RU41852U1 - SHIP missile launcher - Google Patents

Abstract

The utility model relates to the field of military equipment, in particular to missile weapons of surface ships. The ship launcher contains a supporting structure for installing missile weapons. The supporting structure is made in the form of a rotary support device containing a guidance platform designed to install guidance devices and launch modules for Igla-type anti-aircraft missiles, vertical and horizontal rotation drives of the guidance platform, and a control system. Launch modules of Igla type anti-aircraft missiles are installed on the guidance platform so that their axes in a vertical plane are inclined at an angle of 6 degrees to 16 degrees to the optical axis of sight of the guidance means. The axis of the launch modules mounted symmetrically relative to the vertical axis of rotation of the guidance platform, make an angle from 1.5 degrees to 5 degrees with each other. EFFECT: reduced weight and size characteristics, increased reliability, improved accuracy of aiming at the target.

Description

The technical field to which the utility model relates.

The utility model relates to the field of military equipment, in particular to missile weapons, and can be used as anti-aircraft missile systems of surface ships.

State of the art

Known highly effective portable anti-aircraft missile system "Needle". MANPADS "Igla" was intended for use by ground forces. High performance characteristics make the complex one of the most competitive types of weapons in its class. The idea of using Igla MANPADS on naval surface ships promises to significantly improve the characteristics of naval air defense.

It is known to use Igla MANPADS on surface ships of river patrols (Military Knowledge. November, 1998, pp. 29-30), patrol boats (Military Parade, July-August, 1999, pp. 124-126), anti-submarine ships (Military Parade September-October, 1996, pp. 92-95). In these projects, Igla MANPADS are used for firing at air targets from the operator’s shoulder. However, the specificity of this complex is the need for high-precision guidance of the missile at the target. In the conditions of the ship’s pitching and maneuvers, it is difficult to manually ensure stable and high-precision guidance of the Igla missiles, especially during a battle. All this dramatically reduces the high potential of the complex.

As the closest analogue, the well-known ship missile launcher containing the supporting structure intended for the installation of missile weapons (RU 2219469 C1, 12.20.2003) was selected. This installation is stationary, that is, guiding a rocket at a target is possible only due to the maneuver of the ship. This significantly reduces the performance characteristics of the complex.

Utility Model Disclosure

The objective of this utility model is to create a short-range shipboard missile launcher with improved tactical and technical characteristics.

As a result of solving this problem, it is possible to obtain a set of technical results consisting in providing firing in one gulp, reducing the weight and size characteristics of the launcher, increasing the speed and accuracy of pointing missiles at targets, increasing the stability of target capture (especially low-flying) and their tracking, expanding operational and functional capabilities installation. An additional technical result is to increase the reliability of combat work and the survivability of weapons systems that require guidance on the target, installed on the ship.

The specified set of technical results is achieved by the fact that the ship’s launcher contains a supporting structure intended for the installation of missile weapons, the supporting structure is made in the form of a rotary support device containing a guidance platform designed to install guidance devices and launch modules for anti-aircraft missiles of the Igla type, vertical and horizontal rotation of the guidance platform and the control system, while the launch modules of the Igla type anti-aircraft missiles are installed on the guidance platform so that their axes in a vertical plane are inclined at an angle of 6 degrees to 16 degrees to the optical axis of sight of the guidance tools, and the distance between the launch modules of the Igla missiles mounted symmetrically with respect to the vertical axis of rotation of the guidance platform is from 70 cm to 260 cm.

A distinctive feature of this utility model is that the universal launch modules for Igla type MANPADS are mounted on the surface of the ship on a slewing ring (the so-called turret), containing

guidance platform, rotating in horizontal and vertical planes under the action of power tracking drives of vertical and horizontal guidance. Another distinctive feature is that the guidance means and launch modules are installed on a single guidance platform, i.e., the optical axis of sight of the guidance means is oriented in space together with anti-aircraft missiles. The axis of the launcher modules of anti-aircraft missiles of the Igla type, symmetrically mounted relative to the vertical axis of rotation of the guidance platform, are overestimated relative to the optical axis of sight of the means of guidance at an angle of 6 to 16 degrees and the distance between the launcher modules of missiles of the Igla type installed symmetrically with respect to the vertical axis of rotation guidance platforms range from 70 cm to 260 cm.

Brief Description of the Drawings

Figure 1 shows the General view of the installation and the structure of the control system.

FIG. 2 schematically shows a front view of a slewing ring.

Figure 3 schematically shows a top view of the location of the launch modules of missiles of the type "Needle".

FIG. 4 schematically shows a side view of the Central section aa in FIG. 2.

Utility Model Implementation

Tough, constantly increasing demands are placed on modern missile weapons for ships in terms of speed, weight, reliability, versatility, etc.

The ship missile launcher in accordance with this utility model contains a supporting structure on which missile weapons are mounted, as shown in FIG. 1. The supporting structure is made in the form of a rotary support device containing a guidance platform designed to install guidance means 2 and launcher modules 1 of Igla-type anti-aircraft missiles

(FIG. 2), vertical and horizontal rotation of the guidance platform and the control system. The installation of guidance and launch modules on a single guidance platform rigidly connects the position of the optical axis of sight with the position of the optical axes of the homing missile type Igla, which increases the speed and accuracy of pointing missiles at targets, as well as increases the stability of capture targets (especially low-flying) and their escort. As a means of guidance, a television sight and / or thermal imager can be used.

Figure 1 also shows the structure of the launcher control system.

TsU - target designation signals. TI is a television indicator. PU is the control panel, i.e. the workplace of the system operator, from which he observes the air situation in the television indicator, and, if necessary, gives commands for automatic or manual tracking of the target, launching a rocket, launching test programs of the control system, etc. CVK is a central computing complex that solves, in particular, the tasks of guidance, tracking, and prelaunch training. TA - a television machine that performs the functions of processing a video signal for feeding to the CVC and automatically tracking the selected target image. УУПр - a drive control device that generates control signals for drives. TU - turret. BC - video signal.

As missile weapons used anti-aircraft missiles such as "Needle". Any modifications of Igla type MANPADS, in particular Igla-1, Igla-S, can be used. Universal launch modules of this complex are installed and fixed on the guidance platform.

Launch modules 1 of Igla type anti-aircraft missiles, as shown in FIG. 4, are mounted on the guidance platform so that their axes in the vertical plane are inclined at an angle β from 6 degrees to 16 degrees to the optical axis 4 of the sighting means of the guidance 2. Angle overestimation when installing the launch modules relative to the axis of 4 sighting is necessary to implement the firing mode "slide", necessary to defeat low-flying targets. With this installation of the launch modules, a ballistic trajectory to the target is provided, while the optical axis 4 of the sighting of the guidance means 2 is directed directly at the target. The specified range is established experimentally for effective combat work in the conditions of rolling of the ship. When the angle β is less than 6 degrees are not used effectively

properties of the internal means of guiding missiles of the Igla type, and when the angle β is greater than 16 degrees, there is too much deviation of the rocket’s flight path from the line of sight, which reduces the likelihood of hitting targets (especially low flying).

To ensure reliable firing, it is important to optimally select the distance between the launch modules. It has been experimentally established that the distance L from 70 cm to 260 cm is optimal, as shown in FIG. 2. When the distance L between the launch modules is less than 70 cm, it is impossible to shoot in one gulp, because the jet stream of a launching rocket with its thermal field acts on the head of a neighboring launching rocket, as a result of which the latter, with its homing means, can capture it as a target and hit it. In addition, with a small distance, maintenance and charging of the installation are difficult. At a distance of more than 260 cm, the dimensions of the installation and its mass sharply increase, which leads to an increase in inertia and, consequently, a decrease in speed.

The axis of the launch modules mounted symmetrically relative to the vertical axis of rotation of the guidance platform, make an angle from 1.5 degrees to 5 degrees with each other, as shown in FIG. 3. This installation of missiles is necessary to ensure volley fire.

Volley shooting is associated with the following difficulties.

The simultaneous launch of two missiles can lead to the fact that the homing means (i.e., the optical homing head 3) of one of them will capture the thermal field of the neighboring rocket as a target. As a result of this, the missile will adopt a new target designation from internal guidance and will hit its missile. To prevent this from happening, it is necessary to place missiles that start in one gulp not parallel, but at a small angle to each other, i.e. provide a slight divergence of the head parts. In this case, missiles launching simultaneously, due to their different orientations, will fly towards the target along different paths, one of which will be shorter than the other. Even if the lagging missile captures the flying ahead as a target, then, since the missiles are identical and the flight speeds are the same, it simply will not catch up with it. FIG. H schematically shows a top view of the placement of missiles installed with the "collapse" a. It was experimentally established that the angle a between the axes of the missiles mounted symmetrically with respect to the vertical axis of rotation of the guidance platform, i.e. between missiles firing simultaneously in a salvo, should be between 1.5 degrees and 5 degrees. If the angle is less than 1.5

degrees, the difference in the path to the target will be small and it is possible that one missile will be hit by another. At an angle of more than 5 degrees, difficulties will arise in simultaneously guiding missiles at one target. The choice of such a range is due to the use of Igla-type missiles in the specific conditions of the ship. The choice of angle a is influenced by the maneuverability characteristics of the ship and its speed. Thus, the indicated range was experimentally selected for sea-based MANPADS of the Igla type.

It is optimal that an even number, but not less than four Igla-type anti-aircraft missiles, be installed on the slewing ring. This will allow firing in volleys of two missiles. Missiles can be mounted traditionally symmetrically from the center of the installation. Possible installation of missiles under each other. Universal launch modules are an assembly of the missile itself with a block containing the functional units necessary for combat work (power supply, signal processing, etc.). FIG. 2 schematically shows a launcher with launch modules, each of which has two Igla-type missiles.

Guidance missiles to the target is carried out by the guidance mechanism along the course (horizontal guidance) and the guidance mechanism by elevation (vertical guidance). These mechanisms can be implemented in any known manner.

For example, the guidance mechanism in the direction can be made in the form of a platform mounted for rotation around a vertical axis and equipped with a rotation drive. The guidance mechanism in elevation can be made in the form of a pair of helical gears equipped with a drive. The rotation of the screws is converted into translational movements of the mechanisms that ensure the movement of rockets in a vertical plane. During tests and exercises, it was found that for the most effective combat work, the mechanisms of the slewing ring device should provide guidance angles in azimuth from minus 130 degrees to plus 130 degrees and in elevation from minus 15 degrees to plus 60 degrees. The implementation of the rotary support device with large ranges of pointing angles significantly complicates and increases the cost of the device without significantly improving the performance characteristics. The simultaneous operation of two mechanisms allows you to direct a missile at any target located in the affected area.

The rotary support device and the control system are capable of guiding missile weapons taking into account the qualities of the ship, changes

course, as well as taking into account the maneuver being performed. As you know, the homing missile type "Needle" can independently capture and accompany the target in a sector with a central angle of not more than 1 degree. Depending on weather conditions, onboard and / or keel pitching can cause the ship to deviate by an angle of up to 16 degrees or more. A sharp change in the course of movement or the execution of a maneuver can also lead to the fact that the target leaves the capture and tracking sector of the Igla missile.

In this regard, it is necessary that the control system and the slewing ring provide compensation for changes in the position of the ship as a result of rolling, maneuver, etc., i.e. provided stabilization of the position and orientation of rockets in space, regardless of the movement of the ship itself. This can be achieved by creating a plant control system with the properties of a tracking system. The essence of the tracking system is that information from navigation sensors, as well as from pitching sensors, is processed in real time by the control system, recounted and formed into a control action supplied to the drives of the mechanisms of the slewing ring. The drives work out the received signals by moving the rocket relative to the ship, but maintaining its orientation to the target, which ensures constant capture and tracking of the target by means of homing missiles. Spent movement is converted by the appropriate position sensors and in feedback mode is transmitted to the control system, which determines the error signal and, if necessary, repeats the cycle. The control system also works in exactly the same mode when transmitting target designation signals to the drives of the slewing ring.

It is extremely important to ensure the optimal speed of the slewing ring for the development of target designation signals, ship qualities, heading changes, etc. With a low speed of signal processing, the installation does not provide the necessary speed, which reduces the tactical and technical characteristics when dealing with fast-flying targets. If the development speed is too high, the missile homing system may not have time to capture the target on the go (for example, in airspace scanning mode in search of a target), since the homing system located in the missile head has a certain inertia. In addition to the rocket's own properties, the tactical and technical characteristics of modern targets influence the choice of this parameter.

It has been experimentally established that the optimal speed of signal processing by the mechanisms of the slewing ring is up to 50 degrees per second. It is with these values that reliable and stable capture and tracking of statistically most probable targets is ensured.

In order to increase reliability and expand functional capabilities, the control system is configured to accept target designation both from general ship target detection, guidance and tracking systems, as well as from navigation systems, and from an autonomous guidance system. General ship control and guidance systems generate external target designation signals, taking into account the capabilities and condition of all available weapons in the arsenal of the ship. This ensures the most efficient use of ship weapons. External target designation signals can be generated both in the ship coordinate system (relative) and in geographical (absolute). In this mode, the launcher control system provides the reception of external target designation signals, generates control actions on the drives of the slewing ring and, when the target is captured, launches the Igla missile.

However, general ship systems can be disabled in battle. Then the control system goes offline. Its essence lies in the fact that an internal target designation signal is generated, for example, by an optoelectronic guidance system, which is part of the control system. The optoelectronic system comprises a television camera mounted on a guidance platform of a slewing ring device that generates a television signal. Next, the received television signal is processed and an escort object is extracted from it, i.e., the target. Next, the system determines the coordinates of the target, estimates the parameters of its movement and generates control actions on the drives of the slewing ring. These effects are practiced by the drives and the missile is aimed at the target.

The control system, including the optoelectronic system, provides capture and tracking of the target in both automatic and manual modes. Automatic capture and retention of the target is carried out through the optical channel. If necessary, the launcher can be manually controlled by the operator from the cutting device via a television channel. In addition to controlling their own missiles, internal target designation can be transferred to other weapons on the ship.

Thus, we can draw the following conclusions.

The use of Igla-type missiles in a ship’s launcher on a rotary support device provides the creation of a highly effective anti-aircraft air defense system with minimal weight and size characteristics. The reduction in the mass and dimensions of the installation is ensured, firstly, by the small mass of the Igla missiles proper in comparison with other similar missiles, and secondly, by the fact that the slewing ring designed for Igla missiles will also be much lighter than slewing rings for missiles of other types. This is because less powerful, and therefore less heavy gears, drives, mechanisms, etc. are needed to move a light rocket.

The choice of the distance between the Igla type extreme rocket mounted on the slewing ring and the nearest mounted rocket in the range from 70 cm to 160 cm provides on the one hand speed when moving the missiles, on the other hand it prevents neighboring missiles from affecting the rocket when firing in one gulp.

The ability to fire in one gulp is provided by installing launch modules on the guidance platform with an angular “collapse” from 1.5 degrees to 5 degrees.

The overestimation of missiles in the vertical plane relative to the optical axis of sight at an angle of b to 16 degrees increases the likelihood of hitting low-flying highly maneuverable targets.

Improving the speed and accuracy of targeting missiles on target is achieved by placing missiles of the type "Needle" and guidance on a single guidance platform of an automated slewing ring.

Improving the stability of the capture of the target and its support, as well as expanding the operational and functional capabilities of the installation, is achieved by the fact that the rotary support device and the control system are capable of guiding missile weapons taking into account the qualities of the ship and / or course change.

Improving the reliability of combat work and the survivability of other weapons systems that require guidance on a target installed on a ship is achieved by the fact that the missile launcher, in accordance with this utility model, has autonomous guidance means, information from which can be transferred to other systems in case of failure general ship systems or their own means of guidance.

Claims (5)

1. A ship launcher containing a supporting structure intended for the installation of missile weapons, characterized in that the supporting structure is made in the form of a rotary support device containing a guidance platform designed to install guidance means and launcher modules of anti-aircraft missiles of the “Igla” type, drives vertical and horizontal rotation of the guidance platform and the control system, while the launch modules of the Igla type anti-aircraft missiles are installed on the guidance platform so that their axes a vertical plane inclined at an angle of 6 to 16 ° to the optical axis of the sighting means of guidance and the distance between the missile launchers modules of type "needle" mounted symmetrically relative to the vertical pivot axis pointing platform amounts to between 70 and 260 cm. 2. The installation according to claim 1, characterized in that the control system includes an optical-electronic system that provides capture and tracking of targets in both automatic and manual modes. 3. Installation according to claim 2, characterized in that the rotary support device and the control system are capable of pointing missiles of the Igla type taking into account the qualities of the ship and / or course change, while the control system is configured to guide missiles of the Igla type ”Both in standalone mode and on target designation from general ship systems for detecting, guiding and tracking targets. 4. The installation according to claim 3, characterized in that the mechanisms of the support-rotary device provide guidance angles in the direction from -130 to + 130 °, in elevation from -15 to + 60 °. 5. Installation according to claim 1, characterized in that the axis of the launch modules mounted symmetrically with respect to the vertical axis of rotation of the guidance platform, make an angle from 1.5 to 5 ° with each other.