RU2208213C1 - Self-propelled antiaircraft rocket mount for detection, tracking and lighting of targets, guidance and launching of rockets of medium-range rocket complex - Google Patents

Abstract

FIELD: defense equipment, in particular, mobile antiaircraft complexes, applicable for organization of antiaircraft defense of troops and military objects against destruction by enemy means of air attack. SUBSTANCE: the self- propelled antiaircraft rocket mount has a phased aerial array, radar station, rotatable launcher with rockets and transducer of the angle of rotation, digital computer, gyroscopic system of measurement of the heading, bank and pitch angles, as well as the navigation, topographic survey and orientation system, use is also made of the system of comparison and storage of the angles of the gyroscopic system and the system of correction of time instability of the gyroscopic system of angles measurement. The output of the gyroscopic system is connected to the combined inputs of the system of comparison and storage and the system of time instability of the gyroscopic system. The navigation, topographic survey and orientation system is coupled respectively to the input of the gyroscopic system and to the second input of the comparison and storage system, the transducer of the rotary angle of the launcher is connected to the third input of the comparison and storage system, whose output via the system of correction of time instability of the gyroscopic system is connected to the central computer, whose output busbar is coupled to the phased aerial array. EFFECT: the self-propelled mount for detection, tracking, guidance and launching of rockets of the medium-range antiaircraft rocket complex provides for prolonged combat operation simultaneously against several perspective means of air attack, first of all against winged missiles flying at extreme low altitudes due to elimination of the time instability of the gyroscopic system of measurement of the heading, bank and pitch angles of the aerial array. 2 dwg

Description

 The proposed technical solution relates to the field of defense technology, in particular to mobile anti-aircraft missile systems (SAM), and can be used to organize air defense of troops and military installations from defeating enemy air attack weapons.

 In the structure of modern air defense (air defense), a radar station (RLS) is the main and almost the only source of information about the air situation of air attack weapons (IOS), and the tactical order of modern aviation, together with ballistic missiles and cruise missiles designed to break through air defense, necessarily provides fire suppression of air defense, since the radar provides control of the area of responsibility of air defense and the issuance of target designation by active-targeting radar systems - З K and fighter aircraft.

 A known air defense system (see Soldat und Technik, 1987, 4, p. 262), containing three modules, each of which is placed on a separate trailer, a three-coordinate radar for viewing, detecting and tracking targets, as well as an anti-aircraft missile control system (SAM) , a two-beam radar for target and missile tracking, a firing unit with missiles and an electron-optical system for automatically tracking missiles and targets.

 The presence of two parallel operating guidance systems allows the complex to simultaneously direct two missiles, however, placement on three trailers requires a large deployment time of the complex, which increases the reaction time and reduces the effect of its use.

 Known self-propelled anti-aircraft missile system (SAM) "Cube" (see Equipment and weapons, 1999, 5-6, p. 28-34), consisting of a self-propelled launcher with missiles, a self-propelled installation of reconnaissance and guidance, containing a radar station ( Radar) detection of air targets and target designation and radar tracking of targets and lighting, means of target recognition, navigation system, topographic location and orientation (SNTO), a radio telecode communication system with a launcher, a television optical sight (TOV), an autonomous power source, an anti-rise system nna and leveling. The complex is single-purpose and is located on several tracked vehicles.

 A mobile combat installation is known, equipped with a multi-barrel missile launcher (see patent DE 2356462 IPC F 41 G 07/00, 1976), comprising a radar, guidance and target designation system, calculation and control equipment, search and tracking antennas, and transmission of control commands to the missile as well as a television camera, a laser rangefinder and an infrared target tracking system.

 Known self-propelled combat vehicle short-range air defense systems (see patent RU 2121645 IPC F 41 H 07/00, 1998), comprising a self-propelled chassis with a cabin, an antenna-starting device rotating on a support bearing, consisting of a guidance system with an antenna, a target detection system with antenna and a starting device, in addition, the machine contains a shaft located in the antenna starting device.

 The specified technical solution provides a small range of destruction of the air enemy.

 Known SAM with PRGS SAM "HOCK" (see Wehrtechnik, 1977, 1-2), containing radar detection of air targets, fire control system, radar tracking and illumination and missiles with PRGS.

 Known SAM "Krotal" (see Foreign Military Review, 1999, 10, p. 2-5), containing radar detection, launcher with a vertical launch missiles.

 A VT-1 rocket is used for cold start, a feature of which is firing a rocket with a powder pressure accumulator at a speed of 40 m / s, driven by a gas generator, then the main engine is launched, and the rocket is rotated using a separate rotary module controlled by an onboard by computer.

 Famous SAM "Patriot", located on several wheeled chassis (see Equipment and armament, 1992, 9-10, p. 38-39, V.V. Malikov, SAM "Patriot"), containing a multi-function radar with headlight, antenna group for suppression of side lobes, a block of transmitters, a block of receivers, a digital signal processing system, a digital control and synchronization computer system (DAC), an alien identification system, equipment for generating and transmitting control commands on board a missile under radio countermeasures, a gas turbine generator for power supply, p item management, communication, diagnostics system for monitoring the state of the elements of the complex. The complex requires a lot of deployment time.

The above analogues have one or another of the following main disadvantages:
- Separate deployment of radar for detection, tracking, illumination of targets for guiding missiles and a launcher with missiles on several military air defense systems;
- the lack of the possibility of combat work simultaneously for several purposes.

 The closest in technical essence and the achieved result is a self-propelled gun mount (SOU) 9А3 10-M1 SAM "BUK-M1 GS1.641.006 TO (see Military Parade, 1997, 1, p. 28-32, V.V. Matyashev, SAM "BUK-M1; Equipment and armament, 1999, 5-6, p. 35-41), containing the radar for the detection, tracking and illumination of targets in the X-band, as well as a rotary launcher with missiles, and the radar is located on a self-propelled launcher and consists of an electromechanical antenna, a transceiver system, a digital computer control system I and synchronization, a synthesizer for generating letter frequency signals, a friend-or-foe recognition system, equipment for generating and transmitting radio correction (control) commands on board a rocket, in addition, roll and pitch angle sensors, as well as a navigation system, are located on the launcher, topographic location and orientation, telecode communication system and operational-command communication.

 For accurate measurement of target coordinates, missile guidance and stabilization of the antenna beam in space when the launcher is rotated in the horizontal plane, if there are rolls, the angle of rotation of the launcher in the horizontal plane and gyroscopic angular velocity sensors on the moving mirror of the antenna are used.

 The disadvantage of this technical solution is the impossibility of combat work simultaneously for several purposes.

 The technical result of the proposed solution is the creation of a self-propelled firing system for detecting, tracking, guiding and launching medium-range anti-aircraft missile systems, ensuring long-term combat operation simultaneously on several promising air attack means, primarily cruise missiles flying at extremely low altitudes by eliminating temporary instability of the gyroscopic system for measuring heading angles, roll and pitch of the antenna array.

 The technical result is achieved by the fact that in a self-propelled firing system (SDA) containing a phased antenna array, a radar station, a rotary launcher with missiles and a rotation angle sensor, a digital computer system, a gyroscopic system for measuring heading angles, roll and pitch, as well as a navigation system , topographic reference and orientation, a series-connected system for comparing and remembering the angles of the gyroscopic system, a system for correcting temporary instability, and the output are gyroscopic the system is connected to the combined inputs of the comparison and storage system and the correction system for temporary instability of the gyroscopic system, and the navigation, topographic and orientation system is connected respectively to the input of the gyroscopic system and to the second input of the comparison and storage system, in addition, the output of the launcher rotation angle sensor is connected to the third input of the comparison and storage system, the output of which is connected to a centrally located system of correction of temporary instability of the gyroscopic system th computing system, the output bus of which is connected to a phased antenna array.

 The “departures” of the gyroscopic system are periodically corrected (reduced to zero), which ensures the required accuracy of measuring coordinates simultaneously accompanied by several targets for guiding and launching missiles.

 Comparison of the proposed solution with well-known technical solutions shows that it has a new set of essential features that can successfully achieve the goal.

 The essence of the proposed technical solution will be clear from the following description and the attached graphic material.

In FIG. 1 and 2 depict the structural and functional diagrams of a self-propelled firing system, on which the following devices and systems are indicated by numbers:
1 - phased array antenna PAR;
2 - radar radar station;
3 - digital computer system;
4 - launcher launcher;
5 - angle sensor;
6 - a navigation, topographic and orientation system;
7 - gyroscopic system;
8 - correction system;
9 - a system of comparison and memorization;
10 - communication bus;
11 - self-propelled chassis.

 A self-propelled firing installation for detecting, tracking and illuminating targets, guiding and launching missiles of an anti-aircraft missile system of medium range contains a phased antenna array 1, a radar station 2, a digital computer system 3, a rotary launcher 4 with missiles and a rotation angle sensor of the launcher 5, and on the rotary launcher 4 also houses a gyroscopic system for measuring heading angles, roll and pitch 7, which is necessary to stabilize the beam of the phased antenna array 1, and the bottom of the chassis 11 houses a navigation, topographic and orientation system 6, a correction system 8, and a comparison and memory system 9.

 Self-propelled firing installation works as follows.

After setting the SDA to the combat position from the navigation and orientation system 6 into the gyroscopic system 7, the comparison and memorization system 9, the value of the SDA heading angle (the angle between the longitudinal axis of the SDA and the north direction) is entered. The heading angle of the SDA is used in the gyroscopic system 7 as initial conditions, and in the process of further work, the gyroscopic system gives out the course value taking into account this angle. In the system of comparison and storage, the heading angle of the SDA is used in correction sessions to calculate the angle ψ of the _calculation .

 The signals from the output of the PAR 1 are issued to the input of the radar 2, which carries out the detection, capture, tracking and illumination of several targets simultaneously.

 After amplification and conversion, target signals are issued from the output of the radar 2 to the first input of the DAC 3, in which the control signals of the launcher 4 are generated to generate lead angles and the formation of missile guidance signals. The generated signals are issued from the output of the DAC 3 to the input of the PU 4.

A gyroscopic system for measuring heading angles, roll and pitch 7 is installed on control unit 4, which is necessary to stabilize the headlight 1 in space when turning the control unit 4 in the horizontal plane and in the presence of rolls, and a rotation angle sensor is installed 5. Measured course angle values from the gyroscopic output angular measurement system coordinate ψ _MOD 7 and the measured values from the sensor rotation angles φ _PUizm PU 5 corresponding to the current position of the UE 4 are supplied to the inputs 1 and 3 of the reference system and storing _edited 9. The angle ψ is measured horizontally th plane, and the angle φ _ПУиз - in the plane of rotation of ПУ 4, determined by the roll angles. In correction sessions, which are carried out once every twenty to thirty minutes, the measured angles φ _{ПУizm are recalculated} into a horizontal plane and the course angle ψ is _calculated using the course angle of the SDA. To increase the accuracy of calculations performed averaging angles ψ and ψ _{calc ism.} After averaging, the difference Δ = ψ _ism -ψ _{calculation is calculated} . The angle Δ contains a component due to inaccurate adjustment of the sensors of the angle of rotation of the PU and the angle of the gyroscopic system, and a component determined by the "departures" of the gyroscopic system. In the very first correction session, when there are no "departures", the angle Δ is stored. From the difference between the stored angle Δ _zap and the current angle Δ, a correction correction δ = Δ _zap -Δ is determined. For the first correction session, the correction value will be zero, and for subsequent sessions, the correction will be equal to the value of "departure" at the time of the correction session. This correction value is stored and used in each step of inputting information from the sensors of the gyroscopic system to determine the true heading value. In the correction system 8, the true value of the course ψ _truth = ψ _ism + δ is calculated. This value is issued to the second input of the DAC 3 and then used in all calculations. The interval between correction sessions is chosen so that the compensated value of the course “departures” does not exceed the required accuracy of the course angle measurement.

 Thus, hardware “departures” (temporary instability) of the gyroscopic system 7 are excluded and long-term combat operation of the SDA is ensured.

Claims (1)

 Self-propelled firing system for detecting, tracking and illuminating targets, guiding and launching missiles of an anti-aircraft missile system of medium range, containing a phased antenna array, a radar station, a rotary launcher with missiles and an angle sensor, a digital computer system, a gyroscopic system for measuring heading angles, and pitch required for electronic stabilization of the phased array beam, as well as a navigation, topographic and orientation system, characterized in that in a system for comparing and remembering the angles of the gyroscopic system and a system for correcting the temporary instability of the gyroscopic system for measuring angles, while the output of the gyroscopic system is connected to the combined inputs of the system for comparing and memorizing and the system for correcting the temporary instability of the gyroscopic system, the navigation, topographic, and orientation systems are connected respectively with the input gyroscopic system and with the second input of the comparison and storage system, the output of the angle sensor rotation of the launcher The novelty is connected to the third input of the comparison and memory system, the output of which through the system for correcting the temporary instability of the gyroscopic system is connected to the central computer system, the output bus of which is connected to the phased antenna array.

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