RU2167390C1 - Guided anti-aircraft missile - Google Patents

Abstract

FIELD: rocketry. SUBSTANCE: guided anti- aircraft missile has a detachable zero stage and a sustainer stage with a radio-command control equipment and a luminous radiator unit in the rear section of the stage. Installed in the luminous radiator unit in a luminous element is a pulse laser semiconductor radiator made in the form of a solid cylindrical heat-accumulating casing, hermetically closed by a cover with a glass outlet port. Radiating crystal diode units are installed inside the casing on the circular surface of the insulator - heat sink uniformly in the circumference in different planes and at an angle to each other. EFFECT: enhanced noise immunity of the optical communication line, reduced power consumption and overall dimensions of the optical radiator. 3 dwg

Description

 The invention relates to the field of rocketry and can be used in both large and small-sized missiles launched from transport and launch containers.

 Known anti-aircraft guided missile [1] complex "Tunguska" - solid fuel, two-stage bicaliber with a detachable starting engine - made according to the scheme "duck". The marching stage has a rod warhead of large elongation, control equipment and a block of continuous light radiation - a tracer.

 The disadvantages of this rocket are the low noise immunity of the optical communication line of the rocket with the ground-based optical direction finder, and the large overall dimensions of the tracer.

 Known anti-aircraft guided missile [2] complex "Tunguska-M1", which is located in the transport and launch container, is made according to the bicaliber scheme and consists of a marching stage and detachable by the separation mechanism of the launch stage. The march stage consists of combat equipment, including a fragmentation-rod warhead, contact and non-contact fuses with a head fairing, and functional blocks containing a steering gear, gyroscopic coordinator, electronic equipment, a high-frequency unit and a light emitter unit in the form of a pulsed light source - a lamp- headlights, with a semi-automatic, radio command optical link with the control system.

However, this anti-aircraft guided missile, with all its advantages, has a number of disadvantages:
1. The use of a headlight lamp with a reflector does not exclude the effect of flickering light noise and fluctuation background from sun exposure on the ground-based optical direction finder.

 2. The headlamp has a wide spectrum of radiation from infrared to ultraviolet, while in the direction finder of the ground equipment, the sensitive element, due to its relative narrowband, receives only part of the energy, which reduces the energy efficiency of the optical communication line with significant energy consumption on board the rocket from the source nutrition.

 3. The lamp-headlight requires the use of a high-voltage pulse source of ignition voltage, a large-diameter reflector, which leads to significant dimensions of the emitter unit, and therefore, to an increase in the dimensions of the march stage.

 The objective of the invention is to eliminate the above disadvantages, namely: increasing the noise immunity of the optical communication line from flickering noise and fluctuation background from sun exposure, increasing the energy efficiency of the optical communication line, reducing the power consumption of the optical emitter while reducing its size.

 This task is achieved by the fact that in an anti-aircraft guided missile, consisting of a detachable launch stage and a march stage with control equipment with a light emitter unit installed in the rear part of the march stage, a pulsed laser semiconductor emitter is installed as a light element, which is made in the form of a continuous cylindrical heat-accumulating case hermetically closed by a lid with a glass exit window, inside of which on the annular surface and olyatora heatsink-uniformly along the circumference and in different planes at an angle to each other are installed crystalline emitting laser diode units.

 The essence of the invention lies in the fact that this design of the anti-aircraft guided missile allows to increase the noise immunity of the optical communication line when installing an optical filter with a passband equal to the spectral width of the light emitter in the ground optical direction finder due to the monochromatic radiation of the laser emitter in the infrared region, to increase the optical efficiency communication lines due to the concentration of a large amount of energy in a narrow spectral density, reduce energy consumption reduction, reduce the size due to microminiaturization of the light emitter unit.

On the proposed drawings (Fig. 1) shows the proposed design of anti-aircraft guided missiles, where:
1 - starting stage;
2 - march stage with control equipment (Fig. 2);
3 - the back of the marching stage;
4 - block light emitter;
5 - pulsed laser semiconductor emitter (Fig. 3 and 4);
6 - emitter housing;
7 - a cover with a glass exit window;
8 - the annular surface of the insulator - heat sink;
9 - crystalline laser diode blocks.

 The device of a pulsed laser semiconductor emitter is as follows: a pulsed laser semiconductor emitter 5 has a massive copper heat-storage casing 6, inside of which on the annular surface of the insulator - heat sink 8 are mounted uniformly around the circumference, in different planes and at an angle to each other, crystal laser diode blocks 9, which are interconnected in parallel chains of two series-connected blocks in each chain and are hermetically sealed under pressure in environments e inert gas "argon" cover 7 with a glass exit window.

 Since the pulsed laser semiconductor emitter is located in the radiation unit, i.e. in a small limited volume of air and the absence of forced convection and effective heat sinks outside this volume, the heat-accumulating case in the form of a solid copper cylinder provides the necessary heat removal from laser crystals and guarantees continuous operation of the emitter with maximum light power, ensuring all missile flight time.

 Emitting crystal laser diode blocks are mounted uniformly around the circumference in various planes and at an angle to each other, to ensure uniform filling of the spatial cone by radiation, forming the radiation pattern.

 The assembly sequence and operation of the anti-aircraft guided missile is as follows: first, the launch stage 1, consisting of an engine with a solid fuel charge and an installed stabilizer, is assembled, then the march stage 2, which consists of combat equipment and control equipment with a light emitter 4 unit with a pulsed laser semiconductor, is assembled emitter 5, which is installed in the rear part 3 of the march stage 2, the emitter in the direction opposite to the movement of the rocket. The assembled marching and starting stages are interconnected by means of a separation mechanism.

 During the flight of an anti-aircraft guided missile at the launch site until the engine of the launch stage ends, the light flux from the torch of the launch engine enters the continuous channel of the optical direction finder, combined with the optical sight of the anti-aircraft control system. When the starting engine is separated, the radiation unit with a pulsed laser semiconductor emitter is switched on, from which the laser pulse enters the pulse channel of the rocket direction finder, aligned with the continuous direction finding channel, and is converted into an electrical signal proportional to the deviation of the rocket from the target line of sight. The electric signal is fed to a digital computer system that generates control commands that are encrypted and transmitted through the target tracking station in the form of code packets to the rocket.

 At the same time as the control commands, the target tracking station transmits a code message to start the laser emitter. The on-board equipment decrypts these code messages and generates steering control commands and starts the laser emitter. The missile is displayed on the line of sight and held on it with high accuracy.

 The use of a laser emitter, which allows one to concentrate a large amount of energy in a narrow spectral band at high efficiency, provides absolute noise immunity of the optical communication line, makes it possible to hit targets equipped with any type of optical interference with high probability.

Sources of information
1. Magazine of the Military-industrial complex "Military Parade", November-December 1994, article "Anti-aircraft gun and missile system" Tunguska ", pp. 139-141 - analogue.

 2. Magazine of the Military-industrial complex "Military Parade", May-June 1999, the article "Tunguska" becomes more effective ", pp. 86 - 88, and March-April 1999, the article" Antiaircraft gun-missile complex "Tunguska -M1 ", p. 20 is a prototype.

Claims (1)

 Anti-aircraft guided missile, consisting of a detachable launch stage and march stage with radio command control equipment and a light emitter unit installed in the rear part of the stage, characterized in that a pulsed laser semiconductor emitter is installed as a light element in the light emitter unit, which is made in the form of a solid a cylindrical heat-retaining case, hermetically sealed by a lid with a glass exit window, inside of which on the annular surface of the insulator The heatsinks are distributed uniformly around the circumference in various planes and at an angle to each other, emitting crystalline laser diode blocks.

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