[0001] This invention generally relates to anti-missile missiles and more particularly concerns
such missiles having means to render the guidance components of an incoming precision
seeker guided threat missile inoperative for performing the mission of guiding the
incoming missile to a target without requiring that the anti-missile impact with the
incoming threat missile.
[0002] Since the second World War, technological advances have permitted the construction
of precision, seeker guided munitions (PSGM) that are actively guided during flight
to their intended target and thus have a high probability of kill (PK). The high PK
and the relatively inexpensive costs of these munitions, especially as compared to
potential targets, make them cost effective weapons systems. The high PK, mature,
available manufacturing technology, comparatively modest purchase price, and ready
availability, have resulted in a proliferation of PSGMs. A variety of these systems
are built and marketed by a multitude of companies and countries. As older PSGMs become
obsolete and are replaced by more sophisticated systems, a large secondary market
filters these older munitions to less financially endowed countries and organizations.
This proliferation has increased the hazards from these weapons, both to combatants
and non-combatants, especially as these munitions are obtained by fanatic/terrorist
countries and/or organizations.
[0003] A precision, seeker guided munition is any munition, free fall or propelled that
can be guided to its target via an onboard seeker and control system. The PSGMs addressed
here are those that are either guided autonomously, that is, have an onboard or integral
seeker and electronics sophisticated enough to recognize a target by shape, energy
emissions/reflectance, comparison to a reference or other means, or are guided remotely
but with the controller receiving target information through an on-munition seeker.
PSGMs are characterized by their high PK and extreme lethality. PSGMs are a major
threat, in all areas of combat, land, air and afloat. Man portable, seeker guided
precision anti-aircraft missiles have the potential to be a significant terrorist
threat to civil aviation.
[0004] Defense strategies to counter PSGMs are as varied as the possible munition's targets.
An obvious defense stratagem is camouflage or preventing detection. Camouflage is
attempted through paints that change the visual or energy reflective/emissive characteristic
of a potential targets or by nets or materials that physically screen the target.
Additional defensive ploys include decoys, obscurants, shoot downs and maneuver. Decoys
attempt to mislead a precision guided munition so that is misses the target (flares
and chaff are excellent examples), obscurants (smoke) hide the target behind an aerosol
particulant distribution through which the target cannot be identified and methods
are being attempted to shoot down a precision guided weapon, physically by blast or
kinetics (thus far unsuccessful due to the small size, high speed and short flight
time), or to disable the precision guided munitions seeker by directed energy, typically
laser, thus rendering the missile unable to track its intended target. Additionally,
maneuver may be used if the target can perform vector or positional changes that exceed
the PSGMs seekers ability to track or flight control system to compensate for to obtain
a hit. Other methods described have varying degrees of success against different types
of precision guided munitions. None is perfect, none works against all threats, and
none works, singly or in combination, with a high degree of assurity to negate the
threat of PSGMs.
[0005] PSGMs have several systems components in common. All PSGMs are minimally possessed
of a seeker, a commanding system, a guidance system, a maneuvering (flight control)
system and a warhead. In other words, precision guided munitions broadly encompasses
everything from free fall bombs fitted with a seeker and flight control mechanism,
artillery projectiles fitted with a seeker and fight control mechanism, to self propelled
fire and forget anti-armor, anti-aircraft or anti-ship missiles. Analysis of these
systems reveals that the common items are the seeker, command system, flight controls
and warhead. Generally the warheads are fairly stable compounds that must be detonated
by a specific firing impulse from a specific mechanism. Warheads are extremely difficult
to detonate prematurely. The flight controls are mechanical devices or gas reaction
jets that are controlled in a number of different ways depending upon the munition.
They are robust mechanisms not easily disrupted by external influences. The command
system is either an onboard system or a remote system connected through cables to
the launching vehicle. Because of the wide variety of possible commanding sources,
a single mechanism able to defeat several or all of the command system types if not
considered practical. Practically all precision guided munitions contain a seeker
that receives, then passes information to an onboard guidance system or to a remote
system. The seeker on a precision guided munition may be tailored to any or several
portions of the energy spectrum, however the point of similarity is that all seekers
must receive energy to track their intended target. The energy reception portion of
the seeker is a delicate and sensitive mechanism and is always protected by being
located behind a window (faring, nose cone, glass, etc.) that is transparent to the
energy frequency of interest. Disruption, degradation, elimination or overload of
energy receipt by the seeker effectively binds the PSGM. A blind PSGMs probability
of striking its intended target decreases as a function of the distance away from
the target the munition is blinded, the dynamics of the atmosphere through which the
munition is moving, the control laws governing the munitions flight path and the maneuverability
and ability of the intended target to change location.
[0006] Defense against PSGMs may be achieved by blinding the inbound missile's seeker, or
disabling/degrading the incoming missile seekers ability to differentiate or perceive
its target. Blinding is achieved by inserting a shield such as an inert or incandescent
cloud of material in front of and intersecting an inbound munitions flight path so
that the energy transparency characteristics of the precision, seeker guided munition's
seeker aperture or the total energy received by the seeker are changed when the PSGM
views and/or transits the dispersed material cloud. Obviously the nose of the missile,
containing the energy aperture or "window" as the foremost component, transits the
shield first and will be impacted by whatever the shielding material consists of.
During transit of the shield or cloud of material, the "window' on the nose of the
missile, through which energy must pass to be received by the seeker, may be crazed,
cracked, abraded and or coated to either scatter inbound energy so that target source
is no longer discernible/identifiable, or energy receipt is sufficiently outside seeker
parameters so that the received energy is beyond the seekers perception threshold.
[0007] The material of the shield may or may not have obscurant characteristics similar
to that of well known and documented smoke (normally white phosphorous) or other obscurants.
While the dispersed material may (though it does not have to ) obscure the intend
target, the purpose of the dispersed material is to change the energy reception of
the threat PSGMs seeker so that the seeker is no longer able to maintain a track on
the intended target. With smoke or obscurates, once the PSGM has transited the obscurant
cloud, it is again able to reacquire and track a target.
[0008] US-A-4196668 (considered the closest prior art) discloses apparatus intended to stop
airborne vehicles from operating. A disabling cloud of delayed hardening foam is sprayed
to disable an enemy vehicle. The foam is typically plastics and is still soft when
it is directed towards the enemy vehicle. The soft foam is sucked into moving parts
of vehicles (such as the air inlets of aero combustion engines); the foam subsequently
hardens and disables the moving parts. The arrangement of US-A-4196668 includes a
missile for disabling an airborne threat without requiring impact, the missile, including
a body having a container including means for disabling the airborne threat and means
for ejecting the disabling means from the container at a point spaced from the airborne
threat but in the vicinity of the trajectory of the airborne threat.
[0009] US-A-5194687 discloses a missile arrangement for disabling an armoured vehicle whereby
a solidifying rigid foam, having metallic flakes dispersed therein, is directed towards
the vehicle. The foam solidifies on emitters or receptors causing attenuation, distortion
of visible, radio frequency or other signals destroying the effectiveness of the vehicle.
The arrangement disclosed is suitable and intended for use in disabling landborne
tactical armoured vehicles.
[0010] EP-A-0557200 discloses a missile arrangement which is suitable and intended for use
in disabling landborne tactical armoured vehicles. A smoke forming gel adheres to
the armoured vehicle disabling the vehicle systems.
[0011] It is, therefore, an object of the present invention to provide an anti-missile missile
with means to render the guidance system of an incoming threat missile inoperative
for performing the function of guiding the incoming missile to a predetermined target.
[0012] It is another object of the present invention to provide an anti-missile missile
with such means for injecting a shield material into the path of the incoming threat
missile which will destroy its guidance capabilities.
[0013] It is still another object of the present invention to provide such shield material
in the form of a cloud which will effectively "blind" the optical components of its
guidance system as the missile penetrates the cloud.
[0014] It is yet another object of the present invention to provide such shield material
which serves to coat, craze, crack, erode the seeker aperture or overload the sensing
capabilities of the seeker of a precision guided missile to a level outside the parameters
of the missile's seeker ability to track.
[0015] The missile according to the present invention is described in claim 1.
[0016] The anti-missile may be more clearly understood from the following description given
by way of example only, with reference to the accompanying drawings, wherein:
BRIEF DESCRIPTION OF THE DRAWINGS
[0017] Figure 1 is a diagrammatic illustration of a typical precision seeker guided missile
in its trajectory to a target.
[0018] Figure 2 is a view similar to Figure 1 but illustrates the missile of Figure 1 being
intercepted by a shield in the form of a cloud of material capable of rendering the
guidance system of the incoming threat missile incapable of operating properly.
[0019] Figure 3 is a view similar to Figure 2 and illustrates the "blinded" trajectory of
the incoming threat missile responsive to being intercepted by the shield of the present
invention.
[0020] Figures 4a-4c are diagrammatic elevational views of various states of a missile seeker.
Figure 4a illustrates a typical seeker which has not been exposed to the shield means
of the present invention and thereby permits energy from the target to pass there
through to the guidance components of the missile and thus enable the threat missile
to reach its target. Figure 4b illustrates a missile seeker which has been subjected
to the shield means of the present invention which has caused the seeker to be coated,
crazed, cracked, eroded or overloaded and has destroyed its ability to track. Figure
4c illustrates a coated seeker aperture in which no or insufficient energy passes
to the control components of the threat missile.
[0021] Figure 5-8 illustrates various munitions in which the shield material of the present
invention may be housed for transport to the intercept point with the incoming threat
missile. Figure 5 is an elevational view of a guided time fuzed missile. Figure 6
is an elevational view of a guided, seeker missile. Figure 7 is an elevational view
of an unguided missile. Figure 8 is an elevational view of a guided projectile.
[0022] Figure 9 is a diagrammatic view of the shield ejection system including an initiator
for initiating an explosive which fractures the container for dispersion of the shield
material to the atmosphere.
[0023] Figure 10 is a view similar to Figure 9 but illustrates an explosive initiator for
opening ports through which the shield material is released to the atmosphere.
[0024] Figure 11 is a plan view of the embodiment of the shield means wherein an adhering
strip of material is provided with electrical conductors therein.
[0025] Figure 12 is a diagrammatic view of a wire guided threat missile having tracking
wires which are shown to be electrically shorted by the strips as shown in Figure
11.
[0026] As shown in Figure 1, an incoming threat missile 10 is in a trajectory 12 ending
at a target 14, illustrated as being a tank. The trajectory typically includes an
initial portion 16 which places the missile in the vicinity of the target and terminal
portion 18 in which final course adjustments are made to assure impact of the missile
with or in the immediate vicinity of the target 14. Missile 10 is shown to include
a seeker 20 mounted at the forward end of the missile to receive energy containing
target information. This energy may be radar, electrical impulses, laser beams, heat
energy and any other type of reflection or transmissions containing target information.
The received energy cooperates with guidance and control components to direct the
missile to a target in known manner.
[0027] Figure 2 illustrates an intercept missile 22 having a body 24 including a container
portion 26 for containing a shield dispersant 28. Figure 2 illustrates the container
portion as being ruptured and a dispersant 28 as having been ejected therefrom in
the form of a cloud 30.
[0028] Figure 3 illustrates the "blinding effect" created on the incoming threat missile
as a result of the guidance component (seeker) being exposed to the dispersant cloud
of Figure 2. As seen in Figure 3, the incoming threat vehicle, although not destroyed
by impact is incapable of receiving guidance information from the sensor and, therefore,
is incapable of being guided to the target.
[0029] Figure 4a illustrates a seeker aperture 32 which has not been subjected to the shield
dispersants of the present invention. As shown in Figures 2 and 3, the unaffected
seeker aperture 32 passes the incoming energy to a seeker energy receptor or antenna
34 and onto a seeker processor 36 which processes the incoming energy signals, in
known manner, to guide the missile to the target.
[0030] As shown in Figure 4b, wherein like numerals refer to like parts, the seeker aperture
32 is illustrated as having been subjected to a dispersant containing particulants
of a predetermined size and as a result has become crazed, cracked, eroded or overloaded
so as to render it inoperative to pass energy to the antenna or processor.
[0031] Figure 4c is a view similar to Figure 4a, wherein like numerals refer to like parts,
but illustrates the seeker aperture as having been subjected to a coating 37 dispersant
and as a result has become coated so as to blind it to incoming energy and thus render
it inoperative to pass energy to the antenna or processor.
[0032] Figures 5-8 illustrate various anti-missile missiles in which the dispersant may
be housed for transport to the intercept point with the incoming threat missile. As
seen in Figure 5, a guided time fuzed missile 40 is shown to include a body 42 having
forward a forward flight control section 41 and an aft propulsion section 43 respectively
provided with flight control fins 44 and 46. Section 41 includes a computer/guidance
section 48, a dispersant container 50 for enclosing the shield dispersant, and a container
ejection section 51 for ejecting the container 50 from the missile body, if desired.
[0033] Figure 6 is a view similar to Figure 5, wherein like numerals refer to like parts,
and illustrates a guided, seeker missile 54 containing all of the above-identified
sections plus an initiator 52 such as a timer/seeker/sensor at the tip of the container
to aid in guiding the anti-missile missile in its trajectory to a target and to provide
an electrical signal for actuating the dispersant release mechanism at the desired
time.
[0034] Figure 7 is an elevational view of an unguided missile 54 which is merely shot, unguided,
into the path of the threat missile and includes a container/casing 50 enclosing the
dispersant and initiator 52 such as a time/sensor/seeker at the forward tip of the
body of the projectile. The initiator provides an electrical pulse to actuate the
dispersant release means as will be described hereinbelow.
[0035] Figure 8 is a view similar to Figure 7 wherein like reference numerals refer to like
parts, and illustrates a guided missile 56 as having the initiator 52 (such as a time/seeker/sensor)
at the forward tip of the container and a guidance and control section 48 and fins
62 at the aft end of the missile. No aft propulsion section is required in this type
of missile (projectile).
[0036] Figure 9 illustrates a mechanism for rupturing the dispersant container. The mechanism
includes a pressurizing container 64 which provides pressure to expel the dispersant
from the container. As seen in Figure 9, initiator 52 ignites an explosive device
68 through an exploding bridge wire 69 or the like and this detonation releases pressure
from pressurizing container 64 to pressurize and rupture the dispersant container
50 so that the dispersant may be expelled to the atmosphere.
[0037] Figure 10 illustrates the dispersant container 50 as being provided with ports 70
around the periphery thereof. The ports are covered with a membrane or closure member
72 which is structurally weaker than the container and is ruptured responsive to pressurization
of the container by the source of pressure 64 which is actuated by a signal from an
initiator 52. Upon rupturing of the closure member 72, the dispersant is expelled
to the atmosphere.
[0038] Figure 11 illustrates a shield 74 used to disable incoming wire guided missiles.
Shield 74 includes a strip of adhering material 75 having electrically conductive
members 76 carried thereon.
[0039] Figure 12 illustrates a wire guided threat missile 80 having wires 78 connected thereto
and to a control console. Such wire guided missiles are known in the art. The wires
transmit guidance and control information to the missile for directing the missile
to a target. If an electrical short occurs in the wires, target information cannot
be received by the missile. The present invention provides a means whereby such an
electrical short can be made to occur. This is accomplished by providing missile 10
with a shield container 50 which contains the conductive adhering strips 74 of Figure
11 and ejecting this shield material in the manner discussed supra, the adhering conductive
strips will adhere to the trailing wires and provide an electrical short in the wires.
[0040] It is to be understood that the device used to blind a PSGM consists, minimally,
of a dispersant delivery mechanism/system, a dispersant ejection mechanism and a dispersant
of "blinding" material.
[0041] The shield means delivery mechanism/system of the present invention in its most basic
form can be as simple as a container/casing that is projected/shot to intercept the
inbound flight path of the threat precision, seeker guided missile. An initiator such
as a timer (time determined and set by the launching mechanism) or an in-projectile
sensor activator initiates the dispersant mechanism when the threat missiles flight
path is intercepted. Figures 7 and 8 illustrate such delivery system. Complexity and
sophistication can be increased such that the delivery system is self propelled, contains
a guidance, control and seeker systems and has the capacity to detect the inbound
precision guided munition, project its flight path, plot it's own flight path to an
intercept point and initiate dispersion at a optimal time for maximum pattern penetration
by the inbound munition. Figures 5 and 6 illustrate such delivery systems.
[0042] It is to also be understood that the dispersion mechanism can be any of a multitude
of well known methods or mechanisms. For example, the dispersion mechanism may be
as simple as the fracturing of the casing of the material container and using the
relative air stream velocity as the dispersant force. The dispersion mechanism may
be mechanical (spring, gas, pyrotechnique, etc.) that either fractures the case and
disperses the material or ejects the material through orifices, ports or other exits.
The dispersion mechanism may be an explosive or pyrotechnique that is separate from
the dispersant material, embedded in the dispersant material or be a component of
the dispersant material. It is to be further understood that the dispersed material
is used to change the characteristics (amount) of energy entering said aperture to
thereby affect the operational capabilities of the guidance and control components.
This is accomplished by altering the energy transmissivity of the PSGMs energy receiving
aperture by destroying or modifying the energy transparent aperture on the PSGM through
which the energy must pass in its traverse to the guidance and control system or by
overloading the seeker's sensing capability. To achieve this result, the material
may be one of, or a combination of the following:
1. A dense or sufficiently sized cloud of particulants that will crack, shatter or
stove in the energy transparent aperture of the threat precision, seeker guided munition
thus destroying/degrading the seeker or rendering the seeker incapable of performing
its function.
2. A silica or other abrasive material that will craze, abrade, erode, corrode, minutely
fracture or otherwise change the energy transparency properties of the threat seekers
aperture cover so that the energy received by the seeker is not usable in tracking
its target.
3. An adhering material be it a paint type or a pyrotype material that coats the transiting
PSGMs energy transparent aperture and makes it opaque. By application of an opaque
coating the energy of interest to the seeker no longer can pass through the cover
or can not pass through in sufficient quantity for the seeker to discriminate it's
target and track on it. In the case of a munition with an on board radar, the applied
material may cause an intense reflected return from the on board radar's emissions
that overloads, damages or renders the seeker non-operational, or it may reduce the
return inbound energy to below the seeker's perception threshold.
4. The adhering material may be in the form of fine strands or strips that would,
on impact, adhere to the nose of the munition and cover the energy transparent aperture
thus reducing or completely eliminating the passage of the required energy and "blinding"
the munition.
5. The material may be of a form that will burn or incandesce so that sustained increase
in available energy entering the seeker overloads the seeker reception ability or
drowns out the energy of interest. The material may continue to burn or incandesce
even as it impacts and adheres to the PSGM's nose. An example of such material is
magnesium oxide. Ignition of the magnesium oxide may be accomplished by the initiator
at the time the initiator energizes the pressurizing source.
6. The adhering material may include metallic elements to short the trailing command
cables on PSGMs that are guided by electrical command wires.
[0043] The present invention lends itself to incorporation into or with other defensive
systems, either as a separate component or as a part of another munition For example,
proposals have been made to build small munitions that would destroy inbound threat
munitions by kinetic kill or near explosion. The addition of the blinding mechanism
and materials to a kinetic kill or explosive warhead munition would materially expand
the probability that the munition would render the inbound threat ineffective. The
blinding mechanism and material would be deployed as described and the kinetic kill
or explosive warhead would continue as designed and attempt to kill the inbound threat.
If an explosive or kinetic kill were not achieved, the deployed blinding materials
would achieve, what in military parlance is known as a "soft" kill, as a back-up.
Such a system would greatly enhance the probability of rendering the threat munition
ineffective.
[0044] It is to be understood that the word "missile" as used herein refers to an object
which is launched toward a target. Such objects, of course, include guided or ballistic
missiles, rocket propelled vehicles and other munitions and projectiles.
1. An anti-missile missile (22) for effectively disabling the guidance and control system
of an incoming guided threat missile (10) without requiring impact of the anti-missile
missile (22) with the incoming guided threat missile (10), the anti-missile missile
comprising (22):
(a) a body (24) having a container portion (26) enclosing shield means (28) for disabling
the guidance and control system of the threat missile (10); and
(b) means for ejecting the shield means from the container portion (26) at a point
spaced from the threat missile (10), but in the vicinity of the trajectory of the
threat missile (10);
wherein the shield means (28) comprises:
(i) blinding material (30) arranged when ejected from the container portion (26) of
the body (24) to modify the permissivity of a seeker aperture (20) or window provided
for the threat missile (10), thereby to inhibit incoming target related energy from
entering the seeker (20) and reaching the guidance and control system; the blinding
material (30) comprising:
(a) a material which is able to adhere to the receiving aperture (20) or window of
a seeker provided for the threat missile (10) whilst the threat missile (10) is in
flight, the adhering material inhibiting incoming energy carrying target information
from entering the aperture, window or seeker and/or releasing energy through the seeker
aperture (20) or window to overload the guidance and control system the adhering material
being a paint type material or a pyrotype material, that is able to coat a missile
window and to render it opaque, or the adherent material being in the form of fine
strands or strips that, on impact, adhere to the seeker; or
(b) an abrasive which crazes or cracks the seeker aperture (20) or window to inhibit
incoming energy carrying target information from entering the seeker aperture or window
(20).
2. An anti missile according to claim 1, wherein the shield means further comprises,
shorting means for adhering to trailing conductors provided externally of the threat
missile (40) and whilst in flight, the trailing conductors comprising a part of the
guidance and control system, the adhering shorting means creating a short circuit
between the trailing conductors.
3. An anti-missile missile according to any preceding claim, wherein the ejection means
comprises means for rupturing at least a portion of the container portion (26) of
the missile for release of the shield means (28) to the atmosphere; and
a pressurising medium is carried in the container portion (26) for pressurisation
thereof to exert pressure on the shield means (28) for release of the shield means
(28) from the container portion (26) of the missile (22); and
the portion of the container portion which is arranged to rupture includes a plurality
of ports (70) disposed around the periphery thereof including cover members (72) disposed
for rupturing to release the shield means.
4. An anti-missile missile according to any preceding claim, wherein the shorting means
comprises at least one strip of adhering material having electrically conductive members
disposed therein (74).
5. An anti-missile missile according to any preceding claim, wherein the blinding material
comprises a silica material carried in the container for ejection therefrom in the
vicinity of the threat missile, so as to physically alter the aperture or window of
the seeker such that insufficient target related energy is passed therethrough for
operational control of the guidance and control system thereby rendering the guidance
and control system ineffective to guide the threat missile to the target.
1. Antiraketenrakete (22) zum effektiven Außergefechtsetzen des Führungs- und Steuerungssystems
einer herannahenden geführten bedrohenden Rakete (10), ohne dass ein Auftreffen der
Antiraketenrakete (22) auf die herannahende geführte bedrohende Rakete (10) notwendig
ist, wobei die Antiraketenrakete (22) umfasst:
(a) einen Körper (24), mit einem Behälterbereich (26), der Abschirmungsmittel (28)
zum Außergefechtsetzen des Führungs- und Steuerungssystemes der bedrohenden Rakete
(10) beinhaltet; und
(b) Mittel, um die Abschirmungsmittel aus dem Behälterbereich (26) an einer von der
bedrohenden Rakete (10) beabstandeten Stelle, aber in der Nähe der Flugbahn der bedrohenden
Rakete (10) auszuwerfen;
wobei das Abschirmungsmittel (28) umfasst:
(i) Blendmaterial (30), das so eingerichtet ist, dass es, wenn es aus dem Behälterbereich
(26) des Körpers (24) ausgeworfen wird, die Permissivität einer für die bedrohende
Rakete (10) vorgesehenen Sucherblende (20) oder eines Sucherfensters verändert, um
dadurch die hereinkommende zielbezogene Energie daran zu hindern, in den Sucher (20)
einzutreten und das Führungs- und Steuerungssystem zu erreichen; wobei das Blendmaterial
(30) umfasst:
(a) ein Material, das sich an die für die bedrohende Rakete (10) vorgesehene empfangende
Sucherblende (20) oder das Sucherfenster anhaften kann, während die bedrohende Rakete
(10) im Flug ist, wobei das anhaftende Material die hereinkommende, Zielinformation
tragende Energie daran hindert, in die Blende, das Fenster oder den Sucher zu gelangen,
und/oder Energie durch die Sucherblende (20) oder das Fenster frei setzt, um das Führungs-
und Steuerungssystem zu überlasten, wobei das anhaftende Material ein farbartiges
Material oder ein pyrotechnisches Material ist, das das Raketenfenster bedecken und
undurchlässig machen kann, oder wobei das anhaftende Material die Form von feinen
Spänen oder Streifen besitzt, die nach dem Auftreffen am Sucher anhaften, oder
(b) ein Schleifmittel, das die Sucherblende (20) oder das Fenster rissig macht oder
bricht, um hereinkommende Zielinformation tragende Energie daran zu hindern, in die
Sucherblende oder das Sucherfenster (20) einzutreten.
2. Antirakete gemäß Anspruch 1, wobei die Abschirmungsmittel weiterhin Kurzschlussmittel
zum Anhaften an außen und während des Fluges an der bedrohenden Rakete (40) vorgesehenen
Schleppleitungen umfassen, wobei die Schleppleitungen einen Teil des Führungs- und
Steuerungssystems bilden und die anhaftenden Kurzschlussmittel einen Kurzschluss zwischen
den Schleppleitungen verursachen.
3. Antiraketenrakete nach einem der vorhergehenden Ansprüche, wobei die Auswurfmittel
Mittel zum Zerbrechen von wenigstens einem Abschnitt des Behälterbereiches (26) der
Rakete umfassen, um die Abschirmungsmittel (28) in die Atmosphäre zu entlassen; und
ein Druckmedium in dem Behälter (26) zur Druckausübung daraus transportiert wird,
um Druck auf die Abschirmungsmittel (28) auszuüben, um die Abschirmungsmittel (28)
aus dem Behälterbereich (26) der Rakete (22) frei zu setzen; und
ein Abschnitt des Behälterbereiches, der zum Zerbrechen vorbereitet ist, eine Vielzahl
von Öffnungen (70) beinhaltet, die entlang seiner Peripherie unter Einschluss von
Verschlussteilen (72) angeordnet sind, welche zum Zerbrechen vorbereitet sind, um
die Abschirmungsmittel frei zu setzen.
4. Antiraketenrakete nach einem der vorhergehenden Ansprüche,
wobei die Kurzschlussmittel wenigstens einen Streifen anhaftenden Materials umfassen,
in dem elektrisch leitende Teile angeordnet sind (74).
5. Antiraketenrakete gemäß einem der vorhergehenden Ansprüche,
wobei das Blendmaterial ein Silicamaterial umfasst, das in dem Behältnis zum Auswurf
aus letzterem in der Nähe der bedrohenden Rakete transportiert wird, um so die Blende
oder das Fenster des Suchers physikalisch zu verändern, so dass durch diese keine
ausreichende zielbezogene Energie für die operationelle Steuerung des Führungs- und
Steuerungssystems hindurchgeführt wird, was das Führungs- und Steuerungssystem untauglich
macht, die bedrohende Rakete ins Ziel zu führen.
1. Missile antimissile (22) pour mettre hors d'état de manière efficace le système de
guidage et de commande d'un missile hostile guidé arrivant (10) sans nécessiter l'impact
du missile antimissile (22) avec le missile hostile guidé arrivant (10), le missile
antimissile (22) comportant:
(a) un corps (24) ayant une partie de conteneur (26) enfermant des moyens de bouclier
(28) pour mettre hors d'état le système de guidage et de commande du missile hostile
(10), et
(b) des moyens pour éjecter les moyens de bouclier depuis la partie de conteneur (26)
à un point distant du missile hostile (10), mais à proximité de la trajectoire du
missile hostile (10),
dans lequel les moyens de bouclier (28) comportent :
(i) un matériau aveuglant (30) conçu, lorsqu'il est éjecté depuis la partie de conteneur
(26) dû corps (24), pour modifier la permissivité d'une ouverture d'autodirecteur
(20) ou fenêtre fournie pour le missile hostile (10), de manière à empêcher qu'une
énergie associée à une cible d'arrivée n'entre dans l'autodirecteur (20) et n'atteigne
le système de guidage et de commande, le matériau aveuglant (30) comportant :
(a) un matériau qui est capable d'adhérer à l'ouverture de réception (20) ou fenêtre
d'un autodirecteur fourni pour le missile hostile (10) alors que le missile hostile
(10) est en vol, le matériau d'adhérence empêchant qu'une énergie d'arrivée portant
des informations de cible n'entre dans l'ouverture, la fenêtre ou l'autodirecteur
et/ou la libérer l'énergie à travers l'ouverture d'autodirecteur (20) ou fenêtre pour
surcharger le système de guidage et de commande, le matériau d'adhérence étant un
matériau de type peinture ou un matériau pyrotype, qui est capable de revêtir une
fenêtre de missile et de la rendre opaque, ou le matériau d'adhérence ayant la forme
de minuscules fibres ou bandes qui, lors d'un impact, adhèrent à l'autodirecteur,
ou
(b) un abrasif qui fendille ou fissure l'ouverture d'autodirecteur (20) ou fenêtre
pour empêcher qu'une énergie d'arrivée portant des informations de cible n'entre dans
l'ouverture ou la fenêtre d'autodirecteur (20).
2. Missile antimissile selon la revendication 1, dans lequel les moyens de bouclier comportent
de plus, des moyens de court-circuit pour adhérer aux conducteurs arrière agencés
à l'extérieur du missile hostile (40) et lors du vol, les conducteurs arrière comportent
une partie du système de guidage et de commande, les moyens de court-circuit d'adhérence
créant un court-circuit entre les conducteurs arrière.
3. Missile antimissile selon l'une quelconque des revendications précédentes, dans lequel
les moyens d'éjection comportent des moyens pour casser au moins une partie de la
partie de conteneur (26) du missile pour la libération des moyens de bouclier (28)
dans l'atmosphère, et
un milieu de pressurisation est transporté dans la partie de conteneur (26) pour
une pressurisation de celle-ci afin d'exercer une pression sur les moyens de bouclier
(28) pour la libération des moyens de bouclier (28) depuis la partie de conteneur
(26) du missile (22), et
la partie de la partie de conteneur qui est conçue pour se casser comporte une
pluralité d'orifices (70) disposés autour de la périphérie de celle-ci incluant des
éléments de couvercle (72) disposés pour se casser afin de libérer les moyens de bouclier.
4. Missile antimissile selon l'une quelconque des revendications précédentes, dans lequel
les moyens de court-circuit comportent au moins une bande de matériau d'adhérence
ayant des éléments électriquement conducteurs disposés à l'intérieur (74).
5. Missile antimissile selon l'une quelconque des revendications précédentes, dans lequel
le matériau aveuglant comporte un matériau de silice porté dans le conteneur pour
une éjection de celui-ci à proximité du missile hostile, de manière à altérer physiquement
l'ouverture ou la fenêtre de l'autodirecteur de sorte qu'une énergie associée à une
cible insuffisante est passée à travers celle-ci pour une commande opérationnelle
du système de guidage et de commande de manière à rendre le système de guidage et
de commande inefficace pour guider le missile hostile vers la cible.