RU2350887C1 - Device to launch guided missile - Google Patents

Abstract

FIELD: weaponry.

SUBSTANCE: invention relates to rocket production. Device comprises container with bottom chamber representing accumulator with solid propellant charge and pyro-igniter, obturator with seals fixed on the guided missile and to be separated there from at the missile flight end and obturator stops. In compliance with the invention, the proposed device differs in that the obturator represents piston attached to the guided missile tail part on the nozzle face and comprises central part extending in the missile engine nozzle. It also incorporates tight peripheral part bent towards the missile. Note here that the pressure source is fastened on the obturator central part and has its nozzle oriented towards the container bottom.

EFFECT: reduced damages of missiles assemblies due to ruling out effects of accumulator effluent gases.

4 cl, 3 dwg

Description

The invention relates to rockets, and in particular to launchers for guided missiles, and can be used to create launchers.

A device for launching a guided projectile is described in RF patent No. 2114371, which is taken as a prototype containing a container with a bottom chamber, a pressure source in the form of accumulators with solid fuel charges and pyro-candles, mounted on the projectile in the annular gap between the projectile and the container, a seal obturator with seals with the possibility of separation from the projectile at the end of its movement, stops for the shutter.

The common essential features with the proposed technical solution are as follows: a device for launching a guided projectile contains a container with a bottom chamber, a pressure source in the form of an accumulator with a charge of solid fuel and pyro-candles, an obturator with seals mounted on a guided projectile with the possibility of separation from it at the end of the projectile , and stops for the shutter.

The disadvantage of this design is the effect of high-temperature gases under high pressure, flowing out of the batteries with solid fuel charges during their operation, on the projectile during its movement in the container, which can lead to damage to the shell, plumage and components of the projectile.

The present invention solves the technical problem of eliminating the effects of high-temperature gases under pressure flowing from a battery with solid fuel charges on a rocket when it is launched from the container.

To achieve the named technical result, in a device for launching a guided projectile containing a container with a bottom chamber, a pressure source in the form of an accumulator with a charge of solid fuel and a pyro-candle, an obturator with seals mounted on a guided projectile with the possibility of separation from it at the end of the projectile movement, and stops for the obturator, the obturator is made in the form of a piston mounted on the tail of the guided projectile along the nozzle exit, and includes a central part protruding into the nozzle of the projectile engine, and metichnuyu peripheral portion concave in the direction of the projectile, wherein the pressure source is mounted on the central portion of the obturator and its nozzle directed toward the bottom of the container.

In addition, to prevent impact when the shutter stops at the stop at the end of the stroke, the stop is made in the form of a casing fixed to the inside of the container wall, which contains a torus container made of elastic film filled with oil, and a catcher and rod in the form of a cone are mounted on the shutter bushings.

In addition, to ensure the strength and rigidity of the casing with the capacity of the container wall and the casing are connected by screws, and corresponding slots are made on the rod.

In addition, to relieve pressure from the container after the launch of the projectile, the container is equipped with a gas discharge device from the pressure source.

Distinctive features of the proposed device from the above are the following: the obturator is made in the form of a piston mounted on the tail of the guided projectile along the nozzle exit, and includes a central part protruding into the nozzle of the projectile engine and a sealed peripheral part concave towards the projectile, while the source pressure is fixed on the central part of the shutter and is oriented by its nozzle to the bottom of the container. In addition, the emphasis is made in the form of a casing fixed on the inside of the container wall, in which a torus container made of an elastic film filled with oil is placed, and a catcher and a rod in the form of a conical sleeve are fixed on the obturator; the walls of the container and the casing are connected by screws, and corresponding slots are made on the rod; openings are made in the central part of the shutter protruding into the nozzle of the projectile engine.

Due to the presence of these distinctive features, the following technical result is achieved: the influence of high-temperature gases under pressure on the body, plumage and shell units is excluded, which eliminates their damage.

The proposed technical solution can find application in the design and manufacture of devices for launching rockets.

The proposed device for launching a guided projectile is illustrated by the drawings shown in figures 1, 2, 3.

Figure 1 shows a longitudinal section of a device.

Figure 2 shows a section aa.

Figure 3 shows the element B of figure 1.

Presented in figure 1, 2, 3, the device for launching a guided projectile contains a container 1 with a bottom chamber 2, a pressure source - an accumulator 3 with a charge of solid fuel and a pyro-candle 4, a shutter 5 with seals 6.

The obturator is based on the tail of the projectile 7 along the belt 8 of the bottom cut of the nozzle 10. The pressure source 3 is mounted on the obturator 5 with a flange 9 and placed inside the nozzle 10 of the projectile 7. The nozzle 11 of the pressure source 3 is directed to the bottom of the container 1, which reduces the effect of hot gases on the shutter 5.

In order to soften the blow of the shutter 5 at the end of the stroke against the stop, the stop is made in the form of a casing 12, bolted 13 to the wall of the container 1; In this case, a torus container 14 with oil is placed in the casing 12, and a trap 15 and a rod in the form of a conical sleeve 16 are mounted on the obturator 5. To increase the strength and rigidity of the structure, the casing 12 and the wall of the container 1 are connected by screws 17, and for their passage when moving on the corresponding grooves 18 are made to the tapered sleeve 16. For bleeding hot gases from the container 1 after the projectile 7 is launched, a special device is provided in the container 1 (not shown in the drawings), which can be made in the form of holes or a valve and placed in any part of the bottom oh the chambers 2.

The reusability of the use of the device to launch a guided projectile is provided by replacing a torus tank with oil 14 and a pressure source 3 with a pyro-candle 4.

The device operates as follows.

At start-up, pyro-candle 4 is triggered and solid fuel in the battery 3 is ignited. The evolved gases through the nozzle 11 enter the chamber 2, and acting on the sealed wall of the obturator 5, they move it, and with it the projectile 7 to the exit of the container 1. At the end of the stroke, the obturator 5 stops at the stop, and the projectile 7 flies away.

When the shutter stops, the conical sleeve - the rod 16 first deforms, and then breaks the torus tank 14 with oil, damping the impact and significantly reducing its level; the oil is drained into the trap 15.

After the projectile leaves the container, hot gases from the pressure source exit the container 1 through a gas bleed device.

Claims (4)

1. A device for launching a guided projectile containing a container with a bottom chamber, a pressure source in the form of an accumulator with a charge of solid fuel and pyro-candles, an obturator with seals mounted on a guided projectile with the possibility of separation from it at the end of the projectile movement, and stops for the obturator, characterized the fact that the obturator is made in the form of a piston mounted on the tail of the guided projectile along the nozzle exit, and includes a central part protruding into the nozzle of the projectile engine and a sealed peripheral part, concave towards the projectile, while the pressure source is fixed on the central part of the obturator and is oriented by its nozzle to the bottom of the container. 2. The device according to claim 1, characterized in that the emphasis is made in the form of a casing fixed on the inside of the container wall, in which a torus container of elastic film filled with oil is placed, and a catcher and a rod in the form of a conical sleeve are mounted on the obturator. 3. The device according to claim 2, characterized in that the walls of the container and the casing are connected by screws, and corresponding slots are made on the rod. 4. The device according to any one of claims 1 to 3, characterized in that the container is equipped with a device for bleeding gases from the pressure source after the launch of the projectile.

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