RU2514324C1 - Portable surface-to-air missile system /versions/ - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: invention relates to weapons, namely, to portable surface-to-air missile systems. The portable surface-to-air missile system (PSTAM) comprises a missile launching canister (MLC) (cross section in the part of the engine has the shape of a rhombus or oval, or a rectangle or a hexahedral non-axisymmetric figure), a monitor, a surface-to-air missile or two PSTAMs with missiles of radar and infrared type, a missile control unit, an optical sight of an operator. The missile comprises a transmitter and a receiver with four and more antennas. The MLC comprises a start engine with two more nozzles, linked to the rear part of the MLC with titanium wire or heat-resistant rope, a flap or a sliding bracket with a thermal imaging device, a flap leg.

EFFECT: invention makes it possible to destroy high-speed targets at high distances and heights.

13 cl, 6 dwg

Description

The invention relates to portable launchers, but a missile from it can be used both in motorized complexes and as an air-to-air missile, including as a missile defense launched from aircraft.

Known portable missile systems (hereinafter MANPADS) containing an anti-aircraft missile in a transport and launch container (hereinafter “container”), see, for example, the Internet, Wikipedia, MANPADS “Igla”.

The practice of recent local wars has shown that long-range anti-aircraft systems are very vulnerable and are quickly destroyed by the enemy. And existing MANPADS cannot hit targets at an altitude of more than 3600 m or flying at a speed of more than 400 m / s. As a result, enemy aircraft flying at altitudes of more than 4,000 m or with speeds of more than 1.3 M freely hit ground targets with guided and unguided bombs and missiles of all types.

The need has ripened for creating MANPADS with reach in height of up to 15,000 m, in range of up to 20,000 m and in speed of up to 2.5 M. This has become possible thanks to the invention of the “Open Frame Self-Feeding Engine”, US Pat. No. 2431052 and even more advanced "Staroverov Rocket Engine - 8 (options)", application No. 2012106695, as well as a number of invented rocket fuels, "flat" rockets according to US Pat. No. 2439376, guidance systems according to US Pat. No. 2400590 and a laser fuse according to US Pat. No. 2412427, "Warhead" (application without number). In some cases, an anti-helicopter missile according to US Pat. No. 2443968. The use of all these inventions will create a new generation of MANPADS. Additional qualities can be given to a rocket by the appearance of television (and thermal imaging) systems for detecting and holding a target in the field of view of a television camera (thermal imager). Such systems may have a greater detection range and a larger viewing angle than existing ones.

This MANPADS is not intended to replace existing ones, but to complement them. Of course, his missile can be used both as a missile for the Shell, Dagger, Tunguska complexes, and as an air-to-air missile. In view of the larger caliber and mass, the missile of the complex can have both a thermal homing head (hereinafter referred to as GOS) and a radar.

OPTION 1. The aforementioned “Staroverov-8 Rocket Engine”, which has no body or nozzle and consists of 99% solid rocket fuel, can have stabilizers, each of which is a few short stabilizers glued to the engine block connected “nose” in the tail "using the connection" protrusion-groove ". Such stabilizers in total will have a length slightly greater than the length of the checkers, and will evenly transmit lateral aerodynamic forces to the checker of the engine. But they have one drawback - they do not add up.

"Flat" anti-aircraft missile according to the mentioned US Pat. No. 2439376 gives the rocket great advantages in flight - it has not four, but only two rudders, two steering drives and two full-size stabilizers, that is, their aerodynamic drag is approximately 1.9 times less and 1.9 times less than their weight. In addition, thanks to the aforementioned engine, the rocket is shortened in flight, and its aerodynamic drag decreases, and maneuverability, on the contrary, increases. A “flat” rocket also has an advantage in storage and transportation - the front vertical rudders can be made folding, since there are only two of them instead of the usual four, and the container will not be too bulky. But folding steering wheels are also possible - within the stabilizer dimensions, this is quite simple.

Due to these factors, in such a MANPADS, the transport and launch container has a flattened cross-section in the engine part. A flattened view means a rhombus, an oval, an ellipse, a rectangle, a hexagonal non-axisymmetric figure, etc. (see figures 1, 2, 3, 4). Such a container will fit well on the operator’s shoulder or on two shoulders of the calculation of two operators (it is desirable to provide soft lodgements). The expected weight of the rocket will be about 50-60 kg, the weight of the total MANPADS is about 65-80 kg, length is 2.2-2.5 meters, so the launch can be carried out either by one strong person, or with the help of two people.

A launch option with support on the ground is also possible - it is easier to lift and direct MANPADS alone. In this case, in order to create a gap for the exit of gases from the container, there can be a hinged leg for supporting it on the ground in its lower rear part (all directions are given relative to the direction of rocket launch).

It should be noted one more positive quality of the aforementioned engine - a rocket with it does not need to be divided into stages - any speed, for example 10 M, is achievable in one stage, it is enough to provide the necessary ratio of the mass of the head part and the mass of the engine’s checkers.

It should be noted that for the implementation of the technology of "direct hit" control must be of the type "Weather vane regressive" duck "according to US Pat. No. 2410286 - mechanical or electrical options.

OPTION 2. It will not always be possible to launch a rocket under ideal conditions - standing or from a knee, possibly with support on the ground. On the contrary, it is very likely that the enemy’s ground means will launch a rocket - shelling from small arms, grenade launchers or artillery and mortar shelling. In this case, it is necessary to provide for the possibility of launching from behind a shelter, from a funnel, ravine or from a well-shaped trench specially dug for this purpose. For this, the transport and launch container has a hinged or retractable bracket in front with a thermal imager that can be rotated in a vertical plane or in two planes, and the rotation of the thermal imager with the help of remote position sensors is synchronized with the rotation of the movable homing missile.

In this embodiment, only the thermal imager lens protrudes from the trench, is aimed at the target and the rocket is launched. Having flown out of the container only 30-40 centimeters, the homing head will already see the target. The first second, the rocket should fly, not being controlled by the rudders due to their low efficiency at low speed, but by tracking the target’s position by turning the homing head. And only then the rudders turn on, and the rocket chooses a preemptive course. You can not provide for a special shutdown of the rudders - they simply will be ineffective up to some speed.

The use of patent No. 2443968 is useful - the rocket first gains altitude at an angle of about 45 degrees to exit the dense layers of the atmosphere, and only then turns at the target at an altitude of about 5000 m (this mode can be deactivated). However, during this climb, horizontal guidance must be carried out on the target to generate a lead.

OPTION 3. Mounting the thermal imager can be bivariate - on the bracket and on the container, while the monitor is mounted opposite the operator’s eye. But it is possible that the sighting imager with the monitor is located far from the container and connected to it with a cable that controls the movable homing head, or the imager is located in the homing head, and the monitor is in the distance. In this case, the container can simply be laid on the edge of the unevenness of the soil, trench or funnel (you can provide a two-legged support in front). In this case, the operator does not run the risk of being fired after launching the rocket - the place where the empty container is left will be fired.

OPTION 4. The ejection of a rocket by a powder charge from a container having a non-circular shape is difficult, since the internal pressure will tend to give the container a more rounded shape. This can lead either to deformation of the container and jamming of the rocket, or to the need to significantly strengthen the container, which will lead to an increase in its weight.

To launch a missile, this MANPADS has a launch rocket engine with a rearward-facing nozzle / nozzles located behind the missile, and its operating time corresponds to the appearance of a cut of the nozzle of this engine near the front cut of the container. That is, the engine only works when it moves inside the container, and when it aligns with the front cut of the container, it finishes its work so as not to burn the operator. At the same time, the rocket receives sufficient initial speed to fly away from the operator several meters to safely turn on the main engine.

However, there is a danger that the starting engine when the main engine is started will be discarded by the operator. If the tests show such a possibility, then to prevent this from happening, the starting engine may be forced to brake. For example, it can be tied to the back of the container with a heat-resistant cable, wire or chain (titanium or carbon fiber), laid in a spiral, which limits its flight. Moreover, the wire, cable or chain can even stretch and break at startup - they will still extinguish its speed and prevent the starting engine from flying far from the container.

OPTION 5. A more interesting option is when the complex has behind the rocket a starting engine with two or more nozzles, turned outward from the longitudinal axis by an angle of 30-60 degrees (optimally 45). In this case, the jets of this engine with oblique thrust vectors, even after exiting the container, do not burn the operators, as they are directed back and side at an angle of about 45 degrees. The engine's efficiency is only 71% of its potential efficiency, but since it does not work long and weighs a little, you can come to terms with this.

This option has two advantages over the previous one, firstly, the engine can run much longer - it can take the rocket several tens of meters away from the operator, and secondly, it will allow the use of toxic components in the main engine, for example, beryllium borohydride. Starting engine fuel must be non-toxic.

To prevent dust from rising from the ground and to prevent burning of the legs of a standing operator, it is advisable for the starter engine to have two nozzles located in a horizontal plane.

OPTION 6. Mentioned starting engine / engines with oblique thrust vectors can be located in front of the rocket to the side of it, moreover, the nozzles of one or two engines should be directed in the same longitudinal plane relative to the center of gravity of the rocket - launch engine link (so that the resulting traction vector passed through the center of gravity of the ligament). In this case, even one engine will provide a rectilinear motion of the rocket.

Such an engine (s) can be mounted on a rocket using a forward inclined pin (s) entering a blind hole, or on the front handlebars (there are only two in the same plane) if they have sufficient strength. After starting and burning fuel in them, the starting engines themselves are separated.

Moreover, if you place two engines on the rudders or just direct two jets from the engine / engines on the rudders, then the rocket will be able to be controlled from the first meters of the trajectory (although this is not particularly necessary).

This option is also good because no gases come out of the back of the container - during start-up it can be immersed in water or dirt, or it can be put on the ground without the leg mentioned in the first version. The container is shorter.

This option with two engines has one drawback - if the ignition of one engine fails, the rocket will uncontrollably turn in the air, and together with the container. To eliminate this drawback, both engines should be with two diametrically located nozzles.

The engine in this embodiment should be well glued to the head part, otherwise it may come off when pulling over the head part.

OPTION 7. The recognition system "friend or foe" has a wide radiation pattern, and indeed can be deceived by modern electronics. Therefore, this MANPADS has a second optical sight of a larger magnification for the second operator.

The calculation of MANPADS works like this: the first (main) operator carries out rough aiming through a thermal imaging sight, for example, a 6-fold increase. And the second operator, looking through the second optical sight, say, 200 times, will see the target with a large increase for a short time and can visually determine its affiliation by the type of aircraft. On his handle (he may have a separate handle on the container), he will pull the trigger, which will turn off the recognition system and give permission to start.

OPTION 8. When using a radar seeker, the rocket will not see the stealth target. Therefore, in this embodiment, the complex consists of two MANPADS with radar homing heads, with the transmitter of the first missile and the receiver of the second working at the same frequency, and the transmitter of the second missile and the receiver of the first working at a different frequency.

A directional receiver may consist of four or more directional antennas with a reception sector of about ± 25-30 degrees.

The meaning of this is that the stealth target does not reflect the radio emission that hit it in the direction from which it came, but reflects it in almost all other directions. That is, the first missile highlights the target for the second missile, and vice versa.

This option works like this: in the direction of the intended location of the target at an angle of about 90 degrees, two missiles are fired simultaneously. At a given point, for example after 2 km, they turn 45 degrees so that they fly in parallel. At the same time, each rocket periodically scans (most conveniently in a spiral) the space in a sector of about ± 45 degrees at one frequency and constantly receives in the same sector a directional receiver at a different frequency. Upon detecting the reflected signal, both missiles turn towards the target.

The antennas of such a missile should have no side lobes of radiation and / or reception, otherwise the missiles will simply be turned towards each other.

One rocket must hit the target a little earlier than another. In this case, the second missile loses target illumination and may miss. To prevent this, the missile control unit has a lock when the backlight signal from another missile disappears, the lock node connected to the receiver frequency tuner switches the receiver to the frequency of its transmitter.

OPTION 9. GOS of the radar type is usually heavier than the GOS of the infrared type. That is, a missile with a radar seeker will have a warhead of less mass or will not have it at all (direct hit). To increase the likelihood of hitting a target, the complex in this embodiment contains two MANPADS - one with a radar-type missile, and the second with an infrared-type missile, and has a time relay that automatically launches an infrared missile after a specified time after the launch of the radar missile.

The meaning of this is as follows: in order to hit a target in cloud cover, in fog, in rain or snowfall, a radar missile is launched first, and after a short period of time nearby (but not from one place, so as not to burn the GOS of an infrared rocket) it starts in the same direction infrared rocket, which captures the nozzle of a radar rocket and goes into its tail with a slight lag. The lag should be such that the infrared rocket does not lose the signal from the nozzle of the radar rocket under these conditions of poor visibility, for example 0.1 s or in terms of a distance of about 100 meters at a speed of 1000 m / s.

The weight and speed of both missiles must be exactly the same. If an infrared rocket catches up with a radar, both will explode. If it lags behind, then in conditions of poor visibility it may lose radar. However, since the second missile flies in the aerodynamic trail of the first, then perhaps it should be somewhat heavier and less streamlined than the first (tests are needed).

Figure 1, 2 shows the top and side of the proposed MANPADS missile, consisting of a solid rocket checker of engine 1, the head part 2, not the same from the top and side of the stabilizers 3 (the upper and lower stabilizers are several times smaller than the side ones). On the head part there are 4 rudders (the dashed line shows the folding version of the rudders).

Figure 3, 4 shows a container 5 from above and in section (a rocket with stabilizers is shown inside). It can be seen that non-folding rudders do not significantly increase the dimensions of the container, but they simplify, facilitate and increase the reliability of the structure. And you can just make the steering wheels of the same magnitude as the stabilizers - at high speed this is not essential. The container is slightly longer than the rocket, since in this embodiment, the rear location of the starting engine is provided. If a starting engine with oblique nozzles is used, it should have small stabilizers to give it a horizontal orientation during storage and start-up.

Figures 5, 6 show, in bottom and front-rotated form, the head part of the rocket 2 with the starting engine 6, which has two jet nozzles 8 on two nozzles 7, directed at an angle of 45 degrees to the longitudinal axis of the rocket and directed to the rudders 4 (thanks to this, the rocket can be controlled at zero speed). The front starting engine slightly increases the size of the container “down”, but this does not matter, since the handle, cylinder, identification system and tablet (if any) are located in the same direction.

With this arrangement of the starting engine, the container lid should include a part of the expansion, in Fig. 3, to ensure unhindered outflow of jet jets from nozzles 8.

The MANPADS works like this: the starting engine 6 pulls the rocket out of the container 5 and takes it to a safe distance, after which the main engine 1 starts and the rocket starts flying. As the checkers of engine 1 are burned and shortened, stabilizers 3 (both wide and narrow), consisting of 15-20 smaller stabilizers, gradually fall off. The rocket is controlled in height by the rudders 4, and in the direction of the roll created by the “scissors” of the rudders 4, and again by the synchronous deviation of these rudders in the roll position, that is, as an airplane (in the control system, a gyroscope that monitors the predominantly horizontal position of the rudders 4 is desirable) .

Particular attention should be paid to the operation of the missile as a missile defense system. A feature of the open-frame engineless engine is that it can be made of any length, depending on the desired final speed. For use in the missile defense system, the missile is equipped with an engine 2-3 times longer than for MANPADS and a curly collar for the ejection launcher (the second point is on the warhead). The clamp should follow the contours of the engine with a gap with the stabilizers, that is, a hollow cross-shaped contour (after starting it is blown away by the stream). Everything else is the same.

After the alarm is announced, the fighter plane should quickly rise above the clouds, from where even without the locators the approaching warheads in the atmospheric section of the trajectory are clearly visible - they glow brightly in all ranges. Due to the high speed of the warhead, it is necessary to shoot from a distance of 40-50 km towards or 15-20 km to the side.

It will be the cheapest missile defense, because the cost of the missile is low, and the fighter after the destruction of the warhead immediately, without landing on the ground, can begin to perform its direct duties, that is, its cost is not included in the cost of the missile defense.

Claims (13)

1. A portable anti-aircraft missile system containing an anti-aircraft missile and a transport and launch container, characterized in that the transport and launch container has a cross-section in the engine part in the form of a rhombus, or an oval, or a rectangle, or a hexagonal non-axisymmetric figure. 2. The complex according to claim 1, characterized in that in the lower rear of the container there is a hinged leg for support on the ground. 3. A portable anti-aircraft missile system comprising an anti-aircraft missile and a transport and launch container, characterized in that the transport and launch container has a hinged or retractable bracket in front with a thermal imager that can be rotated in a vertical plane or in two planes, and the thermal imager is rotated using remote sensors The position is synchronized with the rotation of the movable homing missile. 4. A portable anti-aircraft missile system containing an anti-aircraft missile and a transport and launch container, characterized in that the sighting thermal imager with a monitor is located far from the container and connected to it by a cable through which the movable homing head is controlled, or the thermal imager is located in the homing head , and the monitor is in the distance. 5. A portable anti-aircraft missile system comprising an anti-aircraft missile and a transport and launch container, characterized in that the launch rocket engine with a rearward-facing nozzle / nozzles located behind the missile, and its operation time corresponding to the appearance of a nozzle cut of this engine near the front cut of the container. 6. The complex according to claim 5, characterized in that the starting engine is tied to the rear of the container with a heat-resistant cable or wire (titanium), laid in a spiral, which limits its departure. 7. A portable anti-aircraft missile system containing an anti-aircraft missile and a transport and launch container, characterized in that it has a launch engine behind the rocket with two or more nozzles that are turned outward from the longitudinal axis by an angle of 30-60 degrees. 8. A portable anti-aircraft missile system comprising an anti-aircraft missile and a transport and launch container, characterized in that it has a starting engine (s) with thrust vectors directed back and side, which is located in front of the rocket to the side of it, with one or two nozzles engines should be directed in one longitudinal plane relative to the center of gravity of the rocket - launch engine ligament. 9. A portable anti-aircraft missile system comprising an anti-aircraft missile and a transport and launch container, characterized in that it has a second optical sight of a larger magnification for the second operator. 10. A portable anti-aircraft missile system containing an anti-aircraft missile and a transport and launch container, characterized in that the complex consists of two MANPADS with radar homing heads, the transmitter of the first missile and the receiver of the second operating at the same frequency, and the transmitter of the second missile and receiver of the first operate at a different frequency. 11. The complex of claim 10, characterized in that the directional receiver contains four or more directional antennas with a reception sector of about ± 25-30 degrees. 12. The complex according to claim 10, characterized in that the rocket control unit has a lock - when the backlight signal from another rocket disappears, the lock node connected to the receiver frequency tuner switches the receiver to its transmitter frequency. 13. A portable anti-aircraft missile system containing an anti-aircraft missile and a transport and launch container, characterized in that the complex contains two MANPADS - one with a radar type missile and the other with an infrared type missile, and has a time relay that automatically launches an infrared missile through set time after launching a radar missile.

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