RU2582437C1 - Multipurpose missile system - Google Patents

Abstract

FIELD: rocketry.

SUBSTANCE: multipurpose missile system comprises a carrier with a right and left guidance devices with lifting and rotary parts, while lifting parts have instruments with guiding channels, guides with two guided missiles, drives for transfer into combat and traveling position, weapons control device. Rotary parts are made so as to ensure limitation of rotation angles, depending on the length of the interval between axes of rotary parts, the length of the radius from the rotary part to the most remote points of the guided missile and minimum distance between guided missiles in the mode of simultaneous firing from the right and left guidance devices.

EFFECT: invention allows to increase the fire efficiency and to ensure arrangement on a wide spectrum of carriers with low carrying capacity.

3 cl, 2 dwg

Description

The present invention relates to weapons technology and can be used to create mobile systems with guided weapons.

At present, the armies of many countries of the world have a wide range of anti-tank missile systems (ATGMs), which are tasked with repelling attacks of armored vehicles in defense, providing fire support for anti-terrorist operations, and destroying firing points and other enemy targets. At the same time, the vast majority of complexes do not provide for the defeat of low-speed air targets (combat helicopters, remotely piloted aircraft, attacking attack aircraft), which have become the most dangerous opponents on the battlefield in modern conditions. Moreover, the effective range of their weapons (5-6 km) exceeds the range of most of the anti-tank systems. The aforementioned determines the need to create multi-purpose systems with guided weapons, ensuring the defeat of armored vehicles and aircraft from the safe zone while ensuring combat performance, characteristic of complexes of shorter range. Thus, the solution of these conflicting requirements is an urgent task.

Known anti-tank guided missile weapons (US Patent US 7,086,318 B1 from 08/08/2006), designed to destroy various armored vehicles. Armament, consisting of at least two missile launchers, and an armament control device are installed in a cradle located on a rotary platform built into the body of the combat vehicle. A lifting platform is installed on the turntable to move around the elevation. Aiming weapons at the target is provided by electric drives. The pivoting platform is a shoulder strap integrated in the roof of the carrier with a diameter commensurate with the width of the carrier. Inside the body of the combat vehicle there is a target tracking automaton, an operator station, including a biocular display and an operator console, an operator seat, as well as electric communication lines connecting an operator station, a target tracking automaton and electric guidance drives. The armament of the complex can be transferred from the combat readiness position to the stowed position, in which the size of the combat vehicle in the stowed position is much smaller than the combat one. The specified weapon has a range of 3750 m, which does not ensure the defeat of aircraft from the safe zone, as well as sufficient combat performance.

Also known is the Caracal ATGM (Collection of scientific and technical information No. 3 (37) Tula, 2011), designed to destroy various armored vehicles at ranges up to 5500 m. The Carakal ATGM contains the following main elements: remotely controlled combat module, including: 2 or 4 ATGMs in a container, launcher; control panel, carrier. The launcher is located on the lifting mechanism. In the stowed position, it is located inside the body of the combat vehicle, and when transferred to the combat position, it rises above the body. The launcher includes: guides for missiles, a guidance device, a thermal imaging sight, a target tracking machine, guidance drives. The control panel is located in the middle of the combat vehicle. All information on combat work is displayed on the operator’s display. Using the control panel, the operator checks the operability of the equipment, launches and guides the rocket in flight and evaluates the results of the shooting. The complex is located on the chassis of a combat vehicle with a 4 × 4 wheel formula.

The disadvantage of this technical solution is the lack of combat performance at maximum firing range. Also known ATGM "Chrysanthemum-S" (Collection of scientific and technical information No. 1, Tula, 2002), adopted by the authors for the prototype. The Chrysanthemum-C system can be installed on various carriers, wheeled and tracked. The combat weight of the system is 19.4 tons. The calculation of the system consists of two people: the commander - gunner and driver, their places are located in front of the carrier. This system is capable of hitting not only the main battle tanks at long ranges, but also helicopters and planes flying at low speeds and low altitudes. The system has two guidance channels: automatic, using radar, and semi-automatic on the laser beam. The radar operating in the millimeter range is equipped with a guidance device with lifting and turning parts, is installed on the left side of the tower roof and is used to detect targets and direct missiles in the target auto tracking mode, while the “shot and forget” principle is implemented. When there is no need to use a radar, it is retracted into the hull under armor protection using the mechanism of transfer to the combat and traveling positions. The second mode is a semi-automatic laser beam guidance. Here, a guidance device with a lifting and turning parts is used, installed in front of the upper inclined armored plate of the combat vehicle. The laser aiming sight is mounted on the lifting portion of the guidance device. In the stowed position, the device does not retract inside the combat vehicle. Since the system uses two guidance channels and a launcher for two missiles, it has the ability to hit two targets at the same time, using different guidance methods: automatic radar, semi-automatic laser beam and combined. In combined mode, two missiles are launched sequentially. The first is guided by the radar (automatically), and the second - along the laser beam (semi-automatically). Two-channel guidance system significantly increases the efficiency of the complex. The launcher has vertical and horizontal guidance mechanisms, electrically connected with the guidance channels, and in the stowed position is retracted inside the carrier using the transfer mechanism to the combat and stowed position. In the combined mode, firing is performed in two stages: - the target is guided by the radar in automatic mode, the launcher fires a missile at the radar control beam, and then the second target is captured in the semi-automatic mode using the second channel. The launcher rotates in the direction of the second channel and fires the rocket at the control beam of the second channel. The guidance angles when shooting in any of the modes are limited. The firing range is 6000 m. The disadvantage of this ATGM is insufficient fire performance, due to the fact that it does not fully utilize the advantages of a two-channel guidance system, as well as the heavy weight of the complex, which requires the use of a large payload carrier.

The present invention is the creation of a multi-purpose missile system that provides high fire performance, as well as the possibility of its placement on a wide range of lightweight carriers.

The solution to this problem is achieved by the fact that in a multi-purpose missile system containing a carrier, right and left guidance devices with lifting and turning parts mounted on it at intervals, fixed devices with guidance channels mounted on the lifting parts, guides with guided missiles installed in them, translation mechanisms in combat and marching positions, an arms control device that provides various firing modes, in it guides with guided missiles installed in them are fixed on the lifting parts of the right and left guidance devices, and their rotary parts - on the mechanisms of transfer to the combat and traveling position. The rotary parts are designed to limit rotation angles in the simultaneous firing mode from the right and left pointing devices. The rotation angles A in the simultaneous firing mode are determined from the relation: A = arc cos x,

where cos x = (B-D) / 2C,

B - the length of the interval between the axes of the rotary parts, mm;

C is the length of the radius from the axis of the turning part to the farthest point of the guided missile, mm;

D is the minimum distance between guided missiles while firing, mm.

The presence of guides with guided missiles installed in them on the lifting parts of the right and left guidance devices allows you to exclude a separate launcher with guidance drives from the complex, which significantly reduces the mass and dimensions of the complex and allows you to place it on a carrier with a small payload capacity.

The guides of the right and left guidance devices are designed to ensure that at least two guided missiles are placed on them, which allows for intensive firing, for example, "in one gulp" from the right and left guidance devices at the same time, while there are 4 missiles in flight to the target. This design does not require additional time to rotate the launcher from one control beam to another with a two-channel firing mode. In the case of firing with only one guidance device in combat position, the angle of horizontal guidance is not limited.

In the firing position, the right and left guided missiles with guided missiles are located above the roof of the carrier, and in the stowed position they are retracted using the mechanisms of transfer to the combat and stowed position inside the carrier, while the carrier has no protruding parts, which improves its operational characteristics. The present invention improves the combat performance of the complex and allows you to place it on small-capacity carriers.

The essence of the invention is illustrated by drawings, where:

FIG. 1 shows a general front view of a multipurpose missile system in a combat position (dotted lines show guidance devices in a stowed position);

FIG. 2 shows a view of the complex from above and a diagram for determining the angles of guidance during simultaneous shooting.

Multipurpose missile system (Fig. 1) contains a carrier of small payload 1, mounted on it right 2 and left 3 guidance devices with lifting 4 and rotary parts 5 with axles 6. On the lifting parts are fixed devices 7 with guidance channels 8 and guides 9 with installed guided missiles on them 10. On the carrier body 1, the mechanisms of transfer to the combat and traveling positions 11 are installed, on which the guidance devices 2 and 3 are fixed with their rotary parts 5. The angles of their rotation in the simultaneous firing mode are limited by ohm A defined by the relation: A = arc cos x,

where cos x = (B-D) / 2C;

B - the length of the interval between the axes of 6 rotary parts, mm;

C is the length of the radius from axis 6 to the farthest point 14 of the guided missile 10, mm;

D is the minimum distance between the points of 14 guided missiles during crossfire, mm.

The turning parts 5 are equipped with guidance angle sensors 12, connected by communication channels 13 to the weapon control device 14, the memory of which contains the value of angle A. In the simultaneous firing mode, the rotation angles 1 taken from the sensors 12 are compared in the weapon control device with angle A and If they coincide, the above device limits the movement of the rotary parts 5. The guidance devices are mounted on the carrier with an interval B between the axes 6 of the rotary mechanisms (Fig. 2). The phono-target environment is displayed on the display 16 of the operator console 17.

Combat work of a multi-purpose missile system is as follows. Depending on the combat situation, either one or two guidance devices are brought to the combat position. The operator searches for targets, while the phono-target environment is displayed on the operator panel display. If one or more targets are detected at a range of up to 10,000 m, the operator decides to attack and selects the guidance mode. In the semi-automatic guidance mode, the operator combines the aiming mark with the target, firing and holding the mark on the center of the target until it is defeated. In automatic mode, the operator combines the reticle with the target and turns on the weapon control device in the auto tracking mode. The target tracking machine, which is part of the armament control device, keeps the center of its aiming frame on the center of the target, and the operator launches and evaluates the firing results. In the two-channel operation mode, firing is carried out from two guidance devices at two different targets with sequential launch of missiles. The operator combines the reticle with the target, puts one guidance device in auto tracking mode, launches a guided missile, and then puts the second guidance device in auto tracking mode and launches a second guided missile. The target tracking machine keeps the aiming frames on the target centers until missiles hit the target. In this case, the operation of one guidance device in automatic, and the second in semi-automatic mode, is allowed.

In all of the above modes, two missiles are fired in one salvo in the same information beam of the guidance channel, which provides an increased probability of hitting the most dangerous targets. Up to eight guided missiles can be in a combat position, ready for firing, which allows for intensive firing without reloading.

Claims (3)

1. A multi-purpose missile system containing a carrier, right and left guidance devices installed on it at intervals with lifting and turning parts, devices mounted on the lifting parts with guidance channels, guides with guided missiles installed in them, and mechanisms for transferring them to the combat and traveling positions, armament control device providing various firing modes, characterized in that the guides with guided missiles installed in them are fixed on the lifting parts of the right and left guidance devices, the rotary parts of which are fixed on the mechanisms of transfer to the combat and traveling positions, and the rotary parts are designed to limit rotation angles in the simultaneous shooting mode from the right and left pointing devices. 2. Multipurpose missile system according to claim 1, characterized in that the rotation angles A during simultaneous firing are determined from the relation: A = arc cos x,
where cos x = (B-D) / 2C;
B - the length of the interval between the axes of the rotary parts, mm;
C is the length of the radius from the axis of the turning part to the farthest point of the guided missile, mm;
D is the minimum distance between guided missiles while firing, mm. 3. Multipurpose missile system according to claim 1 or 2, characterized in that the guides of the right and left guidance devices are made to ensure that at least two guided missiles are placed on them.

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