RU2690958C1 - Antiaircraft missile complex - Google Patents

Abstract

FIELD: radar ranging.

SUBSTANCE: invention relates to air defense systems, in particular, to radar stations for detecting and tracking anti-aircraft systems of the near frontier. Anti-aircraft missile system is fitted with a platform for the installation of a target detection station (TDS) with swinging and rotating parts, a self-contained azimuthal rotation drive of the TDS, stops of swinging and rotating parts of platform with control, monitoring and diagnostics units. Space survey speed is controlled. Positions of the TDS antenna bed are controlled and monitored. Controlling supply currents and voltages in real-time mode. Documenting and storing information on state of TDS.

EFFECT: higher combat efficiency and reliability of the complex; operational characteristics are improved.

4 cl, 1 dwg

Description

The invention relates to the field of weapons in particular to anti-aircraft missile systems and can be used in the air defense forces (air defense), in the ground forces and the navy to organize the defense of troops and military facilities from the destruction of enemy air attack weapons.

Known anti-aircraft missile system RBS 23 BAMSE, designed to cover important objects and troops from air strikes in all weather conditions. The complex has a modular design, each of the combat modules is located on a separate trailer. The module with the warhead and the module with the radar are located on separate chassis. The complex’s radar detects targets at ranges up to 100 km.

However, placing modules on different carriers leads to the fact that the minimum tactical unit capable of independently solving combat missions is a battery consisting of a command post and at least 2 ... 4 combat modules. This significantly reduces the efficiency of the complex, its maintenance, operation and use. And also this complex does not provide effective combat work in motion.

Known anti-aircraft missile system, described in the patent RU 2321818, adopted by the authors as a prototype. This anti-aircraft missile system contains a tower with pointing drives, a radar target detection (SOC), a computing system, one of the outputs of which is connected to the output of the SOC; Launcher corners and turret lug generation unit.

The complex described in the prototype ensures high mobility and efficiency of the complex with massive air strikes.

However, at the same time, the described solution does not provide control of the space review modes with the necessary stabilization of the SOS antenna pattern in a given azimuthal direction, and in the implemented system there is no monitoring of SOC and protection against real-time voltage overload while preserving the information.

The task of the invention is to improve the combat effectiveness of the complex by controlling the speed of review of the SOC, controlling the position of SOC, increasing the reliability of the complex by controlling the supply currents and voltages in real time, increasing operational characteristics due to the possibility of documenting and storing information on the SOC.

The technical result is achieved by an anti-aircraft missile system containing a tower with pointing drives, a radar target detection system, a computing system, one of the outputs of which is connected to the output of a target detection system; the unit for generating the angles of the launchers of the launchers and the turret, is that the target detection system is placed on a platform consisting of connected hingedly fixed, swinging and rotating parts, the fixed part is fixed on the outside of the tower and connected to the swinging and rotating hydraulic cylinders and the system electrical cables; at the same time, on the swinging part of the platform there is a coagulation-deployment drive, a position sensor of the swinging part and two stoppers of the swinging part; and on the rotating part of the platform there is installed an electric actuator of azimuthal rotation and a rotating contact device connected to the SOTS antenna sheet, while the rotating part of the platform is equipped with a rotation angle sensor and a stopper of the rotating part; also introduced a control unit for rotating the SOC, connected by inputs to the sensors of the rotation angle and the computing system, and the output to the electric actuator of the azimuthal rotation of the SOC and the stopper of the rotating part; a control unit for hydraulic cylinders is introduced, which is connected by an input with a sensor for the position of the swinging part of the platform, and the output is driven by the hydraulic cylinders and with the inputs of the stoppers of the swinging part; a switching unit and diagnostics of supply voltages and currents were introduced with supply voltage monitoring sensors and contactless current monitoring sensors and with a device comparing incoming voltages with nominal, connected to the complex power supply system inputs, and outputs to the SOC and platform; a processing and monitoring unit with a non-volatile memory storage device is also introduced. The rotor electric motor is used as an electric drive for azimuthal rotation. At the same time, the control units and the processing and control unit with a storage device are combined on a single printed circuit board, and the processing and control unit with a storage device with a non-volatile memory has a technological output on the external SOC panel.

The proposed technical solution is illustrated graphic material. FIG. 1 shows a functional diagram of an anti-aircraft missile system, where the following notation is used:

1 - tower and launchers with pointing drives;

2 - computer system (VS);

3 - block generation of the corners of the lapel of the tower (BVU);

4 - radar target detection (SOC);

5 - platform with fixed, rotating and swinging parts (PVC);

6 - rotating contact device (VKU);

7 - electric drive azimuthal rotation (EPAS);

8 - position angle sensor of the rotating part (DVR);

9 - stopper of the rotating part (CB);

10 - drive coagulation - deployment (RPS);

11 - the swing position sensor (DICK);

12 - stopper of the swinging part (SC);

13 is a rotation control unit (CCU);

14 - control unit hydraulic cylinders (BUG);

15 - processing and control unit with a storage device (BC with memory);

16 - switching unit and diagnostics (BKD).

The composition of PVK 5 includes swinging and rotating parts, as well as a fixed part for securing SOC 4 on PVC 5 and the PVC 5 itself on the tower. The swinging part of the platform using the RPS 10 performs the folding and unfolding of SOC 4 and the exit to the rotation mode in no more than 90 s. The rotating part of the platform using the EPAS 7 rotates the SOC 4 at a speed of up to 250%, while the developed torque is up to 1000 N m. This allows the implementation of the tower rotation compensation algorithm, i.e. while rotating the tower, SOC 4 retains its speed and direction of rotation, or the current angle in the stabilized coordinate system.

PVC 5 is designed to install and mount SOC 4 as part of an anti-aircraft missile complex, folding SOC 2 into its initial position and deploying it into combat, rotating the SOC 4 antenna web at a given speed and turning the SOC SOC 4 lattice back to given angles combat position, providing electrical transmission of signals and supply voltages to the rotating part of the SOC 4.

The composition of the rotating part of the PVK includes:

- VKU 6;

- EPA 7;

- DUW 8;

- NE 9.

The composition of the rocking part of the PCC includes:

- PSR 10;

- DPK11;

- SC 12.

SV is a single stopper, which provides locking of the rotating part of SOC, when transferred to the initial state.

SK are two stoppers - left and right, responsible for locking the AKP, when it is in extreme positions.

The control of the PVK 5 operation, diagnostics, supply of supply voltages and their control is carried out by the operation of the rotation control unit 13, the hydraulic cylinder control unit 14, the processing and control unit with the storage device 15 and the switching and diagnostics unit 16.

PSR 10 on the commands of the control unit of hydraulic cylinders 14 includes electric motors that pressurize two hydraulic cylinders, which ensure deployment of the rotating part of SOC 4 when switching to the firing position, and its collapsing when switching to the stopping position. When the system reaches the extreme position, the DDC 11 is triggered by closing the corresponding limit switch, which signals in the BUG about the need to remove the command for the folding or unfolding of the drive and lock the SOC 4.

The EPAS 7 operates according to the commands of the rotation control unit 13 to set a given rotational speed in accordance with the space review mode. When the SOC 4 is operating in the sector mode with electronic scanning of the space, the commands of the rotation control unit provide the EPAV 7 antenna pattern of the SOC 4 at the given azimuth in the earth coordinate system.

Through ICS 6, by means of rings and current collectors, supply voltages and exchange signals between SOC 4, interfacing system blocks and anti-aircraft missile system systems are transmitted to the antenna SOC signal 4.

The processing unit and the control with a storage device 15 is designed to provide on and off SOC 4 on commands from the sun 2.

The switching unit and diagnostics of the supply voltage 16 performs the function of switching the power supplied from the power supply system of the anti-aircraft complex, monitoring the supply voltages and consumption currents of the PVC 5 and SOC 4 systems, ensuring the protection of PVC 5 and SOC 4 from overloads on the power supply.

The control unit hydraulic cylinders 14 provides control of the RPS.

The control unit rotation 13 provides the issuance of commands for the rotation of the STC 5.

The work of the proposed anti-aircraft missile system is as follows. From the power supply system of the carrier, the supply voltage of 27 V, 380 V 50 Hz and 220 V 400 Hz is supplied to the inputs of the switching and diagnostics unit. Then, from aircraft 2 of the anti-aircraft missile complex, the inputs to the switching and diagnostics unit 16 and the processing and monitoring unit with the storage device 15 receive a command to turn on the SOC 4. This command closes the corresponding electrical circuits and the current flows to the voltage and current sensors, where in real mode they are compared with nominal values, with positive results of the comparison, power is supplied to PVC 5 and SOC 4. Voltages and currents are monitored constantly and protection is ensured in case of non-compliance with nominal values tons of PVK 4 and SOC 5 overloads or emergency shutdown of systems is performed, opening the corresponding electrical circuits and returning information about the system status via the communication channels to the BC 2. At the same time, the processing and control unit with the storage device 15 broadcasts through serial communication channels to PVC 5 and SOC 5 commands from Sun 2 and back; monitors their execution and records information in non-volatile memory in real time.

Upon receipt of the command from the sun 2 to transfer the SOC 4 from the traveling state to the initial control unit of hydraulic cylinders 14 interrogates DNA 11, made in the form of limit switches, generates and issues control codes and relay turn-on signals to the SGP 10 for translation

SOC 4 in a firing position. The left and right ICs 12 are disconnected. When the SOC antenna 4 reaches its extreme position, the IC 12 closes in the extreme positions of the swinging part of the platform. Closes the limit switch PSR 10 in the position of "antenna canvas deployed." At the same time, CB 9 is closed and keeps the SOC antenna wire 4 in a fixed position until the next commands are received.

Upon receipt of the assignment of space review mode for SOC 2 by SC 2, the rotation control unit 13 forms a command to open CB 9, and also generates and issues corresponding control codes to the EPAL 7, specifying the rotational speed of the SOC signal 4 and corners of the cuff; monitoring the result with the help of a remote memory 8. In the case of a tower movement, the unit allows, together with the EPAS 7, to provide stabilization of the rotational speed of the SOC antenna channel 4 or hold it at a given azimuth. Simultaneously with the review mode on SOC 4, job assignments are issued. Antenna canvas SOC 4 performs electrical scanning of the space with the issuance of radar information on the detected targets via exchange channels through the ICS 6 to the aircraft 2 of the complex. Sun 2 of the complex decides on further work on the detected targets and assigns tasks to them for precise tracking and / or conducting combat work. In parallel, the SOC 4 operation can be carried out in the same review mode, or it can be assigned another one, regardless of the operations performed, by other tasks of the complex.

On command from the aircraft 2 to transition to the initial state, the processing and control unit with the storage device 15 generates and, through the CCU 13, commands the EPA 7 to set the zero position of the SOC channel 4, closes the CB 9. The CCU 13 polls the remote memory 8 and transmits the corresponding information in the processing and control unit with a storage device 15. Where does the command come from in BUG 14 to roll up SOC 4? The operations corresponding to the deployment are performed only in the reverse order. BUG 14 receives information that the “antenna canvas is minimized” limit switch is closed, and reports this information to the processing and control unit with the storage device 15. It issues to the VS 2 a ready-to-power-off signal, and when the station turn-off signal is removed from the aircraft 2 removes power from all systems. After removing power from all systems of the complex, it is possible to perform operations on saving the recorded information to a memory device on the work carried out on an external personal computer using a process cable.

The turret and launchers with pointing drives 1, BC 2, RBO 3, SOC 4, as well as other units and systems of the anti-aircraft missile system are known systems with executions and connections as in the complex adopted for the prototype.

The proposed technical solution enhances the combat effectiveness of the complex by controlling the speed of viewing the space, controlling and controlling the position of the SOS antenna pattern; increases the reliability of the complex due to the ability to control the supply currents and voltages in real time; improves operational characteristics due to the possibility of documenting and storing information on the status of SOC.

Claims (4)

1. An anti-aircraft missile system containing a tower with pointing drives, a radar target detection (SOC), a computing system, one of the outputs of which is connected to the output of SOC; a unit for generating corners of the flap of launchers and a tower, characterized in that the SOC is located on a platform consisting of connected hingedly fixed, swinging and rotating parts, the fixed part is fixed on the outer side of the tower and connected to the swinging and rotating part of hydraulic cylinders and an electric cable system; on the swinging part of the platform there is a folding-unfolding drive, a position sensor of the swinging part and two stoppers of the swinging part; an electric actuator of azimuthal rotation and a rotating contact device are installed on the rotating part of the platform; the rotating part of the platform is equipped with a rotation angle sensor and a stopper of the rotating part; A SOS rotation control unit is introduced, which is connected by inputs with rotation angle sensors and a computing system, and the output is electrically driven azimuthal rotation of the SOC and a stopper of the rotating part; a control unit for hydraulic cylinders is introduced, which is connected by an input with a sensor for the position of the swinging part of the platform, and the output is connected with the drive of hydraulic cylinders and the inputs of the stoppers of the swinging part; a switching unit and diagnostics of supply voltages and currents were introduced with supply voltage monitoring sensors and contactless current monitoring sensors and with a device comparing incoming voltages with nominal, connected to the complex power supply system inputs, and outputs to the SOC and platform; A processing and control unit with a non-volatile memory storage unit is introduced. 2. Anti-aircraft missile system under item 1, characterized in that a rotary electric motor is used as an electric drive for azimuthal rotation. 3. Anti-aircraft missile system under item 1, characterized in that the control units and the processing and control unit with a storage device combined on a single printed circuit board. 4. Anti-aircraft missile system under item 1, characterized in that the processing and control unit with a storage device has a technological output on the external panel SOC.

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