RU2146352C1 - Antirocket rocket - Google Patents

Abstract

FIELD: defensive means. SUBSTANCE: given antirocket rocket to prevent attacking rocket to hit target does not require encounter of antirocket rocket with attacking rocket. Approaching attacking rocket is fitted with guidance and control system designed to receive guidance energy from external radiator to guide attacking rocket to target. Antirocket rocket has body carrying container and screening aids placed in container and intended to be thrown out of container near attacking rocket. Screening aids are meant to change quantity of guidance energy received by guidance and control system and to disable guidance and control system of attacking rocket attacking target. Throwing device is intended to throw screening aids near attacking rocket. EFFECT: increased efficiency of combating of attacking rockets. 6 cl, 14 dwg

Description

 The invention generally relates to anti-missile missiles and, in particular, to those missiles that have means for bringing the guidance units of an approaching high-precision attack missile, guided by a homing head, to a state of inability to aim an approaching attack missile at a target without an anti-missile strike.

 After World War II, advances in technology made it possible to create high-precision ammunition controlled by a homing head (Homing), which during a flight to an intended target is actively guided and as a result has a high probability of destruction. The high probability of destruction and relatively low cost, especially in comparison with the potential target, make them cost-effective weapon systems. The high probability of defeat, excellence, affordable production technology, a relatively reasonable price and high combat readiness led to the spread of WBGS. A variety of systems of this kind are produced and sold by many companies and countries. As VBUHS obsolete previous releases and replaced by more advanced systems, these obsolete ammunition from the vast secondary market fall into less affluent countries and organizations. This proliferation has increased the danger posed by these weapons to both warring and non-belligerent parties, especially if these munitions are received by fanatical or terrorist countries and / or organizations.

 A precision-guided munition controlled by a homing head is any munition freely falling or propelled by an engine that can be aimed at a target using an onboard homing head and a control system. The WBIGs considered here are autonomously controlled, i.e. have an onboard or integrated homing head and sufficiently sophisticated electronics for target recognition by silhouette, radiation / reflection of energy, compared to a standard or other method, or are remotely controlled, but the control device receives information about the target through the homing head located on the munition. IWBFS are highly likely to be affected and are extremely deadly. VBUGS is the main threat in all battles, land, air or sea. Managed homing missiles are potentially a significant threat to civil aviation by terrorists.

 The defense strategy to counteract the WBGS is as diverse as the likely targets of these munitions. An obvious defense is to mask or prevent detection. Masking is carried out by means of paints that change the visual or energy characteristics of the reflection / radiation of potential targets or using networks or materials that physically shield the target. Additional defenses include false targets, camouflage curtains, destruction and maneuvering. With the help of false targets, they try to change the flight path of a precision guided munition so that it misses the target (thermal traps and dipole reflectors are good examples). Camouflage curtains (smoke) hide the target behind a distributed aerosol material consisting of particles through which it is impossible to identify the target, and they try to physically destroy high-precision guided weapons with an explosion or blow (which is ineffective due to their small size, high speed and short flight time ), or by incapacitating the homing head with directed energy, usually using a laser, as a result of which the rocket becomes incapable of tracking It is for the intended purpose. Additionally, maneuvering can be applied if the target is capable of making such changes in direction or position that exceed the tracking capabilities of the homing heads or the capabilities of the flight control system to carry out corrections to ensure a hit. The other methods described have varying degrees of success against various types of precision guided munitions. None of them is ideal, none works against any threat, and not one individually or in combination with others is capable of eliminating the threat of the IWBFS with a high guarantee.

 VBUHS have a number of common system components. All of them at least have a homing head, a command control system, a guidance system, a maneuvering system (flight control) and a warhead. Thus, high-precision guided munitions include a wide range from artillery shells and freely falling bombs equipped with a homing head and flight control mechanism, to equipped with an autonomous guidance system for anti-tank, anti-aircraft or anti-ship missiles on a self-propelled launcher. An analysis of these systems shows that the common nodes are the homing head, a command control system, flight controls, and a warhead. As a rule, warheads are fairly stable blocks that must detonate from a special igniting pulse created by a special mechanism. It is extremely difficult to cause premature detonation of a warhead. Flight controls are mechanical devices or gas jets controlled in various ways depending on the type of ammunition. These are durable mechanisms that are not easy to destroy by external exposure. Command control system - an on-board or remote system connected by a cable to the launcher. Due to the wide variety of possible command sources, it is almost impossible to create a single mechanism that can hit several or all types of guidance systems. Almost all high-precision guided munitions contain a homing head, which receives information that is then transmitted to the airborne or remote guidance system. The homing head of a high-precision guided munition can be designed to work in any area or any areas of the energy spectrum, but the common thing is that all homing heads must receive energy to track the intended purpose. The energy receiver of the homing head is a thin, sensitive mechanism, always protected by placing it outside the window (fairing, head cone, protective glass, etc.), which is transparent to energy of a given frequency. Interruption, decrease in intensity, cessation or exceeding a predetermined level of energy supply to the homing head effectively blinds VBUHS. The probability of a blinded VBUGS getting into a given target decreases depending on the distance to the target at which the ammunition is blinded, the dynamics of the atmosphere in which it is moving, the flight path control algorithms, and the ability of the intended target to maneuver and change its position.

 Protection from VBUGS can be done by blinding the homing head of an approaching missile or depriving (decreasing) its homing head of the ability to distinguish or perceive its target. Blinding is achieved by placing a screen, for example, in the form of an inert or luminous cloud of some material in front of an approaching munition across its flight path, so that when transmitting and / or passing through a cloud of dispersed material, the characteristics of energy transmission through the homing hole of a high-precision munition controlled by a homing head change , or the total amount of energy entering the homing head changes. Obviously, the nose of the rocket, having an opening for energy input, or a “window”, being the front element, passes the screen first, being exposed to the impact of the material that the screen consists of. When a screen or cloud passes from the material, a “window” on the rocket’s nose, through which energy enters the homing head, can be cracked, cracked, abrasive and / or coated, resulting in the dissipation of the incoming energy, so that the source belonging to the target cannot be distinguished or identify, or the output of the received energy beyond the parameters of the homing head, i.e. beyond the threshold of its perception.

 The screen material may or may not have masking curtain properties similar to those of well-known and documented fumes (typically white phosphorus) or other masking curtains. Although the dispersed material can (but does not have to) hide the intended target, its purpose is to change the energy input to the homing head of the attacking VBUGS so that the homing head can no longer maintain the direction to the intended target. When using smoke or a masking curtain after passing VBUGS through a masking cloud, it again becomes able to capture the target and monitor it.

 In the book of Nikolaev M.N. Rocket against a rocket, - M .: Military Publishing House, 1963, p. 159-161, a Nike Zeus missile defense is described, made in the form of a three-stage anti-ballistic missile for disabling the guidance and control system of an approaching attacking guided missile of the enemy without hitting the anti-missile with the enemy missile and containing, in particular, a body with a compartment. The striking factor of such a missile defense is the release of a large amount of energy during its explosion, which destroys the enemy missile guidance system. The disadvantage of such a projectile is that it must be aimed at its target with very high accuracy, and its explosion should be carried out in close proximity to the head of the enemy’s missile, since otherwise all the damaging factors will act much weaker and for a shorter period time, which reduces the likelihood of disabling the missile guidance system of the enemy.

 An object of the present invention is to provide an anti-missile missile containing means for bringing the guidance system of an approaching attacking enemy missile into a state of inability to fulfill the function of guiding this missile to a given target by placing screen material on its trajectory, which deprives this missile of its guidance ability, and also creating such screen material in the shape of the cloud, which effectively blinds the optical elements of the enemy’s missile guidance system as it passes through the cloud.

 The solution to this problem is provided by the fact that in an anti-missile missile for effective disabling of the guidance and control system of an approaching attacking guided missile of the enemy without impact of an anti-missile containing a housing with a compartment, a container compartment is used as this compartment, in which screening means for launching failure of the guidance and control system of the enemy’s missile and means of ejecting screen means from the container compartment in a place remote from the enemy’s missile, o the flight path of the enemy’s rocket, while the screen means contain: dazzling material to change when the permeability of the window of the homing of the enemy’s rocket from the container compartment is prevented from entering the homing head and achieving a guidance and control system of incoming energy that characterizes the target for the enemy’s rocket, containing: a substance with a strong ability to adhere to adhere to the inlet or window of the homing of an enemy rocket when found during flight and preventing it from entering the homing window or homing head and achieving a guidance and control system for incoming energy characterizing the target for an enemy missile, and / or releasing energy through the homing head window to overload the guidance and control system, or abrasive causing cracking, splitting or punching the window of the homing head to prevent the energy that characterizes the target for the enemy missile from entering the window of the homing head; and / or means of causing a short circuit and designed to adhere to external conductors reaching for an enemy missile and forming part of its guidance and control system, to short circuit these conductors.

 The presence in the anti-ballistic missile of screen means containing the above substances and / or means that cause a short circuit, as well as means of ejecting the screen means from the container compartment, allows these screen means to be placed on the trajectory of the enemy’s missile, which deprives it of the ability to aim and create a screen in the shape of a cloud that effectively blinds the optical elements of the enemy’s missile guidance system as it passes through the cloud or is capable of coating, cracking, cracking or scratching about Verstov homing precision-guided missiles or overload sensing ability of the head with the withdrawal of its outside tracking capabilities.

 The blinding material can be made in the form of thin fibers or strips which, when they collide with the homing head, adhere to it.

 The ejection means may include a device for tearing at least part of the container compartment of the rocket to release the screen means into the atmosphere, means for creating pressure can be placed in the container compartment to provide an impact on the screen means for releasing them from the container compartment of the rocket, and in the part of the container compartment, made with the possibility of tearing, can be made located on its periphery of the hole with covers installed with the possibility of tearing to release the screen means.

 Short-circuiting means may contain at least one strip of sticky material on which electrical conductors are placed, and the blinding material may contain silicon dioxide located in the container and intended to be ejected from it near the enemy rocket to change the physical properties of the inlet or the head window homing, when changing which the energy passed through it, which characterizes the target for the enemy’s missile, is not enough for the operational operation of the homing system tions and management, resulting in a homing head being brought into the failure of the enemy missile guidance to the target.

 The blinding material may also contain a substance that has the property of stable glow before contact with the enemy missile and during it to change the physical properties of the inlet or window of the homing head, when changing which the energy transmitted through it, characterizing the target for the enemy’s missile, is not enough for the operational operation of the system guidance and control, as a result of which the homing head is brought into a state of inability to aim the enemy missile at the target, and as a blind The material can be used with the possibility of luminescence due to the burning of the substance.

The invention is described below with reference to the accompanying drawings, in which:
FIG. 1 schematically depicts a typical high-precision missile controlled by a homing head on a flight path to a target,
FIG. 2 is a view similar to that of FIG. 1, on which the missile’s path is blocked by a cloud-shaped screen made of material capable of bringing the adversary’s approaching missile guidance system into a state of inability to work properly,
FIG. 3 is a view similar to that of FIG. 2, which shows a "blind" trajectory of an approaching enemy rocket blinded by interaction with the proposed screen,
FIG. 4A-4B schematically depict a side view of a homing missile in various states, with FIG. 4A shows a typical homing head not exposed to the proposed screen and therefore transmitting energy from the target to the missile guidance elements and thus ensuring the achievement of the target by the enemy missile, FIG. 4B depicts a homing missile subjected to the impact of the proposed screen, which led to its coating, cracking, splitting, erosion or overload and deprived of its tracking ability, and FIG. 4B shows a homing head, on the inlet of which a coating is applied, through which energy does not penetrate to the control elements of an enemy rocket or a small amount penetrates it,
FIG. 5-8 depict various ammunition in which the material of the proposed shield can be enclosed for delivery to an intercept point of an approaching enemy rocket, with FIG. 5 is a side view of a guided missile with a timer fuse; FIG. 6 is a side view of a guided missile with a homing head; FIG. 7 is a side view of an unguided rocket, and FIG. 8 is a side view of a guided projectile,
FIG. 9 is a schematic view of an ejection system including a detonator for driving an explosive that destroys a container for dispersing screen material in the atmosphere,
FIG. 10 is a view similar to that of FIG. 9, but shows an explosion detonator for opening holes through which screen material is discharged into the atmosphere,
FIG. 11 is a plan view of screen means in an embodiment providing for the use of adhesive strips with electrical conductors, and
FIG. 12 is a schematic view of an enemy attack rocket guided by wires, the wires of which are short-circuited behind by the strips shown in FIG. eleven.

 As shown in FIG. 1, an attacking missile 10 of an adversary has a trajectory 12 ending in target 14, depicted in the form of a tank. The trajectory usually includes the initial part 16, which displays the rocket a small distance from the target, and the final part 18, on which the final correction is carried out to ensure that it hits the target 14 or in the area directly near the target. The rocket 10 is shown with a homing head 20 mounted on the front end of the rocket to receive energy containing information about the target. This energy can represent electrical radar pulses, laser beams, thermal radiation and any other form of reflection or transmission containing information about the target. The received energy interacts with the guidance and control elements, and the rocket is sent to the target in a known manner.

 FIG. 2 depicts an interceptor missile 22 having a body 24 including a container portion 26 for receiving dispersible screen material 28. FIG. 2 depicts the destruction of the container portion and the ejection of dispersible material 28 in the form of a cloud 30 from it.

 FIG. 3 depicts the “blinding effect” of an approaching enemy missile created as a result of exposure to a guidance component (homing head) of a cloud of dispersed material shown in FIG. 2. As can be seen from FIG. 3, an approaching enemy missile, although not destroyed as a result of the collision, is not able to receive guidance information from the sensor and therefore is not able to aim at the target.

 4A shows a homing head window 32 not exposed to the dispersible materials of the proposed screen. As shown in FIG. 2 and 3, the unexposed window 32 transmits the incoming energy to the energy receiver or homing antenna 34 and to the homing processor 36, which processes incoming energy signals in a known manner to direct the missile at the target.

 As shown in FIG. 4B, in which identical parts are denoted by the same numbers, the homing window 32 is shown after exposure to dispersible material containing particles of a certain size, leading to its breaking, cracking, erosion or overload, which caused its inability to transmit energy to the antenna or processor.

 FIG. 4B is a view similar to that of FIG. 4A, depicting the input window of the homing head after coating 37 of dispersible material, which blinded it with respect to the incoming energy and caused an inability to transmit energy to the antenna or processor.

 5-8 depict various anti-missile missiles in which dispersible material can be enclosed for transport to an intercept point of an approaching attack missile. As can be seen from FIG. 5, the guided missile 40 with a timer fuse includes a housing 42 having a front flight control compartment 41 and aft engine compartment 43, respectively equipped with flight control stabilizers 44 and 46. Compartment 41 includes a computer or guidance part 48, a container 50 for accommodating scattered screen material, and an ejection part 51 for ejecting the container 50 from the rocket body, if necessary.

 FIG. 6 is a view similar to that of FIG. 5, which shows a missile 54 controlled by a homing head and containing all of the above compartments, as well as a detonator 52 located at the end of the container, for example, a timer / homing / sensor type, which helps to guide a missile on its path to the target and generates an electrical signal to actuate the mechanism for releasing dispersible material at a given time.

 FIG. 7 depicts a side view of an unguided rocket 54, which is simply fired without being controlled so that it is in the path of the attacking rocket and which includes a container / body 50 with dispersible material and a detonator 52 located at the front end of the projectile body, for example, a timer / sensor / head type homing. The detonator creates an electrical impulse to actuate the means for releasing the dispersible material, as described below.

 FIG. 8 is a view similar to that of FIG. 7, of a guided missile 56, having a detonator 52 located on the front end of the container, for example, a timer / homing / sensor type, and also guidance and control compartments 48 and stabilizers 62 located on the aft end of the missile. This is the aft engine compartment for the missile (projectile) of this type is not required.

 FIG. 9 shows a mechanism for destroying a container of dispersible material. The mechanism includes a pressure container 64, which is a source of pressure for displacing the dispersed material from the container. As can be seen from FIG. 9, the detonator 52 ignites an explosive device 68, for example, through connecting wires 69, and as a result of this detonation, pressure from the container 64 is supplied to the container 50 with dispersible material and breaks the container, expelling the material to the atmosphere.

 FIG. 10 shows a container 50 with dispersible material provided with peripheral openings 70. The holes are closed by a membrane or cover 72, the structural strength of which is less than the strength of the container, and which breaks as a result of the increase in pressure supplied to the container from the pressure source 64 by a signal from the detonator 52 After breaking the cover 72, the dispersible material is displaced into the atmosphere.

 FIG. 11 depicts a screen 74 used to disable approaching missiles guided by wire. The screen 74 contains a strip of adhesive material 75 with electrical conductors 76 located thereon.

 FIG. 12 depicts a wire-driven attack rocket 80 having wires 78 connecting it to a control panel. Such wire-guided missiles are well known. Guidance and control information is transmitted over the wires to the missile to direct the missile toward the target. In the event of a short circuit in the wires, information about the target cannot be received by the rocket. The present invention provides a means by which such a short circuit can be implemented. This is accomplished by equipping the rocket 10 with a screen-creating container 50, which contains the electrically conductive adhesive strips 74 shown in FIG. 11, and discarding this screen material in the manner described above. At the same time, adhesive conductive strips stick to the wires and create a short circuit in them.

 It should be noted that the device used to blind the VBUHS contains at least a device for delivering dispersible material, a mechanism for ejecting dispersible material, and a dispersible "blinding" material.

 The device for delivering the material of the proposed screen in its most general form can be made as simple as a container / case that is fired / fired to block the approaching attacking high-precision missile controlled by the homing head. A detonator, such as a timer (time is determined and set by the trigger) or a sensor installed in the projectile, initiates the device of the dispersed material when it hits the flight path of an attacking missile. FIG. 7 and 8 depict such a delivery device. The complexity and sophistication of the delivery device can be enhanced by equipping it with an engine, guidance, control and search system, means of detecting high-precision ammunition, determining its flight path, calculating its own flight path to the interception point and dispersing at the optimal time to obtain maximum penetration of the approaching ammunition in a scattered cloud. FIG. 5 and 6 depict such delivery devices.

It should also be noted that dispersion can be carried out by any of many well-known methods or mechanisms. For example, dispersion can be accomplished in such a simple way as breaking the body of the material container and using the relative air velocity as the dispersing force. The dispersion mechanism may be mechanical (spring, gas, pyrotechnic cartridge, etc.), which destroys the housing and disperses the material, or throws the material through nozzles, holes or other outlets. The dispersion mechanism can be explosive or pyrotechnic, it can be separated from the dispersed material, located inside the dispersed material or be an integral part of the dispersed material. It should also be noted that the dispersed material is designed to change the characteristics (quantity) of energy entering through the specified window, and thereby affect the functionality of the control and guidance components. This is done by changing the energy transfer characteristics of the VBUGS window as a result of the destruction or change of the VBUGS window transmitting energy through which energy is supplied to the guidance and control system, or as a result of overloading of the sensitive elements of the homing head. To achieve this result, one of the following materials (combination) can be used:
1. A cloud of sufficient density or size of particles capable of breaking, splitting or piercing an energy-transmitting window of an attacking high-precision missile controlled by a homing head, resulting in the destruction, deterioration or failure of the homing head.

 2. Silicon dioxide or other abrasive material that causes cracking, abrasion, destruction, corrosion, the formation of small cracks or other changes in the transmission properties of the energy of the element covering the receiving hole of the attacking homing head, so that the energy supplied to the homing head cannot be used for tracking the target.

 3. A sticky material, like paint or pyrotechnic material, covering the energy-transmitting window of VBUGS and making it opaque. As a result of applying an opaque coating, the specified energy can no longer pass into the homing head through the coating or can not pass in sufficient quantity for the homing head to recognize its target and track it. If the ammunition is equipped with an airborne radar, the applied material can cause intense reflected backward radiation from the airborne radar, overloading, damaging or disabling the homing head. The applied material can also reduce the amount of incoming reverse energy so that it does not exceed the sensitivity threshold of the homing head.

 4. The sticky material can be made in the form of thin threads or strips adhering when touching the nose of the munition and closing the energy-transmitting window, as a result of which the transmission of the required energy is reduced or completely eliminated and the ammunition is “blinded”.

 5. The material may be burning or luminous, which causes a steady increase in the energy entering the homing head, which leads to overloading the receiver of the homing head or to killing the specified energy. The material may continue to burn or glow even after contact with the nose of VBUGS and sticking to it. An example of such a material is magnesium oxide. The ignition of magnesium oxide can be carried out by a detonator by supplying energy from the detonator to a pressure source.

 6. The sticky material may include metal elements for shorting the cable control team VBUGS controlled by electrical wires.

 This invention is intended to work with other defense systems as a separate component or as part of another munition. For example, there are proposals for the manufacture of small ammunition that would destroy approaching attacking ammunition by kinetic action or an explosion nearby. If the ammunition of kinetic destruction or the ammunition equipped with an explosive warhead is supplemented with glare mechanism and materials, this will significantly increase the probability of incapacitation of approaching attacking missiles. In this case, the glare mechanism and material are actuated as described above, after which the kinetic or explosive warheads perform the specified actions to destroy the approaching threat. If attempts at explosive or kinetic destruction are unsuccessful, with the help of blinding material used as a backup agent, the so-called “mild” defeat can be achieved. Such a system significantly increases the probability of failure of the attacking ammunition.

 It should be noted that the word “rocket,” as used here, refers to an object launched toward a target. Obviously, this concept covers guided or ballistic missiles, rocket-powered aircraft, and other ammunition and shells.

Claims (7)

 1. A missile for effective destruction of the guidance and control system of an approaching attacking guided missile of the enemy without impact of an anti-missile with an enemy missile, comprising a housing with a compartment, characterized in that the container compartment is used as a compartment in which screening means for incapacitating guidance systems and guidance of the enemy’s missile and means of ejecting screening equipment from the container compartment in a place remote from the enemy’s missile, near the field trajectory and the enemy’s missiles, while the screen means contain dazzling material to change when the permeability of the window of the enemy’s homing head is thrown out of the container compartment, preventing the homing head from reaching the homing head and achieving the guidance and control system of the incoming energy that characterizes the target for the enemy’s missile, containing a substance that has a strong the ability to stick to stick to the inlet or window of the homing head of an enemy rocket when it is in flight and pre This means hitting the window or homing head and achieving a guidance and control system for the incoming energy characterizing the target for an enemy missile and / or releasing energy through the homing head window to overload the guidance and control system, or abrasive causing cracking, cracking or punching of the head window homing to prevent the energy that characterizes the target for an enemy missile from entering the window of the homing head, and / or means that cause a short circuit and pre Assigning to adhere to the outer conductors, trailing behind enemy missile and integral part of its guidance and control system for a short circuiting of the conductors.  2. The missile missile according to claim 1, characterized in that the blinding material is made in the form of thin fibers or strips that, when they collide with the homing head, adhere to it.  3. The missile missile according to claim 1 or 2, characterized in that the means of ejection contain a device for tearing at least a portion of the container compartment of the rocket for releasing the screen means into the atmosphere, means for creating pressure are placed in the container compartment to provide an impact on the screen means for releasing them from the container compartment of the rocket, and in the part of the container compartment, made with the possibility of rupture, made located on its periphery of the hole with covers installed with the possibility of rupture for obozhdeniya screen means.  4. Missile defense missile according to any one of claims 1 to 3, characterized in that the means for creating a short circuit contain at least one strip of sticky material on which electrical conductors are placed.  5. Missile defense missile according to any one of claims 1 to 4, characterized in that the blinding material contains silicon dioxide located in the container and designed to be ejected from it near the enemy’s rocket to change the physical properties of the inlet or homing window, when changing which is missed through it, the energy characterizing the target for an enemy missile is not enough for the operational operation of the guidance and control system, as a result of which the homing head is brought into a state of inability avedeniya enemy missiles at the target.  6. Missile defense missile according to any one of claims 1 to 5, characterized in that the blinding material contains a substance having the property of a stable glow before contact with the enemy missile and during it to change the physical properties of the inlet or window of the homing head, which, if changed, through it, the energy characterizing the target for an enemy missile is not enough for the operational operation of the guidance and control system, as a result of which the homing head is brought into a state of inability to aim tions of the enemy missile at the target.  7. A missile missile according to claim 6, characterized in that as a blinding material used a substance with the possibility of glow due to the burning of the substance.

Images