RU2538509C1 - Guided missile firing method - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: performed is topographic control of target indicator and launching facility to the terrain by ground satellite receiver, determined are coordinates of launching facility and location and ephemeris for each space vehicle of satellite positioning system, detected and measured are target coordinates, the coordinates are transmitted to artillery position control station, set is universal computer time in reconnaissanceman's console and artillery position control station, calculated and transmitted are shooting settings to launching facility automatic control unit, performed is missile launching procedure, the missile is launched from transporter-launcher container along the preset ballistic course, the missile is oriented by on-board navigation satellite receiver, when the missile approaches the target it is oriented by laser emitter.

EFFECT: providing higher probability of guided missile hitting the target.

Description

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

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

A known method of firing [Patent RU No. 2468327 of 11/27/2012, MPK7 F41G 5/00, 7/22 - Method of firing a guided missile with a laser semi-active homing], which is as follows. The firing position (launcher) is located at a great distance from the line of contact with the enemy. A scout with a laser target indicator - range finder (LCD), satellite navigation equipment, a digital radio station and a reconnaissance console is sent to the battle contact line, and the LCD outputs, satellite navigation equipment and digital radio station are connected via connectors to the reconnaissance console, the firing position commander has a fire control console a position with satellite navigation equipment and a digital radio station. Using satellite navigation equipment, the coordinates of the LCD are determined and entered into the reconnaissance console. The coordinates of the launcher are entered into the firing position control panel from satellite navigation equipment. The scout, using LCD, measures the distance to the target, azimuth, and elevation angle of the target relative to the target indicator. The measurement results are transmitted to the reconnaissance panel, converted to a rectangular coordinate system, displayed on the reconnaissance panel screen and transmitted to the firing position control panel via a digital radio channel. In the firing position control panel, using the coordinates of the targets received by radio, the measured coordinates of the launcher, the firing settings for the guided missile and the launcher are calculated. The calculated installations are transmitted via a digital communication channel to the launcher automation unit and then to the electronic equipment of the guided missile. Guidance the launcher in azimuth and elevation. The operator from the position control panel issues a start command to the launcher, by which the rocket is launched.

At the time of starting, the firing position control panel reads the starting time according to the readings of the clock timer of the single time system. A message about the fact of the shot and the time the LCD was turned on in the target illumination mode is transmitted via a digital radio communication channel from the firing position control panel to the reconnaissance panel, where, when the necessary time is reached, a signal is sent to the LCD to turn on the laser radiation, by which the guided missile is aimed at the target.

The disadvantage of the prototype is that in this method the guidance of the rocket to the target is carried out only by signals from the laser homing head when the target is illuminated by laser radiation of the target, which occurs only on the final section of the flight path of the rocket, and until that moment the rocket maintains the direction to the target only under control a gyroscopic system, which, when firing at long ranges, may not provide a missile exit to the target area and lead to a miss.

The objective of the invention is to increase the reliability of hitting a target through the implementation of a three-stage method of controlling a rocket.

This task is achieved due to the fact that in the known method of firing a guided missile, which includes topographic reference of the target and the launcher to the terrain, target detection by the target, measuring the target coordinates by the target and transferring them to the firing position control panel, setting up a single computer time in the reconnaissance panel and the firing position control panel, calculating the firing position control panel of the guided missile and launcher firing installations, transferring the firing positions according to the rocket launcher and the rocket to the launcher automation unit and then to the missile, guiding the launcher, giving the firing position from the control panel of the launcher control unit to the launch and launch launch with fixing the moment of its production, transferring the firing position from the control panel to the reconnaissance panel via a digital communication channel, the time of turning on the laser radiation of the target indicator, automatic sending from the remote control of the scout to the target pointer the signal for turning on the laser radiation when the required In addition to turning on the target, guiding the guided missile at the target illuminated by the laser radiation of the target designator, it is new that the topographic location of the launcher is carried out by a ground-based satellite receiver with the simultaneous determination of the coordinates of the location of the launcher and ephemeris for each spacecraft of the satellite positioning system, when the firing installations are sent to the guided missile additionally transmit the coordinates of the target and the ephemeris of the satellite constellation, guiding the guided missile at the target is carried out They are divided into three stages: at the first stage, after the rocket starts and leaves the transport and launch container, the rocket flies along a predetermined ballistic trajectory, at the second stage of guidance, the missile is controlled along the trajectory of the satellite navigation receiver, and at the third stage, when approaching the target, guidance is carried out on target, illuminated by laser radiation of the target according to the signals from the laser homing head, and at the first stage of guidance onboard navigation satellite receiver rockets begins to determine the coordinates of the location of the rocket by the ephemeris entered before launch.

Management of guided missile firing from the launcher according to the proposed method is as follows.

Using the navigation satellite equipment of the firing position control panel, the coordinates of the location of the launcher and the ephemeris for each spacecraft of the satellite positioning system are determined.

To the control panel of the firing position, for example, via the GOST R 520070-2003 interface, the launcher automation unit is connected. The launcher with missiles loaded into it can be located at a distance of up to 100 m from the firing position control panel. In addition, a set of communication tools is connected to the firing position control panel, with the help of which a digital communication channel is organized with a reconnaissance officer located at a command and observation post at a considerable distance from the firing position in the target area. A scout has a reconnaissance console, to which a target indicator and a set of communications equipment are connected. The scout using the reconnaissance panel determines the coordinates of the location, with the help of a target indicator, detects the target and enters the coordinates of the target in the polar coordinate system into the reconnaissance panel. Information about the target is transmitted via a digital communication channel to the firing position control panel. In the firing position control panel, target-shooting installations for the launcher and guided missile are calculated.

At a command from the firing position control panel via a digital communication channel with the launcher automation unit, the guided missile 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 missile’s electronic equipment.

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 firing position control panel automatically and remotely records the start time by interrogating the corresponding contacts of the presence of the rocket on the launcher. From the firing position control panel via a digital communication channel to the reconnaissance panel, the time for switching on the laser radiation of the target indicator is transmitted.

Aiming guided missiles at the target is carried out in three stages. At the first stage, after the rocket launches and leaves the transport and launch container, the rocket flies along a predetermined ballistic trajectory, while the on-board navigation satellite receiver begins to determine the current location of the rocket several seconds after leaving the container by entering information about the ephemeris for each spacecraft satellite positioning system.

At the second stage of guidance, rocket control on the trajectory is carried out under the control of the 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.

The target indicator is automatically turned on in the target illumination mode by laser radiation at a given point in time, while the rocket is in the target area. The third stage begins, pointing the missile at the target illuminated by the laser radiation of the target indicator, according to signals from the laser semi-active homing head.

To implement the described method, the equipment described in the patent can be used [Patent RU No. 2468327 dated November 27, 2012. IPC F41G 5/00, 7/22 - Method for firing a guided missile with a semi-active laser homing].

Using the invention, it will be possible to ensure that the missile is aimed at the target not only by the signals of the laser semi-active homing head, but also by the signals of the onboard navigation satellite receiver, which will increase the likelihood of hitting the target. The effectiveness of the method is tested on a prototype guided missile.

Claims (1)

A guided missile firing method, including topographic reference of the target and launcher to the terrain, target detection by the target, target measurement of target coordinates and their transfer to the firing position control panel, installation of a single computer time in the reconnaissance panel and firing position control panel, calculation in the firing control panel positions of guided missile and launcher firing installations, transfer of firing launcher and missile launcher installations to the launcher automation unit woks and further into the rocket, guidance of the launcher, command from the control panel of the firing position to the launcher automation unit for launching and launching with a fixation of the moment of its production, transmission from the control panel of the firing position to the reconnaissance panel via the digital communication channel of the time the laser was turned on target indicator, automatic sending from the reconnaissance panel to the target indicator of the laser radiation activation signal upon reaching the necessary activation time, guiding the guided missile at the target, eternal by laser radiation of a target designator, characterized in that the topographic location of the launcher is carried out by a ground-based satellite receiver with the simultaneous determination of the coordinates of the location of the launcher and ephemeris for each spacecraft of the satellite positioning system, while transferring the firing installations to the guided missile, the coordinates of the target and ephemeris of the satellite constellation are additionally transmitted, and Guided missile guidance on the target is carried out in three stages: at the first stage after the launch and exit of the cancer you are guided from the transport and launch container according to a predetermined ballistic trajectory, at the second stage of guidance, the missile is controlled on the trajectory under the control of the on-board navigation satellite receiver, at the third stage, when approaching the target, guidance is directed at the target illuminated by the laser radiation of the target according to the signals from the laser head homing, and in the first stage of guidance using the on-board navigation satellite receiver rockets begin to determine the coordinates of the place Assumption rocket from the ephemeris entered before starting.