RU2543437C1 - Complex of control and communication of remote control unit for shooting with guided missiles from launching unit - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: complex of control and communication of the remote control unit for shooting with guided missiles (GM) from the launching unit comprises the means of communication with the observation position, the commander control unit with an additional interface and the satellite navigation equipment, a digital communication channel, a laser gyro compass on the launching unit, the automation unit, the means of communication with the observation position in the form of terminal of satellite communication, the satellite navigation equipment in the form of sensor of data about ephemeris, the unit of remote transmission to GM through the radio channel of flight mission.

EFFECT: invention enables to increase the effective range of hitting the guided missiles targets.

2 cl, 2 dwg

Description

The invention relates to the field of control and regulation, and more specifically to guided weapons.

The invention is intended to control the firing of guided missiles from the launcher.

A known method of firing guided ammunition [Patent RU No. 2359214 of 06/20/2009 IPC F41G 7/00 - Method of firing with artillery guided projectile], in which the commander’s console and digital radio station are used as control means at the firing position.

This complex at a firing position incorporates a commander’s console with satellite navigation equipment to solve design problems, communication tasks and determine the coordinates of the gun’s location. A radio station is connected to the commander’s console via a digital communication channel, providing a voice and digital communication channel with an observing position located at distances up to 20 km. To record the calculated firing settings, the commander’s console is connected via a digital cable communication channel to the guided missile and, on command from the commander’s console, the flight mission settings are recorded in the electronic equipment of the guided munition.

There is also a known method of firing guided ammunition [Patent RU No. 2379614 dated 01/20/2010 IPC F41G 5/00 - A method for controlling an artillery gun when firing], in which an gun terminal is used in addition to the commander’s console and digital radio station as control tools , from which the flight mission settings are recorded in guided munitions. In this case, before the shot, the flight mission settings are transferred from the commander’s remote control to the gun terminal via a digital communication channel, after which the gun terminal is connected to the guided munition and the command from the gun terminal records the flight mission in the memory of the electronic equipment of the guided munition (missile).

At the moment of the shot by controlled ammunition, the button on the commander’s console is pressed, by which a message about the fact of the shot is transmitted through a digital radio communication channel to the observation position, where, when the necessary time is reached, the laser target-range finder is switched on in the laser radiation mode, by which the guided ammunition is aimed at the target.

The disadvantages of this complex are the complexity of use, which is manifested in the inability to ensure the launch of a guided missile at considerable distances, in addition, the time to fire a shot must be fixed manually, it is not possible to automatically launch by a command given remotely, there is no way to automatically record firing settings from a selected missile from the composition of missiles charged in the launcher. This complex does not allow to prepare data for the launch of a guided missile, which is guided by the signals of a satellite navigation receiver. In addition, the complex does not provide the ability to adjust the flight mission of a guided missile after a shot.

The objective of the invention is to increase the operational characteristics of the weapons complex by increasing the range of destruction of targets and increasing its reliability.

This is achieved in a comprehensive way by increasing the range of the complex’s communication with the observing position, providing the possibility of preparing data for firing guided missiles with guidance from the signals of a navigation satellite receiver, providing the possibility of adjusting the flight mission of a guided missile after firing, providing remote preparation for launch, remote launch of a guided missile and automatic fixation the time the rocket left the launcher.

The solution to the problem is achieved by the fact that in the control and communication complex of the remote control point for firing guided missiles from the launcher containing communication means with an observation position, a commander’s console with satellite navigation equipment, and the communication means and satellite navigation equipment are connected to the commander’s panel via a digital channel communication, new is that it is equipped with a laser gyrocompass installed on the launcher and connected to the commander’s console via a digital communication channel, into a coma console Ndira introduced an additional interface for providing a digital communication channel for the commander’s console with the launcher’s automation unit and guided missiles at the launcher, the communication means with the observation position is made in the form of a satellite communication terminal, satellite navigation equipment is made in the form of an ephemeris data sensor for each spacecraft of the system space navigation.

Ephemeris contain information about the coordinates of the space navigation system at a certain point in time.

To improve operational performance by changing the flight mission of the rocket after firing, a remote control unit for the flight mission of the guided missile after firing over the air is connected to the commander’s console via a digital communication channel to the control and communication complex of the remote control center.

The invention is illustrated by graphic material.

Figure 1 presents a block diagram of a device according to claim 1 of the formula. Figure 2 presents the block diagram of the device according to claim 2 of the formula.

The control and communication complex of the remote control point for firing guided missiles from the launcher (FIG. 1) contains a commander’s panel 4 (PC) with satellite navigation equipment 5 (ASN), a launcher orientation device in the form of a laser gyrocompass 6 (LG), a communication facility with an observing position in the form of a satellite communication terminal 7 (ST). The laser gyrocompass 6 is connected to the commander's console 4 via a digital communication interface, for example, via the RS-232 interface. The satellite communication terminal 7 is connected to the commander's console 4 via a digital interface such as Ethernet. The commander’s console is connected to the automation unit 2 (BA) of the launcher 1 (PU) and guided missiles 3 (UR), for example, via the main serial interface according to GOST R 52070-2003.

The proposed control and communication complex remote control for firing guided missiles from the launcher operates as follows.

Using satellite navigation equipment 5 remote commander 4 determine the coordinates of the location of the launcher 1 (PU) and ephemeris for each spacecraft satellite positioning system.

An automation unit 2 of launcher 1 is connected to the commander’s console, for example, via GOST R 52070-2003 interface. Launcher 1 with missiles 3 loaded into it can be located far from the commander’s console 4. In addition, a satellite communications terminal is connected to the commander’s console 4 7, by means of which a digital communication channel is organized with an observation position that can be located at a considerable distance from the firing position in the target area. From the observation position, commander 4 receives information about the reconnaissance targets. In the commander’s console 4, target shooting installations for the launcher and guided missile are calculated.

Launcher 1 according to the laser gyrocompass 6 is induced in the horizontal and vertical plane in the direction of the target.

On command from the commander’s remote control 4 via a digital communication channel with the automation unit 2 of the launcher 1, the guided missile 3 is remotely prepared for launch, which includes the following operations: applying voltage to the selected guided missile, transmitting and recording the calculated firing installations to the electronic equipment of the missile .

When transmitting firing installations to a guided missile, the coordinates of the target and the ephemeris of the satellite constellation are additionally transmitted. Information about the ephemeris of the satellite constellation from the electronic equipment of the guided missile is transmitted to the on-board navigation satellite receiver, which immediately, when energized, enters the mode of determining the coordinates of the location of the rocket without losing time searching for satellites.

A launch permit is generated and, on a launch command, a guided missile is automatically launched.

At the time of launch, the commander’s console automatically and remotely records the launch time by interrogating the corresponding contacts of the presence of the rocket on the launcher. From the firing position commander’s remote control via a digital communication channel, the fact of the shot and the time of switching on the laser rangefinder laser pointer are transmitted to the observation position.

Aiming a guided missile at a target is carried out under the control of an on-board navigation satellite receiver. At the same time, the flight path of the rocket is adjusted taking into account the current location of the rocket and the information about the coordinates of the target entered before launch.

At the final guidance site at the observing position, the laser target indicator-range finder is automatically turned on in the target illumination mode by laser radiation at a given point in time.

The control and communication complex of the remote control point for firing guided missiles from the launcher can be implemented using the following technical means. The commander’s remote control is the Commander’s Remote Control (PC) [TECA.466225.035 TU], the satellite communications terminal is the mobile broadband satellite terminal EXPLORER 500 of the BGAN network, and the laser gyrocompass is the laser gyrocompass [BINS-1M, LLC developer Research and Production Complex "Electrooptics"], as a navigation satellite equipment - [Geos-1 module, developed by KB "GeoStar Navigation"]. The commander’s console communication with the automation unit and guided missiles can be carried out via the main serial interface according to GOST R 52070-2003.

In the particular case (Figure 2) in a portable control and communication system, the commander’s console 4 is connected via a digital communication channel, for example, via the RS-232 interface, the remote transmission unit 8 (BPZ) of the flight mission to the guided missile is connected after firing. This unit is a radio modem that supports a radio channel with a communication module on board a guided missile. If necessary, after a shot, a new target is indicated on the commander’s remote control, the coordinates of the target are transmitted to the remote transmission unit of the flight mission, from which they are transmitted via radio channel with the guided missile to the electronic equipment of the guided missile, where guidance commands to the target with new coordinates begin to be generated.

The block of remote transmission of the flight mission to the guided missile after firing can be implemented on the basis of the IP67 SATELLINE-3ASd Epic Pro radio modem.

The present invention gives a qualitatively different result compared to the prototype. Using the invention according to claim 1 of the formula will make it possible to realize the following qualitatively new properties for increasing operational characteristics, namely, increasing the range of application of the complex by several times while maintaining the effectiveness of hitting targets and increasing its reliability under interference conditions by 1.5–2 times.

Using the invention according to claim 2 of the formula will allow for the possibility of adjusting the flight mission of the guided missile after the shot.

In the proposed wearable complex of reconnaissance and target designation equipment, the effectiveness of combat operations when firing guided munitions is growing, which is tested on the layout of the complex.

Claims (2)

1. The control and communication complex of the remote control point for firing guided missiles from the launcher, comprising communication means with an observing position, a commander’s console with satellite navigation equipment, the communication means and satellite navigation equipment connected to the commander’s console via a digital communication channel, characterized in that it is equipped with a laser gyrocompass installed on the launcher and connected to the commander’s console via a digital communication channel, an additional interface is introduced into the commander’s console s to provide a digital communication channel for the commander’s console with the launcher’s automation unit and guided missiles at the launcher, the communication means with the observation position is made in the form of a satellite communication terminal, satellite navigation equipment is made in the form of an ephemeris data sensor for each spacecraft of the space navigation system. 2. The complex according to claim 1, characterized in that in order to provide the possibility of changing the flight mission of the guided missile in flight, an additional unit for remote transmission of the flight mission to the guided missile after firing via the radio channel is connected to the commander’s console via a digital communication channel.

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