RU2351508C1 - Short-range highly accurate weaponry helicopter complex - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: invention relates to defense arms, namely, to highly-accurate guides short-range weapons to be used at attack helicopters and aircraft. Proposed complex incorporates surveillance-aiming system with thermal vision sight, guidance drives and turn angle pickups, onboard computer, video monitor, helicopter flight parameters pickups and control board. It comprises also missiles with steering drives, booster and sustainer arranged in transport-and-launch containers mounted on the launching unit. The represents lift-and turn system, while the surveillance-aiming system is additionally furnished with laser beam rocket control unit and target tracking automatic device.

EFFECT: efficient hitting of several stationary and movable small-sixe surface and high-speed air targets by battery launching of high-velocity guided missiles.

1 dwg

Description

The present invention relates to defense technology, namely to high-precision guided weapons of the near tactical zone, and can be used on attack helicopters and attack aircraft.

At present, in our country and abroad, great importance is attached to attack helicopters, which provide effective fire support to the ground forces due to their mobility, maneuverability and the ability to quickly concentrate on the required areas of military operations.

An analysis of the development trends of aviation technology shows that the main directions for improving attack helicopters are to equip them with high-precision guided weapons, autonomous target designation and precise aiming. This will allow helicopters with a high probability to hit small-sized ground and air targets at any time of the day, in various weather conditions during fire and informational counteraction of the enemy.

Within the framework of the FCS program, a key area of US efforts to create advanced helicopter guided weapons is the development of the JCM guided missile designed to equip Apache Longbow and OH-58D AH-64D attack helicopters (Zarubezhnye Voyennoye Obozreniye magazine No. 1, 2006). pg. 40-44). The missile should come in exchange for the AGM-114 Hellfire and AGM-65 Mayverik missiles, its firing range is 16 km, the maximum speed is not more than 300 m / s, the first deliveries for the troops will begin in 2008.

The specified weapons complex is analogous to the claimed one and contains a radar station for search, detection and tracking of targets, a heat and television sight, a laser rangefinder, a target indicator, a unit for transmitting control commands to a missile via radio or fiber optic communication line (FOCL), an information display system (video monitors), helicopter motion parameters sensors, computer and missile launcher. The missile is located in the transport and launch container and contains the engine, control equipment, homing head (GOS) homing (laser semi-active, passive thermal imaging, active radar), fiber optic link, steering gear and radio or fiber optic data reception unit.

The missile’s flight control system operates in two modes: active homing when homing the target before launch at short range and manually correcting the flight path of the rocket on the radio or fiber optic link when there is no hijacking of the target before launch, and then switching from manual control to homing at the final section.

The main disadvantages of the analogue are:

- the complex does not provide volley firing of missiles at long ranges (more than 4-5 km) due to manual correction of the flight path in the event of the capture of the target seeker during the flight in the final section;

- low noise immunity from organized radio interference due to the presence of a radio channel for correction of missile flight path.

As a prototype, for comparison with the claimed device, the Spike-ER complex (Israel) was adopted, designed to destroy armored and other nomenclature targets at ranges up to 8 km and placed on attack helicopters AN-1 Cobra, SA 330L Puma and others (Military Technology, 1998, No. 4, pp. 26-28; Compendium by Armada, Anti-Armor Weapons, 2000, pp. 1-30).

The Spike-ER complex contains a sighting and surveillance system with a heat-television sight, a video monitor, a computer, a control panel for the complex and a launcher (fixed) with missiles. The missiles are placed in a transport and launch container and each contains a launch-marching engine, a thermal television, an electronic unit, a steering gear and a fiber optic coil.

The effective firing range of the complex is 8 km, the maximum flight speed of the rocket is 180 m / s, the average is 160 m / s, the flight time of the rocket is 8 km is 50 s, the probability of hitting a tank-type target is 0.6-0.7 . The complex was adopted by the Israeli Armed Forces and will be in service until 2020.

The complex uses two missile control modes: autonomous homing in case of capturing the target's GOOS before launch when firing at ranges of 4-5 km and combined manual FOCL control with the participation of the pilot (if there is no target capturing of the seeker before launch) and homing at the final section at subsequent capture of the GOS target.

The main disadvantages of the prototype are:

- volley firing of missiles at several targets at ranges of more than 4-5 km is not ensured due to manual pilot guidance of the missile at the fiber optic link;

- effective firing at high-speed air and moving ground targets at long ranges is not ensured due to the low speed and long flight time of the rocket (50 s per 8 km). For example, during this time, a tank-type target moving at a speed of 15 m / s will cover a distance of 750 m and with a high probability can hide behind a fold of terrain, a barrier or structure;

- the presence of manual guidance with the participation of the pilot requires a significant reduction in missile speed, while the likelihood of a helicopter hitting an enemy’s air defense system increases;

- the presence of a combined missile control system complicates the design of the rocket (thermal television GOS, FOCL coil) and the complex as a whole, which significantly increases their cost.

The objective of the invention is the creation of a helicopter complex of high-precision short-range weapons, which provides effective destruction of several stationary and moving small-sized ground and high-speed air targets by volley launch of high-speed guided missiles under the influence of enemy air defense means with a relatively simple missile design.

The solution to this problem is achieved by the fact that in a helicopter complex of high-precision short-range weapons, which contains a sighting and sighting system with a heat-television sight, guidance drives and angle sensors, a computer, a video monitor, helicopter motion sensors and control panel, as well as rockets with a steering gear and starting-marching engine, placed in transport-launch containers that are installed on the launcher, while the outputs of the angle sensors of the angle sighting system inen with the first input of the calculator, the second input of which is connected to the output of the helicopter motion parameters sensors, the third input is with the first output of the control panel, the first output of the calculator is connected to the first input of the video monitor, the second input of which is connected to the output of the heat-television sight, the second output of the control panel is connected to the first input of the guidance and guidance systems of the survey and sighting system, and the third output - with the input of the rocket launch-propulsion engine, the new one is that the launcher is made up-and-rotate and a laser sighting unit for missile control and an automatic target tracking system were introduced, while the second output of the calculator is connected to the input of the laser beam missile control unit, the third output of the calculator is connected to the inputs of the guiding actuators of the launcher, the input of the target tracking automaton is connected to the output of the thermal television the sight, and the output - with the second input of the guidance drives of the sighting and sighting system, and on the rocket introduced in series connected radiation receiver and electronic separation unit I coordinate the rocket whose output is connected to the input of the steering gear.

The invention is illustrated by graphic material, where the drawing shows a block diagram of the proposed helicopter complex of high-precision weapons, containing 1 - sighting and sighting system (OPS), 2 - heat-and-television sight, 3 - OPS guidance drives, 4 - OPS rotation angle sensors, 5 - calculator 6 - video monitor, 7 - helicopter motion parameters sensors, 8 - control panel, 9 - rocket, 10 - steering gear, 11 - main engine, 12 - laser beam missile control unit, 13 - target tracking machine, 14 - rotary launcher installation, 15 - guidance guidance launcher drives, 16 - radiation receiver, 17 - missile coordinate allocation electronic unit.

The proposed complex works as follows.

The helicopter pilot sends 8 commands from the control panel to the guidance drives 3 of the sighting system 1 and guides the sighting line of the sight 2 in azimuth and elevation. At the same time, the space surveyed by the sight is reproduced on the screen of the video monitor 6.

Having detected and recognized targets on the monitor screen 6, the pilot points the reticle to the priority target and puts the tracking of the sight line of sight 2 behind the target in automatic mode using the target tracking machine 13, which controls the targeting device 3 of the fire alarm system based on the processing of the image signals of the target from sight 2 by contrast-correlation method.

Signals proportional to the angles and angular velocities of the line of sight from the OPS rotation angle sensors 4 are fed to the input of the calculator 5, to the second input of which signals from the helicopter motion parameters sensors 7 (speed, flight altitude, course, pitch, roll, etc.) .

The calculator 5, according to certain algorithms, generates control signals for the guidance drives 15 of the lift-rotary launcher 14, according to which the launcher monitors the position of the line of sight of the sight 2 with the necessary lead angles to ensure accurate shooting of missiles into the control beam of the laser beam unit 12. At the same time from the computer to the video monitor, information about the parameters of the helicopter’s movement, the target and the shooting conditions (signal “dangerous”, “launch allowed”, etc.), as well as from the computer, is fed commands for correcting the flight path of the rocket to the input of the laser beam unit 12 are proportional to the angular velocity of the line of sight and changes in the parameters of the helicopter and the target during the launch process.

With the stable tracking of the target by the automatic machine 13 and the presence of an alarm on the monitor screen about the launch permission, the pilot from the remote control 8 gives a command to start the launch-marching rocket engine 11. After shooting the rocket into the beam generated by the laser-beam control unit 12, the radiation receiver 16 of the rocket receives an optical signal, converts it into an electrical signal, decodes it and transmits it to the electronic unit for selecting the coordinates of the rocket 17. Unit 17 generates control commands proportional to the coordinates of the rocket relative to the axis of the beam, aligned with the line of sight of the sight 2, and command correction of the flight path of the rocket. The total command is given to the aerodynamic steering gear 10, as a result of which the missile is aimed at the target.

Laser-beam missile control unit 12 is made in the form of a shaper of a narrow flat beam, sequentially scanned along the course and pitch. The signals about the coordinates of the scanned plane beam in the rocket control field and the correction commands from the computer are encoded in block 12 and transmitted in the form of code-pulsed laser radiation aimed at the target. On board the rocket, the receiver 16 and the electronic unit 17 receive, decode the signal embedded in the beam, and select the coordinates of the “strip” of the beam in the control field corresponding to the coordinates of the rocket at the time of its irradiation with the “strip”, as well as the command for correcting the path. When multiple rockets are fired in multiple shots at nearby targets, from the calculator 5, correction commands encoded for each specific missile are transmitted, corresponding to the difference in the coordinates of the targets observed in sight 2 and calculated in block 5.

The proposed helicopter complex of high-precision short-range weapons in comparison with the known has the following advantages:

- provides accurate guidance of superhigh-speed missiles in a salvo over stationary and moving small-sized ground and air targets thanks to the use of a missile control system in direct laser beam, which does not limit the speed of the missile and allows you to transmit information about changes in helicopter motion parameters, targets and shooting conditions to the missiles during the flight;

- has a high noise immunity from organized interference due to the introduction of a laser-beam missile control unit in the direct laser beam into the complex, and on a rocket a radiation receiver oriented in space to the opposite side from the enemy, which eliminates the penetration of organized radio and optical interference;

- has a simple hardware composition of the rocket, because in comparison with the prototype does not contain complex and expensive blocks (thermal imaging seeker and FOCL coil), which greatly simplifies the design of the rocket and the complex as a whole;

- lift-rotary launcher provides firing missiles at targets in sight of the sight, without changing the flight heading angle of the carrier.

Claims (1)

Helicopter complex of high-precision short-range weapons, containing a sighting and sighting system with a thermal television sight, guidance drives and angle sensors, a calculator, a video monitor, helicopter motion sensors and control panel, as well as rockets with a steering drive and a starting-marching engine, placed in a transport -launch containers that are installed on the launcher, while the outputs of the angle sensors of the survey and sighting system are connected to the first input of the calculator, the second input which is connected to the output of the helicopter motion parameters sensors, the third input is to the first output of the control panel, the first output of the calculator is connected to the first input of the video monitor, the second input of which is connected to the output of the heat-and-television sight, the second output of the control panel is connected to the first input of the guidance drives of the sighting system and the third exit - with the input of the rocket launch-propulsion engine, characterized in that the launcher is made up-and-down and laser-l are introduced into the sight and sight system a missile control unit and a target tracking machine, while the second output of the calculator is connected to the input of the laser beam missile control unit, the third output of the calculator is connected to the inputs of the launcher guidance drives, the input of the target tracking automaton is connected to the output of the heat and light sight, and the output to the second the input of the guidance drives of the sighting system, and on the rocket introduced sequentially connected radiation receiver and an electronic unit for selecting the coordinates of the rocket, the output of which is connected to steering gear Odom.