RU2317511C1 - Anti-aircraft target missile - Google Patents

Abstract

FIELD: rocketry, applicable at proving grounds as a target object.

SUBSTANCE: an infra-red radiation unit in the form of a thick-walled shell with through diametrically arranged slotted gas passages is installed in the nose compartment of the anti-aircraft target missile before the corner reflector. A power module in the form of a case with an annular diaphragm and outside tubular gas passages perpendicular to one another and aligned with the slotted gas passages is installed in the shell cavity coaxially with the longitudinal axis of the target missile. A charge of the bottom gas generator with a piston and an initiator is installed in the case inner cavity of the power module. The power module end face is tightened up to the stop of the shell by the front corner reflector of SHF energy installed in the shell in alignment with the longitudinal axis of the target missile and closed with a radiotransparent ballistic fairing.

EFFECT: provided detection of the target missile by the radars of the anti-aircraft missile complex in the radar and infra-red imaging modes at any angles of direction of its flight.

2 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 (SAM).

Known anti-aircraft missile target (Russian patent No. 21395948, IPC 7 F42B 15/10, BI No. 24, 08/27/1999, prototype), 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, on the case of which there are made through diametrical slots, while in the head compartment inside the shell angular reflectors of microwave energy are installed, consisting of interconnected by means of grooves thin-walled mutually perpendicular metal plates with a variable pitch, and tracers are installed in the inner cavity of the tip, and the sum Naya tip slits area greater than or equal to the cross-sectional area of tracers.

This design of an anti-aircraft target missile, with all its advantages, has the following disadvantages:

1) a short operating time of the tracers, since the tracers are switched on simultaneously with the engine starting and the tracers are ignited from each other, which gives an increase in the brightness of the glow and a slight increase in time by the difference between the ignition of the second tracer. An increase in the operating time of the tracer will lead to a significant increase in its dimensions and, as a result, to an increase in the dimensions of the target rocket, which is unacceptable, since the target missile in its dimensions must correspond to simulated targets, which include high-speed unmanned means of attack of a likely enemy;

2) when the target missile is operating on itself, when the mid-section of the target missile is perpendicular to the direction of flight and equal to the caliber of the target, at a great distance of 18 ÷ 20 km, it is not always captured by the radar of the SAM detection station operating in radar modes when the target is illuminated by microwave the energy of the locator, which, reflected from the angular reflector of the target rocket located along the rocket, dimly indicates itself on the monitor, or in the thermal imaging mode (infrared) due to the rapid cooling (cooling) of the target tip bubbled tracers, which is why the target is not visible. Therefore, the object of the invention is to eliminate the above disadvantages, namely the creation of a universal design of the target missile detected by radar and thermal imaging radar and radar modes at any angles of flight direction 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 a corner microwave energy reflector, according to the invention, an infrared radiation unit in the form of a thick-walled shell with through diametrically located shells is installed in front of the microwave corner energy reflector slotted gas ducts, while in the cavity of the shell coaxially to the longitudinal axis of the target missile, an energy module is installed in the form of a housing with an annular diaphragm and outer perps dicular to each other by tubular gas ducts coaxially aligned with the slotted gas ducts of the shell, while the charge of this gas generator with a piston and initiator is installed in the inner cavity of the housing of the energy module, and the energy module is pressed against the shell against the end by the front corner reflector of microwave energy installed in the shell coaxial with the longitudinal axis of the target missile, and covered by a radiolucent ballistic radome. The essence of the invention lies in the fact that this design of an anti-aircraft target missile with an infrared block and a front corner reflector of microwave energy under a radiolucent radome mounted in the middle of the target missile allows the SAM to detect, track and destroy this target missile flying under any angle of attack, both in radar mode and in thermal imaging mode at any time of the day, regardless of weather conditions in real time.

In the attached drawing (figure 1, 2) 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 - block infrared radiation;

5 - thick-walled steel shell;

6 - slotted gas ducts of the shell;

7 - energy module;

8 - housing of the energy module;

9 - annular diaphragm;

10 - tubular gas ducts;

11 - the internal cavity of the housing;

12 - the charge of this gas generator;

13 - a piston;

14 - initiator;

15 - front corner reflector of microwave energy;

16 - radiolucent ballistic fairing;

17 - the top of the corner reflector;

18 - pin;

19 - groove of the annular diaphragm;

20 - annular ledge of the shell.

The device, assembly sequence and operation of the anti-aircraft target missile are as follows: first, a propulsion system with a stabilizer 1 is assembled, then a radio-transparent head compartment 2, in which a corner reflector of microwave energy 3 is installed, and docked with each other.

Separately, the energy module 7 is assembled in the form of a steel casing 8 with an annular diaphragm 9 and external tubular gas ducts perpendicular to each other, while the bottom gas generator 12 is charged with the piston 13 and initiator 14 in the internal cavity of the energy module casing 8 and inserted coaxially with the longitudinal axis of the rocket targets in a thick-walled shell 5, coaxially aligning the tubular gas ducts 10 with the slotted gas ducts 6 of the shell 5, and the grooves 19 with the centering diametrically located pins 18. Then the energy module 7 are pressed by the front corner reflector 14 into the annular ledge 20 of the thick-walled shell 5 (made, for example, of steel) coaxially to the longitudinal axis passing through the top 17 of the front corner reflector of microwave energy 15 and closed with a radio-transparent ballistic fairing 16, thereby obtaining an infrared block radiation 4, which is aligned coaxially with the radiolucent head compartment 2. Thus, the obtained anti-aircraft missile target is installed in the transport and launch container, joining 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 . When starting the propulsion system 1, the initiator 14 mounted in the piston 13 is simultaneously triggered, the hot powder gases of which through the throttle bore of the piston move the charge igniter of the bottom gas generator 12. In this case, the piston shoots forward of the power module body, where it remains, the target rocket leaves the transport launch container. Hot powder gases of the charge of the bottom gas generator, in the form of a flame passing through the body through tubular gas ducts combined with slotted gas ducts of the shell, burst out. At the same time, the housing of the energy module is very hot to a temperature of about 500 ° C, transferring heat to a thick-walled steel shell, which emits infrared (thermal) radiation into space. Since the charge of the bottom gas generator works (heats) throughout the flight of the target rocket, the shell is constantly maintained at a temperature above 100 ° C, which allows it to be identified as a target in the thermal imaging mode. When the anti-aircraft target missile hits the firing zone, the SAM combat calculation simultaneously accompanies the target with the reflected signal from the corner reflectors of microwave energy and infrared radiation and launches the anti-aircraft guided missile to intercept the target.

External trajectory measurements to determine the missile value of a guided missile during the passage of a target missile accompany the target missile by the torch of the charge of the bottom gas generator, which makes it possible to obtain the coordinates of the target missile and the coordinates of the point of detonation of the warhead of the anti-aircraft guided missile on a video (photo) film.

Claims (1)

An anti-aircraft target missile containing a propulsion system with a stabilizer, a radiolucent head compartment with a corner reflector of microwave energy, characterized in that an infrared radiation unit is installed in the head compartment in front of the corner reflector in the form of a thick-walled shell with through diametrically located slotted gas ducts, while in the cavity shell coaxially to the longitudinal axis of the target missile, an energy module is installed in the form of a housing with an annular diaphragm and outer tubular heights perpendicular to each other by coaxially aligned with the slotted gas ducts of the shell, a charge of the bottom gas generator with a piston and initiator is installed in the inner cavity of the housing of the energy module, and the energy module is pressed against the shell end-to-end by the front corner reflector of microwave energy installed in the shell coaxially with the longitudinal axis of the target missile , and covered with a radiolucent ballistic radome.

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