RU65202U1 - FIGHTING MACHINE - Google Patents

Abstract

The utility model relates to the field of military equipment and can be used in the construction of short-range anti-aircraft installations with cannon-rocket weapons. A useful model solves the problem of increasing the combat effectiveness of BM, by ensuring the use of missile weapons at night and in difficult weather conditions, pointing several missiles at one target, implementing the principle of "shot and forgot" for a quick change of position after the launch of missiles. The technical result is achieved by the fact that in a combat vehicle containing a turret with cannon and missile weapons, a target tracking radar, a BM control panel, a BM digital computer system, the output of the BM control panel is connected to the first input of the BM digital computer system, the first output of which the control signal is connected to the input of the target tracking radar, the output of which is connected to the second input of the BM digital computer system by signals from the elevation, azimuth and range signals; SAM aratura, control and communication unit, guidance platforms (PN) right and left, PN control units right and left, universal launcher modules (MUP) right and left, while the second output of the BM digital computer system is connected to the input by the readiness for firing signal SAM control panel, the third and fourth outputs by control signals of elevation guidance are connected to the inputs of the guidance platforms right and left through the first inputs of control units of the left right MO, respectively, the first and second outputs of the control panel according to the control signals of the shooting modes of the SAM, they are connected to the inputs of the guidance platforms right and left through the second inputs of the corresponding control units of the PN, the third output by the prelaunch signal of the SAM is connected to the input of the control and communication unit, the first and second outputs of which are triggered by the “start” signal connected to the inputs of the universal launcher modules of the right and left, respectively, the mechanical inputs of which are connected to the mechanical outputs of the guidance platforms of the right and left, respectively. 2 ill.

Description

The utility model relates to the field of military equipment and can be used in the construction of short-range anti-aircraft installations with cannon-rocket weapons.

A device for controlling the armament of an anti-aircraft complex with combined missile and cannon weapons according to patent RU No. 2191974 [1], comprising a main tower mounted on the housing of the anti-aircraft complex with the possibility of rotation about a vertical axis, rocket and cannon armament mounted for rotation around a horizontal axis . At the same time, the anti-aircraft complex is equipped with a rotary platform mounted on the main tower with the possibility of rotation around a vertical axis. Missile weapons are mounted on a turntable, and cannons on the main tower.

However, this device is characterized by some drawbacks: the presence of two independent guidance platforms for cannon and missile weapons implies a complication of software that generates control signals for the missile weapons platform for firing missiles and the guidance platform for cannon weapons to guide guns at an anticipated point, with constant tracking of the changing coordinates of this point as the air target moves. Accordingly, the computing means of the anti-aircraft complex, forming the guidance signals of weapon platforms, should be subject to increased requirements for speed and productivity. Additionally, the presence of two independent guidance drives significantly complicates the anti-aircraft system and reduces its reliability and maintainability.

Known anti-aircraft missile-cannon fighting vehicle (BM) according to patent RU No. 2156943 [2], containing a turret installation with cannon and rocket weapons, with a radar station (radar) for detecting targets, radar tracking targets cm-band with an antenna column and guidance drives and stabilization, with optical-electronic equipment for sighting an anti-aircraft guided missile (SAM), consisting of a coordinate pick-up device and a missile coordinate allocation unit, and a digital computer system, as well as a mm-range radar transponder installed missiles, mm-range radar sighting channel,

consisting of capture and output antennas in azimuth and elevation, the main antenna, a beam-forming circuit, a two-channel high-frequency receiver mounted on an antenna column, and a two-channel low-frequency receiver located in a tower installation. At the same time, the mm-range radar transponder is connected by inputs of capture and output antennas in azimuth and elevation angle and the input of the main antenna by transmitting high-frequency signals, the antenna outputs are connected to the inputs of the beam-forming circuit, the outputs of which are connected to the azimuth and elevation inputs of a two-channel high-frequency receiver, the outputs of which respectively connected to the azimuthal and elevation inputs of a two-channel low-frequency receiver, consisting of analog parts connected in series, analog ovo-digital converter and a digital control device, which outputs are connected to the control inputs of azimuth and elevation, the beamforming scheme and a two-high frequency receiver antennas capture and output, and the output of the two-channel low-frequency receiver connected to the input of a digital computer system BM.

During combat missile weapons, after target detection and target designation of the radar of detection, the target is captured for auto tracking of the sm-range radar. When a target enters a missile weapon strike zone, a missile launcher is launched, after which the missile launcher falls into the directional patterns of capture and output antennas in azimuth and elevation, as well as into the field of view of the optoelectronic equipment for sighting the missile launchers, which begin to independently monitor the missile . In this case, the coordinates of missiles are continuously fed into the digital computing system BM. Depending on weather conditions, the guidance mode is selected by optoelectronic equipment or mm-band radar channel. The optoelectronic system is selected in clear daylight conditions. It is advisable to choose a radar channel in night and difficult weather conditions. The BM digital computing system determines the angular deviations of the missiles in relation to the line of sight of the target and generates the corresponding control commands, transmitting them to the cm-band tracking radar, where they are encoded and then transmitted onboard the missiles. The SAM system processes control commands and carries out the output of the SAM on the line of sight and hold on it until the target is hit.

However, this device also has drawbacks: the SAM response signal generated in the mm range is characterized by a large attenuation in the atmosphere and, especially, in difficult weather conditions (snow, rain, fog) [3]. The result is a sharp decrease in the range of guided missiles and the accuracy of its guidance, and

accordingly, the combat effectiveness of the anti-aircraft complex is reduced. At the same time, the mm-range guidance channel is subject to deliberate electronic interference, as a result of which the signals of the SAM defendant can be completely suppressed, which will lead to a complete failure of the guidance [4].

Closest to the technical nature of the claimed is BM according to patent No. 2244242 [5], containing a tower installation with cannon and rocket weapons and radar target detection. On the electrical functional diagram of the prototype (figure 1) are also included in the well-known BM, radar 1 target tracking with antenna 2, drive 3 guidance and stabilization of the antenna, block 4 correction drive guidance and stabilization of the antenna; optical guidance channel 5 with an optical sight (OD) 6, command sensor 7, drive 8 guidance and stabilization of the OP, block 9 converting control signals and the adder 10; control panel 11 BM, digital computing system 12 BM, block 13 calculating the speed of changing the angular coordinates of the target and the generation of tracking signals, device 14 for generating the “Unload” command.

This BM implements two target tracking modes: radar and optical with the ability to switch from one mode to another.

The radar mode is fully automatic and is carried out by the target tracking radar in three coordinates: azimuth β, elevation angle ε and range D. The radar mode is designed to carry out cannon weapon guidance.

The optical mode is designed to control missile weapons and is semi-automatic. This mode provides guidance on the target OP gunner only in the angular coordinates β, ε.

Famous combat vehicle operates as follows. A radar for detecting targets (not shown) performs a circular overview of the space and when a “strange” mark (target) appears on the screen of the circular viewing indicator, the radar operator combines a target designation marker with a mark from the target, while signals proportional to the azimuth are received in the 12 BM digital computer system β and the range D to the target, which then go to the antenna guidance and stabilization drive 3 and the range finder of the target tracking radar 1, after which the target tracking radar searches the target by elevation angle ε and takes the target for auto tracking three coordinates β, ε, D. In this case, the target coordinates β, ε, D enter the 12 BM digital computer system. When the target enters the zone of destruction of SAMs from the control panel 11 BM to the device 14 of the formation of the command "Unloading" receives the command "P". Coordinates

tracking target β, ε from the target tracking radar 1 are sent to block 13 for calculating the rates of change in the angular coordinates of the target and generating tracking signals. From block 13, the control signal enters the device 14 of the formation of the “Unloading” command, and high-speed tracking signals are fed through the adder 10 to the input of the drive 8 for guidance and stabilization of the optical drive, which processes them, thereby automatically tracking the optical 6 for a speedy change in the angular coordinates of the target.

After visual detection of the target by the gunner from the remote control 11 BM control is issued the command "OP", which is fed to the input device 14 of the formation of the command "Unloading". If there is a control signal at the inputs of the device 14 of the formation of the “Unloading” command and the “OP” and “P” commands, the “Unloading” command is generated, which enters the guidance and stabilization drive correction unit 4 to the drive structure switch, which operates and connects the unit 4 to drive 3 guidance and stabilization of the antenna, while changing the structure of the drive guidance and stabilization of the antenna, increasing the smoothness and accuracy of tracking, by narrowing the bandwidth of the tracking system. The “Unloading” command is also sent to the control signal conversion unit 9 to the control speed switch, which is activated and connects the unit 9 to the command sensor 7, which reduces the rate of change of control signals from the command sensor. In the adder 10, the control signals are summed with the tracking signals and then the total signal is fed to the input of the drive 8 guidance and stabilization of the optical sight. Further participation of the gunner in the guidance process is reduced to visual observation of the tracking of OP 6 for the target, followed by radar 1 and, if necessary, the adjustment of tracking by smoothly combining the target with the OP brand. Thus, improved accuracy characteristics of target tracking by the gunner are provided, which are necessary for aiming at the target with SAM.

However, this device is characterized by disadvantages: tracking a target with a gunner with an optical sight is possible only in clear daylight conditions, the use of rocket weapons at night or in difficult weather conditions (snow, rain, fog) is impossible; The method of semi-automatic guidance provides for continuous tracking of the target by the gunner from the moment the missile is launched until the target is hit, during this time the combat vehicle must remain in position, maneuvering in conditions of guided missile defense is prohibited [6], while combat work for other targets or aiming at one target multiple rockets is impossible. In conditions of a massive air raid, this leads to increased

vulnerabilities of a combat vehicle.

The objective of the utility model is to increase the combat effectiveness of BM, by ensuring the use of missile weapons at night and in difficult weather conditions, pointing several SAMs on one target, implementing the principle of “shot and forgot” to quickly change position after the launch of SAMs.

The specified technical result is achieved by the fact that in a combat vehicle containing a turret with cannon and missile weapons radar target tracking, BM control panel, BM digital computer system, while the output of the BM control panel is connected to the first input of the BM digital computer system, the first output of which the control signal is connected to the input of the target tracking radar, the output of which is tracked along the elevation angle ε, azimuth β and range D is connected to the second input of the BM digital computer system , a control panel for SAM equipment, a control and communication unit, guidance platforms (PN) right and left, control panels for PN right and left, universal launcher modules (MUL) right and left, the second output of the BM digital computer system by the readiness signal for firing is connected to the input of the control panel of the SAM system, the third and fourth outputs are guided by guidance signals for elevation angle e connected to the inputs of the guidance platforms right and left through the first inputs of the control units of the left and right MVs, respectively, the first and second outputs of the control panel of the missile launcher equipment are connected to the inputs of the guidance platforms right and left through the second inputs of the corresponding control units of the missile launcher by signals from the control modes of the missile launcher, the third output is connected to the input of the control and communication unit, the first and second outputs of which at the “start” signal, they are connected to the inputs of the universal launcher modules of the right and left, respectively, the mechanical inputs of which are connected to the mechanical outputs of the guidance platforms of the right and left howling accordingly.

The utility model is illustrated by the drawing shown in figure 2, which shows an electrical functional diagram of a combat vehicle.

The combat vehicle contains a turret with cannon and missile weapons (not shown), a target tracking radar 1, a BM control panel 11, a BM digital computer system 12, a missile control system 15, a control and communications unit 16, a guidance platform 17, left 17 and left 18 , control units PN right 19 and left 20, universal launcher modules right 21 and left 22. Moreover, the output of the BM control panel 11 is connected to the first input of the digital computing

BM system 12, the first output of which is connected via a control signal to the input of the target tracking radar 1, the output of which is tracked by the elevation angle ε, azimuth β and range D connected to the second input of the BM digital computer system 12. The second output of the digital computing system 12 BM on the signal of readiness for firing is connected to the input of the remote control 15 of the equipment for SAM control, the third and fourth outputs on control signals for guidance in elevation e are connected to the inputs of the guidance platforms right 17 and left 18 through the first inputs of blocks 19, 20 control the right and left MO, respectively, the first and second outputs of the remote control 15 of the equipment for SAM; according to the control signals of the shooting modes of the SAM, are connected to the inputs of the guidance platforms right 17 and left 18 through the second inputs correspond monitored control units 19, 20, the third output, according to the prelaunch signal of the SAM, is connected to the input of the control and communication unit 16, the first and second outputs of which are connected to the inputs of the universal launch modules of the right 21 and left 22, respectively, whose mechanical inputs are connected to the mechanical outputs of the guidance platforms right 17 and left 18, respectively.

The combat vehicle operates as follows. The radar station (radar) 1 tracking the target searches for targets in the sector or circular search mode, the parameters of which are set by the control signals of the digital computing system 12 BM. When the mark from the target appears on the screen of the all-round visibility indicator, the radar operator searches the target by elevation angle e and takes the target for auto tracking along three coordinates β, ε, D. Moreover, the coordinates of the target β, ε, D go to the 12 BM digital computer system , which calculates the trajectory of the target and determines the moment the target enters the affected area with cannon "Zone A" or missile "Zone P" weapons. The operator makes a choice of cannon or missile weapons. Combat work with cannon armament is carried out by pointing anti-aircraft guns at the anticipated point, the coordinates of which are calculated by a digital computer system 12 BM. When the target approaches the missile arsenal from the 12-BM digital computer system, the command 15 to control the SAM systems receives a command “before the target enters the launch zone for 5 seconds”. On the remote control 15 of the equipment for missiles, relevant information is displayed and when the operator makes a decision on the use of missile weapons to the control and communication unit 16, a command is sent to conduct prelaunch preparations for the missiles. The control and communication unit 16 selects the existing combat-ready missiles and generates a sequence of commands for pre-launch preparation of missiles.

After connecting the rocket's power circuits to the electric circuits of the combat vehicle, the rocket turns on, the homing head gyroscope (GOS) begins to spin, the nitrogen entering the rocket enters the microcooler, cooling the GOS photodetector, the liquid nitrogen phase accumulates for the rocket to fly. The time it takes the rocket to go to mode is no more than 5 seconds. If necessary, the operator can prelaunch several missiles.

At the same time, the BM digital computer system 12 generates guidance signals along the elevation angle ε that arrive at the PN control units on the right 19 and the left 20. The target is guided in the azimuthal plane β by turning the tower also by the signals (not shown) of the BM 12 digital computer system. The control units of the right side of the right 19 and the left 20 form the control signals for the power drives of the guidance platforms (PN) of the right 17 and the left 18, respectively, for guiding the guidance platforms to the target location to ensure the target is captured by the GSN missile defense.

The moment of entry of the target into the launch zone by the signals of the digital computing system 12 BM is indicated on the remote control 15 of the equipment of missiles Zona R ". After receiving this message, the operator can, depending on the tactical situation, launch a single, multiple or multiple launch on one or several targets.

The proposed technical solution is implemented in a new modification of the 2A6M4 self-propelled anti-aircraft gun (Shilka-M4). Currently, the 2A6M4 product has successfully passed preliminary (factory) tests. The structure of self-propelled anti-aircraft installation introduced a set of control equipment and launch modules "Sagittarius" 9C846, designed for single, sequential or multiple launch missiles from portable anti-aircraft systems (MANPADS) "Igla".

Literature

1. Patent RU No. 2191974. Published October 27, 2002

2. Patent RU No. 2156943. Published September 27, 2000

3. Barton D. Radar systems, translation from English. Ed. K.N. Trofimova. Military Publishing House, Moscow: 1967, 480 p., Ill.

4. Vakin S.A., Shustov L.N. Fundamentals of radio countermeasures and electronic intelligence. Soviet radio. - M .: 1968, 448 p., Ill.

5. Patent RU No. 224242. Published January 10, 2005 (prototype).

6. 2S6M1.00.00.000 IE. User's manual. Part 1. Combat work.

7. 9C846.00.00.000 RE. Manual. Set of control equipment and starting modules

Claims (1)

A combat vehicle (BM) containing a turret with cannon and missile weapons, a target tracking radar, a BM control panel, a BM digital computer system, while the output of the BM control panel is connected to the first input of the BM digital computer system, the first output of which is connected to the radar input tracking the target, the output of which according to tracking signals in elevation, azimuth and range is connected to the second input of the BM digital computer system, characterized in that an anti-aircraft control equipment control panel is introduced into it missile (SAM), control and communication unit, guidance platforms (PN) right and left, control panels for PN right and left, universal launcher modules (MUP) right and left, while the second output of the BM digital computer system is connected to the input of the control panel missile defense equipment, the third and fourth outputs are connected to the inputs of the guidance platforms right and left through the first inputs of the control units PN right and left, respectively, the first and second outputs of the control panel of the missile defense system are connected to the inputs of the guidance platforms right and left through the second inputs of the corresponding control units of the PN, the third output is connected to the input of the control and communication unit, the first and second outputs of which are connected to the inputs of the universal launcher modules of the right and left, respectively, the mechanical inputs of which are connected to the mechanical outputs of the guidance platforms of the right and left, respectively.