RU2737634C2 - Firing method of guided missile with laser half-active homing head and device realizing thereof - Google Patents

Abstract

FIELD: weapons.

SUBSTANCE: invention relates to guidance of artillery guided projectiles with a laser semi-active homing head (LSAHH), capturing the illuminated target on the trajectory final section, and is intended to control barrel artillery fire of calibres 120, 122, 152, 155 mm during firing by controlled ammunition with LSAHH. Method of firing a guided projectile with LSAHH consists in the fact that the firing position is topographed to the area, calculating and realizing firing settings, establishing digital radio communication channel with firing position panel, establishing a single computer time in target designator and firing position panel, performing topographic referencing of target designator to area, transmitting television image of target area to fire position panel, detecting target on television image, changing target indicator into automatic tracking mode of target, performing a shot after checking the target radiation reflected from the target laser designator in the field of view of the guided projectile homing head when it reaches the target, transmitting from the firing position panel to the target designator the time for switching on the laser radiation of the target designator, the laser emitter of the target designator when the required switching time is reached, aiming the aiming device at the target illuminated by laser radiation of the target designator. At that, firing into the design centre of the allowable sector of reflection of the target illumination beam of the projectile-target designator, target designation by the reconnaissance and target designation module (RTDM) is performed, the RTDM self-destruct means are activated when falling on the ground. Shell-projectile is characterized by that shell body used is lighting ammunition body, and same calibre as projectile with LSAHH, which will be aimed at target.

EFFECT: technical result is higher efficiency due to faster delivery of reconnaissance means and target designation to target without using an unmanned aerial vehicle.

4 cl, 4 dwg

Description

The invention relates to the guidance of guided artillery projectiles with a laser semi-active homing head (LPGSN), capturing the illuminated target at the end of the trajectory, and is intended to control the fire of cannon artillery calibers 120, 122, 152, 155 mm when firing guided munitions, with LPGSN.

Interpretation of terms used in the application.

Under installations for firing are understood the installation of sighting devices and fuses on which they open fire [Rules for firing and fire control of artillery. Division, battery, platoon, gun. Part 1 - M .: Voenizdat, 2011 - S. 410].

The known method of firing a guided projectile with a laser semi-active homing head [patent RU 2247297 C1 from 27.02.2005. IPC F41G5 / 00, 7/22 - The method of firing a guided projectile with a laser semi-active homing head], which consists in the following: the target is detected by the target designator, then the distances from the target designator to the target and from the firing position to the target are measured with the topographic reference of the target, target designator and fire positions to the terrain, calculation and implementation of firing settings based on target coordinates and firing position. Next, the projectile is aimed at the target, including sequential aiming of the gun at the target at the corners of the ballistic installations and the projectile's turn to the target, illuminated after the shot by the laser radiation of the target designator, the topographic binding of the target to the terrain and the transformation of its coordinates into a sequence of binary codes is carried out using the reconnaissance console, and the calculation of the settings of the tool is carried out using the tool control panel. At the same time, a single computer time is organized in the reconnaissance console and in the gun control panel, and after the shot is fired, before the target designator is turned on, the time value of the target designator laser radiation switching on is transmitted from the gun control panel to the reconnaissance panel via digital radio communication, and the target indicator lightning on signal is automatically sent from the reconnaissance panel into the target designator when the switch-on time is reached.

The disadvantage of this method is low efficiency, since it implies highlighting the target with a laser from the scout's console, but in order for the reconnaissance and artillery fire adjustment group to reach the target area, it takes a long time, in addition, when the illumination equipment is turned on, the group unmasks itself and runs the risk of being destroyed.

Known ammunition for the aerial reconnaissance system [patent RU 2506532 C1 dated 02/10/2014 IPC F42B12 / 36, 25/00, 30/00 - Ammunition for the aerial reconnaissance system], which contains a body and a powder charge. A bottom remote initiating device is located in the housing. The charge is fired from the initiating device and destroys the shell of the ammunition at the required height. The container is adjacent to the powder charge. The container contains a body, a repeater with an antenna, a power supply and a parachute. The building houses the equipment for photo or video recording. A repeater with an antenna transmits the results of the equipment operation to the ground control panel. The power supply supplies electric current to the photo or video recording equipment and the repeater. The parachute is fastened to the container and placed in the cavity of the head of the ammunition body. The power supply unit in its initial state is electrically connected to the photo- or video-recording equipment and a repeater. The power unit is made in the form of a pyrotechnic current source installed by the end of its pyrotechnic equipment to a powder charge. Photo or video recording equipment is located at the opposite end of the container body with a lens towards the parachute. A bracket is placed between the parachute and the container, the ends of which are located along the container and cover it from diametrically opposite sides. EFFECT: simplified design and increased reliability of ammunition operation.

The disadvantage of the ammunition is low efficiency, which is due to the flight speed of the mortar ammunition used and the lack of technical ability to target guided ammunition with LPGSN.

The closest in technical essence and functions performed, taken as a prototype, is a method of firing a guided projectile with a laser semi-active homing head [patent RU 2584210 C1 from 20.05.2016 IPC F41G5 / 00 - Method of firing a guided projectile with a laser semi-active homing head] , which includes the use of a target designator mounted on an unmanned aerial vehicle (UAV) with the ability to automatically track a target, detect it and further automatically track a target designator. It is possible to determine the speed of the UAV, the topographic referencing of the target designator, the firing position and the target to the terrain and transmit periodically with a frequency of 0.2 to 5 Hz of the coordinates and speed of the target designator to the firing position, measure the polar coordinates of the target relative to the target designator, transmit them via digital radio communication to a firing position, calculating firing installations in it and their implementation, setting a single computer time in the target designator and at a firing position, developing a shot permit at the firing position and its production, and it is formed after checking the possibility of hitting the target designator's laser radiation reflected from the target into the field vision of the seeker of a guided projectile when it approaches the target, transmission from the firing position to the target designator via the digital radio channel of the time when the laser radiation is turned on and when the required time is reached, the projectile is aimed at the target illuminated by the laser radiation of the designator.

The disadvantage of the prototype is the low efficiency of destruction of newly identified targets, which is due to the speed of the UAV used, directed to the area of the potential target, in addition, while waiting for the return of the UAV, its operation unit and equipment are in danger of attack from the enemy.

To increase efficiency, by increasing the speed of delivery of reconnaissance and target designation to the target, it is proposed to use an artillery shell.

The closest in its technical essence and functions performed, taken as a prototype, is the sighting complex of a combat unmanned aerial vehicle [patent RU 2294514 C1 from 27.02.2007 IPC F41G3 / 22, G7 / 20, D64D7 / 00 - Aiming system of a combat unmanned aerial vehicle apparatus], which includes a central computing unit, a unit for processing video information and generating control commands, a first power amplifier and a second power amplifier. The optoelectronic system includes television and thermal imaging channels, a two-coordinate rotary device and a line of sight stabilization system. Television and thermal imaging channels of the optoelectronic system can be configured to generate signals of narrow and wide fields of view. A phased array radar can be configured to operate in both real beam and synthetic aperture modes. The stabilization system of the line of sight of the optoelectronic system can be made direct in the form of a gyroscopic platform or indirect.

The disadvantage of the prototype is the low efficiency of destruction of newly identified targets, which is due to the speed of the UAV used, directed to the area of the potential target, in addition, while waiting for the return of the UAV, its operation unit and equipment are in danger of attack from the enemy.

A technical problem in this area is the low efficiency of destruction of newly identified targets, which must be solved by increasing the speed of delivery of reconnaissance and target designation to the target without using a UAV.

The technical problem of the group of inventions is solved due to the fact that in the known method of firing a guided projectile with a laser semi-active homing head, which consists in the following: they make a topographic binding of the firing position to the terrain, calculate the firing settings in the firing position control panel, implement the firing settings, establish the channel digital radio communication with the firing position control panel, set a single computer time in the target designator and the firing position control panel, make topographic binding of the target designator to the terrain, transmit a television image of the target area to the firing position control panel, detect the target from the television image, switch the target designator into automatic target tracking mode, produce a shot after checking the possibility of hitting the target designator's laser radiation reflected from the target in the field of view of the guided projectile's homing head when it approaches the target, is transmitted from the firing position control panel to the target designator. the target designator laser radiation, turn on the target designator laser emitter when the required switch-on time is reached, aim the projectile with the homing head at the target illuminated by the target designator laser radiation, the new is that the target designator projectile is additionally fired into the calculated center of the permissible sector of the target illumination beam reflection, the target designation module reconnaissance and target designation (MRTs), activate the self-destruct MRTs when falling to the ground.

A target designator, which includes a radio communication station, a power supply unit, an altimeter, a central computing unit, a video information processing unit and the formation of control commands, an optoelectronic system made in the form of a gyroscopic platform with a two-coordinate rotary device and a line of sight stabilization system, a television and thermal imaging cameras made with the possibility of generating signals of narrow and wide fields of view, while the first, second, third, fifth inputs of the central computing unit are electrically connected, respectively, to the electrical output of the television and thermal imaging channel of the optoelectronic system, the first output of the video information processing unit and the generation of control commands, the output of the altimeter and the output of the radio communication station, the first, second, third, the outputs of the central computing unit are electrically connected, respectively, to the control input of the optoelectronic system, the third input of the video information processing unit and form control commands, the second input of the radio station, the second and first inputs of the video information processing unit and the formation of control commands are electrically connected, respectively, to the output of the television and thermal imaging channel of the optoelectronic system and the output of the two-coordinate rotary device of the optoelectronic system, the second output of the video information processing and formation unit control commands are electrically connected to the input of a communication radio station, characterized in that it additionally contains a shell body with a remote fuse, a bottom, an expelling charge, two supporting half-cylinders, a reconnaissance and target designation module (MRTs), an earring, a swivel, a parachute, a block of inertial and satellite positioning sensors , a means of self-destruction, while a remote fuse, an expelling charge, two supporting half-cylinders are sequentially placed in the shell of the projectile, inside of which there is an MRC equipped with a self-destruction means with a parachute and a bottom attached through a swivel and shackle and in the electrical circuit of the MRTs, the fourth input of the central computing unit is electrically connected to the output of the inertial and satellite positioning sensor unit, the third output of the video information processing unit and the generation of control commands is electrically connected to the input of the laser designator, plus and minus of the power supply unit are electrically connected to the plus and minus, respectively block of inertial and satellite positioning sensors, with plus and minus altimeter, plus and minus central computing unit, plus and minus optoelectronic system, plus and minus gyro-stabilized platform, plus and minus two-axis rotary device, plus and minus laser designator, plus and minus block of information processing and formation of control commands, plus and minus of the radio communication station.

The target designator projectile is distinguished by the fact that the body of the illuminating ammunition is used as the body of the projectile, and the same caliber as the projectile with a semi-active laser homing head that will be guided at the target.

The target designator projectile differs in that the optoelectronic system additionally contains a laser designator (hereinafter referred to as target designator).

The claimed group of inventions is illustrated by diagrams, where in Fig. 1 shows a diagram of the guidance of a projectile with LPGSN using a target designator projectile, FIG. 2 shows the sequence of actions of the method of firing a projectile with LPGSN and a device that implements it, in Fig. 3 shows a target designator, FIG. 4 shows a block diagram of a target designator.

FIG. 1 positions indicate: 1 - firing position control panel; 2 - firing position; 3 - tool; 4 - target designator projectile; 5 - the calculated center of the permissible sector of reflection of the target illumination beam; 6 - MRC; 7 - digital radio communication channel; 8 - goal; 9 - a projectile with LPGSN; 10 - laser radiation reflected from the target; 11 - laser radiation of the target designator.

FIG. 3 positions indicate: 12 - target designator projectile body; 13 - remote fuse; 14 - bottom; 15 - expelling charge; 16 - supporting half-cylinder; 17 - earring; 18 - swivel; 19 - parachute.

FIG. 4 positions indicate: 21 - block of inertial and satellite positioning sensors; 22 - optoelectronic system; 23 - television and thermal imaging channels; 24 - two-coordinate rotary device; 25 - gyro-stabilized platform; 26 - target designator; 27 - central computing unit; 28 - block for processing video information and generating control commands; 29 - altimeter; 30 - power supply unit; 31 - means of self-destruction; 32 - radio communication station.

To implement the method, the commander's console can be used as a firing position console, which is part of the Malachite automated fire control complex or a Baguette-type console [Baguette is a computer family for special applications. - Design bureau "Korund-M" 109117, Moscow, 2000].

To organize digital radio communication between the firing position console and the MRC, technical solutions similar to the prototype can be used.

For target detection can be used, for example, an automatic target detection and tracking [Vasiliev V.I., Recognition systems. Directory. - Kiev: "Naukova Dumka", 1983, p. 177-186].

The target designator projectile, for example, can be implemented by placing in the factory a sighting complex of a combat unmanned aerial vehicle [patent RU 2294514 C1 from 27.02.2007, IPC F41G3 / 22, 7/20; B64D7 / 00 - Aiming system of a combat unmanned aerial vehicle] based on an illuminating projectile [Weapons and ammunition. Textbook. A.V. Babikin. Eidz. Moscow State Technical University named after N.E. Bauman. 2008, p. 700-703].

An example of hitting a target by the method of firing a guided projectile with a laser semi-active homing head and a device that implements it: an artillery unit (PA) is located at a long distance from the line of contact with the enemy. Having received reconnaissance data about the target, including its coordinates, the PA commander at firing position 2, using the remote control of firing position 1, determines the settings for firing and implements them on gun 2, fires a target designator projectile 4 at the calculated center of the permissible sector of reflection of the target illumination beam 5, at an altitude of 2.5 - 3 km near SC 4, a remote fuse 13 is triggered and activates an expelling charge 15, under the action of which 14 supporting half-cylinders 16 are ejected from the housing 12 of the bottom, containing the MRTs 6 equipped with a self-destruct device 31, the release of the parachute 19 MRTs 6 activates the power supply unit 30, makes a topographic reference to the terrain using signals from the satellite navigation system, determines the rate of descent and side drift with an inertial sensor, establishes digital communication channel 7 with the remote control of firing position 1 and transmits its coordinates, television image, descent rate, lateral demolition, makes the installation of a single computer time. On the remote control of firing position 1 against the background of an electronic map of the terrain, the current location of the MRTs 6 is displayed. After target 8 is detected, a command is sent to the MRTs 6 to automatically track target 8 with a target designator 26, while the actuators deploy target designator 26 to target 8.

In the console of firing position 1, the settings for firing a projectile with LPGSN 9 are calculated, which are implemented on gun 3.

A projectile with a LPGSN 9 is fired after a shot permit is generated in the control panel of the firing position 1, and the permission to shoot is formed after checking the possibility of hitting the target designator 26 reflected from the target laser radiation 10 in the LPGSN field of view when it approaches target 8.

The firing permit is developed taking into account the location of the gun and target, the flight time of the projectile with the LPGSN 9 until the target is captured by the 8 LPGSN, the target illumination time 8, the location and displacement speed of the MRTs 6.

A firing permit will be issued if at the predicted moment of time the guided projectile is in the homing area according to the laser radiation signals the MRTs 6 will be in the admissible illumination sector relative to the projectile flight path, for example, +/- 45 degrees (the condition for the effective use of the laser designator) and at a distance no more than 5 km from the target.

At the moment of firing, the command "Shot" is entered on the firing position 1 panel, then in automatic mode, according to the clock timer of the system time of the firing position 1 console, the target designator 26 is switched on to the target illumination mode and the message is transmitted to the MRC 6 via digital radio channel 7 about the fact of the shot and the time of switching on the laser radiation 11 of the target designator 26.

After the shot, the target 8 is constantly held in the field of view of the target designator 26 MRTs 6 using an automatic tracking machine and a gyro-stabilized platform 25 MRTs 6.

In the electronic equipment of the target designator 26 MRTs 6, upon receiving a message about the shot, the time of switching on the laser radiation 11 of the target designator MRTs 6 is automatically set, based on the readings of the single time of the control panel of firing position 1 and MRTs 6.

At the appropriate time, a signal is issued to turn on the laser radiation 11 of the target designator MRTs 6 and the target 8 is illuminated with laser radiation 11.

When the projectile with the LPGSN 9 approaches the target and the laser radiation 10 reflected from the target hits the field of view of the LPGSN, target 8 of the LPGSN is captured and commands are generated in the projectile on the rudders, ensuring the guidance of the projectile 9 to the center of the laser spot and hitting the target.

MRC 6 continues to decline, reaching the surface of the ground, activates self-destruct 31 and collapses.

An example of the execution of a target designator. As the body of the SC 12, a body of lighting ammunition is used, moreover, the same caliber as the projectile with LPGSN, used to hit the target, inside which a remote fuse 13, an expelling charge 15, two supporting half-cylinders 16 are located, inside which is equipped with a self-destruct device 31 MRC 6 with parachute 19 attached through swivel 18 and shackle 17, and bottom 14.

MRC 6 includes a block of inertial and satellite positioning sensors 21 and an optoelectronic system 22, including television and thermal imaging channels, 23 two-coordinate rotary device 24 and a line of sight stabilization system made in the form of a gyro-stabilized platform 25, a target designator 26.

Television and thermal imaging channels 23, optoelectronic system 22 and two-coordinate rotary device 24 are installed on a gyro-stabilized platform 25.

In addition, the MRTs 6 contains a central computing unit 27, a video information processing unit and the formation of control commands 28, an altimeter 29, a power unit 30. The MRTs 6 communicates with the console of the firing position 1 using a radio communication station 32.

Means of self-destruction 31 MRTs 6 is activated when it reaches the ground surface.

For the calculated center of the permissible sector of reflection of the target illumination beam 5, the center of the permissible target illumination sector relative to the projectile flight path is taken, for example +/- 45 degrees (the condition for the effective use of a laser designator) and at a distance of no more than 5 km from the target.

In the electrical circuit of the radio electronic equipment MRC 6, the first, second, third, fourth, fifth inputs of the central computing unit 27 are electrically connected, respectively, to the electrical output of the television and thermal imaging signal 23 of the optoelectronic system 22, the first output of the video information processing unit and the generation of control commands 28, the output the altimeter 29, the output of the inertial and satellite positioning sensor unit 21, and the output of the communication radio 32, the first, second, third, outputs of the central computing unit 27 are electrically connected, respectively, to the control input of the optoelectronic system 22, the third input of the video information processing unit and the generation of control commands 28, the second electrical input of the radio communication station 32, the second and first inputs of the video information processing unit and the generation of control commands 28 are electrically connected, respectively, to the output of the television and thermal imaging signal 23 of the optoelectronic system 22 and the output of the two-coordinate rotary device 24 of the optoelectronic system 22, the second and third outputs of the video information processing unit and the formation of control commands 28 are electrically connected, respectively, to the electrical input of the radio communication station 32 and the target designator 26, plus and minus of the power supply unit 30 are electrically connected, respectively, to the plus and minus of the unit inertial and satellite positioning sensors 21, with plus and minus altimeter 29, plus and minus central computing unit 27, plus and minus optoelectronic system 22, plus and minus gyro-stabilized platform 25, plus and minus two-coordinate rotary device 24, plus and minus laser target designator 26, the plus and minus of the information processing unit and the formation of control commands 28, plus and minus of the communication radio 32.

The central computing unit 27 and the unit for processing video information and generating control commands 28 can be performed, for example, on the basis of the PLAS.467449.001 processor module and the PLAS.468157.005 stream multiplexer [Overview catalog of Plaz LLC devices. 2017, p. 4-9].

The central computing unit 27 performs the following functions: processes the input information from the unit of inertial and satellite positioning sensors 21, altimeter 29, gyro-stabilized platform 25; generates data for the video information processing unit and the generation of control commands 28 to control the drives for moving the line of sight of the optoelectronic system 22; predicts the descent time of MRTs 6; sets a single computer time with the control panel of firing position 1; receives operator commands via digital communication channel 7.

An optoelectronic system 22 with television and thermal imaging channels 23, made in the form of a gyroscopic platform, can be implemented, for example, on the basis of a gyro-stabilized platform with a FullHD camera [Overview catalog of devices LLC "Plaz". 2017, p. 6].

The television channel 23 of the optoelectronic system 22 can be made, for example, on the basis of a 1/2 "CCD matrix with the possibility of generating signals of narrow and wide fields of view with signal accumulation, which ensures the possibility of observation both in daytime and at night. the composition of the sensitivity is shifted towards the near-IR range, which provides good conditions for observation due to the increased transmission of this range by the atmosphere.

The thermal imaging channel 23 of the optoelectronic system 22 uses a third generation cooled matrix thermal imager with two fields of view, for example, of the Thermovision 1500 type produced by FLIR SYS. The thermal imager provides the ability to form both a black-and-white image and a color one in accordance with the temperature fields of the observed objects. As part of the thermal imager, an effective control system is used that provides automatic adjustment of sensitivity and sharpness during observation. Two switchable fields of view provide the ability to preview large areas of the terrain in a wide field of view and then enlarge the image in the area of interest.

The block for processing video information and generating control commands 28 performs the following functions: improves the images of the target 8 with the issuance of control signals; automatically selects the dimensions of the tracking strobe, which relieves the operator from having to manually set the dimensions of the strobe; carries out electronic image stabilization both with a stationary and a moving field of view; integrates images obtained in different fields of information (in the field of optical contrast - a television image, in the field of thermal contrast - a thermal image), which reduces the time and increases the likelihood of detecting and recognizing targets on complex backgrounds; unfolds the image with vibrations of MRTs 6; carries out electronic image scaling; carries out multipurpose automatic tracking of small targets 8; carries out automatic re-acquisition of target 8 with prolonged interruption of optical communication (up to 6 s).

The block of inertial and satellite positioning sensors can be made, for example, using inertial sensors based on MEMS technology (CRG22) [Sensors for measuring motion parameters based on MEMS technology. Journal "Electronics", No. 1 2011, p. 72-78].

Satellite positioning can be carried out, for example, by signals L1 GPS C / A, L1 GLONASS ST, WAAS, EGNOS navigation receivers of the Geo family (GeoS-3M) [Product catalog of JSC NIIMA Progress. M. 2016. p. 9-10].

The means of self-destruction can be performed, for example, on the basis of an electromechanical explosive device of a projectile [Means of destruction and ammunition. Textbook. A.V. Babikin. Eidz. Moscow State Technical University named after N.E. Bauman. 2008, from 918-936].

The target designator projectile works as follows: the commander of the artillery unit, at firing position 2, using the control panel of firing position 1, determines the settings for firing and implements them on gun 2, fires a target designator projectile 4 at the calculated center of the permissible sector of reflection of the illumination beam of the assigned target 5 , at an altitude of 2.5 - 3 km near SC 4, a remote fuse 13 is triggered and activates an expelling charge 15, under the action of which the bottom 14, two supporting half-cylinders 16 with MRTs 6 and the release of the parachute 19 are ejected from the case 12. the power supply unit 30, the unit of inertial and satellite positioning sensors 21 makes a topographic reference to the terrain according to the signals of the satellite navigation system, determines the speed of descent and side drift, determines the altitude with the altimeter 29, sets the digital communication channel 7 with the remote control of firing position 1 and transmits its coordinates, television image, altitude, rate of descent, side drift and makes the setting of a uniform computer time. On the control panel of firing position 1 against the background of an electronic map of the terrain, the current location of the MRTs 6 is displayed. The received information is analyzed by the operator, and target 8 is detected. After target 8 is detected, a command is sent to the MRTs 6 to automatically track target 8 with a target designator 26, which is sent to the central computing unit 27, the latter generates data for the video information processing unit and the formation of control commands 28, which generates control commands for the two-coordinate rotary device 24 to keep the target 8 in the field of view, while the drive turns the target designator 26 to the target 8.

The block for processing video information and generating control commands 28 generates control commands so that the target 8 always remains in the field of view of the optoelectronic system 2, taking into account the speed of descent of the lateral drift dynamics and the deviation of the line of sight of the optoelectronic system.

After firing a projectile with an LPGSN, the video information processing unit and the formation of control commands 28 from the firing position control panel 1 via radio communication receives information about the time of switching on the laser radiation 11 of the target designator 26 and the duration of its operation, when the required time is reached, the video information processing unit and the formation of control commands 28 turns on target designator 26 for the required time. A projectile with an LPGSN captures reflected radiation, aims at the target and hits it.

MRC 6 continues to decline. It reaches the surface of the ground, which triggers the self-destructive means 31 and destroys the MRC 6.

The method of firing a guided projectile with a laser semi-active homing head and the device implementing it, in comparison with the prototype, makes it possible to increase the efficiency of hitting the assigned target by increasing the speed of delivery of the reconnaissance and target designation module to the target area. The UAV used to implement the method adopted as a prototype can reach speeds of up to 160 km / h [article "Automated fire system based on an unmanned aerial vehicle (UAV) with target designation" (AOS UAV) "in the journal Problems of Defense Technology, series 16 : Technical means of countering terrorism. 2014. No. 7-8]. The average speed of the SC, as a prototype of which it is proposed to use an illumination projectile, is 320 m / s, (1152 km / h), in addition, when using this method, it is excluded to perform tasks of UAV operation that are not characteristic of artillery units.

The calculated data of the effectiveness of the application of the claimed method and device for its implementation are shown in Table 1.

Tab. 1. Calculation of the effectiveness of hitting a target by a projectile with a laser semi-active homing head using a target designator with respect to the prototype.

P / p No. Options Prototype Know-how Efficiency, times one Preparation time: UAV launch, seconds 900 - 2 Shot production time, seconds 15 - 3 Flight time to the target area, seconds 563 78 - 4 Total time, seconds 1463 93 15.7

The following are accepted as initial data:

- TTX UAV "Katran" flight speed 160 km / h [article "Automated fire system based on an unmanned aerial vehicle (UAV) with target designation" (AOS UAV) "in the journal Problems of defense technology, series 16: Technical means of countering terrorism. 2014. No. 7-8];

- Rate of fire of the 152-mm self-propelled howitzer 2S19 - 7-8 rounds per minute [official website of the RF Ministry of Defense https://function.mil.ru/function/search_the_site.htm];

- Average speed of the illuminating projectile 320 m / s [Tables of firing for flat and mountainous conditions 152-mm Howitzer 2A62 and 152-mm Self-propelled howitzer 2S19. TS WG No. 181. Part 1. Publishing house 3 TsNII MO RF, 2005 p. 258-270];

- The distance from the firing position to the target is 25 km.

Claims (4)

1. The method of firing a guided projectile with a laser semi-active homing head, which consists in the fact that the firing position is geo-linked to the terrain, the firing settings are calculated in the firing position control panel, the firing settings are implemented, the digital radio communication channel is established with the firing position control panel, and a single computer time is set in the target designator and the control panel of the firing position, topographic binding of the target designator to the terrain is performed, a television image of the target area is transmitted to the control panel of the firing position, the target is detected on the television image, the target designator is switched to automatic target tracking mode, a shot is fired after checking the possibility of hitting the target designator's laser radiation reflected from the target in the field of view of the homing head of a guided projectile when it approaches the target, the time of switching on the laser radiation of the target designator is transmitted from the control panel of the firing position to the target designator, the laser emitter is turned on For when the required turn-on time is reached, the projectile is aimed at the target illuminated by the laser radiation of the target designator with the homing head, characterized in that: the target designator projectile is fired into the calculated center of the permissible sector of the target illumination beam reflection, target designation is carried out by the reconnaissance and target designation module (MRTs), self-destruction of MRC when falling to the ground. 2. A target designator, including a radio communication station, a power supply unit, an altimeter, a central computing unit, a video information processing unit and the formation of control commands, an optoelectronic system made in the form of a gyroscopic platform with a two-coordinate rotary device and a line of sight stabilization system, television and thermal imaging cameras capable of generating signals of narrow and wide fields of view, while the first, second, third, fifth inputs of the central computing unit are electrically connected, respectively, to the electrical output of the television and thermal imaging channel of the optoelectronic system, the first output of the video information processing unit and the generation of control commands , the output of the altimeter and the output of the communication radio station, the first, second, third, the outputs of the central computing unit are electrically connected, respectively, to the control input of the optoelectronic system, the third input of the video information processing unit and control commands, the second input of the communication radio station, the second and first inputs of the video information processing unit and the formation of control commands are electrically connected, respectively, to the output of the television and thermal imaging channel of the optoelectronic system and the output of the two-coordinate rotary device of the optoelectronic system, the second output of the video information processing and formation unit control commands are electrically connected to the input of a communication radio station, characterized in that it additionally contains a shell body with a remote fuse, a bottom, an expelling charge, two supporting half-cylinders, a reconnaissance and target designation module (MRTs), an earring, a swivel, a parachute, a block of inertial and satellite positioning sensors , a means of self-destruction, while a remote fuse, an expelling charge, two supporting half-cylinders are sequentially placed in the shell of the projectile, inside of which is an MRC equipped with a self-destruction means with a parachute attached through a swivel and an earring, and but, and in the electrical circuit of the MRC, the fourth input of the central computing unit is electrically connected to the output of the inertial and satellite positioning sensor unit, the third output of the video information processing unit and the generation of control commands is electrically connected to the input of the laser designator, plus and minus of the power supply unit are electrically connected respectively to the plus and minus block of inertial and satellite positioning sensors, plus and minus altimeter, plus and minus central computing unit, plus and minus optoelectronic system, plus and minus gyro-stabilized platform, plus and minus two-axis rotary device, plus and minus laser designator, plus and the minus of the information processing unit and the formation of control commands, the plus and minus of the radio communication station. 3. A target designator projectile according to claim 2, characterized in that the body of the projectile is the body of the lighting ammunition, and the same caliber as the projectile with LPGSN used to hit the target. 4. A target designator projectile according to claim 2, characterized in that the optoelectronic system additionally contains a laser designator.

Images