RU2326339C1 - Air defence missile target - Google Patents

Abstract

FIELD: missilery.

SUBSTANCE: an air defence missile-target comprising a propulsion unit with a stabilizer, a front radiotransparent section with liquid propellant, a UHF corner reflector, a fairing and a tracer unit. On the propulsion unit side of the fairing there is a fuze safety and arming mechanism with a damaging agent, and an electric power source, a protection circuit board and a switching circuit board electrically connected to one another. Moreover, said UHF corner reflector is wound along its entire perimeter supported by the fairing facets with an insulated cable that is connected to said switching electronic board, and said liquid propellant is placed in airtight containers, wherein the longitudinal axis of said damaging agent coincides with the longitudinal axis of one of the airtight containers, and said electric power source is a pyrotechnic battery.

EFFECT: ensuring visual effects of damaging the missile target by fragments of the warhead of an air defence guided missile at a calculated acceptable miss distance and with a guaranteed changing of the missile target flight trajectory.

2 cl, 3 dwg

Description

The present invention relates to the field of rocketry and can be used at ranges as a target for training accuracy of firing personnel of combat crews of anti-aircraft missile systems, as well as during demonstration launches for advertising purposes when selling anti-aircraft missile systems.

Known anti-aircraft missile target (Russian patent No. 2135948 from 08.27.1999, BI No. 24, MPK7 F42B15 / 10 - analogue), consisting of a propulsion system with a stabilizer and a head compartment with a cowl, launched from the transport-launch device. The head compartment is made of composite material in the form of a carrier thin-walled radiotransparent shell connected by a fairing to a steel hollow tip, through which diametrical slots are made, while in the head compartment inside the shell angular microwave energy reflectors are installed, consisting of interconnected by means of grooves thin-walled metal plates with a variable pitch, and in the inner cavity of the tip there are tracks, and the total area of the slots of the tip greater than or equal to the cross-sectional area of the tracers.

This design of an anti-aircraft target missile, for all its merits: a large effective dispersion surface (EPR), illuminating the trajectory of the flight path cannot be used for demonstrative launches due to the lack of visibility of the effect of target destruction.

A known design of an anti-aircraft target missile (Russian patent No. 2196953 dated July 20, 2003, Bull. No. 2 is a prototype), consisting of a propulsion system with a stabilizer, a head radio-transparent compartment with corner reflectors of microwave energy, a fairing and a tip with tracers. The head radio-transparent compartment is made in the form of a sealed container with filling holes in the bottom, hermetically sealed plugs, while the head radio-transparent compartment is filled with liquid fuel, and the corner reflectors are fuel dampers. However, this design of the anti-aircraft target missile, for all its advantages (highlighting the trajectory of the flight path with the tracer, providing a visual effect with a direct hit and a sharp change in the flight path) has significant drawbacks, namely: when fragments get from the detonation of the warhead (warhead) of the attacking anti-aircraft guided missiles with an allowable design miss does not always provide liquid fuel ignition of the target missile, which gives the impression of a miss, since the target practically does not change its field trajectory and that the demonstration launches unacceptable.

Therefore, taking into account all the above disadvantages, the objective of the invention is to provide a visual effect of the destruction of the target missile from fragments of warheads of the anti-aircraft guided missile with an allowable design miss and a guaranteed change in the flight path of the target missile.

This is achieved by the fact that in the anti-aircraft target missile containing a propulsion system with a stabilizer, a radio-transparent head compartment with liquid fuel, a corner reflector of microwave energy, a fairing and a tracer unit, according to the invention, a safety-actuating mechanism with a combat mechanism is installed on the reflector on the side of the propulsion system element, a power source, an electronic protection board and a switching electronic board, electrically connected with each other, while the corner reflector of microwave energy for its entire around the perimeter with a support on the edge of the reflector, it is wrapped in an insulated wire connected to the switching electronic circuit board, while the liquid fuel is placed in sealed containers, the longitudinal axis of the combat element being aligned with the longitudinal axis of one of the sealed containers, and a pyrotechnic battery is used as the power source.

The essence of the invention lies in the fact that this design of an anti-aircraft target missile provides a visual effect of hitting a target missile from warhead fragments of an attacking anti-aircraft guided missile with an allowable design miss, because wire breakage inside the target missile from fragments will lead to the detonation of the warhead and ignition of liquid fuel when the sealed container is destroyed, which creates a visual effect of the destruction of the target missile at any time of the day, as well as to an instantaneous change in its flight path, and with a guaranteed miss on impact the wire breaks off on the ground in the target rocket and the target rocket explodes and lights up, thereby indicating the place of impact of the target rocket.

Figure 1, 2, 3 shows the proposed design of an anti-aircraft target missile, where:

1 - propulsion system with a stabilizer;

2 - head radiolucent compartment;

3 - corner reflector of microwave energy;

4 - liquid fuel in an airtight container;

5 - fairing;

6 - tracer unit;

7 - switching electronic board;

8 - safety-executive mechanism (PIM) with a combat element;

9 - power supply - pyrotechnic battery;

10 - electronic protection board;

11 - face of the reflector;

12 - wire;

13 - electrical connectors;

14 - the longitudinal axis of the combat element;

15 - the longitudinal axis of the sealed container.

The device, assembly sequence and operation of the anti-aircraft target missile are as follows: first, the remote control with stabilizer 1 is assembled, then the radiotransparent head compartment 2, into which the corner reflector of microwave energy 3 is installed, in the compartments of which airtight containers filled with liquid fuel 4 are installed in advance and from the side of the remote control 1, a PIM with a combat element 8 is installed, the power source is a pyrotechnic battery 9, a switching electronic board 7 and an electronic protection board 10, electrically connected to by means of electrical connectors 13, and wrapped around a spiral corner reflector of microwave energy along the entire length of the perimeter of the outer surface with support on the edge of the reflector 11 by an insulated thin wire 12, which is connected to the switching electronic board 7 via an electrical connector 13. The longitudinal axis of the combat element 14 is aligned with the longitudinal axis of the sealed container 15. Separately, the tracer unit 6 is assembled, into which an energy module with a charge of the bottom gas generator with an electric igniter is installed m, playing the role of tracers, a front corner reflector and a fairing 5. From the obtained assemblies, according to the design documentation, an anti-aircraft target missile is assembled, which is installed in a transport and launch container, connecting with electrical connectors.

The launch of the anti-aircraft target missiles is carried out from the transport and launch container installed by means of mounting brackets on the launcher, which is a conversion version of ZU-23 and having the ability to change elevation angles in the range from 0 ° to 90 ° in elevation and up to 360 ° in azimuth .

The start of the remote control 1 and tracer unit 6 is carried out simultaneously through the electronic protection board 10, while the power supply is turned on simultaneously - the pyrotechnic battery 9 and the PIM protection stage with the combat element 8, which is charged, is removed from the starting overload of the target missile, i.e. switches to combat mode ″ standby ″. In this case, hot powder gases escape from the gas ducts of the tracer block 6 from the charge of the bottom gas generator. In this case, the body of the tracer unit 6 is very hot, emitting infrared (thermal) radiation into space, which allows the anti-aircraft missile system (SAM) in thermal imaging mode to identify the target missile.

When a target anti-aircraft missile hits the firing zone, the combat calculation of an air defense missile system captures and simultaneously accompanies the target with the reflected signal from the corner reflectors of microwave energy 3 and infrared radiation, launches an anti-aircraft guided missile to intercept the target. When an anti-aircraft guided missile approaches a target for a calculated permissible miss, a non-contact target sensor is triggered, undermining the warhead of an anti-aircraft guided missile. In this case, fragments in the form of steel rods located around the warhead fly apart, hitting the target. When fragments hit the target missile, a thin wire 12 is wound around the corner reflector of microwave energy 3, the switching electronic board 7 is triggered, sending the command through the PIM to undermine the warhead coaxially mounted with a sealed container filled with liquid fuel. In this case, the visual effect of the destruction of the target rocket will occur, which, having broken, will change its ballistic trajectory and fall to the ground. In the case of a guaranteed miss, more than the calculated target, the target rocket will continue to fly along the ballistic trajectory and, falling to the ground, will explode and catch fire, indicating the place of impact.

PIM - designed to prevent unauthorized operation of a combat element, it is cocked from the starting overload acting on the target missile. The cumulative combat element is borrowed from an anti-tank missile and is intended to destroy the tank’s active defense, and is mounted on a corner reflector of microwave energy to overcome obstacles and ignite liquid fuel in an airtight container.

The electronic protection board is designed to prevent unauthorized operation of the remote control and the electric igniter of the tracer unit from static interference of the entire electrical circuit and its components.

The switching electronic board is designed to carry out the PIM charging by sequentially removing its protection stages and preparing the circuit for initiating its electric detonator, and when the wire is broken by fragments of warheads, it transmits a command to undermine the combat element.

When winding a corner reflector of microwave energy with a thin wire, its effective dispersion surface (EPR) decreases. In order not to cause significant damage to the EPR by a wire wound around the corner reflector, the wire is wound in a spiral with a design pitch so that it takes no more than 15% of the EPR from the corner reflector. When selecting an EPR of more than 15%, there will be no capture and tracking of the target by the locator, which is unacceptable.

Claims (2)

1. Anti-aircraft target missile containing a propulsion system with a stabilizer, a head radiotransparent compartment with liquid fuel, a corner reflector of microwave energy, a fairing and a tracer unit, characterized in that a safety-actuating mechanism with a combat element is installed on the reflector on the side of the propulsion system, power supply, electronic protection board and switching electronic board, electrically connected with each other, while the corner reflector of microwave energy over its entire length along the perimeter with supports on the edge of the reflector is wrapped with an insulated wire connected to a switching electronic circuit board, which is capable of transmitting a command to detonate a combat element when the wire is broken, while the liquid fuel is placed in sealed containers, and the longitudinal axis of the combat element is aligned with the longitudinal axis of one of the sealed containers . 2. Anti-aircraft target missile according to claim 1, characterized in that a pyrotechnic battery is used as a power source.

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