RU2453794C1 - Method to control high precision armament and complex of high precision armament - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: method is designed to control high precision armament equipped with launchers with ground-to-air guided missiles and a launcher with guided missiles to damage surface targets. When targets are detected and their coordinates are identified, their type is identified as air or surface, and a criterion of target type is generated. Target autotracking mode is switched on, addresses of guided missiles are generated, in which a criterion of target type is introduced. Missiles are distributed among targets, turnout angles are generated and transmitted to launchers corresponding to a target type. Using cyclograms identical for both types of missiles, their launch is prepared, and then they are launched. Missiles are located, and their coordinates are identified, commands of missile control are generated and sent to an appropriate type of rockets. To damage surface targets, a missile is taken to a zone of capture of a homing guidance head, the control is changed into a homing guidance mode, autonomous searching, recognition, capture and accompanying of a target are carried out with the help of a homing guidance head.

EFFECT: expansion of functional capabilities.

Description

The proposed group of inventions relates to military equipment, in particular to systems of guided weapons of combined use, solving the tasks of the anti-aircraft complex of the near boundary and long-range guided weapons to destroy ground targets, and can be used as for reliable air defense of the Ground Forces and stationary objects from massive air strikes attacks, especially from high-precision weapons, and to defeat single and group mobile and stationary ground, surface objectives, control centers, fire weapons and other important small targets.

A known method of controlling high-precision weapons equipped with launchers (launchers) with anti-aircraft guided missiles (UR), including the detection of air targets and the determination of their coordinates, is described in RF patent No. 2321818, publication 04/10/2008, cl. MKI F41H 11/02, F41G 7/20, F41A 23/42 / I /.

This method is implemented in an anti-aircraft missile-cannon complex containing launchers with guidance drives, anti-aircraft missile launchers on a launcher on a rotary base, a radar station for target detection (SOC), an optical-electronic system (ECO), a target tracking station and missiles (SSCR), the output of which is connected to the input of the ECO, the launch pad, the output of which is connected to the rocket at the time of its launch, the computer system, the input of which is connected to the output of the SOC, the first output is connected to the input of the launch pad, and the second output is connected to the input drives the rotary base pointing and PU, the computer system connected to the multi-channel rails and SSTSR exchange ECO and the zenith flight SD in connection with the lines connected SSTSR or ECO / 1 /.

These known methods of controlling high-precision weapons against air targets and the anti-aircraft missile and gun system for its implementation provide high combat effectiveness in hitting near-target air targets. However, this complex and the like are poorly protected from ground weapons. When performing military operations, there is an operational need to defeat both airborne and a wide range of ground targets: firearms, armored units, fortifications, administrative and industrial buildings, etc. But when working on defensive objects and armored vehicles, the armament of anti-aircraft missile systems of the near border has limitations on the firing range, mass and power of the warhead.

Therefore, the objective of the proposed group of inventions is to eliminate the above disadvantages, namely: together with existing capabilities, giving the complex high-precision weapons versatility due to an additional new feature - the ability to engage mobile and stationary, armored and unarmored ground targets, while being out of the reach of enemy artillery, and also the possibility of using the complex as a means of coastal defense.

In the method of controlling high-precision weapons equipped with launchers with anti-aircraft guided missiles, including the detection of air targets and determining their coordinates, the task is achieved in that, depending on the tactical task encountered, an additional missile defense system with missile defense is connected to the complex of high-precision weapons to destroy ground When detecting and determining the coordinates of targets, they identify their type as air or ground and produce a sign of the type of targets, go into auto mode tracking of targets, form SD addresses where they enter a sign of the type of targets, distribute SDs to targets, generate and transfer the lapel angles to the control panels corresponding to the type of target, prepare for their launch and launch using the same cyclograms for both types of SDs, determine the bearings and determine them coordinates, form SD control commands and transmit to the appropriate type of SD, to hit ground targets, carry the SD output to the homing zone (GOS), transfer the control to homing, offline search, recognition e, capture and tracking of the target with the help of the GOS.

In the complex of high-precision weapons, containing on a rotary base launchers with guidance drives, anti-aircraft guided missiles on the launcher, at the control point there are a radar station for detecting targets, an optoelectronic system, a tracking station for a target and a missile, the output of which is connected to the input of the ECO, a launch console, the output of which is connected to the rocket at the time of its launch, the computing system, the input of which is connected to the output of the SOC, the first output is with the input of the launch console, and the second output is connected to the inputs of the rotary base guidance drives and launchers, while the ECO and the SSR are connected to the computing system with multichannel bus exchanges, and anti-aircraft missile defense in flight are connected by communication lines with the SSR or OES, the task is achieved by the fact that it is equipped with a mobile platform on which launchers with guidance and SD drives are located to defeat ground targets equipped with GPS and a universal warhead of increased power in unified containers with detachable connections, through which SDs for the destruction of ground targets in preparation for launch and launch are connected to the output of the remote control ska, in this case, the guiding actuators of the launcher on the mobile platform are connected to the second output of the computing system, and the missile defense in flight to the homing zone is connected by communication lines to the SSRC or OES, and they provide the same control system as the anti-aircraft missile defense to remove the missile defense to the homing zone.

The technical result is ensured due to the fact that the complex of high-precision weapons is becoming more versatile and can hit in addition to almost the entire spectrum of air targets in the near zone and ground targets, including through the use of a radio command guidance system for SD, and over-the-horizon targets. To do this, in the method of controlling high-precision weapons, an additional missile launcher with SD is connected to destroy ground targets and both air and ground targets are detected, their type is identified as air or ground and they produce a sign of the type of targets, go into target auto tracking mode, form the addresses of SDs into which the sign of type of targets is entered, the SDs are distributed by goals, the lapel angles are generated and transmitted to the control panels corresponding to the type of target, according to the cyclograms identical for both types of SDs, they are produced under testing of their launch and launch, direction finding the bearings and determining their coordinates, generating control commands for the SD and transmitting them to the appropriate type of SD, for hitting ground targets, the SD will be output to the homing zone of the homing head, transferring control to homing mode, autonomous search, recognition, capture and tracking the target using GOS.

In the complex of high-precision weapons, the technical result is ensured, along with the existing means, by supplying the complex with a mobile platform that is equipped with launchers with guidance and SD drives to engage ground targets, equipped with GOS and a universal warhead of increased power in standardized containers with detachable joints for docking the SD with ground control equipment. A mobile platform with weapons can be part of a control point, but depending on the tactical tasks that may arise, it can be delivered to a control point, and the SDs are connected via detachable container connections to the launch console output. Guidance drives PU on a mobile platform connected to the second output of the computing system. SDs for hitting ground targets in flight to the homing zone are connected by communication lines to the SSCR or ECO. To control both types of missile defense use a radio command control system that allows the withdrawal of missile defense to hit ground targets at long ranges. SD for the destruction of ground targets provide the same with anti-aircraft SD control system output SD to the homing zone.

This technical solution is illustrated by graphic material.

The drawing shows a block diagram of a complex of precision weapons, with which they implement the proposed control method, where

1 - control point;

2 - optoelectronic system (ECO);

3 - target detection station (SOC);

4 - station tracking targets and missiles (SSSR);

5 - computing system;

6 - rotary base;

7 - launchers with guidance drives;

8 - anti-aircraft SD on the launcher;

9 - remote control;

10 - mobile platform;

11 - launchers with guidance drives on a mobile platform;

12 - SD for the destruction of ground targets on launchers.

At the control point (1), ECO (2), SOTs (3), SSSR (4), computer system (5), rotary base (tower) (6), launchers with guidance drives (7), anti-aircraft missiles at launchers (8 ), the launch pad (9) can be performed, for example, similarly to known systems with execution and connections as indicated in / 1 /, as well as in RF patent No. 2131577, publication June 10, 1999, cl. MKI F41G 7/20, 5/07 / 2 /.

OES (2) contains an infrared direction finder (IKP), a thermal imager with a teleautomatic device (TA), and guidance drives, the inputs of which are connected to the output of the teleautomaton, the first key whose control input is connected to the logical output of the IKP.

SSSR (4) contains an antenna made in the form of a phased array (PAR) with a beam control system (SUL), the output of which is connected to the inputs of the antenna, a receiver and a transmitter, the input and output of which are connected respectively to the output and input of the antenna, target coordinate allocation blocks and rockets, the inputs of which are connected to the output of the receiver, a processing and control unit containing five buffers, a first switch, a channel interval scheduler (CI), and a synchronizer-encoder, the signal output of which is connected to the transmitter input, and its two sync the outputs are respectively connected to the input of the CI scheduler and the sync input of the ICP, and the first output of the CI scheduler is connected to the first sync inputs of the synchronizer-encoder and the beam control system, with the sync inputs of the second, fourth, fifth buffers, the target coordinate allocation unit, the coordinate output of which is connected to the first input of the fourth a buffer whose output is connected to the first input of the control command generation unit and to the first coordinate input of the fifth buffer, the second coordinate input of which is connected to the TV output tomato, and the second output of the KI scheduler is connected to the second sync inputs of the synchronizer-encoder and the headlight beam control system, with the sync inputs of the first, third buffer, rocket coordinate allocation unit, the logical output of which is connected to the control inputs of the first switch and the first block of generating control commands, the coordinate output of the rocket coordinate allocation unit is connected to the first coordinate input of the third buffer, which is connected by the output to the first controlled input of the first switch, the output is cerned is connected to the second input of the first unit generating the control commands and the coordinate input of the first buffer, the coordinate and outputs the first and second buffers respectively connected to third and fourth inputs of the beam steering system and the second inputs of the third and fourth buffers.

The computing system (5) contains a target designation output unit, the input of which is connected to the SOC output (3), and the second output is connected to the TA input, the launcher angle generation unit of the launchers and the rotary base, the output of which is connected to the inputs of the rotary base guidance drives and launchers , a unit for calculating zone parameters, the output of which is connected to the input of the start-up console, the first and second blocks for generating control commands, while the inputs of the second block for generating control commands are connected to the TA output and the PCP outputs, W A second switch, the two inputs of which are connected to the first output of the target designation unit and the output of the fourth buffer, and its control input is connected to the logic output of the target coordinate allocation unit, while the output of the second switch is connected to the coordinate input of the second buffer, the ICP strobe start setup block, input which is connected to the output of the television, and the output through the first key is connected to the input of the ICP, the unit for forming the launcher of the rocket beam of the PAR, the sync input of which is connected to the first output of the KI anirovschika, and its coordinate input and output are connected respectively to the output of the fifth buffer and the second input of the first switch, the sixth buffer, the two coordinate inputs of which are connected to the outputs of the first and second blocks for generating control commands, and the output of the sixth buffer is connected to the signal input of the synchronizer-encoder moreover, the synchro input of the sixth buffer is connected to the second output of the KI scheduler, the first output of which is connected to the synchro inputs of the target designation unit, the launcher opening angle block generation unit, and a rotary base, a unit for calculating the zone parameters, while the control input of the channel interval planner is connected to the logic output of the target designation unit, the output of the fifth buffer is connected to the inputs of the blocks for generating the corners of the lapel of the rotary base and the launcher and calculate the zone parameters.

Depending on the arising tactical task, a mobile platform (10) is deployed, which contains launchers with guidance drives (11) and SD for hitting ground targets (12) with a universal warhead of increased power located in transport-launch containers (TPK). Data TPK with detachable connections for connecting SD to ground control equipment unified with TPK anti-aircraft missiles. From the output of the start-up panel (9) of the control point (1), the start-up cable, which is connected to the anti-aircraft missile launchers on the launcher (8), is also connected to the detachable connections of the launcher launcher for the destruction of ground targets (12), and the inputs of the guiding actuators on the mobile platform ( 10) - to the output of the block generating the corners of the lapel of the PU and the rotary base of the computing system (5).

At the control point (1), SOC (3) searches for, locates moving, motionless, ground or air targets, determines and transmits their coordinates, elevation angle, azimuth and range, respectively, to the target designation block of the computing system (5), which can also be obtained from an external target designation system, such as, for example, the coordinates of ground targets located beyond the horizon or terrain folds. Computing system (5), in accordance with the program laid down in it, identifies the type of target as air or ground, produces a sign of the type of targets, depending on which it generates a rocket address code, and in the ECO (2) and SSRC (4) it gives the coordinates of one selected for auto tracking and three goals. Blocks (2) and (4) upon receipt of target designation signals from block (5) carry out additional search of targets and their capture for tracking. SSSR (4) accompanies the target by the radar signal reflected from the target, and OES (2) by the thermal contrast of the target. In the computing system (5), the launcher angles of the launcher are determined and, from the second output of the launcher block (5) (from the exit of the launcher angles of the launcher launcher and the rotary base), are fed to the inputs of the launchers of the launcher (7, 11) corresponding to the missile address and the type of targets, and weapons is aimed at the aiming point of targets, followed by ECO (2) or SSCR (6). The address code of the SD from the first output of the computing system (5) (from the output of the zone parameter calculation unit) is input to the start of the remote control (9) so that when the SD is launched, its equipment will set the code for receiving control command messages corresponding to the address.

At the entrance of a target, accompanied by an ECO (2) or SSCR (4), a command from the launch panel (9) of a guided missile corresponding to the type of target is sent to the affected area. At the same time, the UR is fulfilling the start-up and start-up preparation sequence diagram, which is received from the start-up panel (9) via the start-up cable through the TPK connectors.

Launch the SD. The missile is direction-finding by the SSSR (4), its coordinates are determined and fed into the computer system (5), which for each missile generates control commands and transmits them to the SSRC (4), where they are encoded and transmitted via the communication line to the corresponding missile. At the same time, the ICP strobe is combined with the coordinates of the target, followed by the ECO (2). As a result of testing control commands, anti-aircraft missiles are combined with air targets, and missiles to hit ground targets provide the required range and the launch of missiles into the GPS capture zone. GOS, which can be thermal passive, radar, or combined, combining infrared and laser semi-active channels, performs an autonomous search, recognition, tracking of the target and gives a signal to "capture" the target. This signal transfers the missile control from the radio command mode to homing mode, which provides high-precision guidance of the missile at the target.

Mobile platform (10) can be performed, for example, on the basis of a transport-loading machine 73V6-E, Russia's Arms 2001-2002 Military Parade. M., 2001, p. 579/3 /. It can accommodate, for example, a second launcher with guidance drives (7) and missiles to hit ground targets, similar to block (8). Missiles for hitting ground targets (12) with a homing head and control equipment can be performed, for example, similarly to a missile, RF patent No. 2284444, publication 2006, September 27, cl. MKI F41G 7/00, F42В 15/01 / 4 /. TPK for SD can be performed, for example, similarly to the transport and launch container for missiles, RF patent No. 2296937, publication 04/10/2007, cl. MKI F41F 3/042 / 5 /.

Thus, the use of the proposed high-precision weapons control method and high-precision weapons complex allows for a short preparation time to connect to the ground control equipment with anti-aircraft missile defense a mobile platform with high-power missile defense for hitting ground targets, including over-the-horizon targets, and use flexible tactics of military operations due to fire maneuvers in range, direction, power of the warhead, and also provides defeat with high combat effectiveness not only for air targets near on the turn, but also moving and stationary, armored and unarmored ground targets, being outside the reach of enemy artillery fire, and the ability to use complex as a means of coastal defense.

Claims (2)

1. The method of controlling high-precision weapons equipped with launchers (launchers) with anti-aircraft guided missiles (UR), including the detection of air targets and the determination of their coordinates, characterized in that, depending on the tactical task, a complex of high-precision weapons is connected to the additionally introduced launcher with UR to destroy ground targets, when detecting and determining the coordinates of targets, they identify their type as air or ground and produce a sign of the type of targets, go into auto tracking mode th, form the addresses of the SD, into which the sign of the type of targets is entered, distribute the SD to the targets, develop and transfer the lapel angles to the control panels corresponding to the type of the target, prepare for their launch and launch using the same cyclograms for both types of SD, determine the bearings and determine their coordinates form the control commands of the missile defense and transmit it to the appropriate type of missile defense, to defeat ground targets, deploy the missile defense to the homing zone of the homing head (GOS), transfer the control to homing mode, autonomous search, recognition, capture and tracking Waiting for a goal using GOS. 2. A complex of high-precision weapons, containing on a rotary base launchers with guidance drives, anti-aircraft missile defense on launchers, at the control point - a radar target detection system (SOC), optoelectronic system (ECO), a target tracking system and missiles (SSSR), exit which is connected to the input of the ECO, the launch pad, the output of which is connected to the rocket at the time of its launch, the computer system, the input of which is connected to the output of the SOC, the first output is connected to the input of the launch pad, and the second output is connected to the inputs of the guidance drives of the rotary base and Launchers, while the multi-channel exchange buses OEC and SSR are connected to the computing system, and anti-aircraft missiles in flight are connected via communication lines to the SSSR or OES, characterized in that it is equipped with a mobile platform on which launchers with guidance and SD drives are located to destroy ground targets equipped with GOS and a universal warhead of increased power in unified containers with detachable connections, through which SDs for the destruction of ground targets in preparation for launch and launch are connected to the output of the launch console, while PU rows pointing in the mobile platform are connected to the second output computing system and the SD in flight zone to the homing communication lines are connected with SSTSR or ECO, and they provide the same with zenith SD SD output control system to homing zone.