat to the target if it is in fact destroyed or
incapacitated close to the target. For example, any destruction of
the incoming missile close to the target may still result in an
explosion of sufficient magnitude to damage the target, production
of fragments of the incoming missile that have sufficient momentum
to damage the target or may distribute hazardous waste or the like
over the target.
[0003] Early detection of an incoming missile permits
counter-measures in the form of anti-missile missiles to be
deployed. Anti-missile missiles rely on impacting with the incoming
missile or exploding in the vicinity of the incoming missile. The
chances of an anti-missile missile successfully impacting with an
incoming missile, even with sophisticated navigation and
directional control, are low due to the smallness of the incoming
missile and its relative approach speed. The ability of an
anti-missile missile to make a late correction of flight path in
response to a late deviation of the incoming missile is
limited.
[0004] Anti-missile missiles that explode in the vicinity of the
incoming missile provide a multiplicity of fragments in the path of
the incoming missile or, if close enough, can destroy or
incapacitate the incoming missile.
[0005] We have now found that by employing barrel assemblies having
a plurality of projectiles stacked axially within the barrels
together with discrete selectively ignitable propellant charges for
propelling the projectiles sequentially through the muzzle of the
barrels located on an anti-missile missile, the chances of
successfully destroying or incapacitating an incoming missile is
substantially improved.
[0006] Accordingly, in one embodiment, the present invention
provides an anti-missile missile including a missile configured to
intercept an incoming missile wherein said anti-missile missile
further includes at least one barrel assembly having a multiplicity
of projectiles stacked axially within the at least one barrel
assembly together with discrete selectively ignitable propellant
charges for propelling the multiplicity of projectiles sequentially
through the muzzle of the at least one barrel assembly.
[0007] In a second embodiment, the present invention provides a
method of destroying or incapacitating an incoming missile
comprising the steps of launching an anti-missile missile wherein
said anti-missile missile includes a missile configured to
intercept said incoming missile and wherein said anti-missile
missile further includes at least one barrel assembly having a
multiplicity of projectiles stacked axially within the at least one
barrel assembly together with discrete selectively ignitable
propellant charges for propelling the multiplicity of projectiles
sequentially through the muzzle of the at least one barrel and
sequentially firing said multiplicity of projectiles at said
incoming missile.
[0008] Incoming missiles, such as high altitude ballistic missiles,
are widely employed as long-range strike weapons as they are very
effective and difficult to detect in time for adequate defences to
be actioned. Out-of-atmosphere ballistic missiles travel at
extremely high speed and are extremely difficult to intercept in a
hit-to-kill mode that relies on the anti-missile missile striking,
or detonating in the immediate vicinity to the incoming missile. In
some embodiments the present invention provides an anti-missile
missile that may improve the likelihood of destroying or
incapacitating an out-of-atmosphere ballistic missile. The present
invention also has application in the destruction or incapacitation
of other missiles including surface-to-air missiles, air-to-surface
missiles, air-to-air missiles, surface-to-surface missiles,
ship-to-ship missiles, air-to-ship missiles and other combinations
thereof. The exact nature of the incoming missile is not narrowly
critical to the definition of the present invention.
[0009] The anti-missile missile, or defensive missile, may be of
any convenient type capable of intercepting the incoming missile.
Desirably the anti-missile missile is capable of impacting with, or
exploding adjacent to, the incoming missile and destroying or
incapacitating the incoming missile. Typically an anti-missile
missile will include an airframe, a propulsion system, a guidance
system and optionally an explosive for destroying or incapacitating
an incoming missile.
[0010] The anti-missile missile typically includes a guidance
system that tracks the path of the incoming missile and maintains
the anti-missile missile on a path that will intercept the incoming
missile. The guidance system may incorporate a path sensing means
that is associated with an aiming mechanism for the at least one
barrel assembly. The guidance system preferably accommodates late
aiming corrections that may be made to the barrel assemblies for
accurately propelling the multiplicity of projectiles into the path
of the incoming missile. Even if the path of the anti-missile
missile is unable to be corrected, by propelling the multiplicity
of projectiles into its path increases the chances of disabling the
incoming missile.
[0011] The anti-missile missile is configured to intercept the
incoming missile. The configuration of the anti-missile missile is
not narrowly critical to the present invention provided that the
anti-missile missile is capable of carrying at least one barrel
assembly and preferably a least one barrel assembly that is capable
of rotation to target the path of the incoming missile.
[0012] The anti-missile missile may be launched by any convenient
means, such as from a land based launch base, a ship, an aircraft
or other.
[0013] The anti-missile missile includes at least one barrel
assembly having a multiplicity of projectiles stacked axially
within the at least one barrel assembly together with discrete
selectively ignitable propellant charges for propelling the
multiplicity of projectiles sequentially through the muzzle of the
at least one barrel.
[0014] Barrel assemblies including a barrel; a multiplicity 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 may be used in the
present invention. Such barrel assemblies are described in
International Patent Application Nos. PCT/AU94/00124,
PCT/AU96/00459 and PCT/AU97/00713.
[0015] The projectile 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.
[0016] The projectile charge may be form as a solid block to
operatively space the 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
projectiles may be provide for reloading a barrel.
[0017] Each projectile may include a projectile head and extension
means for at least partly defining a propellant space. The
extension means may include a spacer assembly which extends
rearwardly from the projectile head and abuts an adjacent
projectile assembly.
[0018] The spacer assembly may extend through the propellant space
and the projectile 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
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.
[0019] The spacer assembly may include 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 that axially compressive loads are transmitted
directly between spacer assemblies thereby avoiding deformation of
the malleable projectile head.
[0020] Complementary wedging surfaces may be disposed on the spacer
assembly and projectile head respectively whereby the projectile
head is urged into 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 there after 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.
[0021] The projectile 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 projectile head and the
complementary tapered spigot causes a radially expanding force to
be applied to the projectile head.
[0022] 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 configuration the barrel houses electrical
conductors which facilitate electrical communication between the
control means and ignition means. This configuration 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.
[0023] A barrel assembly may alternatively include 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 include recesses adapted
to accommodate the ignition means. The outer barrel may also 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.
[0024] The barrel assembly may have adjacent projectiles that are
separated from one another and maintained in spaced apart
relationship by locating means separate from the projectiles, and
each 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 projectiles and the
sealing means suitably includes a skirt portion on each projectile
which expands outwardly when subject to an in-barrel load. The
in-barrel load may be applied during installation of the
projectiles or after loading such as by tamping to consolidate the
column of projectiles and propellant charges or may result from the
firing of an outer projectile and particularly the adjacent outer
projectile.
[0025] The rear end of the 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 projectile
will result in radial expansion of the projectile skirt. This
rearward movement may occur by way of compression resulting from a
rearward wedging movement of the 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 projectile to
its less massive skirt portion.
[0026] Alternatively the 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 projectile. Furthermore the sealing may be
effected by inserting the projectiles into a heated barrel which
shrinks onto respective sealing portions of the projectiles. The
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
projectile which relies on metal flow between the nose of the
projectile and its tail for outward-expansion about the mandrel
portion into sealing engagement with the bore of the barrel.
[0027] The 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 projectile through the barrel. In such
a configuration it is preferred that the propellant charge have a
cylindrical leading portion which abuts the flat end face of the
projectile.
[0028] The 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 projectile. The projectile
may be provided with contractible peripheral locating rings which
extend outwardly into annular grooves in the barrel and which
retract into the projectile upon firing to permit its free passage
through the barrel.
[0029] 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 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 ruses
disposed between normally closed electrical contacts.
[0030] 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 projectile and
controlled consequent ignition causing sequential ignition of the
propellant charge of subsequent rounds. This may be achieved by
controlled rearward leakage of combustion gases or controlled
burning of fuse columns extending through the projectiles.
[0031] In another form the ignition is electronically controlled
with respective propellant charges being associated with primers
which 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.
[0032] 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.
[0033] A number of projectiles can be fired simultaneously, or in
quick succession, or in response to repetitive manual actuation of
a trigger, for example. In such arrangements the electrical signal
may be carried externally of the barrel or it may be carried
through the superimposed 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 projectiles may
carry the control circuit or they may form a circuit with the
barrel.
[0034] The one or more barrel assemblies may be carried by the
defensive missile and respective guns may be arranged to scatter or
deploy fragments to the path of the incoming missile both before
and after the predicted missile to missile engagement position.
Alternatively a single barrel assembly may be utilised to propel
fragments to the path to and from the predicted missile to missile
engagement position. The barrel assembly may also simultaneously
fire rounds in opposite directions so as to minimise any change of
flight path of the anti-missile missile.
[0035] Preferably the projectile may be a grenade-like projectile
that is capable of detonating in the path of the incoming missile
so as to create a column of fragments through which the incoming
missile must pass. The likelihood of destroying or incapacitating
the incoming missile is thereby increased.
[0036] The, or each, projectile may be fired from a rifled barrel
and may use spin count for gauging the distance/timing to the
flight path. In the case of multiple projectiles fired from barrel
assemblies of the type described, the spin count may be preset for
each projectile and the time delay in the firing sequence may
provide the desired separation or intermingling of deployed
fragments along the flight path. Alternatively the timing mechanism
may be adjustable in flight with an appropriate input provided by
incoming missile path sensing means.
[0037] Aiming corrections to the barrel assemblies may be effected
by a rotation on mountings on the defensive missile about its axis
and the mountings may be themselves be rotatable about the missile
axis. Such corrections may be more readily achieved than a late
deflection of the defensive missile's flight path. Such aiming
corrections may be monitored and effected over a relatively long
approach period thereby maintaining a relatively slow corrective
action to achieve on-target firing of the gun or guns.
[0038] The barrel assembly or barrel assemblies may fire a
projectile which explodes when in the desired missile path to
scatter fragments or deploy fragments about the incoming missile
path so as to increase the possibility of collision between the
incoming missile and a fragment carried thereto by the defensive
missile. The fragments may have sufficient mass such that a
collision therewith would at least partially disable the incoming
missile or the fragments may be explosive fragments or charges.
Suitably the projectiles are fired or deployed to a path adjacent
the predicted missile to missile engagement position so that time
lapses between firing and deployment of the fragments or missile to
missile engagement are minimal, minimising flight path variations
of the anti-missile missile and incoming missile and
projectiles.
[0039] We have found that for any given system, an incoming missile
having a known velocity, an anti-missile missile having a known
velocity, barrel assemblies having known muzzle velocities, the
angle at which the barrel assemblies is to be directed is constant
irrespective of how long and where a fragment column is desired.
This is applicable to fragment columns before and after the
predicted impact position of the incoming missile and the
anti-missile missile with the direction of the barrel assemblies
being offset by 180 degrees. This feature of the present invention
is particularly advantageous as it permits equal and opposite
firing to be performed to establish fragment columns before and
after the predicted impact position of the incoming missile and the
anti-missile missile with minimal effect on the direction of the
anti-missile missile.
[0040] The methods of defence against an incoming missile as
variously described above constitute further aspects of this
invention.
[0041] In order that this invention may be more readily understood
and put into practical effect, reference will now be made to the
accompanying drawings and examples that illustrate a typical
embodiment of this invention, wherein:--
[0042] FIG. 1 diagrammatically illustrates a typical anti-missile
missile and its operation, and
[0043] FIG. 2 illustrates a typical trajectory analysis.
[0044] FIG. 3 illustrates an approximate analysis of the trajectory
of the respective missiles and the projectiles in an
out-of-atmosphere environment.
[0045] FIG. 1 provides a diagrammatic illustration of a defensive
missile 10 travelling along an intersection path 11 towards the
path 12 of an incoming ballistic missile. In this embodiment, the
paths 11 and 12 are drawn at right angles for illustration only. As
shown in FIG. 2, the paths 11 and 12 would more likely intersect at
an obtuse angle of 135.degree. or thereabouts.
[0046] The defensive missile 10 includes a turreted gun 13
utilising one or more barrel assemblies of the type described, each
loaded with grenade type projectiles engaged with rifling in the or
each respective barrel for imparting a spin to the projectiles when
fired so that each may be detonated at a selected distance from the
defensive missile 10 which corresponds to a position coincident
with the predicted flight path 12 of the incoming missile by
utilising a spin count control for detonation.
[0047] The gun 13 may be turreted to a position more closely
in-line with the flight path 11 as its fires so as to deposit a
fragment column from exploding grenades along a significant
distance of the incoming missile flight path, such as in the order
of 300 feet of the predicted incoming flight path 12. Alternatively
the gun may remain fixed and the different angles required to
position exploding grenades along the flight path may be produced
by firing the grenades at different velocities so as to provide the
required velocity vector resulting from the velocity of the
defensive missile, the velocity of the defensive missile along the
flight path 11 and the velocity of firing of the missile, to
achieve the result as indicated diagrammatically by the vectors 15
and 16 and vectors therebetween.
[0048] The flight path of the defensive missile 11 is adapted to
intercept the flight path 12 of the incoming missile to produce a
direct hit at 18 with a view to destroying the incoming missile.
However, if this does not occur, damage to the missile sustained
through passing through the produced fragment column 20 may be
sufficient to prevent it from reaching its destination or cause it
to self destruct during transit towards the target zone. In the
case of a ballistic missile, this may occur upon downward travel
through the earth's atmosphere.
[0049] As shown in FIG. 2, the gun is fired on two separate
occasions. Firstly to produce the fragment column 20 in the path 12
of the incoming missile towards the impact position 18 and secondly
to the opposite side of the impact position so as to form a further
fragment zone 21 in the path 12 of the incoming missile after
passage beyond the predicted impact position 18.
[0050] Referring to FIG. 2, it will be seen that the gun will fire
to produce the trailing fragment zone 21 prior to being fired to
produce the leading fragment zone 20.
[0051] As an example given simply to illustrate the possible time
spans involved, it is envisaged that a strategic missile travelling
at 26,000 feet per second could be intercepted by a defensive
missile travelling at 3,400 feet per second. For the first firing
of the gun to produce the trailing fragment zone 21, it is
envisaged that the gun would be aimed to fire backward at 2,685
feet per second in the direction parallel to the incoming fight
path 12 and with a vertical component of 610 feet per second. It is
further envisaged that the firing duration would be 0.012 seconds
during ???? projectiles would be fired and would finish 0.559
seconds and 1900 feet before the impact position 18 and would
result in the production of a fragment column of about 300 foot
long along the path 12 of the incoming missile beyond the impact
position 18.
[0052] The gun would then be rotated to fire from the other side of
the anti-missile missile path 11 either by turreting of the gun 13
or rotation of the defensive missile 10 about its longitudinal
axis. The gun would then fire forwards at 4,193 feet per second in
a direction parallel to the path 12 and with a vertical component
of 736 feet per second. Firing would start 0.456 seconds and 1,552
feet before the impact position 18. The firing duration would be in
the order of 0.012 seconds and again ???? projectiles would be
fired so that the incoming strategic missile would enter the
fragment column 20 approximately 400 feet before the impact
position 18 and would pass through the column for the next 300 feet
before impact.
[0053] This arrangement is possible by the use of a barrel assembly
of the type described which may in the very short duration
available in this instance in the 0.012 seconds of firing propel a
significant number of projectiles which explode when in alignment
with the incoming missile path 12. Further as the barrel assembly
is fully electronic controlled, the electronics can also include
adjustable spin count timing means for adjusting the timing either
in flight or prior to flight to achieve the desired result.
[0054] While a single turreting gun is preferred for minimising
weight, a separate gun or guns may be utilised for firing to the
respective sides. Additionally several guns may be arranged about
the missile with pre set directions and charges and with a view to
producing an array of debris about the anticipated impact zone with
a view to increasing the effective size of defensive missile and
the chance for achieving a collision of some form with the incoming
missile.
[0055] FIG. 3 shows an approximate calculation for determining
firing times and angles of fire for particular scenarios. Where an
incoming missile 31 travels along a trajectory that is defined by
the x-axis 32 and is predicted to be impacted by an anti-missile
missile 32 at 33, the angle of fire of projectiles (not shown) from
the barrel assemblies 34a and 34b may be calculated if the angle of
attack of the anti-missile missile and the respective velocities
are known.
[0056] e is shown as the distance along the trajectory of the
incoming missile at which a projectile is desired to intercept the
incoming missile. During the period of time it takes the incoming
missile to travel distance e, the anti-missile missile travels
distance c: c = e * speed .times. .times. of .times. .times. anti
.times. - .times. missile .times. .times. missile speed .times.
.times. of .times. .times. incoming .times. .times. missile
##EQU1## .theta. is the angle of attack of the anti-missile missile
relative to the direction of the incoming missile. a = c * cos
.function. ( .theta. - 180 ) b = c * sin .function. ( .theta. - 180
) .alpha. = tan - 1 .times. ( b ) e + a ##EQU2## [0057]
.beta.=.alpha.+.theta.-90 where .beta. is the angle of the barrel
assembly relative to the direction of the anti-missile missile
(applicable to firing behind the predicted impact of the incoming
missile and the anti-missile missile. [0058] .gamma.=180-.beta.
where .gamma. is the angle of the barrel assembly relative to the
direction of the anti-missile missile (applicable to firing in
front of the predicted impact of the incoming missile and the
anti-missile missile.
[0059] The time at interception of the projectile with the incoming
missile (t.sub.i). t i = e Velocity .times. .times. of .times.
.times. incoming .times. .times. missile . ##EQU3##
[0060] The time of flight of the projectile (t.sub.f). t f = d
Velocity .times. .times. of .times. .times. projectile .
##EQU4##
[0061] The time of fire of the projectile (t.sub.fire).
t.sub.fire=t.sub.i-t.sub.f
[0062] Based upon the formula outlined above, the time and position
at which the projectiles intercept the incoming missile may be
determined and in Examples 1 to 8 hereinbelow there is shown the
results of these calculations at various velocities of incoming
missiles, anti-missile missiles and projectiles, angles of attack
of anti-missile missiles and positions of interception of
projectiles with incoming missiles. For convenience a few
intermediate impact points have been selected but it will be
understood that the present invention advantageously permits the
firing of extremely high numbers of projectiles in the short period
during which the firing may be effected in close proximity to the
incoming missile. It will be appreciated that the closer the firing
to the incoming missile the less the margin for error and the
greater the likelihood of destroying or incapacitating the incoming
missile.
[0063] 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.
EXAMPLE 1
[0064] TABLE-US-00001 Incoming Missile Velocity 7924.8 ms.sup.-1
Anti-missile Missile Velocity 1036.32 ms.sup.-1 Angle of Attack 220
degrees Projectile Launcher Muzzle velocity 426.72 ms.sup.-1 First
Engagement Intermediate Intermediate Intermediate Initial Impact
Impact Impact Impact Final Impact Intercept incoming missile
relative to -152.4000 -129.5400 -106.6800 -83.8200 -60.9600 impact
with anti-missile missile at (meters) Barrel assembly angle
relative to 315.6309 315.6309 315.6309 315.6309 315.6309 axis of
anti-missile missile (degrees) Time of fire relative to impact of
-0.4133 -0.3513 -0.2893 -0.2273 -0.1653 incoming missile with
anti-missile missile at (seconds) Time projectiles intercept
incoming -0.0192 -0.0163 -0.0135 -0.0106 -0.0077 missile relative
to impact of incoming missile with anti-missile missile at
(seconds) Second Engagement Intercept incoming missile relative to
0.0000 impact with anti-missile missile at (meters) Time of
intercept of incoming missile 0.0000 by anti-missile missile at
(seconds) Third Engagement Intermediate Intermediate Intermediate
Initial Impact Impact Impact Impact Final Impact Intercept incoming
missile relative to 152.4000 175.2600 198.1200 220.9800 243.8400
impact with anti-missile missile at (meters) Barrel assembly angle
relative to 135.6309 135.6309 135.6309 135.6309 135.6309 axis of
anti-missile missile (degrees) Time of fire relative to impact of
-0.3748 -0.4311 -0.4873 -0.5435 -0.5997 incoming missile with
anti-missile missile at (seconds) Time projectiles intercept
incoming 0.0192 0.0221 0.0250 0.0279 0.0308 missile relative to
impact of incoming missile with anti-missile missile at
(seconds)
EXAMPLE 2
[0065] TABLE-US-00002 Incoming Missile Velocity 7924.8 ms.sup.-1
Anti-missile Missile Velocity 1676.4 ms.sup.-1 Angle of Attack 220
degrees Projectile Launcher Muzzle velocity 426.72 ms.sup.-1 First
Engagement Intermediate Intermediate Intermediate Initial Impact
Impact Impact Impact Final Impact Intercept incoming missile
relative to -152.4000 -129.5400 -106.6800 -83.8200 -60.9600 impact
with anti-missile missile at (meters) Barrel assembly angle
relative to 313.3260 313.3260 313.3260 313.3260 313.3260 axis of
anti-missile missile (degrees) Time of fire relative to impact of
-0.4371 -0.3715 -0.3060 -0.2404 -0.1748 incoming missile with
anti-missile missile at (seconds) Time projectiles intercept
incoming -0.0192 -0.0163 -0.0135 -0.0106 -0.0077 missile relative
to impact of incoming missile with anti-missile missile at
(seconds) Second Engagement Intercept incoming missile relative to
0.0000 impact with anti-missile missile at (meters) Time of
intercept of incoming missile 0.0000 by anti-missile missile at
(seconds) Third Engagement Intermediate Intermediate Intermediate
Initial Impact Impact Impact Impact Final Impact Intercept incoming
missile relative to 152.4000 175.2600 198.1200 220.9800 243.8400
impact with anti-missile missile at (meters) Barrel assembly angle
relative to 133.3260 133.3260 133.3260 133.3260 133.3260 axis of
anti-missile missile (degrees) Time of fire relative to impact of
-0.3986 -0.4584 -0.5182 -0.5780 -0.6378 incoming missile with
anti-missile missile at (seconds) Time projectiles intercept
incoming 0.0192 0.0221 0.0250 0.0279 0.0308 missile relative to
impact of incoming missile with anti-missile missile at
(seconds)
EXAMPLE 3
[0066] TABLE-US-00003 Incoming Missile Velocity 7924.8 ms.sup.-1
Anti-missile Missile Velocity 1036.32 ms.sup.-1 Angle of Attack 190
degrees Projectile Launcher Muzzle velocity 426.72 ms.sup.-1 First
Engagement Intermediate Intermediate Intermediate Initial Impact
Impact Impact Impact Final Impact Intercept incoming missile
relative to -152.4000 -129.5400 -106.6800 -83.8200 -60.9600 impact
with anti-missile missile at (meters) Barrel assembly angle
relative to 348.8475 348.8475 348.8475 348.8475 348.8475 axis of
anti-missile missile (degrees) Time of fire relative to impact of
-0.4224 -0.3591 -0.2957 -0.2323 -0.1690 incoming missile with
anti-missile missile at (seconds) Time projectiles intercept
incoming -0.0192 -0.0163 -0.0135 -0.0106 -0.0077 missile relative
to impact of incoming missile with anti-missile missile at
(seconds) Second Engagement Intercept incoming missile relative to
0.0000 impact with anti-missile missile at (meters) Time of
intercept of incoming missile 0.0000 by anti-missile missile at
(seconds) Third Engagement Intermediate Intermediate Intermediate
Initial Impact Impact Impact Impact Final Impact Intercept incoming
missile relative to 152.4000 175.2600 198.1200 220.9800 243.8400
impact with anti-missile missile at (meters) Barrel assembly angle
relative to 168.8475 168.8475 168.8475 168.8475 168.8475 axis of
anti-missile missile (degrees) Time of fire relative to impact of
-0.3840 -0.4416 -0.4992 -0.5568 -0.6144 incoming missile with
anti-missile missile at (seconds) Time projectiles intercept
incoming 0.0192 0.0221 0.0250 0.0279 0.0308 missile relative to
impact of incoming missile with anti-missile missile at
(seconds)
EXAMPLE 4
[0067] TABLE-US-00004 Incoming Missile Velocity 7924.8 ms.sup.-1
Anti-missile Missile Velocity 1036.32 ms.sup.-1 Angle of Attack 220
degrees Projectile Launcher Muzzle velocity 853.44 ms.sup.-1 First
Engagement Intermediate Intermediate Intermediate Initial Impact
Impact Impact Impact Final Impact Intercept incoming missile
relative to -152.4000 -129.5400 -106.6800 -83.8200 -60.9600 impact
with anti-missile missile at (meters) Barrel assembly angle
relative to 315.6309 315.6309 315.6309 315.6309 315.6309 axis of
anti-missile missile (degrees) Time of fire relative to impact of
-0.2163 -0.1838 -0.1514 -0.1189 -0.0865 incoming missile with
anti-missile missile at (seconds) Time projectiles intercept
incoming -0.0192 -0.0163 -0.0135 -0.0106 -0.0077 missile relative
to impact of incoming missile with anti-missile missile at
(seconds) Second Engagement Intercept incoming missile relative to
0.0000 impact with anti-missile missile at (meters) Time of
intercept of incoming missile 0.0000 by anti-missile missile at
(seconds) Third Engagement Intermediate Intermediate Intermediate
Initial Impact Impact Impact Impact Final Impact Intercept incoming
missile relative to 152.4000 175.2600 198.1200 220.9800 243.8400
impact with anti-missile missile at (meters) Barrel assembly angle
relative to 135.6309 135.6309 135.6309 135.6309 135.6309 axis of
anti-missile missile (degrees) Time of fire relative to impact of
-0.1778 -0.2045 -0.2311 -0.2578 -0.2845 incoming missile with
anti-missile missile at (seconds) Time projectiles intercept
incoming 0.0192 0.0221 0.0250 0.0279 0.0308 missile relative to
impact of incoming missile with anti-missile missile at
(seconds)
EXAMPLE 5
[0068] TABLE-US-00005 Incoming Missile Velocity 7924.8 ms.sup.-1
Anti-missile Missile Velocity 1036.32 ms.sup.-1 Angle of Attack 290
degrees Projectile Launcher Muzzle velocity 426.72 ms.sup.-1 First
Engagement Intermediate Intermediate Intermediate Initial Impact
Impact Impact Impact Final Impact Intercept incoming missile
relative to -152.4000 -129.5400 -106.6800 -83.8200 -60.9600 impact
with anti-missile missile at (meters) Barrel assembly angle
relative to 242.6699 242.6699 242.6699 242.6699 242.6699 axis of
anti-missile missile (degrees) Time of fire relative to impact of
-0.3632 -0.3087 -0.2542 -0.1998 -0.1453 incoming missile with
anti-missile missile at (seconds) Time projectiles intercept
incoming -0.0192 -0.0163 -0.0135 -0.0106 -0.0077 missile relative
to impact of incoming missile with anti-missile missile at
(seconds) Second Engagement Intercept incoming missile relative to
0.0000 impact with anti-missile missile at (meters) Time of
intercept of incoming missile 0.0000 by anti-missile missile at
(seconds) Third Engagement Intermediate Intermediate Intermediate
Initial Impact Impact Impact Impact Final Impact Intercept incoming
missile relative to 152.4000 175.2600 198.1200 220.9800 243.8400
impact with anti-missile missile at (meters) Barrel assembly angle
relative to 62.6699 62.6699 62.6699 62.6699 62.6699 axis of
anti-missile missile (degrees) Time of fire relative to impact of
-0.3247 -0.3735 -0.4222 -0.4709 -0.5196 incoming missile with
anti-missile missile at (seconds) Time projectiles intercept
incoming 0.0192 0.0221 0.0250 0.0279 0.0308 missile relative to
impact of incoming missile with anti-missile missile at
(seconds)
EXAMPLE 6
[0069] TABLE-US-00006 Incoming Missile Velocity 7924.8 ms.sup.-1
Anti-missile Missile Velocity 1036.32 ms.sup.-1 Angle of Attack 345
degrees Projectile Launcher Muzzle velocity 426.72 ms.sup.-1 First
Engagement Intermediate Intermediate Intermediate Initial Impact
Impact Impact Impact Final Impact Intercept incoming missile
relative to -152.4000 -129.5400 -106.6800 -83.8200 -60.9600 impact
with anti-missile missile at (meters) Barrel assembly angle
relative to 192.7815 192.7815 192.7815 192.7815 192.7815 axis of
anti-missile missile (degrees) Time of fire relative to impact of
-0.3315 -0.2818 -0.2320 -0.1823 -0.1326 incoming missile with
anti-missile missile at (seconds) Time projectiles intercept
incoming -0.0192 -0.0163 -0.0135 -0.0106 -0.0077 missile relative
to impact of incoming missile with anti-missile missile at
(seconds) Second Engagement Intercept incoming missile relative to
0.0000 impact with anti-missile missile at (meters) Time of
intercept of incoming missile 0.0000 by anti-missile missile at
(seconds) Third Engagement Intermediate Intermediate Intermediate
Initial Impact Impact Impact Impact Final Impact Intercept incoming
missile relative to 152.4000 175.2600 198.1200 220.9800 243.8400
impact with anti-missile missile at (meters) Barrel assembly angle
relative to 12.7815 12.7815 12.7815 12.7815 12.7815 axis of
anti-missile missile (degrees) Time of fire relative to impact of
-0.2930 -0.3370 -0.3809 -0.4249 -0.4689 incoming missile with
anti-missile missile at (seconds) Time projectiles intercept
incoming 0.0192 0.0221 0.0250 0.0279 0.0308 missile relative to
impact of incoming missile with anti-missile missile at
(seconds)
EXAMPLE 7
[0070] TABLE-US-00007 Incoming Missile Velocity 7924.8 ms.sup.-1
Anti-missile Missile Velocity 1036.32 ms.sup.-1 Angle of Attack 220
degrees Projectile Launcher Muzzle velocity 426.72 ms.sup.-1 First
Engagement Intermediate Intermediate Intermediate Initial Impact
Impact Impact Impact Final Impact Intercept incoming missile
relative to -152.4000 -129.5400 -106.6800 -83.8200 -60.9600 impact
with anti-missile missile at (meters) Barrel assembly angle
relative to 315.6309 315.6309 315.6309 315.6309 315.6309 axis of
anti-missile missile (degrees) Time of fire relative to impact of
-0.4133 -0.3513 -0.2893 -0.2273 -0.1653 incoming missile with
anti-missile missile at (seconds) Time projectiles intercept
incoming -0.0192 -0.0163 -0.0135 -0.0106 -0.0077 missile relative
to impact of incoming missile with anti-missile missile at
(seconds) Second Engagement Intercept incoming missile relative to
0.0000 impact with anti-missile missile at (meters) Time of
intercept of incoming missile 0.0000 by anti-missile missile at
(seconds) Third Engagement Intermediate Intermediate Intermediate
Initial Impact Impact Impact Impact Final Impact Intercept incoming
missile relative to 67.2084 92.4215 117.6376 142.8537 168.0667
impact with anti-missile missile at (meters) Barrel assembly angle
relative to 135.6309 135.6309 135.6309 135.6309 135.6309 axis of
anti-missile missile (degrees) Time of fire relative to impact of
-0.1653 -0.2273 -0.2893 -0.3514 -0.4134 incoming missile with
anti-missile missile at (seconds) Time projectiles intercept
incoming 0.0085 0.0117 0.0148 0.0180 0.0212 missile relative to
impact of incoming missile with anti-missile missile at
(seconds)
EXAMPLE 8
[0071] TABLE-US-00008 Incoming Missile Velocity 7924.8 ms.sup.-1
Anti-missile Missile Velocity 1036.32 ms.sup.-1 Angle of Attack 345
degrees Projectile Launcher Muzzle velocity 426.72 ms.sup.-1 First
Engagement Intermediate Intermediate Intermediate Initial Impact
Impact Impact Impact Final Impact Intercept incoming missile
relative to -152.4000 -129.5400 -106.6800 -83.8200 -60.9600 impact
with anti-missile missile at (meters) Barrel assembly angle
relative to 192.7815 192.7815 192.7815 192.7815 192.7815 axis of
anti-missile missile (degrees) Time of fire relative to impact of
-0.3315 -0.2818 -0.2320 -0.1823 -0.1326 incoming missile with
anti-missile missile at (seconds) Time projectiles intercept
incoming -0.0192 -0.0163 -0.0135 -0.0106 -0.0077 missile relative
to impact of incoming missile with anti-missile missile at
(seconds) Second Engagement Intercept incoming missile relative to
0.0000 impact with anti-missile missile at (meters) Time of
intercept of incoming missile 0.0000 by anti-missile missile at
(seconds) Third Engagement Intermediate Intermediate Intermediate
Initial Impact Impact Impact Impact Final Impact Intercept incoming
missile relative to 68.9762 94.8538 120.7313 146.6088 172.4863
impact with anti-missile missile at (meters) Barrel assembly angle
relative to 12.7815 12.7815 12.7815 12.7815 12.7815 axis of
anti-missile missile (degrees) Time of fire relative to impact of
-0.1326 -0.1824 -0.2321 -0.2819 -0.3317 incoming missile with
anti-missile missile at (seconds) Time projectiles intercept
incoming 0.0087 0.0120 0.0152 0.0185 0.0218 missile relative to
impact of incoming missile with anti-missile missile at
(seconds)
* * * * *