RU2730793C1 - Remote targets destruction method - Google Patents

Abstract

FIELD: astronautics.SUBSTANCE: invention relates to methods of hitting group targets with cruise missiles. Data on coordinates of targets are obtained, rockets are prepared for launching, flight task is introduced into BSU, rocket is launched, missile flight is controlled, connecting navigation equipment of location and location fixation, aiming missile at target and striking it. In addition, a radio link is organized, for which the composition includes an orbital spacecraft and each salvo missile is equipped with micro-radar links with a radio transmitter. At critical points of the route, information on the state of the missile and its coordinates is recorded in the memory device of the micro-missile, encrypted and the micro-rocket is fired in the vertical direction. When the upper point of the trajectory is reached, the radio transmitter is switched on and transmitted to other missiles, spacecraft and control station, and corrections are made to the missile trajectory and retargeted to other targets.EFFECT: higher efficiency of remote targets destruction.1 cl

Description

The described proposed invention relates to methods of destruction of remote targets with cruise missiles.

There is a known method of hitting a remote ground target with a Tomahawk cruise missile BGM-109 (USA), in which information about the coordinates of the target is obtained from external sources, the missile is prepared for launch, a flight task is introduced into the onboard missile control system, the missile is launched, at the starting and marching sections of the flight, automatic control of the rocket is carried out according to the commands of the on-board control system (BCS) using an on-board digital computer (BCVM), an inertial platform and a bar altimeter, after the start of terrain enveloping, navigation equipment is connected to the BSU and the correlation subsystem of control along the contour of the terrain TERCOM, using electronic data on the terrain and a radar or laser altimeter, as well as an electro-optical correlation subsystem DSMAC, using digital images of pre-captured terrain areas along the flight path, perform automatic missile control. in the area of the breakthrough of the enemy's air defense (air defense) system according to the BSU commands using the algorithms incorporated in it, they aim the missile at the target according to the BSU commands, hit the target and hit it [1 - Novikov A.V. Methods and control systems for modern missile weapons. - SPb .: VMI, 2002 .-- 75 p. P. 67].

To effectively engage remote targets, the number of missiles allocated to one target is increased, since some of them can be destroyed by air defense systems. This circumstance determines such a disadvantage of the specified method of destruction as the inability to re-target the missile in flight, depending on the results of guidance to the target of the previous missile, which may go off the trajectory for technical reasons or as a result of the impact of enemy air defense.

There is a known method of hitting ground targets with missiles, which differs from the one discussed above in that the first missile is launched in the direction of the nearest target, the target is captured by the missile guidance system and, via the telecontrol system, information is transmitted to the control point, where data on the missile hit the target or miss, after which translates the line of sight of the next missile to another target [2 - Patent for invention RU 2439462 C1. Method of controlling precision weapons / Golovan M.M. et al. - M .: FIPS, 2012. Bull. No. 1]. This method allows the missile to be retargeted depending on the result of the target attack by the previous missile, but the retargeting range is limited by the telecontrol range, which is its disadvantage.

Known guidance systems for high-precision weapons that allow you to hit distant targets. In contrast to the methods discussed above, such systems carry out combined missile control, including autonomous and radio command control, the subsequent transition to autonomous homing in the approach area to the target, search, recognition and refinement of the coordinates of stationary targets located beyond the horizon or terrain folds using airborne or external target designation, recording in the missile decoder before launching an electronic address, which is its "electronic key" for decrypting transmitted information, in which only "own" information is decoded, and the missile's radio responder only responds to "its" request. Such guidance systems make it possible, on a site with combined control, to transmit a flight mission update to each missile and, if necessary, redirect it to another target [3 - Invention Patent RU 2596173 C1. Guidance system for high-precision weapons / Rakhov E.V. and others - M .: FIPS, 2016. Bull. No. 24], [4 - Patent for invention RU 2284444 C2. Guidance system for high-precision weapons in the far zone / A.G. Shipunov. and others - M .: FIPS, 2004. Bull. No. 36]. These guidance systems allow you to hit distant targets and re-target missiles in flight, depending on the results of their attack by previous missiles, but only in the area with combined control, again limited by the radio command telecontrol range.

As a prototype of the invention, a method of hitting remote targets with anti-ship cruise missiles "Granit" is considered, in which information about the coordinates of the target is obtained from external sources, the missiles are prepared for launch, a flight task is entered into the missile control unit, one of the leading salvo missiles is assigned and the missiles are launched , at the launch and cruise sections of the flight, autonomous control of missiles is performed at the commands of their BSU using an inertial platform, an altimeter and a system for mutual information exchange (IZOI), with the help of which the functions of the leading missile can be transferred to another missile, after the first detection of the target by the radar homing head ( RGSN) of the first missile reduce the flight altitude of all missiles of the "flock" and take them beyond the radio horizon for enemy air defense systems, automatically classify targets in the BSU of the leading missile, select the main target and aim the calculated number of missiles at it, the remaining targets are distributed between the remaining missiles "st ai ", in the BSU of each missile, automatic flight control is performed in the area of the breakthrough of the air defense system of the designated target using the algorithms embedded in the BSU, they aim the missile at the target and hit it, after which the remaining missiles are redirected using the VZOI system to other targets [5 - Novikov A .IN. Methods and control systems for modern missile weapons. - SPb .: VMI, 2002 .-- 75 p. S. 60-62]. The method is based on the capabilities of the missile control system to automatically classify the group target, select the main target and effectively hit it with a "flock", re-targeting the missiles during the flight. The disadvantage of this method is the need to find all salvo missiles within the radius of the VZOI system.

The aim of the invention is to develop a method for hitting remote targets with missiles, the high efficiency of which would be ensured by the mutual exchange of information between the salvo missiles and the control point at a large distance from each other, allowing timely target distribution and correction of their trajectory by receiving information from the route from the missiles following on it first.

This goal is achieved due to the fact that a method of hitting remote targets is proposed, in which data on the coordinates of targets is received from external sources of information, prepare missiles for launch, enter a flight task into the on-board control system of each missile, launch the missile, automatically control the missile flight to the launch and marching sections of the flight at the commands of the on-board control system using an inertial guidance system, altimeters, a space navigation system and a system for mutual information exchange; in the flight section with terrain enveloping, navigation equipment for fixing and clarifying the location is connected to the rocket control - a correlation-extreme correction system trajectories along the contour of the terrain with electronic data about it and a radar or laser altimeter, as well as an electro-optical correlation guidance system with digital images previously captured on the flight route p ayons of the area, direct the missile to the designated target and hit it.

In addition, to ensure the operation of the system for the mutual exchange of information between the missiles and the control point at a great distance from each other, a radio communication line is organized, for which an orbital spacecraft is included in it, and each salvo rocket is equipped with micro-missiles with a radio transmitting device at critical points of the route, such as the beginning and end of guidance to the designated and / or detected by the missile target, violation of the flight mode and missile derailment, information about the state of the missile and its coordinates are recorded in the micro-missile memory device, encrypted and the micro-missile is fired in the vertical direction, upon reaching the top point the trajectories turn on the radio transmitter and transmit this data to other rockets, the spacecraft and the control point, after which the missile trajectories are corrected and / or redirected to other targets.

The trajectory correction and / or retargeting of the missile is carried out after receiving information from the missile in front, automatically in the onboard control system of each missile in accordance with the algorithm preset in it.

The technical result of the invention is to improve the efficiency of the method of hitting remote targets when firing missiles by ensuring the mutual exchange of information between the salvo missiles and the control point at a large distance from each other, which allows timely target distribution and correction of their trajectory based on information from missiles following a given route first.

Sources of information used in identifying the invention and drawing up its description:

1. Novikov A.V. Methods and control systems for modern missile weapons. - SPb .: VMI, 2002 .-- 75 p. P. 67.

2. Patent for invention RU 2439462 C1. Method of controlling precision weapons / Golovan M.M. et al. - M .: FIPS, 2012. Bull. # 1.

3. Patent for invention RU 2596173 C1. Guidance system for high-precision weapons / Rakhov E.V. and others - M .: FIPS, 2016. Bull. No. 24.

4. Patent for invention RU 2284444 C2. Guidance system for high-precision weapons in the far zone / A.G. Shipunov. and others - M .: FIPS, 2004. Bull. No. 36.

5. Novikov A.V. Methods and control systems for modern missile weapons. - SPb .: VMI, 2002 .-- 75 p. S. 60-62.

Claims (1)

A method of hitting remote targets, in which data on the coordinates of targets is received from external sources of information, prepare missiles for launch, enter a flight task into the on-board control system of each missile, launch the missile, automatically control the missile's flight at the launch and cruise sections of the flight according to the commands of the onboard control systems using an inertial guidance system, altimeters, a space navigation system and a system for mutual exchange of information, in the flight section with terrain enveloping, navigation equipment is connected to the rocket control for referencing and position refinement - an extreme correlation system for trajectory correction along the contour of the terrain with electronic data about him and a radar or laser altimeter, as well as an electro-optical correlation guidance system with digital images of terrain areas previously captured on the flight route, aim the missile at the designated target and hit it, characterized in that, in addition, to ensure the operation of the system of mutual exchange of information between the missiles and the control point at a great distance from each other, a radio communication line is organized, for which an orbital spacecraft is included in it and each salvo rocket is equipped with micro-rockets of communication with a radio transmitting device, at critical points of the route, such as the beginning and end of guidance to the designated and / or detected by the missile target, violation of the flight mode and the missile derailing from the trajectory, information about the state of the missile and its coordinates is written into the micro-missile memory, encrypted and the micro-missile is fired vertically direction, when the upper point of the trajectory is reached, the radio transmitter is turned on and this data is transmitted to other rockets, the spacecraft and the control point, after which the missile trajectories are corrected and / or redirected to other targets.