Anti-aircraft missile system. Anti-aircraft missile systems based on aviation weapons

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Anti-aircraft missile weapons are classified as ground-to-air missiles and are designed to destroy enemy air attack means with anti-aircraft guided missiles (SAMs). It is represented by various systems.

An anti-aircraft missile system (anti-aircraft missile system) is a combination of an anti-aircraft missile system (SAM) and means that ensure its use.

Anti-aircraft missile system - a set of functionally related combat and technical means designed to destroy air targets with anti-aircraft guided missiles.

The air defense system includes means of detection, identification and target designation, means of flight control of missiles, one or more launchers (PU) with missiles, technical means and electrical power sources.

technical basis The SAM is the SAM control system. Depending on the adopted control system, there are systems for remote control of missiles, homing missiles, combined control of missiles. Each air defense system has certain combat properties, features, the totality of which can serve as classification features that allow it to be attributed to a certain type.

The combat properties of air defense systems include all-weather, noise immunity, mobility, versatility, reliability, degree of automation of combat operations, etc.

Vsepogodnost - the ability of air defense systems to destroy air targets in all weather conditions. There are all-weather and non-all-weather air defense systems. The latter ensure the destruction of targets under certain weather conditions and time of day.

Interference immunity - a property that allows the air defense system to destroy air targets in the conditions of interference created by the enemy to suppress electronic (optical) means.

Mobility is a property that manifests itself in transportability and the time of transition from traveling to combat and from combat to traveling. A relative indicator of mobility can be the total time required to change the starting position under given conditions. An integral part of mobility is maneuverability. The most mobile is the complex, which has greater transportability and requires less time to complete the maneuver. Mobile complexes can be self-propelled, towed and portable. Non-mobile air defense systems are called stationary.

Versatility is a property that characterizes the technical capabilities of air defense systems to destroy air targets in a wide range of ranges and heights.

Reliability - the ability to function normally under specified operating conditions.

According to the degree of automation, anti-aircraft missile systems are distinguished as automatic, semi-automatic and non-automatic. In automatic air defense systems, all operations for detecting, tracking targets and guiding missiles are performed automatically without human intervention. In semi-automatic and non-automatic air defense systems, a person takes part in solving a number of tasks.

Anti-aircraft missile systems are distinguished by the number of target and missile channels. Complexes that provide simultaneous tracking and firing of one target are called single-channel, and several targets are called multi-channel.

According to the firing range, the complexes are divided into long-range air defense systems (RD) with a firing range of more than 100 km, medium-range (SD) with a firing range of 20 to 100 km, short-range (MD) with a firing range of 10 to 20 km and short-range ( BD) with a range of up to 10 km.

The performance characteristics (TTX) determine the combat capabilities of the air defense system. These include: the appointment of an air defense system; range and height of destruction of air targets; the possibility of destroying targets flying at different speeds; the probability of hitting air targets in the absence and presence of interference, when firing at maneuvering targets; number of target and missile channels; noise immunity of ADMS; working hours of ADMS (reaction time); the time of transfer of the air defense system from the traveling position to the combat position and vice versa (the time of deployment and collapse of the air defense system at the starting position); movement speed; missile ammunition; power reserve; mass and overall characteristics, etc.

Performance characteristics are set in the tactical and technical specifications for the creation of a new type of air defense system and are specified in the process of field tests. The values ​​of performance characteristics are due to the design features of the ADMC elements and the principles of their operation.

Appointment of the air defense system- a generalized characteristic indicating the combat missions solved by means of this type of air defense system.

Range(shooting) - the range at which targets are hit with a probability not lower than the specified one. There are minimum and maximum ranges.

Defeat Height(shooting) - the height at which targets are hit with a probability not lower than a given one. There are minimum and maximum heights.

The ability to destroy targets flying at different speeds is a characteristic indicating the maximum allowable value of the flight speeds of targets destroyed in given ranges of ranges and altitudes of their flight. The value of the target flight speed determines the values ​​of the required rocket overloads, dynamic guidance errors, and the probability of hitting the target with one missile. At high target speeds, the required rocket overloads, dynamic guidance errors increase, and the probability of hitting decreases. As a result, the values ​​of the maximum range and height of target destruction are reduced.

Target hit probability- a numerical value characterizing the possibility of hitting a target under given firing conditions. Expressed as a number between 0 and 1.

The target can be hit by firing one or more missiles, therefore, the corresponding hit probabilities P are considered. ; and R P .

Target channel- a set of elements of an air defense system that provides simultaneous tracking and firing of one target. There are single- and multi-channel air defense systems in terms of purpose. The N-channel target complex allows you to simultaneously fire at N targets. The composition of the target channel includes a sight and a device for determining the coordinates of the target.

rocket channel- a set of elements of the air defense system, which simultaneously provides preparation for the launch, launch and guidance of one missile at the target. The structure of the missile channel includes: a launcher (launcher), a device for preparing for the launch and launch of missiles, a sighting device and a device for determining the coordinates of the rocket, elements of the device for generating and transmitting missile control commands. An integral part of the missile channel is the missile defense system. Air defense systems in service are single- and multi-channel. Single-channel portable complexes are performed. They allow only one missile to be aimed at the target at a time. Multi-channel missile defense systems provide simultaneous shelling of one or more targets with several missiles. Such air defense systems have great opportunities for sequential firing of targets. To obtain a given value of the target destruction probability, the air defense system has 2-3 missile channels per one target channel.

As an indicator of noise immunity, the following are used: the noise immunity coefficient, the permissible interference power density at the far (near) border of the affected area in the area of ​​​​the jammer, which ensures timely detection (opening) and destruction (defeat) of the target, the range of the open zone, the range, starting from which the target is detected (revealed) against the background of interference when the jammer sets up the interference.

Working hours of the air defense system(reaction time) - the time interval between the moment an air target is detected by air defense systems and the launch of the first missile. It is determined by the time spent searching for and capturing the target and preparing the initial data for firing. The working time of the air defense system depends on the design features and characteristics of the air defense system and the level of training of the combat crew. For modern air defense systems, its value ranges from units to tens of seconds.

The time of the transfer of air defense systems from traveling to combat- the time from the moment the command is given to transfer the complex to a combat position until the complex is ready to open fire. For MANPADS, this time is minimal and amounts to several seconds. The time of the SAM transfer to the combat position is determined by the initial state of its elements, the transfer mode and the type of power supply.

The time of the transfer of air defense systems from a combat position to a marching one- the time from the moment the command is given to transfer the air defense system to the marching position until the end of the formation of the elements of the air defense system in the marching column.

Combat kit(bq) - the number of missiles installed on one air defense system.

Power reserve- the maximum distance that an air defense vehicle can travel after consuming a full refueling of fuel.

Mass characteristics- limiting mass characteristics of elements (cabins) of air defense systems and missiles.

Dimensions- limiting external outlines of elements (cabins) of air defense systems and missiles, determined by the largest width, length and height.

ZRK affected area

The zone of destruction of the complex is a region of space within which the destruction of an air target by an anti-aircraft guided missile is ensured under the calculated firing conditions with a given probability. Taking into account the effectiveness of firing, it determines the reach of the complex in terms of height, range and heading parameter.

Estimated firing conditions- conditions under which the closing angles of the ADMC position are equal to zero, the characteristics and parameters of the target's movement (its effective reflective surface, speed, etc.) do not go beyond the specified limits, atmospheric conditions do not interfere with the observation of the target.

Realized affected area- part of the kill zone, in which the defeat of a target of a certain type is ensured in specific firing conditions with a given probability.

fire zone- the space around the air defense system, in which the missile is guided to the target.

Rice. 1. SAM affected area: vertical (a) and horizontal (b) section

The affected area is depicted in a parametric coordinate system and is characterized by the position of the far, near, upper and lower boundaries. Its main characteristics are: horizontal (slant) range to the far and near borders d d (D d) and d(D), minimum and maximum heights H mn and H max , limit heading angle q max and maximum elevation angle s max . The horizontal range to the far boundary of the affected area and the limit heading angle determine the limiting parameter of the affected area P pre , i.e., the maximum target parameter at which its defeat is ensured with a probability not lower than a given one. For multi-channel target ADMS, a characteristic value is also the parameter of the affected area Р stro, up to which the number of firing at the target is not less than at zero parameter of its movement. A typical section of the affected area by the vertical bisector and horizontal planes is shown in the figure.

The position of the boundaries of the affected area is determined by a large number of factors related to the technical characteristics of individual elements of the air defense system and the control loop as a whole, the firing conditions, the characteristics and parameters of the movement of an air target. The position of the far boundary of the affected area determines the required range of the SNR.

The position of the implemented far and lower boundaries of the zone of destruction of the air defense system may also depend on the terrain.

SAM launch zone

In order for the missile to meet the target in the affected area, the missile must be launched in advance, taking into account the flight time of the missile and the target to the meeting point.

Missile launch zone - a region of space, when a target is located in which, at the time of missile launch, their meeting in the zone of destruction of the air defense system is ensured. To determine the boundaries of the launch zone, it is necessary to set aside from each point of the affected zone to the side opposite to the target's course, a segment equal to the product of the target's speed V ii for the flight time of the rocket to this point. In the figure, the most characteristic points of the launch zone are respectively indicated by the letters a, 6, c, d, e.

Rice. 2. SAM launch zone (vertical section)

When tracking a CHP target, the current coordinates of the rendezvous point are usually calculated automatically and displayed on the indicator screens. The missile is launched when the meeting point is within the boundaries of the affected area.

Guaranteed launch zone- a region of space, when the target is located in which, at the time of the missile launch, it is ensured that it meets the target in the affected area, regardless of the type of anti-missile maneuver of the target.

In accordance with the tasks to be solved, functionally necessary elements SAMs are: means of detection, identification of aircraft and target designation; SAM flight controls; launchers and launchers; anti-aircraft guided missiles.

Portable anti-aircraft missile systems (MANPADS) can be used to combat low-flying targets.

When used as part of the Patriot, S-300 air defense systems, multifunctional radars act as means of detection, identification, tracking devices for aircraft and missiles aimed at them, control command transmission devices, as well as target illumination stations to ensure the operation of airborne direction finders.

In anti-aircraft missile systems, radar stations, optical and passive direction finders can be used as means of detecting aircraft.

Optical means of detection (OSO). Depending on the location of the source of radiation of radiant energy, optical detection means are divided into passive and semi-active. As a rule, in passive TOs, radiant energy is used, due to the heating of the aircraft skin and operating engines, or the light energy of the Sun, reflected from the aircraft. In semi-active OSOs, an optical quantum generator (laser) is located at the ground control station, the energy of which is used to probe space.

Passive OSO is a television-optical sight, which includes a transmitting television camera (PTC), a synchronizer, communication channels, a video monitoring device (VCU).

The television-optical sight converts the flow of light (radiant) energy coming from the aircraft into electrical signals that are transmitted over a cable communication line and used in the VKU to reproduce the transmitted image of the aircraft, which is in the field of view of the PTC lens.

In the transmitting television tube, the optical image is converted into an electrical image, while a potential relief appears on the photomosaic (target) of the tube, reflecting the distribution of brightness of all points of the aircraft in electrical form.

The reading of the potential relief occurs by the electron beam of the transmitting tube, which, under the action of the field of the deflecting coils, moves synchronously with the electron beam of the VCU. A video image signal appears on the load resistance of the transmitting tube, which is amplified by the preamplifier and fed to the VCU via a communication channel. The video signal after amplification in the amplifier is fed to the control electrode of the receiving tube (kinescope).

Synchronization of the movement of the electronic beams of the PTK and VKU is carried out by horizontal and vertical scanning pulses, which are not mixed with the image signal, but are transmitted via a separate channel.

The operator observes on the kinescope screen the images of the aircraft that are in the field of view of the reticle lens, as well as the target marks corresponding to the position of the optical axis of the TO in azimuth (b) and elevation (e), as a result of which the azimuth and elevation angle of the aircraft can be determined.

Semi-active OSOs (laser sights) in their structure, construction principles and functions are almost completely similar to radar ones. They allow you to determine the angular coordinates, range and speed of the target.

A laser transmitter is used as a signal source, which is triggered by a synchronizer pulse. The laser light signal is emitted into space, reflected from the aircraft and received by the telescope.

A narrow-band filter that stands in the way of the reflected pulse reduces the effect of extraneous light sources on the work of the reticle. The light pulses reflected from the aircraft fall on a photosensitive receiver, are converted into video frequency signals and used in units for measuring angular coordinates and range, as well as for displaying an indicator on the screen.

In the unit for measuring angular coordinates, drive control signals are generated optical system, which provide both an overview of space and automatic tracking of the aircraft in angular coordinates (continuous alignment of the axis of the optical system with the direction to the aircraft).

Identification tools allow you to determine the nationality of the detected aircraft and classify it as "friend or foe". They can be combined and standalone. In combined devices, request and response signals are emitted and received by radar devices.

Detection radar antenna "Top-M1" Optical means of detection

Radar-optical means of detection

A receiver of interrogation signals is installed on "its" aircraft, which receives encoded interrogation signals sent by the detection (identification) radar. The receiver decodes the interrogation signal and, if this signal corresponds to the set code, issues it to the response signal transmitter installed on board "its" aircraft. The transmitter generates a coded signal and sends it in the direction of the radar, where it is received, decoded and, after conversion, is displayed on the indicator in the form of a conditional label, which is displayed next to the mark from "its" aircraft. The enemy aircraft does not respond to the radar interrogation signal.

Target designation means are designed to receive, process and analyze information about the air situation and determine the sequence of shelling of detected targets, as well as transmit data about them to other combat means.

Information about detected and identified aircraft, as a rule, comes from the radar. Depending on the type of terminal device for target designation, the analysis of information about the aircraft is carried out automatically (when using a computer) or manually (by the operator when using screens cathode ray tubes). The results of the decision of the computer (calculating device) can be displayed on special consoles, indicators or in the form of signals for the operator to make a decision about their further use, or transmitted to other air defense systems automatically.

If a screen is used as terminal devices, then the marks from the detected aircraft are displayed as light signs.

Target designation data (decisions to fire targets) can be transmitted both via cable lines and radio links.

Means of target designation and detection can serve both one and several ZRV units.

When an aircraft is detected and identified, the operator analyzes the air situation, as well as the procedure for firing targets. At the same time, devices for measuring range, angular coordinates, speed, generating control commands and transmitting commands (command control radio link), an autopilot and a missile steering path are involved in the operation of the SAM flight controls.

The range measuring device is designed to measure the slant range to aircraft and missiles. Ranging based on straightness of propagation electromagnetic waves and the constancy of their speed. Range can be measured by radar and optical means. For this, the time of signal propagation from the radiation source to the aircraft and back is used. Time can be measured by the delay of the pulse reflected from the aircraft, the amount of change in the frequency of the transmitter, the amount of change in the phase of the radar signal. Information about the range to the target is used to determine the moment of launch of the SAM, as well as to develop control commands (for systems with telecontrol).

The device for measuring angular coordinates is designed to measure the elevation (e) and azimuth (b) of aircraft and missiles. The measurement is based on the property of rectilinear propagation of electromagnetic waves.

The speed measurement device is designed to measure the radial speed of the aircraft. The measurement is based on the Doppler effect, which consists in changing the frequency of the reflected signal from moving objects.

The control command generating device (UFC) is designed to generate electrical signals, the magnitude and sign of which correspond to the magnitude and sign of the missile's deviation from the kinematic trajectory. The magnitude and direction of deviation of the SAM from the kinematic trajectory are manifested in the violation of the links determined by the nature of the movement of the target and the method of aiming the SAM at it. The measure of violation of this connection is called the mismatch parameter A(t).

The value of the mismatch parameter is measured by means of ADMC tracking, which, based on A(t), form the corresponding electrical signal in the form of voltage or current, called the mismatch signal. The error signal is the main component in the formation of the control command. To improve the accuracy of pointing the missile at the target, some correction signals are introduced into the control team. In telecontrol systems, when implementing the three-point method, in order to reduce the time of launching the missile to the meeting point with the target, as well as to reduce errors in pointing the missile at the target, a damping signal and a signal for compensating dynamic errors due to the movement of the target, the mass (weight) of the missile can be introduced into the control command .

Device for transmitting control commands (command radio control lines). In telecontrol systems, the transmission of control commands from the point of guidance to the on-board device of the missile defense system is carried out by means of the equipment that forms the command radio control link. This line provides the transmission of rocket flight control commands, one-time commands that change the operating mode of the onboard equipment. The command radio link is a multi-channel communication line, the number of channels of which corresponds to the number of commands transmitted while simultaneously controlling several missiles.

The autopilot is designed to stabilize angular movements missiles relative to the center of mass. In addition, the autopilot is an integral part of the missile flight control system and controls the position of the center of mass itself in space in accordance with the control commands.

Launchers (PU) and launchers are special devices designed for placement, aiming, pre-launch preparation and missile launch. PU consists of a starting table or guides, aiming mechanisms, leveling devices, test and starting equipment, and power supplies.

Launchers are distinguished by the type of missile launch - with vertical and inclined launch, by mobility - stationary, semi-stationary (collapsible), mobile.

Stationary launcher C-25 with vertical launch

Portable anti-aircraft missile system "Igla"

Launcher of the Blowpipe man-portable anti-aircraft missile system with three guides

Stationary launchers in the form of launch tables are mounted on special concreted platforms and cannot be moved.

Semi-stationary launchers, if necessary, can be disassembled and, after transportation, installed in another position.

Mobile launchers are placed on special vehicles. They are used in mobile air defense systems and are carried out in self-propelled, towed, wearable (portable) versions. Self-propelled launchers are placed on tracked or wheeled chassis, providing a quick transition from traveling to combat position and back. Towed launchers are installed on caterpillar or wheeled non-self-propelled chassis, transported by tractors.

Portable launchers are made in the form of launch tubes into which a rocket is installed before launch. The launch tube may have a sighting device for pre-targeting and a trigger mechanism.

By the number of missiles on the launcher, single launchers, twin launchers, etc. are distinguished.

Anti-aircraft guided missiles are classified according to the number of stages, aerodynamic scheme, guidance method, type of warhead.

Most missiles can be single- and two-stage.

According to the aerodynamic scheme, missiles are distinguished, made according to the normal scheme, according to the “rotary wing” scheme, and also according to the “duck” scheme.

According to the method of guidance, self-guided and remote-controlled missiles are distinguished. A homing missile is one that has flight control equipment on board. Remote-controlled missiles are called missiles controlled (guided) by ground-based controls (guidance).

According to the type of combat charge, missiles with conventional and nuclear warheads are distinguished.

Self-propelled launcher SAM "Buk" with an inclined start

Semi-stationary launcher S-75 SAM with inclined launch

Self-propelled launcher S-300PMU with vertical launch

MANPADS are designed to deal with low-flying targets. The construction of MANPADS can be based on a passive homing system (Stinger, Strela-2, 3, Igla), a radio command system (Blowpipe), and a laser beam guidance system (RBS-70).

MANPADS with a passive homing system include a launcher (launch container), a trigger mechanism, identification equipment, and an anti-aircraft guided missile.

The launcher is a sealed fiberglass tube in which the missile is stored. The pipe is sealed. Outside the pipes are sights for preparation of rocket launch and launcher.

The launcher (“Stinger”) includes an electric battery for powering the equipment of both the mechanism itself and the homing head (before the missile is launched), a refrigerant cylinder for cooling the receiver of thermal radiation of the seeker during the preparation of the missile for launch, a switching device that provides the necessary sequence passage of commands and signals, indicator device.

The identification equipment includes an identification antenna and an electronic unit, which includes a transceiver, logic circuits, a computing device, and a power source.

Rocket (FIM-92A) single-stage, solid propellant. The homing head can operate in the infrared and ultraviolet ranges, the radiation receiver is cooled. The alignment of the axis of the optical system of the GOS with the direction to the target in the process of tracking it is carried out using a gyroscopic drive.

A rocket is launched from a container using a launch booster. The sustainer engine is turned on when the rocket moves away to a distance that prevents the anti-aircraft gunner from being hit by a jet of a running engine.

The radio command MANPADS include a transport and launch container, a guidance unit with identification equipment and an anti-aircraft guided missile. The conjugation of the container with the missile located in it and the guidance unit is carried out in the process of preparing MANPADS for combat use.

Two antennas are placed on the container: one - command transmission devices, the other - identification equipment. Inside the container is the rocket itself.

The guidance unit includes a monocular optical sight, providing capture and tracking of the target, an IR device for measuring the deviation of the missile from the line of sight of the target, a device for generating and transmitting guidance commands, a software device for preparing and producing a launch, an interrogator for identification equipment “friend or foe”. On the body of the block there is a controller used when aiming a missile at a target.

After launching the SAM, the operator accompanies it along the radiation of the tail IR tracer using an optical sight. The launch of the missile on the line of sight is carried out manually or automatically.

In automatic mode, the deviation of the missile from the line of sight, measured by the IR device, is converted into guidance commands transmitted to the missile defense system. The IR device is turned off after 1-2 seconds of flight, after which the missile is guided to the meeting point manually, provided that the operator achieves alignment of the image of the target and the missile in the field of view of the sight by changing the position of the control switch. Control commands are transmitted to the missile defense system, ensuring its flight along the required trajectory.

In the complexes providing guidance of missiles by a laser beam (RBS-70), laser radiation receivers are placed in the tail compartment of missiles to guide the missile to the target, which generate signals that control the flight of the missile. The guidance unit includes an optical sight, a device for forming a laser beam with a focus that changes depending on the distance of the SAM.

Telecontrol systems are those in which the movement of a missile is determined by a ground guidance point that continuously monitors the parameters of the target and missile trajectory. Depending on the place of formation of commands (signals) for controlling the missile's rudders, these systems are divided into beam guidance systems and telecontrol command systems.

In beam guidance systems, the direction of missile movement is set using directed radiation of electromagnetic waves (radio waves, laser radiation, etc.). The beam is modulated in such a way that when the missile deviates from a given direction, its on-board devices automatically detect mismatch signals and generate appropriate missile control commands.

An example of the use of such a control system with teleorientation of a missile in a laser beam (after it is launched into this beam) is the ADATS multi-purpose missile system developed by the Swiss company Oerlikon together with the American Martin Marietta. It is believed that such a method of control, compared with the command telecontrol system of the first type, provides a higher accuracy of pointing the missile at the target at long ranges.

In command telecontrol systems, missile flight control commands are generated at the guidance point and transmitted to the missile via a communication line (telecontrol line). Depending on the method of measuring the coordinates of the target and determining its position relative to the missile, command telecontrol systems are divided into telecontrol systems of the first type and telecontrol systems of the second type. In systems of the first type, the measurement of the current coordinates of the target is carried out directly by the ground guidance point, and in systems of the second type, by the onboard missile coordinator with their subsequent transmission to the guidance point. The development of missile control commands in both the first and second cases is carried out by a ground guidance point.

Rice. 3. Command telecontrol system

The determination of the current coordinates of the target and the missile (for example, range, azimuth and elevation) is carried out by the tracking radar. In some complexes, this task is solved by two radars, one of which accompanies the target (target sighting radar 7), and the other - a missile (missile sighting radar 2).

Target sighting is based on the principle of active radar with a passive response, i.e., on obtaining information about the current coordinates of the target from the radio signals reflected from it. Target tracking can be automatic (AC), manual (PC) or mixed. Most often, target sights have devices that provide different kinds target tracking. Automatic tracking is carried out without the participation of the operator, manual and mixed - with the participation of the operator.

To sight a missile in such systems, as a rule, radar lines with an active response are used. A transceiver is installed on board the missile, emitting response pulses to the request pulses sent by the guidance point. This method of sighting the missile ensures its stable automatic tracking, including when firing at considerable distances.

The measured values ​​of the coordinates of the target and the missile are fed into the command generation device (UVK), which can be performed on the basis of an electronic digital computer or in the form of an analog computing device. Commands are formed in accordance with the selected guidance method and the accepted mismatch parameter. The control commands generated for each guidance plane are encrypted and the command radio transmitter (RPK) is issued on board the missile. These commands are received by the onboard receiver, amplified, decoded, and through the autopilot in the form of certain signals that determine the magnitude and sign of the deflection of the rudders, they are issued to the rudders of the rocket. As a result of turning the rudders and the appearance of angles of attack and slip, lateral aerodynamic forces arise that change the direction of the rocket's flight.

The missile control process is carried out continuously until it meets the target.

After the launch of the missile to the target area, as a rule, with the help of a proximity fuse, the problem of choosing the moment of detonation of the warhead of an anti-aircraft guided missile is solved.

The command telecontrol system of the first type does not require an increase in the composition and mass of onboard equipment, and has greater flexibility in the number and geometry of possible missile trajectories. The main drawback of the system is the dependence of the magnitude of the linear error in pointing the missile at the target on the firing range. If, for example, the value of the angular guidance error is assumed to be constant and equal to 1/1000 of the range, then the miss of the missile at firing ranges of 20 and 100 km will be 20 and 100 m, respectively. In the latter case, to hit the target, an increase in the mass of the warhead will be required, and hence launch mass of the rocket. Therefore, the telecontrol system of the first type is used to destroy missile targets at short and medium ranges.

In the telecontrol system of the first type, the target and missile tracking channels and the radio control line are subject to interference. The solution to the problem of increasing the noise immunity of this system is associated by foreign experts with the use, including in a complex way, of different frequency ranges and operating principles of target and missile sighting channels (radar, infrared, visual, etc.), as well as radar stations with a phased antenna array ( FAR).

Rice. 4. Command telecontrol system of the second type

The target coordinator (radio direction finder) is installed on board the missile. It tracks the target and determines its current coordinates in a moving coordinate system associated with the missile. The target coordinates are transmitted over the communication channel to the guidance point. Therefore, the airborne radio direction finder generally includes a target signal receiving antenna (7), a receiver (2), a device for determining target coordinates (3), an encoder (4), a signal transmitter (5) containing information about the target coordinates, and a transmitting antenna ( 6).

The target coordinates are received by the ground guidance point and fed into the device for generating control commands. The current coordinates of the anti-aircraft guided missile are also sent to the UVK from the tracking station (radio sight) of the missile. The command generating device determines the mismatch parameter and generates control commands, which, after appropriate transformations, are issued by the command transmission station to the rocket. To receive these commands, convert them and work out by the rocket, the same equipment is installed on its board as in the telecontrol systems of the first type (7 - command receiver, 8 - autopilot). The advantages of the telecontrol system of the second type are the independence of the missile guidance accuracy from the firing range, the increase in resolution as the missile approaches the target and the possibility of targeting the required number of missiles.

The disadvantages of the system include an increase in the cost of an anti-aircraft guided missile and the impossibility of manual target tracking modes.

According to its structural scheme and characteristics, the telecontrol system of the second type is close to homing systems.

Homing is the automatic guidance of a missile to a target, based on the use of energy coming from the target to the missile.

The missile homing head autonomously carries out target tracking, determines the mismatch parameter and generates missile control commands.

According to the type of energy that the target radiates or reflects, homing systems are divided into radar and optical (infrared or thermal, light, laser, etc.).

Depending on the location of the primary energy source, homing systems can be passive, active and semi-active.

In passive homing, the energy radiated or reflected by the target is created by the sources of the target itself or by the target's natural irradiator (Sun, Moon). Therefore, information about the coordinates and parameters of the target's movement can be obtained without special target exposure to energy of any kind.

The active homing system is characterized by the fact that the energy source that irradiates the target is installed on the missile and the energy of this source reflected from the target is used for homing the missiles.

With semi-active homing, the target is irradiated by a primary energy source located outside the target and the missile (Hawk ADMS).

Radar homing systems are widely used in air defense systems due to their practical independence of action from meteorological conditions and the possibility of guiding a missile to a target of any type and at various ranges. They can be used on the entire or only on the final section of the trajectory of an anti-aircraft guided missile, i.e. in combination with other control systems (telecontrol system, program control).

In radar systems, the use of the passive homing method is very limited. Such a method is possible only in special cases, for example, when homing missiles to an aircraft that has on its board a continuously operating jamming radio transmitter. Therefore, in radar homing systems, special irradiation (“illumination”) of the target is used. When homing a missile throughout the entire section of its flight path to the target, as a rule, semi-active homing systems are used in terms of energy and cost ratios. The primary source of energy (target illumination radar) is usually located at the point of guidance. In combined systems, both semi-active and active homing systems are used. The limitation on the range of the active homing system occurs due to the maximum power that can be obtained on the rocket, taking into account the possible dimensions and weight of the onboard equipment, including the homing head antenna.

If homing does not begin from the moment the missile is launched, then with an increase in the firing range of the missile, the energy advantages of active homing in comparison with semi-active ones increase.

To calculate the mismatch parameter and generate control commands, the tracking systems of the homing head must continuously track the target. At the same time, the formation of a control command is possible when tracking the target only in angular coordinates. However, such tracking does not provide target selection in terms of range and speed, as well as protection of the homing head receiver from spurious information and interference.

Equal-signal direction finding methods are used for automatic tracking of the target in angular coordinates. The angle of arrival of the wave reflected from the target is determined by comparing the signals received in two or more mismatched radiation patterns. The comparison may be carried out simultaneously or sequentially.

Direction finders with instantaneous equisignal direction, which use the sum-difference method for determining the angle of deviation of the target, are most widely used. The appearance of such direction-finding devices is primarily due to the need to improve the accuracy of automatic target tracking systems in the direction. Such direction finders are theoretically insensitive to amplitude fluctuations of the signal reflected from the target.

In direction finders with equisignal direction created by periodically changing the antenna pattern, and, in particular, with a scanning beam, a random change in the amplitudes of the signal reflected from the target is perceived as a random change in the angular position of the target.

The principle of target selection in terms of range and speed depends on the nature of the radiation, which can be pulsed or continuous.

With pulsed radiation, target selection is carried out, as a rule, in range with the help of strobe pulses that open the receiver of the homing head at the moment the signals from the target arrive.

Rice. 5. Radar semi-active homing system

With continuous radiation, it is relatively easy to select the target by speed. The Doppler effect is used to track the target in speed. The value of the Doppler frequency shift of the signal reflected from the target is proportional to the relative velocity of the missile approach to the target during active homing, and to the radial component of the target velocity relative to the ground-based irradiation radar and the relative velocity of the missile to the target during semi-active homing. To isolate the Doppler shift during semi-active homing on a missile after target acquisition, it is necessary to compare the signals received by the irradiation radar and the homing head. The tuned filters of the receiver of the homing head pass into the angle change channel only those signals that are reflected from the target moving at a certain speed relative to the missile.

As applied to the Hawk-type anti-aircraft missile system, it includes a target irradiation (illumination) radar, a semi-active homing head, an anti-aircraft guided missile, etc.

The task of the target irradiation (illumination) radar is to continuously irradiate the target with electromagnetic energy. The radar station uses directional radiation of electromagnetic energy, which requires continuous tracking of the target in angular coordinates. To solve other problems, target tracking in range and speed is also provided. Thus, the ground part of the semi-active homing system is a radar station with continuous automatic target tracking.

The semi-active homing head is mounted on the rocket and includes a coordinator and a calculating device. It provides capture and tracking of the target in terms of angular coordinates, range or speed (or in all four coordinates), determination of the mismatch parameter and generation of control commands.

An autopilot is installed on board an anti-aircraft guided missile, which solves the same tasks as in command telecontrol systems.

The composition of an anti-aircraft missile system using a homing system or a combined control system also includes equipment and apparatus for preparing and launching missiles, pointing the radiation radar at the target, etc.

Infrared (thermal) homing systems for anti-aircraft missiles use a wavelength range, usually from 1 to 5 microns. In this range is the maximum thermal radiation of most air targets. The possibility of using a passive homing method is the main advantage of infrared systems. The system is made simpler, and its action is hidden from the enemy. Before launching a missile defense system, it is more difficult for an air enemy to detect such a system, and after launching a missile, it is more difficult to create active interference with it. The receiver of the infrared system can be structurally made much simpler than the receiver of the radar seeker.

The disadvantage of the system is the dependence of the range on meteorological conditions. Thermal rays are strongly attenuated in rain, in fog, in clouds. The range of such a system also depends on the orientation of the target relative to the energy receiver (on the direction of reception). The radiant flux from the nozzle of an aircraft jet engine significantly exceeds the radiant flux from its fuselage.

Thermal homing heads are widely used in short-range and short-range anti-aircraft missiles.

Light homing systems are based on the fact that most aerial targets reflect sunlight or moonlight much stronger than their surrounding background. This allows you to select a target against a given background and direct an anti-aircraft missile at it with the help of a seeker that receives a signal in the visible range of the electromagnetic wave spectrum.

The advantages of this system are determined by the possibility of using a passive homing method. Its significant drawback is the strong dependence of the range on meteorological conditions. Under good meteorological conditions, light homing is also impossible in directions where the light of the Sun and Moon enters the field of view of the goniometer of the system.

Combined control refers to the combination of different control systems when aiming a missile at a target. In anti-aircraft missile systems, it is used when firing at long ranges to obtain the required accuracy of aiming a missile at a target with allowable mass values ​​of missiles. The following sequential combinations of control systems are possible: telecontrol of the first type and homing, telecontrol of the first and second type, autonomous system and homing.

The use of combined control makes it necessary to solve such problems as pairing trajectories when switching from one control method to another, ensuring that the target is captured by the missile's homing head in flight, using the same on-board equipment devices at various stages of control, etc.

At the moment of transition to homing (telecontrol of the second type), the target must be within the radiation pattern of the receiving antenna of the GOS, the width of which usually does not exceed 5-10 °. In addition, guidance of tracking systems should be carried out: GOS in range, in speed or in range and speed, if target selection is provided for given coordinates to increase the resolution and noise immunity of the control system.

Guidance of the GOS on the target can be carried out in the following ways: by commands transmitted to the missile from the point of guidance; the inclusion of an autonomous automatic search for the GOS target by angular coordinates, range and frequency; a combination of preliminary command guidance of the GOS on the target with the subsequent search for the target.

Each of the first two methods has its advantages and significant disadvantages. The task of ensuring reliable guidance of the seeker to the target during the flight of the missile to the target is quite complex and may require the use of a third method. Preliminary guidance of the seeker allows you to narrow the range of the search for the target.

With a combination of telecontrol systems of the first and second types, after the start of operation of the onboard radio direction finder, the device for generating commands of the ground guidance point can receive information simultaneously from two sources: a target and missile tracking station and an onboard radio direction finder. Based on the comparison of the generated commands according to the data of each source, it seems possible to solve the problem of conjugation of trajectories, as well as to increase the accuracy of pointing the missile at the target (reduce random error components by choosing a source, weighing the variances of the generated commands). This way of combining control systems is called binary control.

Combined control is used in cases where the required characteristics of the air defense system cannot be achieved using only one control system.

Autonomous control systems are those in which flight control signals are generated on board the rocket in accordance with a predetermined (before launch) program. During the flight of a missile, the autonomous control system does not receive any information from the target and the control point. In a number of cases, such a system is used in the initial section of the rocket's flight path to bring it into a given region of space.

Elements of missile control systems

A guided missile is an unmanned aircraft with a jet engine designed to destroy air targets. All onboard devices are located on the rocket airframe.

Glider - the supporting structure of the rocket, which consists of a body, fixed and movable aerodynamic surfaces. The body of the airframe is usually cylindrical in shape with a conical (spherical, ogive) head.

The aerodynamic surfaces of the airframe serve to create lift and control forces. These include wings, stabilizers (fixed surfaces), rudders. According to the mutual arrangement of the rudders and fixed aerodynamic surfaces, the following aerodynamic schemes of missiles are distinguished: normal, "tailless", "duck", "rotary wing".

Rice. b. Layout diagram of a hypothetical guided missile:

1 - rocket body; 2 - non-contact fuse; 3 - rudders; 4 - warhead; 5 - tanks for fuel components; b - autopilot; 7 - control equipment; 8 - wings; 9 - sources of onboard power supply; 10 - sustainer stage rocket engine; 11 - launch stage rocket engine; 12 - stabilizers.

Rice. 7. Aerodynamic schemes of guided missiles:

1 - normal; 2 - "tailless"; 3 - "duck"; 4 - "rotary wing".

Guided missile engines are divided into two groups: rocket and air-breathing.

A rocket engine is an engine that uses the fuel that is completely on board the rocket. It does not require the intake of oxygen from the environment for its operation. According to the type of fuel, rocket engines are divided into solid propellant rocket engines (SRM) and liquid propellant rocket engines (LRE). Rocket gunpowder and mixed solid propellant are used as fuel in solid propellant rocket engines, which are poured and pressed directly into the engine combustion chamber.

Air-jet engines (WFD) are engines in which oxygen taken from the surrounding air serves as an oxidizing agent. As a result, only fuel is contained on board the rocket, which makes it possible to increase the fuel supply. The disadvantage of VRD is the impossibility of their operation in rarefied layers of the atmosphere. They can be used on aircraft at flight altitudes up to 35-40 km.

The autopilot (AP) is designed to stabilize the angular movements of the rocket relative to the center of mass. In addition, the AP is an integral part of the missile flight control system and controls the position of the center of mass itself in space in accordance with the control commands. In the first case, the autopilot plays the role of a rocket stabilization system, in the second, it plays the role of an element of the control system.

To stabilize the rocket in the longitudinal, azimuth planes and when moving relative to the longitudinal axis of the rocket (roll), three independent stabilization channels are used: in pitch, heading and roll.

The onboard flight control equipment of the rocket is an integral part of the control system. Its structure is determined by the adopted control system implemented in the anti-aircraft and aircraft missile control complex.

In command telecontrol systems, devices are installed on board the rocket that make up the receiving path of the command radio control link (KRU). They include an antenna and a radio signal receiver for control commands, a command selector, and a demodulator.

The combat equipment of anti-aircraft and aircraft missiles is a combination of a warhead and a fuse.

The warhead has a warhead, a detonator and a body. According to the principle of action, warheads can be fragmentation and high-explosive fragmentation. Some types of missiles can also be equipped with nuclear warheads (for example, in the Nike-Hercules air defense system).

The striking elements of the warhead are both fragments and finished elements placed on the surface of the hull. High-explosive (crushing) explosives (TNT, mixtures of TNT with RDX, etc.) are used as combat charges.

Missile fuses can be non-contact and contact. Proximity fuses, depending on the location of the energy source used to trigger the fuse, are divided into active, semi-active and passive. In addition, proximity fuses are divided into electrostatic, optical, acoustic, radio fuses. In foreign samples of missiles, radio and optical fuses are more often used. In some cases, the optical and radio fuses work simultaneously, which increases the reliability of undermining the warhead in conditions of electronic suppression.

The operation of the radio fuse is based on the principles of radar. Therefore, such a fuse is a miniature radar that generates a detonation signal at a certain position of the target in the fuse antenna beam.

According to the device and principles of operation, radio fuses can be pulsed, Doppler and frequency.

Rice. 8. Structural diagram of a pulsed radio fuse

In a pulse fuse, the transmitter generates high-frequency pulses of short duration, emitted by the antenna in the direction of the target. The antenna beam is coordinated in space with the area of ​​expansion of the fragments of the warhead. When the target is in the beam, the reflected signals are received by the antenna, pass through the receiving device and enter the coincidence cascade, where a strobe pulse is applied. If they coincide, a signal is given to detonate the detonator of the warhead. The duration of the strobe pulses determines the range of possible firing ranges of the fuse.

Doppler fuses often operate in the continuous beam mode. The signals reflected from the target and received by the antenna are fed to the mixer, where the Doppler frequency is extracted.

At given speeds, the Doppler frequency signals pass through the filter and are fed to the amplifier. At a certain amplitude of current fluctuations of this frequency, an undermining signal is generated.

Contact fuses can be electric and percussion. They are used in short-range missiles with high firing accuracy, which ensures the detonation of the warhead in the event of a direct missile hit.

To increase the probability of hitting a target with fragments of the warhead, measures are being taken to coordinate the areas of operation of the fuse and the expansion of fragments. With good coordination, the region of fragmentation, as a rule, coincides in space with the region where the target is located.

The S-125 low-altitude mobile anti-aircraft missile system is designed to engage air targets at low and medium altitudes. The complex is all-weather, capable of hitting targets on a collision course and in pursuit. The characteristics of the missile and the warhead make it possible to fire at both ground and surface radar-observed targets.
Testing of the complex began in 1961, at the same time it was adopted by the air defense forces of the Soviet Army. At the same time, shipborne versions of the M1 "Wave" and M1 "Wave M" complex were developed for the Navy. Soon, the new anti-aircraft missile system was tested in real combat conditions - in Vietnam and Egypt.

The 5V24 two-stage solid-propellant rocket is made according to the normal aerodynamic configuration. The rocket has a solid-propellant starting engine, the time of which before dropping is 2.6 seconds. The sustainer engine is also solid-propellant, it starts after the end of the starting one and runs for 18.7 seconds. If the missile does not hit the target, it will self-destruct.

A missile guidance station is used to detect and track air targets. The maximum target detection range is 110 km. The complex uses launchers 5P71 or 5P73. One 5P71 launcher accommodates 2 anti-aircraft guided missiles, 5P73 launcher - 4 anti-aircraft guided missiles. Loading time - 1 minute. For transportation and loading of missiles, a transport and loading vehicle based on a ZIL-131 or ZIL-157 off-road truck is used. For preliminary detection of targets, radar stations P-15 and P-18 are used.

The main combat test of the complex took place in 1973, when Syria and Egypt used a large number of complexes against Israeli aircraft. The S-125 anti-aircraft missile system was used by the Armed Forces of Iraq, Syria, Libya, and Angola. Eight S-125 divisions were used to defend Belgrade in repelling NATO air raids against Yugoslavia. The S-125 low-altitude missile system is in service with the armies and navies of the CIS countries, as well as many foreign countries, remaining today a formidable air defense weapon.

Anti-aircraft missile system S-75M "Desna"

The S-75 anti-aircraft missile system is designed to destroy air targets at medium and high altitudes, on a collision course and in pursuit. The transportable (towed) complex was developed to cover important administrative, political and industrial facilities, military units and formations. The S-75 is single-channel for a target and three-channel for a missile, that is, it is simultaneously capable of tracking one target and directing up to three missiles at it.

During its existence, the S-75 air defense system has been modernized many times. In 1957, a simplified version of the SA - 75 "Dvina" was adopted, in 1959 - the C - 75M "Desna". The next modification was the S-75M Volkhov complex. Rockets of all serial modifications are two-stage, made according to the normal aerodynamic configuration. The first stage (starting accelerator) is solid propellant, it is a powder jet engine running for 4.5s.
The second stage has a liquid-propellant jet engine running on a combination of kerosene and nitric acid. Warhead - high-explosive fragmentation weighing 196 kg. The maximum target engagement range for the S-75 Desna is 34 km. The maximum speed of the fired target towards - 1500 km / h.

The S-75 anti-aircraft missile system is in service with the anti-aircraft missile division, which includes a missile guidance station, an interface cabin with an automated control system, six launchers, power supply facilities, and airspace reconnaissance facilities. Typically, launchers are located in a circle at a distance of 60 - 100 meters around the missile guidance station. Elements of the complex can be located in open areas, in trenches or stationary concrete shelters. The combat crew of the complex consists of 4 people - one officer and three escort operators in angular coordinates.

In the USSR, the C-75's baptism of fire took place on May 1, 1960, when a high-altitude American reconnaissance aircraft U-2 Lockheed, piloted by CIA pilot Powers, was shot down near Sverdlovsk. The result of this use of the S-75 was that the United States stopped its reconnaissance flights over the territory of the USSR and thereby lost an important source of strategic intelligence information. Under the name "Volga" (export name), the complex was supplied to many countries of the world. Deliveries were made to Angola, Algeria, Hungary, Vietnam, Egypt, India, Iraq, Iran, China, Cuba, Libya and other countries.

Anti-aircraft missile system S - 300P

The S-300P anti-aircraft missile system was put into service in 1979 and is designed to defend the most important administrative, industrial and military facilities from air attacks, including non-strategic ballistic missiles. It replaced the S-25 Berkut air defense systems located around Moscow, as well as the S-125 and S-75 systems. The S-300P anti-aircraft missile system was in service with anti-aircraft missile regiments and brigades of the country's air defense forces.

In the S-300P complex, towed launchers with a vertical launch of 4 missiles and transport vehicles designed to transport missiles were used. In the S - 300P complex, the V - 500K rocket was originally used. The rocket has a solid propellant engine, at launch it was thrown out of the transport and launch container with the help of squibs to a height of 25 m, and then the rocket engine was started. The maximum range of destruction of an aerodynamic target was 47 km.

The S-300P complex includes: a radar for illumination and guidance, which aims up to 12 missiles at 6 simultaneously tracked targets, a low-altitude detector, up to 3 launch complexes, each of which can have up to 4 launchers, and each launcher - up to 4 missiles of type B - 500K or B - 500R.

During 1980 - 1990. The S-300 anti-aircraft missile system has undergone a number of deep upgrades that have significantly increased its combat capabilities.

Anti-aircraft missile system S-200V

The S-200 long-range anti-aircraft missile system is designed to combat modern and advanced air targets: early warning and control aircraft, high-altitude high-speed reconnaissance aircraft, jammers and other manned and unmanned air attack weapons in conditions of intense radio countermeasures. The system is all-weather and can be operated in various climatic conditions.

During its existence, the S-200 air defense system was modernized many times: in 1970 it entered service with the S-200V (Vega) and in 1975 with the S-200D (Dubna). In the Soviet Union, the S - 200 was part of the anti-aircraft missile brigades or regiments of mixed composition, which also included S - 125 divisions. The S - 200 anti-aircraft guided missile was two-stage. The first stage consists of four solid propellant boosters. The sustainer stage is equipped with a two-component liquid rocket engine. The warhead is high-explosive fragmentation. The missile has a semi-active homing head.

The S-200 air defense system includes: control and target designation point K-9M; diesel - power plants; target illumination radar, which is a high-potential continuous-wave radar. It provides target tracking and generates information for missile launch. The complex has six launchers, which are located around the target illumination radar. They carry out storage, pre-launch preparation and launch of anti-aircraft missiles. For the early detection of air targets, the complex is equipped with an aerial reconnaissance radar of type P - 35.

S-200 air defense systems, served by Soviet crews, were supplied to Syria and used in combat operations in the winter of 1982/1983 against Israeli and American aircraft. The complex was delivered to India, Iran, North Korea, Libya, North Korea and other countries.

In the Russian army, there are two types of short-range anti-aircraft missile systems: "Tor" and "Pantsir-S". The complexes have the same purpose: the destruction of low-flying cruise missiles and UAVs.

ZRPK "Pantsir-S" armed with 12 anti-aircraft guided missiles and four automatic guns (two twin 30-mm anti-aircraft guns). The complex is capable of detecting targets at ranges up to 30 km. The missile range is 20 kilometers. The maximum height of the defeat is 15 km. The minimum height of the defeat is 0-5 meters. The complex ensures the destruction of targets by missiles at speeds up to 1000 m/s. Anti-aircraft guns ensure the destruction of subsonic targets. ZRPK is capable of covering industrial facilities, combined arms formations, long-range anti-aircraft missile systems, airfields and ports. Radar station ZPRK millimeter range with an active phased antenna array (AFAR).

SAM "Tor"- short-range anti-aircraft missile system. The complex is designed to destroy targets flying at ultra-low altitudes. The complex effectively fights cruise missiles, drones and stealth aircraft. "Thor" is armed with 8 guided anti-aircraft missiles.

Short-range anti-aircraft missile systems are indispensable, as they intercept the most dangerous and difficult targets - cruise missiles, anti-radar missiles and unmanned vehicles.

Pantsir-SM

Evaluation of the highest efficiency of short-range complexes

IN modern war high-precision weapons play a crucial role. Short-range air defense systems structurally should be in each battalion, regiment, brigade and division. At the level of platoons and companies, MANPADS should be used. A motorized rifle battalion must structurally have at least one Pantsir-S or Tor. This will significantly increase security during the battalion's mobile maneuver. Missile brigades must have the largest number short-range anti-aircraft systems.

"Pantsir-S" is able to cover the launchers of tactical missiles while being a few kilometers from them. This will allow tactical missiles to be launched while still being safe from return fire. Let's take the Iskander operational-tactical missile system as an example. The maximum range of its ballistic missiles reaches 500 km. Without the cover of the Pantsir-S air defense missile system, the tactical missile system risks being destroyed by enemy aircraft. The radars of modern aircraft are capable of detecting a missile launch. In general, missile launches are clearly visible in the radar and infrared range. So it is likely that the launch will be clearly visible even for hundreds of kilometers.

Having fixed the missile launch, enemy aircraft will fly to the launch site. The cruising speed of a supersonic aircraft is 700-1000 km/h. Also, the aircraft is able to turn on the afterburner mode and accelerate to speeds greater than 1500 km / h. Overcoming a distance of 50-300 km for an aircraft in a short time (several minutes) will not be difficult.

The operational-tactical complex will not have time to prepare for the marching position and leave for a distance of at least more than 5-10 km. The time of folding and deployment of the Iskander OTRK is several minutes. Travel 10 km top speed about 60 km it will take about 8 min. Although it will be impossible to accelerate to 60 km on the battlefield, the average speed will be 10-30 km, given the unevenness of the road, mud, etc. As a result, the OTRK will not have any chance to go far so as not to fall under an airstrike.

For this reason, the Pantsir-S ZPRK would be able to protect the launchers from air missile attacks as well as their air bombs. By the way, a very small number of anti-aircraft missile systems are capable of intercepting air bombs. These include Pantsir-S.

AGM-65 "Meiverik"

AGM-65 "Meiverik" against short-range air defense systems

The range of the NATO tactical air missile "Maverick" (eng. Meiverik) is up to 30 km. The speed of the rocket is subsonic. The missile attacks the target by gliding towards it. Our anti-aircraft cannon-missile system is capable of detecting a missile launch at ranges up to 30 km (taking into account the millimeter range of the Pantsir-S radar and the lack of stealth protection of the Maverick missile) and will be able to attack it already from 20 km (maximum launch range ZPRK missiles). At a distance of 3 to 20 km, an aircraft missile will be an excellent target for an anti-aircraft complex.

From 3000 m, automatic guns 2A38 will begin to fire at the rocket. Automatic guns have a caliber of 30 mm and are designed to destroy subsonic targets, such as the Maverick missile. The high density of fire (several thousand rounds per minute) will destroy the target with a high degree of probability.

SAM "Tor-M1"

If the Iskander OTRK had covered the Tor, then the situation would have been somewhat different. Firstly, the radar of the complex has a centimeter range, which somewhat reduces the ability to detect targets. Secondly, the radar, unlike Pantsir-S, does not have an active antenna array, which also worsens the detection of small targets. The air defense system would have noticed an aircraft missile at ranges up to 8-20 km. From a range of 15 km to 0.5 km, the Thor could effectively fire at the Maverick missile (the effective firing range is approximate, based on the performance characteristics of the radar and its ability to fire targets with a similar effective dispersion area).

According to the results of a comparison of the Pantsir-S air defense missile system and the Tor air defense system, the first one is somewhat superior to its competitor. The main advantages: the presence of an AFAR-radar, a millimeter-range radar and rocket and cannon weapons, which have certain advantages over rocket weapons (rocket and cannon weapons allow you to fire at much more targets due to the fact that guns are additional weapons that can be used when the missiles run out).

If we compare the capabilities of the two systems to combat supersonic targets, then they are approximately equal. Pantsir-S will not be able to use its cannons (they only intercept subsonic targets).

Pantsir-S1 fires

The advantage of "Pantsir-S" - automatic guns

A significant advantage of the Pantsir-S ZPRK is that its automatic guns, if necessary, are capable of firing at ground targets. The guns can hit enemy manpower, lightly armored and unarmored targets. Also, given the very high density of fire and a decent range (approximately the same as for air targets), the ZPRK is able to fire at the calculation of the ATGM (portable anti-tank missile system), protecting itself and the protected launchers of operational-tactical missiles.

Conventional heavy machine guns mounted on tanks and small-caliber automatic cannons of infantry fighting vehicles do not have such a huge speed and density of fire, because of this they usually have little chance of firing at an ATGM crew from ranges of more than 500 m and as a result are often destroyed in such "duels". Also, "Pantsir-S" is able to fire at an enemy tank, damaging its external devices, a cannon and knocking down a caterpillar. Also, the ZPRK is almost guaranteed to destroy any lightly armored vehicles that are not equipped with long-range anti-tank guided missiles (ATGM) in the confrontation.

"Thor" in terms of self-defense from ground equipment cannot offer anything, except for desperate attempts to launch a guided anti-aircraft missile at an attacking target (purely theoretically possible, in fact I heard only one case during the War in South Ossetia, a Russian small rocket ship Mirage launched an anti-aircraft missile of the Osa-M complex into an attacking Georgian boat, after which a fire started on it, in general, anyone who is interested can see it on the Internet).

Pantsir-S1, automatic guns

Options for covering armored vehicles and their fire support

ZPRK "Pantsir-S" can cover advancing tanks and infantry fighting vehicles at a safe distance (3-10 km) behind armored vehicles. Moreover, such a range will make it possible to intercept aircraft missiles, helicopters, UAVs at a safe distance from advancing tanks and infantry fighting vehicles (5-10 km).

One ZPRK "Shell-S" will be able to provide protection for a tank company (12 tanks) within a radius of 15-20 km. On the one hand, this will allow dispersing tanks over a large area (one ZPRK will still cover from air attacks), on the other hand, a significant number of Pantsir-S ZPRKs will not be needed to protect a tank company. Also, the Pantsir-S radar with an active phased antenna array will make it possible to detect targets up to 30 km (10 km before the maximum range of destruction) and inform the crews of armored vehicles about an upcoming or possible attack. Tankers will be able to set up an aerosol smoke screen that makes it difficult to target in the infrared, radar and optical range.

It will also be possible to try to hide vehicles behind any hill, shelter, turn the tank with its frontal part (the most protected) towards the attacking air target. It is also possible to try to shoot down an enemy aircraft or low-speed aircraft with a guided anti-tank missile on your own, or to fire at them with a heavy machine gun. Also, the ZPRK will be able to give target designation to other anti-aircraft systems that have a large range of destruction or are closer to the target. ZPRK "Pantsir-S" is also capable of supporting tanks and infantry fighting vehicles with fire from automatic cannons. Probably in the "duel" between the BMP and the ZPRK, the latter will come out the winner due to much faster-firing barrels.

/Alexander Rastegin/