RU2399854C1 - Method of guiding multi-target high-precision long-range weapon and device to this end - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: proposed method comprises target search, identification and determination its coordinates by operational target designation system (OTGS), transmission of data on target coordinates and appropriate ground map. Coordinates of control center are also defined, each target is associated with control center coordinates and battery rockets are distributed among targets. Besides instructions to control radar beams are generated, coordinates are defined and instructions to control every rocket relative to aforesaid beams are generated. Now, rockets are moved into self-homer lock-on zone. Rocket control is changed over from radio-command mode into self-homing mode, targets are searched for, identified, locked on and tracked. Note here that before target search by OTGS, target location coordinates are defined as well as preliminary coordinates of targets and data on the latter, and OTGS targets are searched for in target location area.

EFFECT: shorter target search interval, increased life of target designation means and correction of target designation in real time.

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Description

The proposed group of inventions relates to military equipment, in particular to guided weapon systems and rocket, artillery equipment with homing heads (GOS), can be used in guided weapon systems to destroy single and group mobile and stationary ground, surface and air targets, control points, fire weapons and other important small targets within the tactical zone up to 100 km.

There is a method of guidance of long-range artillery shells that controls a projectile (missile) in all sections of the flight path, while in the initial and middle sections of the path for correcting the flight path of the projectile using a command system for transmitting an image of the background-target environment (FTC) to the operator and manual missile control via fiber-optic cable (FOC), as well as data from the NAVSTAR space radio navigation system (CRNS), which allows determining the spatial position and the coordinates of the projectile relative to the target and generate steering control commands; on the final section of the projectile flight path, a homing system based on the thermal imaging seeker. This method is implemented in guidance systems of promising projectiles XM982 and ERGM (USA) with a range of 57 km and 120 km, respectively, to destroy armored targets, in the guidance system of a multi-purpose anti-tank missile system (ATGM) EFOG-M with a range of up to 100 km, the development of which maintained in the USA, the journal “Foreign Military Review”, No. 4, 2001, p.26 / 1 /, also in the guidance system developed by Germany, France and Italy of the Polyphene missile system, the magazine “Foreign Military Review”, No. 2, 2001, pp. 24-28 / 2 /.

The indicated guidance systems contain an inertial navigation system (ANN) on the rocket, an SRS receiver, control equipment with a computer, a wok coil, a thermal imaging seeker and an aerodynamic steering gear, and at the command post there is a space reconnaissance data receiving unit, a topographic reference system, an FTC image pickup unit, and transmitting control commands over the EQA, video monitor and aiming system / 1 /, / 2 /.

In these systems, the operator exercises manual control of the rocket in all areas of its flight. Information is transmitted to the operator about the FTC and the issuance of missile control commands by the EQA. In this case, manual guidance of the rocket imposes a significant limitation on the maximum speed of the rocket and excludes the possibility of simultaneous guidance of several rockets. The speed of missiles guided by the EQA does not exceed 220 m / s. These systems do not provide volley firing of missiles at several targets due to manual guidance, do not provide effective firing at moving targets at long ranges due to the long flight time of the missile, have a complex missile hardware due to the presence of ANNs with precision gyroscopic devices, CRNS equipment and wok coils, which increases the cost of the rocket.

Closest to the proposed invention is a method of pointing multi-purpose high-precision weapons of the far zone, which implements combined missile control in a salvo: radio command telecommanding at the initial and middle sections of the flight path and autonomous homing at the missile approach to targets. In this method, the target designation system searches, recognizes and determines the coordinates of targets, transmits information about the coordinates of the targets and the corresponding electronic map of the area, determines the coordinates of the command post, carries out the binding of each target to the coordinates of the command post and the distribution of the salvo missiles by targets, determines the coordinates of the missiles, forms radar beam control commands, control missiles relative to the axes of the radar rays, launch missiles into the GOS capture zone, autonomous search, recognition and coping ozhdenie goal, missile guidance translation from radio command mode homing mode, RF patent number 2284444, published in 2006, 27 September, IPC F41G 7/00, F42B 15/01 / 3 /.

This method is implemented in the guidance system of high-precision weapons of the far zone, containing at the command post a targeting data receiving unit, the input of which is connected by a radio link to the targeting system, and the output is connected to the first input of the computer, the second input of which is connected to the output of the topographic location system, and the first output is connected to video monitor input, a radar station with a phased array, missile direction finding channels, control command transmission channels and a beam control unit and a synchronization and coding unit the outputs of the direction finding channels of the missiles are connected to the third input of the calculator, the second output of which is connected to the input of the beam control unit, and the third output is connected to the input of the synchronization and coding unit, the first output of which is connected to the first inputs of the direction finding channels of the rockets, the second output is connected to the inputs of the control command transmission channels, the output of the beam control unit is connected to the first input of the phased array antenna, the second input of which is connected to the outputs of the control command transmission channels, and the output to the second input the odes of the direction finding channels of the missiles and the homing head containing the missile, control equipment, the first output of which is connected to the input of the steering gear, a radio transponder, a radio receiver, a command decoder and a command switch, while the second output of the control equipment is connected to the radio transponder input, and the input to the output command switch, the first input of which is connected to the output of the thermal imaging homing head, the second input - with the output of the control command decoder, the first input of which is connected to they yield sync block and coding, and the second input - to the output radio / 3 /.

The indicated high-precision weapon system of the far-field zone uses a remotely piloted aircraft (UAV) as an air targeting system, which usually contains an information radio transmitter, navigation system, control equipment, control device drives, an optical-electronic system (ECO) with a laser target designator a rangefinder (LCD), the first output of the control equipment being connected to the input of the drives of the control devices, and the second to the control input of the ECO with the LCD, the navigation system connected to the first input of the information transmitter, the second input of which is connected to the output of the ECO with LCD, and is an operational target designation system.

These known methods of targeting multi-purpose high-precision weapons of the far zone and guidance system for its implementation provide reconnaissance with the use of UAVs and the defeat of several stationary and moving small-sized targets in the depths of the enemy battle formation by volley launch of high-speed guided missiles. However, reconnaissance of targets only of UAVs requires a large resource of its work, increases the time it takes to search for targets, and reduces survivability of UAVs. In the conditions of suppression by the enemy of the satellite navigation system (SNA), which is very likely, for automatic flight, the UAV uses an on-board navigation system. In the process of target designation, coordinate errors of the on-board navigation system are accumulated, reducing the accuracy of determining the coordinates and the probability of hitting targets.

Therefore, the task of the proposed group of inventions is to eliminate the above disadvantages, namely: reducing the time of reconnaissance of targets, increasing the survivability of target designation means, ensuring high accuracy in determining the coordinates of targets, accuracy of withdrawal of missiles into the target capture zone of the GPS and the probability of hitting targets, as well as providing a guidance complex autonomy and self-sufficiency, combat stability.

The problem is achieved in that the method of pointing multi-purpose high-precision weapons of the far zone includes searching, recognizing and determining the coordinates of targets by the operational targeting system (SOC), transmitting information about the coordinates of the targets and the corresponding electronic terrain map, determining the coordinates of the command post, linking each target to the coordinates of the command point, the distribution of volley missiles by targets, the formation of commands for controlling the rays of a radar station (radar), the determination of coordinates and the formation of com and control of each missile relative to the axes of the radar rays, launching missiles into the GPS capture zone, transferring missile control from the radio command mode to homing mode, autonomous search, recognition, capture and tracking of targets, while the coordinates of the target location area, preliminary coordinates are determined before searching for SOC targets goals and data about them, the search for SOC goals is carried out in the area where the targets are located, when determining the coordinates of the targets, the SOCs are detected by the radar of the command post and the current SOC coordinates are determined relative to of the same point, compare them with the given ones, correct the SOC trajectory, compensate for the SOC coordinate errors, use the SOC to measure the explored target and determine the angular position of the line of sight, determine the current coordinates of the target relative to the SOC by the distance and position of the target line of sight relative to the SOC, and link each target to the command post is carried out through the current coordinates of the target relative to the SOC and the current coordinates of the SOC relative to the command post,

and also the fact that in the guidance complex of multi-purpose high-precision weapons of the far zone, containing an operational targeting system equipped with an information transmitter, navigation system, control equipment, control device drives, optoelectronic system (OES) with a laser target range finder (LCD), moreover the first output of the control equipment is connected to the input of the drives of the control devices, and the second output is connected to the control input of the ECO with LCD, the navigation system is connected to the first input of the radio transmitter information, the second input of which is connected to the output of the ECO with an LCD, a missile with a GPS and on-board equipment of the control system, a command post on which the first data receiving unit and computer, a topographic location system, a video monitor, a synchronization and coding unit, a radar station are placed ) with a phased antenna array (PAR), direction finding channels, control command transmission channels and a beam control unit, while the input of the first data receiving unit is connected by a radio line to the output of the radio transmitter SOC information, the second input of the computer is connected to the output of the topographic reference system, the third input is with the outputs of direction finding channels, the first output of the computer is with the input of the video monitor, the second output is with the input of the beam control unit, and the third output is with the input of the synchronization and coding unit, the first output which is connected to the first inputs of the direction finding channels, the second output - to the inputs of the control command transmission channels, the third output, before the rocket launch - to the rocket address input, the output of the beam control unit is connected to the first PAR input, the second input which is connected to the outputs of the control command transmission channels, and the output - to the second inputs of the direction finding channels, are additionally included at the command point a target designation system, a second data receiving unit, and in the SOC - a radio answering machine, a radio receiver and a control command decoder connected in series, while the input of the second block data reception is connected by a radio line to the output of the target designation system, and the output is connected to the fourth input of the calculator, the fourth output of which is connected to the second input of the SOC control equipment before the start of the SOC, the input is for transponder connected to the third output control apparatus, a first input coupled to an output of the decoder control commands.

The technical result is achieved due to the fact that in the method of pointing multi-purpose high-precision weapons of the far zone and the device for its implementation, before searching for targets in the SOC, the targeting system of the command point determines the coordinates of the target location, preliminary coordinates of the targets and data about them, which are received through the second data receiving unit and a computer in the control equipment of the SOC before it starts. The SOC searches for targets in the area where the targets are located, when determining the coordinates of the targets, determine the current SOC coordinates relative to the command post by locating the radar from the headlamp of the SOC radio receiver-radio responder system and processing the information received from the radar through direction finding channels to the computer. The SOC coordinates are compared with the route set before its start, if necessary, the SOC trajectory is adjusted. Using the ECO located on the SOC with the LCD, the reconnaissance target is measured and the angular position of the SEC line of sight is determined, this information is sent via the radio line to the first data receiving unit and to the command station calculator, where the target’s current coordinates relative to the SOC are calculated from the distance and position of the target line of sight relative to the SOC , the binding of each target to the command post is carried out through the current coordinates of the target relative to the SOC and the current coordinates of the SOC relative to the command post.

In the proposed method for targeting multi-purpose high-precision weapons of the far zone and a device for its implementation, combined missile control is implemented in a salvo: radio command remote control at the initial and middle sections of the flight path and autonomous homing at the missile approach target.

The proposed method is as follows.

Depending on the tactical task being solved, upon receipt of a command to attack the targets, preliminary intelligence is determined about them: the coordinates of the target location area, type, class, etc., transmit information to the command post. The availability of such operational information saves time searching for goals, a resource of work, increases the accuracy and speed of guidance, survivability of the guidance complex and its components. At the same time determine the coordinates of the command post. However, the range of preliminary intelligence, depending on their source, may be limited by the horizon. Therefore, in the area where the targets are located, additional reconnaissance of the horizontal targets of the mobile SOC is carried out, which, using preliminary target designation, searches, recognizes and determines the coordinates of stationary and moving targets, transfers this information and the corresponding electronic map of the area to the command post. In this case, the multifunctional radar of the command post is detected by the SOC, the current coordinates of the SOC relative to the command post are determined by range, elevation and azimuth, the SOC trajectory is adjusted, compensating for the accumulating coordinate errors of the onboard navigation system. The SOC operator located at the command post, manipulating the channels of technical vision of the ECO with LCD, selects the most advantageous position of the SOC from the point of view of minimum optical, acoustic and radar visibility from the picture obtained from the SOC, performs additional search for targets, takes them for auto tracking, measures the slant range before them, by means of the ECO with the LCD that the SOC is equipped with, determines the position of the line of sight of the target relative to the ECO in the SOC coordinate system. Using this information, as well as knowing the current location of the SOC, the radar direction finding command post, the current coordinates of the targets in the system associated with the command post are calculated. Thus, the target, including the moving one, is “tied” to the command post with coordinates with high accuracy and the target designation is corrected in real time. The system of “preliminary target designation - operational target designation” (blocks 3, 2) allows to reduce the time of reconnaissance of targets, more accurately determine their coordinates, saves the resource of work and increases the survivability of SOC.

Based on the target designation data, the salvo missiles are distributed according to targets and radar beam control commands are formed in such a way as to ensure their movement along given coordinates in the direction of the chosen target. Missiles are controlled relative to the axes of the rays formed by the radar according to the pre-flight program and according to target designation. Using the radar, they detect the missiles and determine their coordinates, on the basis of which they form control commands for each missile, proportional to the linear deviations of the missile from the radar beam. The vertical vertical control of the beams and the control of the missiles relative to the beams provide the required flight range and the launch of missiles into the GPS capture zone. GOS performs an autonomous search, recognition and tracking of the target and gives a signal to "capture" the target. According to this signal, the missile control transitions from the radio command mode to the homing mode using the proportional approach method, which provides high-precision guidance of the missile to the target.

The drawing shows a block diagram of a complex guidance of multi-purpose high-precision weapons of the far zone, with which they implement the proposed method, where

1 - command post;

2 - SOC;

3 - target designation system;

4 - radar;

5 - the second data receiving unit;

6 - block synchronization and coding;

7 - calculator;

8 - topographic reference system;

9 - video monitor;

10 - direction finding channels;

11 - transmission channels of control commands;

12 - beam control unit;

13 - the first data receiving unit;

14 - PAR;

15 - a radio responder;

16 - a radio receiver;

17 - information transmitter;

18 - navigation system;

19 - control equipment;

20 - decoder control commands;

21 - drives control devices;

22 - ECO with LCD;

23 - a rocket;

24 is the goal.

The inventive device operates as follows.

The target designation system (3), which the command post is equipped with (1), searches for targets and determines preliminary intelligence about them: type, class, current coordinates, etc. This information is transmitted over the air to the second data receiving unit (5). As a target designation system (3), a radar-optical system can be used that provides the operational nature of the information. Having received preliminary target designation through the second data receiving unit (5), the SOC route (2) is formed in the computer (7) and the route and preliminary coordinates of the target location area are entered into the control equipment (19) of the SOC (2) before it starts. From the control equipment (19) to the control device drive (21), the SOC (2) receives commands corresponding to a given route and the SOC (2) is advanced to the target location area using the inertial-type on-board navigation system (18) when the enemy suppresses the satellite navigation system, which is very likely.

SOC is equipped with a radio frequency transponder identical to that of the prototype / 3 / located on the rocket and consisting of a radio transponder (15), a radio receiver (16) and a control command decoder (20). The multifunctional radar (4) with the PAR (14) until the SOC (2) leaves the target area is in contact with the transponder on the basis of a “request-response-transmission command” and it detects SOC (2). Direction finding channels (10) from the signals received from the radio transponder (15) determine the coordinates of the SOC (2) in range, elevation and azimuth in the measuring system; coordinates and are transmitted to the computer (7). At the same time, from the topographic reference system (8), the computer (7) receives information about the coordinates of the command post (1). In the calculator (7), the coordinates of the SOC (2) are compared with the route specified before its start and the control commands of the SOC are formed. The calculated information is transmitted to the synchronization and coding unit (6), where it is encoded and synchronously transmitted to the transmission channels of control commands (11), which via the PAR (14) send a radio signal request signal (15), and to the SOC (2) a radio receiver ( 16) provides reception of encoded information, transmits it to a decoder (20), which starts the radio transponder (15) through the control equipment (19). Based on this information, the control equipment (19) also generates the signals of the drives of the control devices (21), controlling which they correct the trajectory of the SOC (2) and compensate for the accumulating coordinate errors. The complex operator can also adjust the SOC trajectory, receiving updated intelligence about the location of targets. The commands coming from the output of the control equipment (19) to the ECO with LCD (22) allow you to manipulate the position of the line of sight of the ECO with LCD (22) and determine the angular position of the line of sight, measure the slant range to the targets and form a picture of the field of view. This information is transmitted via a broadband noise-protected radio frequency video channel by an information transmitter (17) to the first data receiving unit (13) of the command post (1) and then to the computer (7) and to the video monitor (9). The operator of the complex according to the picture of the video monitor (9) performs an additional search for targets, takes them for auto tracking, measures the slant range to the targets and determines the angular position of the line of sight.

Based on the coordinates of the targets in the coordinate system of the SOC and the position of the line of sight of the ECO with the LCD (22), received from the information transmitter (17), and also taking into account the coordinates of the SOC, the radar direction finding (4), the calculator (7) of the command point (1) determines the coordinates goals in the system associated with the command post.

In the calculator (7), based on the target designation data in the coordinate system of the command post, radar beam control commands (4) are generated in such a way as to ensure their desired angular position in the direction of the selected target.

The missile, similar to the prototype / 3 /, contains a homing head, steering gear, control equipment, the first output of which is connected to the input of the steering gear, a radio transponder, a radio receiver, a command decoder and a command switch, while the second output of the control equipment is connected to the radio transponder input, and the input is with the output of the command switch, the first input of which is connected to the output of the homing head, the second input is with the output of the control command decoder, the first input of which is connected to the third output b before starting synchronization and coding eye, and the second input with the output of the radio receiver, and the first input of the control command decoder is the address input of the rocket, which at the time of launch of the rocket receives information about the address of the rocket from the third output of the synchronization and coding block (6) at the start of the rocket (6) )

Missiles are controlled relative to the axes of the rays formed by the PAR (14) according to target designation according to the program embedded in the calculator (7), through the beam control unit (12) similarly to the prototype / 3 /.

In the proposed device, the target designation system (3) can be performed, for example, as a gyrostabilized optoelectronic system GOES (GOES), Jane's Electro-Optic Systems, 2007-2008, p.624-626 / 4 /. As SOC (2) can be used, for example, similarly to the prototype of the Bee-1 UAV with a full-time ECO, the Military Parade magazine, No. 4, 2002, p.22-24, / 5 /, and a laser target designator - LCD range finder - 3М1 ЖГДК.433785.017 ТУ or, for example, unmanned aerial vehicle CL-327 Gardian, Military unmanned aerial vehicles of foreign countries. - 2 Central Research Institute of the Ministry of Defense of the Russian Federation, 2002/6 /. As the ECO installed on it with LCD (22), for example, the multipurpose optoelectronic payload MOSP (Israel), the on-board optoelectronic systems of military aircraft of foreign countries. - 2 Central Research Institute of the Ministry of Defense of the Russian Federation, 2006, p. 83-85, / 6 /. Blocks (4) - (21), (23) can be performed, for example, similarly to the prototype / 3 /.

Thus, the use of the proposed method of pointing multi-purpose high-precision weapons of the far zone and a device for its implementation allows

- reduce target reconnaissance time,

- to increase the survivability of target designation, guidance complex and its components,

- take into account the current position of the targets and adjust the target designation in real time, thereby increasing the accuracy of determining the coordinates of the targets, the accuracy of the output of missiles in the target capture zone of the GOS and the probability of hitting targets in comparison with known technical solutions,

- to provide a guidance complex with the properties of autonomy and self-sufficiency, the ability to function efficiently and not suffer serious losses,

- equip them with various media (ground, surface).

Claims (2)

1. A method of pointing multi-purpose high-precision weapons of the far zone, including searching, recognizing and determining the coordinates of targets by the operational targeting system (SOC), transmitting information about the coordinates of targets and the corresponding electronic terrain map, determining the coordinates of the command post, linking each target to the coordinates of the command post, distribution missile salvo targets, the formation of commands for controlling the rays of a radar station (radar), the determination of coordinates and the formation of commands for controlling each missile relative the radar axes, launching missiles into the homing zone of the homing head, transferring missile control from the radio command mode to homing mode, autonomous search, recognition, capture and tracking of targets, characterized in that before the search for targets the SOC determines the coordinates of the target location area, preliminary coordinates of the targets and data about them, the search for SOC targets is carried out in the area where the targets are located, when determining the coordinates of the targets, the SOCs are detected by the radar of the command post and the current SOC coordinates relative to the command are determined of the second point, compare them with the set ones, correct the SOC trajectory, compensate for the SOC coordinate errors, use the SOC to measure the explored target and determine the angular position of the line of sight, the current coordinates of the target relative to the SOC are calculated from the distance and position of the target line of sight relative to the SOC, and each goals to the command post are carried out through the current coordinates of the target relative to the SOC and the current coordinates of the SOC relative to the command post. 2. A complex for guidance of multi-purpose high-precision weapons in the far zone, containing an operational target designation system equipped with an information radio transmitter, navigation system, control equipment, control device drives, an optical-electronic system (OES) with a laser target designator-rangefinder (LCD), the first output of control equipment connected to the input of the drives of the control devices, and the second output to the control input of the ECO with LCD, the navigation system is connected to the first input of the information transmitter, sec the first input of which is connected to the output of the ECO with the LCC, a missile with a homing head and on-board equipment of the control system, a command post on which the first data receiving unit and computer, the topographic location system, video monitor, synchronization and coding unit, radar station are placed with a phased array (PAR), direction finding channels, control command transmission channels and a beam control unit, while the input of the first data receiving unit is connected by a radio line to the output of the radio transmitter As for SOC information, the second input of the computer is connected to the output of the topographic reference system, the third input is with the outputs of direction finding channels, the first output of the computer is with the input of the video monitor, the second output is with the input of the beam control unit, and the third output is with the input of the synchronization and coding unit, the first the output of which is connected to the first inputs of the direction finding channels, the second output - to the inputs of the control command transmission channels, the third output, before the launch of the rocket - with the address input of the rocket, the output of the beam control unit is connected to the first input of the PAR, the second to One of which is connected to the outputs of the control command transmission channels, and the output - to the second inputs of direction finding channels, characterized in that it also includes a target designation system, a second data receiving unit, and in the SOC - a radio transponder, a radio receiver and a command decoder connected in series control, while the input of the second data receiving unit is connected by a radio line to the output of the target designation system, and the output is connected to the fourth input of the calculator, the fourth output of which is connected to the second input control center SOC, and the input of the radio transponder connected to the third output of the control equipment, the first input of which is connected to the output of the decoder control commands.