Method of launching missile with laser semi-active-guidance head

FIELD: weapons and ammunition.

SUBSTANCE: topographical lock-on of launcher is effected with the help of satellite navigation system prior to setting the fire parameters. Fire control board with digital radio communication means is located 50-100 metres from launcher. Lock-on errors may not exceed 50 metres. Fire control parameters are transmitted in binary code to launcher ACS and, further, to missile. Launcher is turned to azimuth and elevation to launch the missile by command from control board.

EFFECT: increased range of fire, higher safety.

1 dwg

 

The invention relates to the field of armaments, in particular to the management of missile with semi-active laser homing head, exciting highlighted the purpose of the final part of the path.

The invention is intended to control the fire of mortars and cannons calibers type 120, 122, 152, 155 mm when shooting managed ammunition and guided missiles with homing head.

There is a method of firing a controlled missile with semi-active laser homing head [Patent RU No. 2247297 from 24.07.03, a Method for firing the controlled missile with semi-active laser homing head], we have chosen for the prototype.

Scout on the control and observation point detects and maintains target laser designator-rangefinder; transmits the coordinates of the targets on the firing position, where you are shooting tracked target managed projectile. After the shot guided projectile flies like a rocket, which captures the illuminated laser beam aim on the target trajectory.

Named method is the following: consistently produce topographic binding designator and a firing position to the terrain, the target detected by the target designator, and then produce a measurement of the azimuth and distance from the designator to the target and topographic p is ivascu of a target area; calculation and implementation of units firing at the target coordinates and fire position. Topographic coordinates of a target location and transform its coordinates in the sequence of binary codes using the remote scout, and the calculation of the firing settings using the remote control firing position. In remote reconnaissance and remote control firing position organized by a single computer. Next is the missile launch and guidance of missiles at the target, comprising the sequential move the launcher to aim at the corners of the firing settings, input settings shooting a rocket, then launch and spread of missiles at the target, highlighted after shot laser target designator. After the missile is launched to enable designator transfer from the remote control firing position in the remote spy on digital radio time values include laser target designator, and the enable signal highlighting automatically send from the remote control scout in the designator while achieving on-time.

The disadvantage of this method is the limited range missile or artillery shell (up to 20 km) and the need to combat the calculation launchers or guns to be near the starting condition is anouki at launch.

The task of the invention is to increase the firing range of up to 50 km and more through the use of missiles with semi-active laser homing head having a main engine unlike artillery projectile, as well as improving the safety of fighters calculate the firing position by removing the remote control firing position for a few tens of meters from the guide launchers.

To achieve the above objectives, in a known way of firing a guided missile with semi-active laser homing head, comprising the sequential detection of a target designator, the dimension designator azimuth and distance to a target, topographic binding designator and target areas, and topographic binding targets is carried out in the remote scout calculated, after which the remote scout target coordinates is converted into a sequence of binary codes and pass them on digital radio in the remote control firing position, the dimensioning of the firing of the missiles and launchers perform in the remote control firing position on the coordinates of the target and missile launchers, and remote reconnaissance and remote control firing position establishing uniform computer time, perform the production start-up, including serial hovering the s launcher at the target on the angles of shooting, the input units firing at the missile launch and guidance of missiles at the target, illuminated laser target designator, and a switch-on signal of the designator is automatically sent from the remote control scout in achieving on-time transmitted from the remote control firing position in the remote spy on digital radio, and topographic binding launchers perform using satellite navigation equipment cockpit firing position; what's new is that additional topographic binding launchers to the terrain using satellite navigation equipment cockpit firing position to perform the calculation of the firing settings and set the remote control firing position, together with the tools of digital radio at a distance of 50-100 meters from the launcher, ensure that the accuracy of the topographic location of the launcher, target designator and targets for each dimension of the geographic coordinate system did not exceed 50 meters, designed in the remote control firing position installation firing the launcher and the missile passed in binary code in the automation unit launchers and rocket deploy the launcher on the angles of azimuth and installations firing, the missile was produced by a signal from the remote control is the exercise firing position, moreover, the signal on the rocket passed to the automation unit launchers in the binary code, and the transmission delay to switch on the pointer with remote control firing position in remote scout after launch does not exceed 3-6 seconds.

Implementation of the proposed method is illustrated by the flowchart shown in the drawing, showing: 1 - laser designator-rangefinder, 2 - gyro, 3 - satellite navigation equipment, 4 - remote scout, 5 - digital radio, 6 - remote control firing position, 7 - automatic block, 8 - missile.

The proposed method of firing a missile with semi-active laser homing head is implemented as follows: the firing position is located at a great distance from the line of contact with the enemy. To the line of battle of contact sent a scout with laser designator-rangefinder (LCC), satellite navigation equipment, digital radio and the remote scout, and outputs designator, satellite navigation equipment and digital radio stations through connectors and adapters connected to the processor of the remote agent.

Laser designator with the rangefinder and the target channel is used for detection and target tracking, and target coordinates, for example, range and azimuth of the target relative to the LCD.

With p the power of satellite navigation equipment are determined by the coordinates of the pointer in a rectangular geographic system and entered into the control panel of the scout.

Scout with LCD produces measurement target range and azimuth of the target. The results of the measurements are entered into the console scout, is converted, for example, in the terrestrial coordinate system topographic binding to the terrain, are displayed on the screen of the remote scout, is converted into a sequence of binary codes, for example, according to EIA standard interface RS232C and transmitted to the remote control firing position on digital radio.

In the remote control firing position perform topographic binding launchers to the terrain, for example, satellite navigation equipment, entered the latitude, longitude, and height of the launcher, keyboard enter data for ballistic calculations (the weight of the rocket, the temperature of the charge), weather information (metalbulletin or results of ground Metaoutline).

Set the remote control firing position, together with the tools of the digital radio communication at a distance of 50-100 meters from the launcher. This remote control firing position connected via cable to the automation unit launchers.

In the remote control firing position using the received radio coordinates of the target are calculated automatically install the firing launchers and missiles. The calculation of the angles of firing the launcher to perform aetsa, for example, the dependencies that are listed in the [Patent RU No. 2111437 from 20.05.98, the Method and apparatus aiming guns].

The dimensioning of the firing of the rocket may include determining the time of flight to the target and on-time seekers.

Using the gyro-compass is pointing the launcher at the target on the firing settings (azimuth angles and places).

Installation of firing missiles that define the sequence diagram of its flight, is transmitted in binary code in the automation unit launchers and forth in a storage device of the rocket.

The men of the crew firing position performs a reversal of the launcher, enter setup firing into the ship and then take cover in the trench (the dugout) in 50-100 meters from the launcher; there is a missile launch.

After that, over the voice communication channel to the control and observation point, where the Deputy commander, passes the report on the readiness of the launcher to start. With control and observation point over the voice channel connection command "start". This command on the firing line is the start of a rocket.

Before starting the automatic block launcher generates a voltage required for the implementation timeline of the launch.

At the time of launch on the remote control firing position commander button is enabled "the UIC" and automatically generated message to the remote spy on start. With timer hours single time with the remote control firing position reads the time of the shot, and sets the turn-on delay time LCD mode target illumination, taking into account the total time of flight of the rocket. The value of on-time target illumination is transmitted to the remote scout as a sequence of binary codes.

Scout via LCD continues to follow the target, to keep her in the cross hairs of the sighting channel.

In remote scout is automatically set to the switching time of the laser highlighter, based on the testimony of a single time control the firing position and the remote agent. In the corresponding time signal from the remote control scout is issued via a digital interface, such as RS232, LCD, and the laser beam illuminates the target.

After launch the missile launcher can be translated in a marching position and transported to a new position.

At approach of the missile to the target, the seeker on the missile scans the earth's surface in search of the trace of the laser beam. Upon detection of the laser spot in a controlled rocket generates commands to control surfaces, providing a spread of missiles in the center of the laser spot.

The turn-on time of the laser designator can be chosen constant and equal to, for example, 12 seconds to fly the missile to the target. When such inclusion target illumination for the FIC the new period of time before meetings to easier organize work of the rocket control system. To activate the LCD on the illumination to approach the missile to the target is established that the delay transfer signal to switch on the LCD should not exceed 3 to 6 seconds.

Transformation of coordinates in this way can be produced using the following coordinate systems.

The binding to the terrain LCD and a firing position, it is desirable to produce in a geographic coordinate system (CS) with fixing latitude, longitude and height mesostena.

LCD captures the target in polar IC measurement of distance and angles LCD. In the cockpit of the scout coordinates, introduced with LCD, converted to geographic SK. Through radio coordinates of the topographic binding targets in a geographical IC arrive in the remote control firing position.

In the remote control firing position on the coordinates of the target and firing position determine the range to the target, elevation, and calculate the firing settings in polar IC associated with the launcher; and the X-axis of the coordinate system is oriented to the North. These coordinates induce the launcher.

The rocket on the first segment when flying with the main engine moves along the path defined by the tip launchers. On the second site after the inclusion of the homing head control rocket is in the polar IC connected with the longitudinal axis of the missile.

For the realizatsii method can be applied to the following devices.

As a laser designator / rangefinder, gyrocompass, satellite navigation equipment, remote spy, digital radio and remote control firing position can be used in the devices described in the prototype [Patent RU No. 2247297 from 24.07.03, a Method for firing the controlled missile with semi-active laser homing head].

As automation unit can be used by the automation unit complex "Hermes", is described in [Multi-purpose missile system of the WTO helicopter-based Horizons KBP, No. 3, 2007, p.36-38].

As launchers can be used launcher, described on page 365 in the book [Precision-guided weapons to foreign countries. Volume 1. Anti-tank missile systems: survey and analytical reference. / KBP Tula: publishing house "Badretdinov and Co., 2008].

The missile is described on page 38 publication [Multi-purpose missile system of the WTO helicopter-based Horizons KBP, No. 3, 2007, p.36-38].

The proposed method of firing a missile with semi-active laser homing head compared to the prototype allows to increase the range of the missile and to increase job security with a launcher to fire position. The effectiveness of the proposed method for firing confirmed to complex the modeling stand.

The way of firing a guided missile with semi-active laser homing head, comprising the sequential detection of a target designator, the dimension designator azimuth and distance to a target, topographic binding designator and target areas, and topographic binding targets is carried out in the remote scout calculated, after which the remote scout target coordinates is converted into a sequence of binary codes and pass them on digital radio in the remote control firing position, the dimensioning of the firing of the missiles and launchers perform in the remote control firing position on the coordinates of the target and missile launchers, and remote reconnaissance and remote control firing position establish a single computer time, perform the production start-up, including serial hover launcher at the target on the angles of shooting, the input units firing at the missile launch and guidance of missiles at the target, illuminated laser target designator, and a switch-on signal of the designator is automatically sent from the remote control scout in achieving on-time transmitted from the remote control firing position in the remote spy on digital radio, and topographic binding launchers do with p the power of satellite navigation equipment cockpit firing position, characterized in that the topographic binding launchers to the terrain using satellite navigation equipment cockpit firing position to perform the calculation of the firing settings and set the remote control firing position, together with the tools of the digital radio communication at a distance of 50-100 m from the launcher, ensure that the accuracy of the topographic location of the launcher, target designator and targets for each dimension of the geographic coordinate system did not exceed 50 m calculated in the remote control firing position installation firing the launcher and the missile passed in binary code in the automation unit launchers and rocket deploy the launcher on the angles of azimuth and places units firing, the missile was produced by a signal from the remote control firing position, and a signal to start the rocket passed to the automation unit launchers in the binary code, and the transmission delay to switch on the pointer with remote control firing position in remote scout after launch does not exceed 3-6 C.



 

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