Note: Descriptions are shown in the official language in which they were submitted.
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ANTI-MISSILE MISSILES
This invention relates to anti-missile missiles and to a method of destroying
or
incapacitating an incoming missile.
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.
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.
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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.
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.
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.
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.
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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-
s 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.
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.
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
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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.
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.
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.
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.
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.
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.
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
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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
5 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.
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.
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.
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.
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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.
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.
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.
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
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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.
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.
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.
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
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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.
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.
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.
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.
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
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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.
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.
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.
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
tc
continue the electrical circuit through the barrel, or abut in electrical
contact with one
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another. The projectiles may carry the control circuit or they may form a
circuit with
the barrel.
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
5 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.
10 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.
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.
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
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period thereby maintaining a relatively slow corrective action to achieve on-
target
firing of the gun or guns.
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.
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.
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The methods of defence against an incoming missile as variously described
above constitute further aspects of this invention.
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:-
FIG. 1 diagrammatically illustrates a typical anti-missile missile and its
operation, and
FIG. 2 illustrates a typical trajectory analysis.
FIG. 3 illustrates an approximate analysis of the trajectory of the respective
missiles and the projectiles in an out-of-atmosphere environment.
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 or thereabouts.
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.
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
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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.
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.
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.
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.
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
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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.
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.
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.
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
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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.
Figure 3 shows an approximate calculation for determining firing times and
5 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.
10 a 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 = a * J~eed of anti-missile missile
15 speed of incoming missile
0 is the angle of attack of the anti-missile missile relative to the direction
of the
incoming missile.
a = c * cos(0 - 180)
b = c * sin(8 - 180)
a = tan-'( b )
a+a
(3 = a + B - 90 where ~ 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.
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y = 180 - ~i where y 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.
The time at interception of the projectile with the incoming missile (t;).
t; = a
Velocity of incoming missile
The time of flight of the projectile (tf).
tf = d
Velocity of projectile
The time of fire of the projectile (tfre).
tfire = t1 ' tf
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.
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
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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.
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Example 1
Incoming Missile
Velocity 7924.8 ms'
Anti-missile Missile
Velocity 1036.32 ms'
Angle of Attack 220 degrees
Projectile Launcher
Muzzle velocity 426.72 ms'
I First Engagement
Intermediate Intermediateermediate
Int
InitiallmpactImpact Impact ImpactFinallmpact
Intercept incoming missile
relative to
impact with anti-missile
missile at
(meters) -152.4000-129.5400 -106.6800-83.8200-60.9600
Barrel assembly angle
relative to
axis of anti-missile 315.6309 315.6309 315.6309 315.6309315.6309
missile (degrees)
Time of fire relative
to impact of
incoming missile with
anti-missile
missile at (seconds) -0.4133 -0.3513 -0.2893 -0.2273-0.1653
Time projectiles intercept
incoming
missile relative to
impact of
incoming missile with
anti-missile
missile at (seconds) -0.0192 -0.0163 -0.0135 -0.0106-0.0077
Second
Engagement
Intercept incoming missile relative to
impact with anti-missile missile at
(meters) 0.0000
Time of intercept of incoming missile
by anti-missile missile at (seconds) 0.0000
Intermediate
Intermediate
Intermediate
InitiallmpactImpact Impact Impact Finallmpact
Intercept incoming missile
relative to
impact with anti-missile
missile at
(meters) 152.4000 175.2600 198.1200220.9800243.8400
Barrel assembly angle
relative to
axis of anti-missile 135.6309 135.6309 135.6309135.6309135.6309
missile (degrees)
Time of fire relative
to impact of
incoming missile with
anti-missile
missile at (seconds) -0.3748 -0.4311 -0.4873 -0.5435 -0.5997
Time projectiles intercept
incoming
missile relative to
impact of
incoming missile with
anti-missile
missile at (seconds) 0.0192 0.0221 0.0250 0.0279 0.0308
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Exam ple 2
Incoming Missile
Velocity 7924.8 ms'
Anti-missile Missile
Velocity 1676.4 ms'
Angle of Attack 220 degrees
Projectile Launcher
Muzzle velocity 426.72 ms'
First Engagement
Intermediate Intermediateermediate
Int
InitiallmpactImpact Impact ImpactFinallmpact
Intercept incoming
missile relative to
impact with anti-missile
missile at
(meters) -152.4000-129.5400 -106.6800-83.8200-60.9600
Barrel assembly angle
relative to
axis of anti-missile 313.3260 313.3260 313.3260 313.3260313.3260
missile (degrees)
Time of fire relative
to impact of
incoming missile with
anti-missile
missile at (seconds) -0.4371 -0.3715 -0.3060 -0.2404-0.1748
Time projectiles intercept
incoming
missile relative to
impact of
incoming missile with
anti-missile
missile at (seconds) -0.0192 -0.0163 -0.0135 -0.0106-0.0077
Engagement
Intercept incoming missile relative to
impact with anti-missile missile at
(meters) 0.0000
Time of intercept of incoming missile
by anti-missile missile at (seconds) 0.0000
Third Engagement
Intermediate Intermediate
Intermediate
InitiallmpactImpact Impact ImpactFinallmpact
Intercept incoming
missile relative to
impact with anti-missile
missile at
(meters) 152.4000 175.2600 198.1200 220.9800243.8400
Barrel assembly angle
relative to
axis of anti-missile 133.3260 133.3260 133.3260 133.3260133.3260
missile (degrees)
Time of fire relative
to impact of
incoming missile with
anti-missile
missile at (seconds) -0.3986 -0.4584 -0.5182 -0.5780-0.6378
Time projectiles intercept
incoming
missile relative to
impact of
incoming missile with
anti-missile
missile at (seconds) 0.0192 0.0221 0.0250 0.02790.0308
CA 02396074 2002-06-28
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Example 3
Incoming Missile
Velocity 7924.8 ms'
Anti-missile Missile
Velocity 1036.32 ms'
Angle of Attack 190 degrees
Projectile Launcher
Muzzle velocity 426.72 ms'
First Engagement
Intermediate Intermediateermediate
Int
InitiallmpactImpact Impact Impact Finallmpact
Intercept incoming
missile relative to
impact with anti-missile
missile at
(meters) -152.4000 -129.5400 -106.6800-83.8200-60.9600
Barrel assembly angle
relative to
axis of anti-missile 348.8475 348.8475 348.8475 348.8475348.8475
missile (degrees)
Time of fire relative
to impact of
incoming missile with
anti-missile
missile at (seconds) -0.4224 -0.3591 -0.2957 -0.2323-0.1690
Time projectiles intercept
incoming
missile relative to
impact of
incoming missile with
anti-missile
missile at (seconds) -0.0192 -0.0163 -0.0135 -0.0106-0.0077
Engagement
Ilntercept incoming missile relative to
impact with anti-missile missile at
(meters) 0.0000
Time of intercept of incoming missile
by anti-missile missile at (seconds) 0.0000
Third Engagement
Intermediate Intermediate
Intermediate
InitiallmpactImpact Impact ImpactFinallmpact
Intercept incoming
missile relative to
impact with anti-missile
missile at
(meters) 152.4000 175.2600 198.1200 220.9800243.8400
Barrel assembly angle
relative to
axis of anti-missile 168.8475 168.8475 168.8475 168.8475168.8475
missile (degrees)
Time of fire relative
to impact of
incoming missile with
anti-missile
missile at (seconds) -0.3840 -0.4416 -0.4992 -0.5568-0.6144
Time projectiles intercept
incoming
missile relative to
impact of
incoming missile with
anti-missile
missile at (seconds) 0.0192 0.0221 0.0250 0.02790.0308
CA 02396074 2002-06-28
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21
Example 4
Incoming Missile
Velocity 7924.8 ms'
Anti-missile Missile
Velocity 1036.32 ms'
Angle of Attack 220 degrees
Projectile Launcher
Muzzle velocity 853.44 ms'
First
Engagement
IntermediateIntermediate
Intermediate
InitiallmpactImpact Impact ImpactFinallmpact
Intercept incoming missile
relative to
impact with anti-missile
missile at
(meters) -152.4000-129.5400-106.6800 -83.8200-60.9600
Barrel assembly angle
relative to
axis of anti-missile 315.6309 315.6309 315.6309 315.6309315.6309
missile (degrees)
Time of fire relative
to impact of
incoming missile with
anti-missile
missile at (seconds) -0.2163 -0.1838 -0.1514 -0.1189-0.0865
Time projectiles intercept
incoming
missile relative to
impact of
incoming missile with
anti-missile
missile at (seconds) -0.0192 -0.0163 -0.0135 -0.0106-0.0077
Second
Engagement
Intercept incoming missile relative to
impact with anti-missile missile at
(meters) 0.0000
Time of intercept of incoming missile
by anti-missile missile at (seconds) 0.0000
Third Engagement
Intermediate Intermediate
Intermediate
Initiallmpact Impact Impact ImpactFinallmpact
Intercept incoming missile
relative to
impact with anti-missile
missile at
(meters) 152.4000 175.2600 198.1200 220.9800243.8400
Barrel assembly angle
relative to
axis of anti-missile 135.6309 135.6309 135.6309 135.6309135.6309
missile (degrees)
Time of fire relative
to impact of
incoming missile with
anti-missile
missile at (seconds) -0.1778 -0.2045 -0.2311 -0.2578-0.2845
Time projectiles intercept
incoming
missile relative to
impact of
incoming missile with
anti-missile
missile at (seconds) 0.0192 0.0221 0.0250 0.02790.0308
CA 02396074 2002-06-28
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22
Example 5
Incoming Missile
Velocity 7924.8 ms'
Anti-missile Missile
Velocity 1036.32 ms'
Angle of Attack 290 degrees
Projectile Launcher
Muzzle velocity 426.72 ms~'
First Engagement
Intermediate I ntermediateermediate
Int
Initiallmpact ImpactImpact Impact Finallmpact
Intercept incoming
missile relative to
impact with anti-missile
missile at
(meters) -152.4000 -129.5400-106.6800 -83.8200 -60.9600
Barrel assembly angle
relative to
axis of anti-missile 242.6699 242.6699 242.6699 242.6699 242.6699
missile (degrees)
Time of fire relative
to impact of
incoming missile with
anti-missile
missile at (seconds) -0.3632 -0.3087 -0.2542 -0.1998 -0.1453
Time projectiles intercept
incoming
missile relative to
impact of
incoming missile with
anti-missile
missile at (seconds) -0.0192 -0.0163 -0.0135 -0.0106 -0.0077
Second
Engagement
Intercept incoming missile relative to
impact with anti-missile missile at
(meters) 0.0000
Time of intercept of incoming missile
by anti-missile missile at (seconds) 0.0000
Third Engagement
Intermediate Intermediate
Intermediate
InitiallmpactImpact Impact ImpactFinallmpact
Intercept incoming
missile relative to
impact with anti-missile
missile at
(meters) 152.4000 175.2600 198.1200 220.9800243.8400
Barrel assembly angle
relative to
axis of anti-missile 62.6699 62.6699 62.6699 62.669962.6699
missile (degrees)
Time of fire relative
to impact of
incoming missile with
anti-missile
missile at (seconds) -0.3247 -0.3735 -0.4222 -0.4709-0.5196
Time projectiles intercept
incoming
missile relative to
impact of
incoming missile with
anti-missile
missile at (seconds) 0.0192 0.0221 0.0250 0.02790.0308
CA 02396074 2002-06-28
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23
Example 6
Incoming Missile
Velocity 7924.8 ms'
Anti-missile Missile
Velocity 1036.32 ms'
Angle of Attack 345 degrees
Projectile Launcher
Muzzle velocity 426.72 ms'
First Engagement
Intermediate Intermediateermediate
Int
InitiallmpactImpact Impact Impact Finallmpact
Intercept incoming missile
relative to
impact with anti-missile
missile at
(meters) -152.4000-129.5400 -106.6800-83.8200-60.9600
Barrel assembly angle
relative to
axis of anti-missile 192.7815 192.7815 192.7815 192.7815192.7815
missile (degrees)
Time of fire relative
to impact of
incoming missile with
anti-missile
missile at (seconds) -0.3315 -0.2818 -0.2320 -0.1823-0.1326
Time projectiles intercept
incoming
missile relative to
impact of
incoming missile with
anti-missile
missile at (seconds) -0.0192 -0.0163 -0.0135 -0.0106-0.0077
Second
Engagement
Intercept incoming missile relative to
impact with anti-missile missile at
(meters) 0.0000
Time of intercept of incoming missile
by anti-missile missile at (seconds) 0.0000
Intermediate
Intermediate
Intermediate
InitiallmpactImpact Impact Impact Finallmpact
Intercept incoming missile
relative to
impact with anti-missile
missile at
(meters) 152.4000 175.2600 198.1200220.9800243.8400
Barrel assembly angle
relative to
axis of anti-missile 12.7815 12.7815 12.7815 12.7815 12.7815
missile (degrees)
Time of fire relative
to impact of
incoming missile with
anti-missile
missile at (seconds) -0.2930 -0.3370 -0.3809 -0.4249 -0.4689
Time projectiles intercept
incoming
missile relative to
impact of
incoming missile with
anti-missile
missile at (seconds) 0.0192 0.0221 0.0250 0.0279 0.0308
CA 02396074 2002-06-28
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24
Example 7
Incoming Missile
Velocity 7924.8 ms-'
Anti-missile Missile
Velocity 1036.32 ms'
Angle of Attack 220 degrees
Projectile Launcher
Muzzle velocity 426.72 ms'
First Engagement
Intermediate Intermediate
Intermediate
InitiallmpactImpact Impact ImpactFinallmpact
Intercept incoming
missile relative to
impact with anti-missile
missile at
(meters) -152.4000-129.5400 -106.6800-83.8200-60.9600
Barrel assembly angle
relative to
axis of anti-missile 315.6309 315.6309 315.6309 315.6309315.6309
missile (degrees)
Time of fire relative
to impact of
incoming missile with
anti-missile
missile at (seconds) -0.4133 -0.3513 -0.2893 -0.2273-0.1653
Time projectiles intercept
incoming
missile relative to
impact of
incoming missile with
anti-missile
imissile at (seconds) -0.0192 -0.0163 -0.0135 -0.0106-0.0077
Engagement
Intercept incoming missile relative to
impact with anti-missile missile at
(meters) 0.0000
'Time of intercept of incoming missile
by anti-missile missile at (seconds) 0.0000
Third Engagement
Intermediate Intermediate ermediate
Int
Initiallmpact Impact Impact ImpactFinallmpact
Intercept incoming
missile relative to
impact with anti-missile
missile at
(meters) 67.2084 92.4215 117.6376 142.8537168.0667
Barrel assembly angle
relative to
axis of anti-missile 135.6309 135.6309 135.6309 135.6309135.6309
missile (degrees)
Time of fire relative
to impact of
incoming missile with
anti-missile
missile at (seconds) -0.1653 -0.2273 -0.2893 -0.3514-0.4134
!Time projectiles intercept
incoming
imissile relative to
impact of
~~~incoming missile
with anti-missile
(missile at (seconds) 0.0085 0.0117 0.0148 0.01800.0212
CA 02396074 2002-06-28
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Example 8
Incoming Missile
Velocity 7924.8 ms'
Anti-missile Missile
Velocity 1036.32 ms'
Angle of Attack 345 degrees
Projectile Launcher
Muzzle velocity 426.72 ms'
Intermediate
Intermediate
Intermediate
InitiallmpactImpact Impact Impact Finallmpact
Intercept incoming
missile relative to
impact with anti-missile
missile at
(meters) -152.4000-129.5400-106.6800-83.8200-60.9600
Barrel assembly angle
relative to
axis of anti-missile 192.7815 192.7815 192.7815 192.7815192.7815
missile (degrees)
Time of fire relative
to impact of
incoming missile with
anti-missile
missile at (seconds) -0.3315 -0.2818 -0.2320 -0.1823-0.1326
Time projectiles intercept
incoming
missile relative to
impact of
incoming missile with
anti-missile
missile at (seconds) -0.0192 -0.0163 -0.0135 -0.0106-0.0077
Engagement
Intercept incoming missile relative to
impact with anti-missile missile at
(meters) 0.0000
Time of intercept of incoming missile
by anti-missile missile at (seconds) O.OOOOI
Third Engagement
Intermediate Intermediate
Intermediate
InitiallmpactImpact Impact ImpactFinallmpact
Intercept incoming
missile relative to
impact with anti-missile
missile at
(meters) 68.9762 94.8538 120.7313 146.6088172.4863
Barrel assembly angle
relative to
axis of anti-missile 12.7815 12.7815 12.7815 12.781512.7815
missile (degrees)
Time of fire relative
to impact of
incoming missile with
anti-missile
missile at (seconds) -0.1326 -0.1824 -0.2321 -0.2819-0.3317
Time projectiles intercept
incoming
missile relative to
impact of
incoming missile with
anti-missile
missile at (seconds) 0.0087 0.0120 0.0152 0.01850.0218
