RU179821U1 - AUTOMATED GUIDANCE AND FIRE CONTROL SYSTEM OF RUNNING INSTALLATION OF REACTIVE SYSTEM OF VOLUME FIRE (OPTIONS) - Google Patents

Abstract

The utility model relates to the field of military equipment, namely to the automated control of weapon systems as part of a combat vehicle with a multiple launch rocket launcher (MLRS), made on the base chassis of armored vehicles: protected vehicles, armored personnel carriers, infantry fighting vehicles, ground-based robotic shock The technical result of this utility model is to provide tactical autonomy of a combat vehicle with an MLRS launcher, improving the accuracy of missile launches missiles from an arbitrary starting position, increasing the situational awareness of the crew members of the armored vehicles. The technical result is achieved due to the fact that the automated guidance and fire control system (ASUNO) of the MLRS launcher according to the first embodiment contains two antennas, a navigation module, a strapdown inertial navigation system , panel computer, power supply, input-output unit, path measurement sensor, horizontal and vertical guidance drive, electric unit power, meteorological unit. The ASUNO launcher of the MLRS launcher according to the second embodiment further comprises a radar station for reconnaissance of ground targets and a power supply unit. The ASUNO launcher of the MLRS launcher according to the third embodiment further comprises an optical-electronic system.

Description

The utility model relates to the field of military equipment, namely to the automated control of weapon systems as part of a combat vehicle with a multiple launch rocket launcher (MLRS), made on the base chassis of armored vehicles: protected vehicles, armored personnel carriers, infantry fighting vehicles, ground-based robotic shock complexes.

Known automated guidance and fire control system (ASUNO) of a combat vehicle (BM) multiple launch rocket system (MLRS), described in the patent of the Russian Federation No. 2167380 from 03.08.1999.

The ASUNO of the MLRS combat vehicle contains a data receiving and transmitting unit and guidance drives, a guideless guidance system for the guide package, an autonomous orientation system, a navigation system, a calculation system for firing and flight mission data, navigation equipment for consumers of satellite navigation systems, a graphical display system for BM location and orientation .

Another variant of the ASUNO of the MLRS combat vehicle contains a data reception and transmission unit, a guideless package of guides, an autonomous orientation system, a navigation system, a calculation system for shooting targets and flight mission data, navigation equipment for consumers of satellite navigation systems, a graphical display system for BM location and orientation, graphic display system of mismatch of pointing angles.

The disadvantages of the ASUNO combat vehicle MLRS are:

- lack of meteorological support equipment in the MLRS combat vehicle, which does not allow the automatic measurement of meteorological parameters (temperature, pressure, wind speed and direction) necessary for ballistic missile launches of unguided rockets of the MLRS;

- reduced survivability of the combat vehicle due to its long presence at the starting position due to the lack of reconnaissance means (the crew of armored vehicles cannot detect and determine the coordinates of enemy targets);

- low accuracy of launches of rockets MLRS due to the use in ASUNO PU MLRS system of self-orienting gyro guidance (SSGKKU) built on the basis of dynamically adjustable gyroscopes that have dynamic errors, especially in non-stationary conditions, which leads to errors in measuring the angle of inclination, determining the course angle and true azimuth;

- a large preparation time for the opening of the fire (a large number of manual operations) caused by the need for leveling and hanging the MLRS launcher on jacks;

- large dispersion of rockets at volley launch. Known automated guidance control system and

the fire described on pages 60-61 in the monograph S.A. Mosienko (Ground robotic assault and reconnaissance systems for units of the Ground Forces. / Mosienko S.A. - M .: Sampoligraphist, 2014, 250 s). The well-known ASUNO contains a computing device, a system for calculating firing settings and flight mission data, a data receiving and transmitting unit, a high-precision navigation and topographic and geodetic system, guidance drives, a guide rail package and an inertial measuring unit.

The disadvantages described in the ASUNO monograph: the lack of meteorological support equipment, the lack of display equipment with an electronic navigation map and, as a result, the low situational awareness of the crew members of the armored vehicles when performing combat missions.

Another disadvantage of the described device is that it cannot be used for work in armored vehicles due to the lack of a path measurement sensor, which does not allow for a long time to work in conditions of the use of electronic suppression.

Known mobile rocket launcher "mini-grad", described in the patent for utility model of the Russian Federation No. 98559 from 10.20.2010, it includes the MLRS launcher, which is located on the base chassis of an off-road passenger car, while the launcher contains a horizontal and vertical guidance.

Disadvantages of the well-known mobile mini-grad rocket launcher: low accuracy of multiple rocket launcher launches due to the lack of automation for ballistic and navigation data input; large dispersion of rockets during multiple launch, as the dynamic loading of the MLRS launcher during rocket launches changes its position on the ground and causes elastic vibrations of the structure, often with increasing amplitude, as a result of which the guidance angles get lost; there is no situational awareness of the crew members of the combat vehicle.

The aforementioned mini-grad mobile rocket launcher is a prototype.

The technical result of this utility model is to provide tactical autonomy of a combat vehicle with an MLRS launcher, increase the accuracy of launches of unguided rockets from an arbitrary starting position, and increase situational awareness of armored crew members.

The technical result is achieved due to the fact that the automated guidance and fire control system of the launcher of a multiple launch rocket system according to the first embodiment comprises a vertical and horizontal guidance drive designed for vertical and horizontal guidance of the launcher angles, the first and second antennas, designed to receive navigation signals from satellite navigation systems GLONASS (Russia) and GPS (USA), a navigation module designed for automatic detection the coordinates of the location and directional angle (true course) of the object, a strapdown inertial navigation system designed to measure accelerations and angular velocities, rotation angles and inclinations of the launcher, a path measurement sensor designed to measure the distance traveled, an input-output unit, a panel computer, designed to calculate ballistic data, display reconnaissance and navigation data, the location of the object on an electronic navigation map, power supply, power supply unit a power unit, used for measuring meteorological parameters, wherein the first output of the first antenna is connected to the first input of the navigation module, the first output of the second antenna is connected to the second input of the navigation module, the third output of which is connected to the first input of the strapdown inertial navigation system, the second input is the output of which is connected to the first input-output of the panel computer, the second input-output of which is connected to the first input-output of the said input-output unit, the second the input-output of the said input-output unit is connected to the first input-output of the horizontal guidance drive, while the third input-output of the input-output block is connected to the first input-output of the vertical guidance drive, the first output of the path measurement sensor is connected to the third input of the said inertial navigation system, the meteorological unit is connected with the first input-output to the fourth input-output of the input-output unit, while the first output of the power supply is connected to the fourth input of the navigation module and the second input of the meteorological unit, the first output of the said power supply unit is connected to the third input of the panel computer, the second input of the path measurement sensor and the fourth input of the strapdown inertial navigation system.

In another embodiment, the automated guidance and fire control system of the launcher of a multiple launch rocket system additionally comprises a radar for reconnaissance of ground targets and a power supply module, wherein the first input-output of said radar for reconnaissance of ground targets is connected to the fifth input-output of the input-output unit, the first the output of said power supply module is connected to a second input of a ground-based reconnaissance radar.

In another embodiment, the automated guidance and fire control system of the launcher of a multiple launch rocket system further comprises an optical-electronic system for optical reconnaissance, the first input-output of the said optical-electronic system being connected to the sixth input-output of the input-output unit, the first the output of said power supply module is connected to the second input of the optoelectronic system.

The claimed utility model is illustrated by the following drawings: FIG. 1, which shows a block diagram of an automated guidance system and guidance fire launcher of a multiple launch rocket system according to the first embodiment; FIG. 2, which shows a block diagram of an automated guidance and fire control system of a launcher of a multiple launch rocket system according to the second embodiment; FIG. 3, which shows a block diagram of an automated guidance system and guidance fire launcher of a multiple launch rocket system according to the third embodiment; FIG. 4, which shows a photograph of the main elements of an automated guidance and fire control system for a launcher of a multiple launch rocket system according to the first embodiment; FIG. 5, which shows an installation option of elements of an automated guidance system and guidance fire launcher of a multiple launch rocket system on the base chassis of an infantry fighting vehicle (BMP-2).

Consider the structure and operation of an automated guidance system and guidance fire launcher rocket launcher for the first option.

As can be seen from the drawing of FIG. 1, an automated guidance and fire control system (ASUNO) launcher launcher (launcher) multiple launch rocket launcher (MLRS), contains a vertical guidance drive (PVN) 10 and a horizontal guidance drive (PGV) 9, designed for vertical and horizontal pointing angles PU ( not shown), the first antenna 2 and the second antenna 3, designed to receive navigation signals from the GLONASS and GPS satellite navigation systems. In addition, ASUNO contains a navigation module (NM) 4, designed to automatically determine the coordinates of the location and directional angle (true course) of armored vehicles, strapdown inertial navigation system (SINS) 5, designed to measure accelerations and angular velocities, rotation angles and inclination of the launcher . In addition to the fact that ASUNO 1 contains a path measurement sensor (DIP) 7, designed to measure the distance traveled, an input-output unit (BVV) 8, a panel computer (PC) 6, designed to calculate ballistic data, display reconnaissance and navigation data, location object on the electronic navigation chart, power supply, meteorological unit, designed to measure meteorological parameters, power supply unit. The ASUNO elements are interconnected so that the operation of all elements is ensured: the first output of the first antenna 2 is connected to the first input of the HM 4, the first output of the second antenna 3 is connected to the second input of the HM 4, the third output of which is connected to the first input of SINS 5, the second the input-output of which is connected to the first input-output of the PC 6, the second input-output of which is connected to the first input-output of the mentioned BVV 8, the second input-output of the mentioned BVV 8 is connected to the first input-output of PGN 9, while the third input-output BVV 8 is connected from the first PVN input-output 10, the first output of DIP 7 is connected to the third input of the mentioned SINS 5, the meteorological unit is connected to the fourth input-output of the BVV 8, the first output of the power supply is connected to the fourth input of the HM 4 and the second input of the meteorological unit , the first output of the mentioned power supply unit is connected to the third input of PC 6, the second input of DIP 7 and the fourth input of SINS 5.

ASUNO PU MLRS 1 according to the first embodiment works as follows.

Navigation signals from two SNA GLONASS and GPS (not shown in the drawing) are continuously fed to the first 2 and second antenna 3, placed strictly horizontally (not shown) in the base chassis of the armored vehicles. The distance between the first 2 and second 3 antennas should be at least 2000 mm, which will ensure accuracy in determining the course (direction angle) of at least 0.1 deg.

Further, the navigation data, through the connection connector (not shown in the drawing), is fed to the first and second inputs of NM 4. NM 4 automatically searches, captures, monitors the signals of the GLONASS / GPS SNS, and also calculates the navigation parameters of the armored vehicles (current coordinates , altitude, time) and determines the angles of spatial orientation. The basis for determining the true course of armored vehicles is the principle of relative determinations of the phase of the carrier frequency of the SNS GLONASS / GPS signals. To calculate the true heading, the phase differences of the carrier frequency between the first 2 and second 2 antennas installed on the chassis of the armored vehicle are determined.

The navigation data processed in NM 4 via the RS-232 interface is input to the BINS 5. The BINS 5 measures accelerations and angular velocities, rotation angles and tilt of the launcher. It should be noted that SINS 5 is installed on the MLRS launcher, which allows us to solve the problem of automatically recovering the angles of guidance of the launcher from launch to launch, thereby increasing the accuracy of missile launches, and reducing dispersion during launches in one gulp. In addition, SINS 5 together with DIP 7 and NM 4 solves the navigation problem in the absence of signals from the SNA. BINS 5 incorporates (not shown in the drawing) a computing unit, a unit of elements manufactured using the technology of microelectromechanical systems (MEMS): gyroscopes and accelerometers. Under the influence of external interference (not shown) electronic warfare (EW) on the first 2 and second antenna 3, NM 4, the computing unit (not shown) BINS 5 will receive data from DIP 7 and transmit odometric data to PC 6 to display the location of armored vehicles on an electronic navigation map (ENC). BINS 5 is connected to PC 6 via the RS-232 interface.

PC 6 has (not shown in the drawing) a computer and a display designed to display the ENC (not shown) of the combat geographic information system (GIS), which are necessary for situational awareness of the crew members of the armored vehicles. The display of PC 6 displays the following information (not shown in the drawing):

- current coordinates in a rectangular coordinate system (SK-42) or in a geographical coordinate system (WGS-84, SK-42, SK-95, PZ-90.02, PZ-90.11);

- the true course of armored vehicles (in degrees, degrees-minutes, degrees-minutes-seconds, radians, divisions of the goniometer);

- elevation angle (in degrees, degrees-minutes, degrees-minutes-seconds, radians, divisions of the goniometer);

- target designation angles (in degrees, degrees-minutes, degrees-minutes-seconds, radians, goniometer divisions);

- the difference between the values of the current angles and the values of the target designation angles (in degrees, degrees-minutes, degrees-minutes-seconds, radians, divisions of the goniometer);

- the location of the armored vehicles on the battlefield GIS ENC (with the installed operating system and special software.

PC 6 on the basis of navigation and meteorological data using special software (STR) calculates the firing settings and flight mission data (not shown) of rockets MLRS. The combat GIS (not shown in the drawing) displays the current location, direction of movement and orientation of the armored vehicle from the MLRS launcher to the ENC, the target’s location, the distance to it, and the direction to it from the current position, which provides the human operator with a choice of the starting position and indicates the direction of arrival to the starting position. At the starting position, PK 6, using the STR (not shown in the drawing), the launch settings and flight task data are calculated according to the coordinates of the aiming point and the current coordinates of the armored vehicle with the MLRS, in this case, the coordinates of the launch position, the launch pointing angles are calculated installation and transferring them to the STR "targetless launcher guidance" (not shown in the drawing).

Open source software "non-targeting guidance of the guide package" (not shown in the drawing) continuously determines the current orientation angles of the MLRS launcher, calculates their mismatches with the estimated guidance angles and transmits through the BVV 8 to the air defense 10 and PGN 9.

PVN 10 and PGN 9 move PU, reducing these mismatches. As a result, the launcher is aimed at the calculated angles to perform a salvo on the target. After a volley is fired by rockets, armored vehicles with an MLRS launcher either change the starting position, perform an anti-fire maneuver, or follow the technical position for loading and then to the starting position. In both cases, the cycle of functioning is repeated.

BVV 8 has the ability to connect armored vehicles for transmitting navigation data (not shown) to a typical intercom and switching equipment (ABC). AVSK allows, through communication equipment (not shown in the drawing) installed in armored vehicles, to transmit navigation data to an automated troop control system (not shown in the drawing).

DIP 7 is designed to reckon the distance traveled armored vehicles in off-road conditions (dirt, sand) and snow drifts (ice, snow). DIP 7 contains (not shown) a combined microwave transceiver and an integrated microwave transceiver in a metal casing. A bracket is used for mounting on armored vehicles (not shown in the drawing). The output from DIP 7 is transmitted via the RS-232 interface to SINS 5, where the calculation and delivery of the measured data to PC 6 takes place.

DIP 7, in another embodiment (not shown in the drawing) can be a typical odometer, widely used in all types of armored vehicles.

The meteorological block 11 is intended for meteorological support of rocket launches. Meteorological unit 11 allows automatic measurement of meteorological parameters (temperature, pressure, wind speed and direction) necessary for ballistic calculations of launches of unguided rockets of MLRS. One of the most important indicators of the effectiveness of the MLRS is the accuracy of missile launches. The main difficulty in this case is that most rockets of the MLRS are uncontrolled, i.e. after launch, a missile is subject to the destabilizing effect of wind gusts and changes in air density, and it is no longer possible to influence the trajectory of a missile during a flight. The influence of the atmosphere on the flight of unguided rockets MLRS can be divided into the following factors: the influence of wind (longitudinal and lateral component) and the influence of air density. A longitudinal wind changes the range of the missile, and a side wind displaces the missile in the direction. Air density determines the drag force, and consequently, changes the range of a missile (air density in ground artillery is taken into account through air temperature and ground pressure). The task of meteorological preparation during launches of unguided rockets of the MLRS is to determine deviations of meteorological conditions from normal (tabular), necessary for the calculation of installations for launches. It is believed that meteorological errors make the main contribution to missile launch missile launch errors. Failure to take into account meteorological parameters leads to a deterioration in the accuracy of launches of unguided rockets in range and direction, reaching a thousand meters or more.

Measured meteorological parameters (temperature, pressure, wind speed and direction) from meteorological unit 11 through BVV 8 enter PC 6, where the necessary calculation is performed for necessary corrections using the ballistic computer software (not shown). The meteorological preparation of MLRS rocket launches includes calculations in PC 6: deviations of the atmospheric ground pressure at the height of the starting position; ballistic deviation of air temperature within the full trajectory; ballistic deviation of air temperature within the active section of the trajectory; longitudinal and lateral components of the ballistic wind within the active Wax, Waz and passive Wnx, Wnz sections of the trajectory, as well as on the flight section of the combat elements Wex, Wez +.

The voltage for power supply of the ASUNO PU MLRS 1 is supplied from the on-board network of all types of armored vehicles to the power supply unit 10 and then to PC 6 and DIP 7, BINS 5, power supply unit 12, through which power supply takes place: NM 4, meteorological unit 11.

As a result, end-to-end automation of guidance and fire control of the MLRS launcher is implemented, tactical autonomy, minimum time spent at the starting position, firing from an arbitrary starting position with the possibility of its change between volleys are ensured.

Consider the structure and operation of an automated guidance system and guidance fire launcher rocket launcher for the second option.

ASUNO launcher MLRS according to the second embodiment, as shown in the drawing of FIG. 2, contains all the same elements that ASUNO PU MLRS 1 according to the first embodiment, which is described in detail above. However, this ASUNO launcher MLRS 1 further comprises a radar for reconnaissance of ground targets 13 and a power supply module 14, while the first input-output of the said radar reconnaissance of ground targets 13 is connected to the fifth input-output of the input-output unit 8, the first output the aforementioned power supply module 14 is connected to the second input of the radar reconnaissance of ground targets 13.

ASUNO PU MLRS 1 with a radar station for reconnaissance of ground targets 13 allows the crew of armored vehicles: to detect and determine the coordinates of fire artillery of the enemy, tanks, infantry fighting vehicles, armored personnel carriers, objects of control systems; the possibility of further exploration of targets intended for destruction; monitoring the results of missile launches with its launcher.

The coordinates of the enemy’s targets found by the ground-based reconnaissance reconnaissance radar 13 through the BVV 8 are sent to PC 6, the targets are displayed on the display with the military intelligence GIS. The operator decides on the defeat or additional exploration of the targets. When deciding on the defeat, the operator using the STR (not shown in the drawing) enters a command to automatically enter the coordinates of the ground targets 13 detected by the radar reconnaissance reconnaissance station in PC 6, which through BVV 8 transmits data to the reconnaissance patrol 10 and PGN 9 for guiding the MLRS launcher. Next, the guidance of the launcher on the target and the launch of rockets from the launcher MLRS.

Thus, the use of a ground-based target reconnaissance radar 13 provides a solution to the utility model problem: tactical autonomy of armored vehicles with an MLRS launcher, increased situational awareness of armored crew members based on the timely receipt of intelligence data.

Now consider the structure and operation of the ASUNO MLRS launcher in the third embodiment.

ASUNO launcher MLRS 1 according to the third embodiment, as shown in the drawing of FIG. 3, contains all the same devices that ASUNO PU MLRS according to the first and second embodiment, which are described in detail above. However, this automated guidance and fire control system of the MLRS launcher 1 additionally contains an optoelectronic system 15 for optical reconnaissance, while the first input-output of the said optical-electronic system 15 is connected to the sixth input-output of the BVV 8, the first output said power supply module is connected to a second input of the optoelectronic system 15.

The optoelectronic system 15 incorporates (not shown in the drawing): a video camera, a thermal imager and a laser range finder. ASUNO PU MLRS 1 with an optoelectronic system 15 allows you to: visually detect and determine the coordinates of enemy targets and the possibility of additional reconnaissance of targets intended for destruction. The coordinates of the enemy’s targets, detected by the optoelectronic system 15, are automatically transmitted via BVV 8 to PC 6, where they are processed, stored and displayed on the display with the ENC combat GIS. The operator decides on the defeat or carries out additional exploration of the targets. When deciding on the defeat, the operator using the open source software (not shown in the drawing) enters a command to automatically enter the coordinates of the targets detected by the optoelectronic system 15 in PC 6, which through BVV 8 transmits data to the air defense system 10 and PGN 9 to guide the MLRS launcher.

The use of the optoelectronic system 15 in combination with BVV 8 and PK 6 to perform the functions of ballistic calculations during the launch of rockets directly in the armored vehicles with the MLRS launcher made it possible to solve the problem of a utility model: increasing the situational awareness of the crew members of the armored vehicles.

The integration of the ground-based reconnaissance radar 13 with the optoelectronic system 15 increased the situational awareness of the crew members of the armored vehicles by increasing the information content of the obtained intelligence data.

As a result of the functioning of the ASUNO launcher of the MLRS mounted on a typical chassis of armored vehicles:

- preparation for launching rockets, including calculation of launch settings and flight mission data, topographic and geodetic preparation of the launch position, is carried out autonomously;

- from the time of preparation for launching missiles, the time of preliminary topographic and geodetic preparation of the launch position and the calculation time of launch installations and flight mission data are excluded, the guidance time of the launcher is reduced by eliminating manual operations;

- the time of preliminary meteorological support is excluded from the time of preparation for launching rockets, which is carried out autonomously and allows meteorological parameters to be measured automatically;

- it becomes possible to carry out artillery reconnaissance using own means: a radar station for reconnaissance of ground targets and an optoelectronic system.

- excludes possible subjective errors of the operator when entering the values of the specified target pointing angles due to the information content of the obtained intelligence data,

- it becomes possible to guide the launcher in conditions of insufficient visibility (heavy rain, snow, fog).

As a result, end-to-end automation of guidance and fire control of the MLRS launcher on a typical armored vehicle chassis is implemented. In this way, the task of the utility model is solved: providing tactical autonomy of the combat vehicle with an MLRS launcher, improving the accuracy of launches of unguided rockets from an arbitrary starting position, increasing situational awareness of the crew members of the armored vehicles.

In FIG. 4 shows a photograph of the main elements of the ASUNO launcher of the MLRS according to the first embodiment.

In FIG. Figure 5 shows the installation of ASUNO elements of the MLRS launcher on a typical infantry fighting vehicle (BMP-2) 16.

Open source software "launcher guidance-free guidance system" (not shown in the drawing) installed on PC 6 receives initial data from SINS 5 installed directly on the launcher. Open source software "autonomous orientation system" receives data from navigation module 4 and PC 6. Open source software "odometric navigation system" receives data from SINS 5 and DIP 7 installed on the chassis of armored vehicles.

The manufacture of ASUNO PU MLRS 1, depicted in figure 1, is carried out from typical radio-electronic components (REC) and typical products of Russian manufacturers.

The ASUNO sample of the launcher contains an antenna 2 and 3 PRTsL.434854.003 manufactured by NPO PROGRESS LLC, a navigation module of ZAO KB NAVIS TDTsK.461513.111, BINS 5 PRTsL.460250.005 located on the launcher, DIP 7 YM2.553.005TU, PC 6 AGRSh.466229.008-01 with a color graphic display "Orion PK-E-842-01" AGRSh.466229.008-01, BVV 8 PRTSL.460250.005, meteorological block APA-1/2 BVTI.407351.002.

The manufacture of ASUNO PU MLRS 1 depicted in FIG. 2 and 3, are carried out from typical products of Russian manufacturers, including radar station FARA-BP JSC NPO Strela.

The ASUNO sample was tested on the BTR 82A chassis in the conditions of the Arzamas Engineering Plant OJSC test site. Tests have confirmed the feasibility of the proposed technical solution to obtain the above technical result.

Claims (3)

1. An automated guidance system and guidance fire launcher rocket launcher containing vertical and horizontal guidance, designed for vertical and horizontal pointing corners of the launcher, characterized in that it further comprises first and second antennas designed to receive navigation signals from satellite GLONASS (Russia) and GPS (USA) navigation systems, a navigation module designed to automatically determine the location coordinates Objective angle and direction (true course) of the object, a strapdown inertial navigation system designed to measure accelerations and angular velocities, angles of rotation and tilt of the launcher, a path measurement sensor designed to measure the distance traveled, an input-output unit, a panel computer designed to calculation of ballistic data, display of reconnaissance and navigation data, location of an object on an electronic navigation map, power supply, meteorological unit, pred the power supply unit designated for measuring meteorological parameters, wherein the first output of the first antenna is connected to the first input of the navigation module, the first output of the second antenna is connected to the second input of the navigation module, the third output of which is connected to the first input of the strapdown inertial navigation system, the second input-output of which connected to the first input-output of the panel computer, the second input-output of which is connected to the first input-output of the said input-output unit, the second input-output of the aforementioned o the input-output unit is connected to the first input-output of the horizontal guidance drive, while the third input-output of the input-output block is connected to the first input-output of the vertical guidance drive, the first output of the path measurement sensor is connected to the third input of the said inertial navigation system, the meteorological unit is connected with the first input-output to the fourth input-output of the input-output unit, while the first output of the power supply is connected to the fourth input of the navigation module and the second input of the m teorologicheskogo, the first output of said power supply unit is connected to a third input panel computer, the second input of the probe path and the fourth input strapdown inertial navigation system. 2. Automated guidance system and guidance fire launcher rocket launcher according to claim 1, characterized in that it contains a radar station reconnaissance of ground targets and a power supply module, while the first input-output of the said radar reconnaissance system of ground targets is connected to the fifth input the output of the input-output unit, the first output of the aforementioned power supply module is connected to the second input of the ground-based reconnaissance radar. 3. Automated guidance system and guidance fire launcher rocket launcher multiple rocket launcher according to one of paragraphs. 1 and 2, characterized in that it contains an optical-electronic system designed for optical reconnaissance, wherein the first input-output of said optical-electronic system is connected to the sixth input-output of an input-output unit, the first output of said power supply module is connected to a second optical input -electronic system.

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