RU2544253C1 - Method of missile takeoff from transporter-launcher container and device for its implementation - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: method of missile takeoff from the transporter-launcher containers (TLC) consists in inflation with the gas which does not support combustion of sub-cap volume of TLC with simultaneous ingress of gas through the obturator in the bottom volume, after which the inflation is switched off when achievement of the desired pressure in the sub-cap container volume, followed by inflation of the bottom volume of the container with gases from powder pressure accumulator (PPA). The device for implementation of missile takeoff from the TLC comprises an obturator, a PPA, a high-pressure cylinder with an on-off valve connected to the sub-cap container volume by the pipeline, a pressure indicator unit with the pipeline, the opposite end of which is located in the sub-cap container volume.

EFFECT: creation of conditions for reliable underwater missile takeoff from TLC by eliminating hydraulic, oscillating and vibrating effects on the missile housing.

2 cl, 2 dwg

Description

The group of inventions relates to rocket technology and can be used in transport and launch containers (TPK) located in the launchers of predominantly submarines.

Known transport and launch container (module) described in the description of the invention to the patent of the Russian Federation No. 2225503, F41F 3/04, 2005, which is the closest in the set of essential features with the proposed technical solution and which is selected as the closest analogue.

Known TPK contains a sealed enclosure in the form of a glass with front and rear covers with a seal, a rocket is installed inside the housing with a head fairing detachable in flight, which is also the front cover of the container. TPK is equipped with detachable elements for fixing and holding the rocket and an obturator located in the bottom of the rocket, dividing the internal cavity of the container into two parts - the bottom volume and the axillary. Using the brackets, detachably installed on the back cover of the TPK means for creating the off-target (bottom) volume of a given value, including a pressurized balloon with a pyro-valve that does not support combustion, and a powder pressure accumulator (PAD).

In the well-known TPK, a rocket launch method is implemented, which includes the following steps.

According to the “start” signal, the pyrovalve of the boost cylinder is triggered and the gas not supporting combustion creates pressure in the bottom volume of the container. Then, according to the signals, the pyromedia of devices connecting the top cover of the container (the head fairing of the rocket) with the container body (the glass) is triggered, and at the same time the PAD is activated, as a result of which, due to the presence of the shutter, the gases emitted during the combustion of the PAD create increased pressure, and the rocket like a piston in a cylinder, it begins to move along the cylindrical surface of the container glass. When the rocket is moved a certain distance, the rocket engine is turned on, which emerges from under the water and flies toward the target.

The main disadvantage of the TPK, which implements the rocket launch method described above, is the inflow of overboard water into the lining volume of the container, which is associated with its depressurization at the time of rocket launch. The flow of water is due to the fact that the pressure of the outside water is higher than the pressure of the gaseous medium in the axillary volume due to the fact that pressurization of non-supporting gas from the cylinder is carried out into the bottom volume of the container, which is separated from the axillary volume by a seal. The incoming water creates hydraulic, vibrational and vibrational loads on the rocket body, which negatively affects the stability of the rocket's movement, and as a result of a hydraulic shock, rocket destruction can occur.

The aim of the proposed invention is the creation of conditions for reliable underwater launch of the rocket from the TPK by eliminating the hydraulic, vibrational and vibrational effects on the rocket body when the rocket begins to move, caused by the flow of water into the lining volume of the container.

This goal was achieved due to the fact that when the rocket starts from the TPK, the inflator of the container underbody volume is carried out with gas that does not support combustion with the simultaneous flow of gas through the obturator into the bottom volume, after which the boost is turned off when the required pressure in the container undercover volume is reached, followed by the container bottom volume gases from the powder pressure accumulator.

The initial operations at the launch of a rocket from the TPK according to the proposed method, namely, the initial pressurization of the underwing volume of the container (which is actually an annular gap between the rocket and the TPK) to the necessary pressure, prevents the outboard water from entering it when the TPK is depressurized due to the start of the rocket movement. At the same time, a “dry” launch of the rocket is realized over the entire section of its exit from the TPK.

The pressurization pressure of the container liner volume is determined in advance taking into account the maximum possible immersion of the carrier for launching the rocket from the TPK and its value is greater than the water pressure acting on the top cover of the container.

To implement a new method of launching a rocket from TPK, a device is proposed that includes an obturator installed in the bottom of the rocket and a powder pressure accumulator installed in the bottom volume of the container, a high-pressure cylinder with a pyrovalve. New in the proposed device is that the cylinder with a pyrovalve, made shut-off, is connected to the under-roof volume of the container by a pipe passing through the obturator, which is made of profiled elastic material with the possibility of transferring pressurization gas from the under-roof to the bottom volume of the container, while the pressurization system of the container is provided a pressure switch installed in the bottom volume of the container with a pipe connected to it, the opposite end of which is located in the axillary volume IU container, wherein the pressure switch is electrically coupled to puskootsechnym valve.

The proposed technical solution is illustrated by drawings. Figure 1 schematically shows the TPK, a General view, a longitudinal section:

1 - a glass of TPK;

2 - TPK front cover (rocket head fairing);

3 - back cover TPK;

4 - rocket;

5 - shutter;

6 - high pressure cylinder with a gas that does not support combustion;

7 - start-off valve;

8 - pipeline connecting the start-off valve with the axillary volume of the TPK;

9 - pressure signaling device;

10 - pipeline connecting the pressure switch with the axillary volume TPK;

11 - powder pressure accumulator;

"a" is the axillary volume of the TPK (in the form of an annular gap) between the front cover 2 of the TPK and the obturator;

"b" - the bottom volume of the TPK - between the obturator and the back cover 3 TPK.

Figure 2 shows the obturator and the TPK section at the installation site of the obturator.

Units of the pressurization system with a non-burning gas - high pressure cylinder 6, start-up valve 7, pipelines 8, pressure switch 9 with pipeline 10 are placed on an arm (which can be made in the form of a cross-shaped frame) installed in the bottom volume of the container.

Pneumatic connection of the start-off valve 7 with the axillary volume TPK "a" is carried out by pipeline 8.

The obturator 5 is located in the bottom of the rocket 4 and is made of an elastic (rubber-like) material, profiled so that with increasing gas pressure in the underwing volume of the TPK when it is pressurized, the obturator is wrung out from the cylindrical surface of the glass, making it possible to bypass the boost gas from the underwing volume "a "into the bottom volume" b "of the container. The shape of the obturator 5 in cross section can be made, for example, "G" -shaped with an obtuse angle between the sides.

Bypassing from the axillary volume “a” to the bottom volume “b” of the container of a non-burning supercharging gas excludes the possibility of burning out rocket fuel inside the TPK, which reduces the thermal erosion effect on the TPK design.

PAD 11 is installed on the back cover 3 TPK using brackets.

The installation of the pressure indicator 9 precisely in the bottom volume "b" of the container is due to the small gap between the rocket 4 and the glass 1. In this gap, it is possible to place only a small diameter pipe 10 that pneumatically connects the pressure indicator 9 with the underwing volume "a" of the TPK. To signal to stop the boost of volume "a", the signaling device 9 is electrically connected to the start-off valve through, for example, starting equipment.

The proposed device for implementing a new method of launching a rocket from TPK works as follows.

In accordance with the cyclogram, when the rocket is launched, a signal is triggered to trigger the shut-off valve 7, as a result of which gas (for example, nitrogen) under pressure in the cylinder 6, which does not support combustion, enters through the pipe 8 into the axillary volume "a" of the TPK, where it is localized due to the obturator 5. With increasing pressure in the axillary volume “a”, the gas presses the cuff of the shutter off the wall of the glass 1 and begins to flow into the bottom volume of the container “b”.

When the required gas pressure is reached in the axillary volume of the container, which is controlled by the pressure switch 9 through line 10, pressurization is turned off by applying a signal to close the shut-off valve 7.

Further, in accordance with the sequence diagram, a signal is sent to activate the pyromedical devices (not shown) that pair the front cover 2 of the container with the glass 1, and simultaneously use the PAD 11, which, as a result of combustion, produces gases that create high pressure in the bottom volume of container “b” . Under the influence of this pressure, the rocket 4 together with the head fairing 2, which is also the front cover of the container, detaches from the glass 1 and begins to move along its cylindrical surface.

After a certain period of time, the rocket engine is turned on (not shown in the drawing), which leaves the carrier’s TPK, moves in water, leaves the water, and flies to the target.

Thus, the proposed method of launching a rocket from TPK and a device for its implementation implement the initial operations when starting a rocket from TPK, consisting in a certain sequence of pressurizing parts of the volume of TPK (axillary "a" and bottom "b"), and thereby exclude water hammer, as well as vibrational and vibrational effects on the rocket body at the beginning of its movement, which increases the reliability of the integrated design of the rocket and TPK.

Claims (2)

1. A method of launching a rocket from a transport and launch container, including creating excess pressure in the bottom volume of the container by successively pressurizing the container with gas not supporting the combustion system from the pressurization system and pressurizing the gases from the powder pressure accumulator, followed by turning on the rocket engines, characterized in that the container has a liner volume they carry out a gas that does not support combustion with the simultaneous flow of gas through the obturator into the bottom volume; the boost is switched off when the required pressure is reached pouring in the axillary volume of the container with subsequent pressurization of the bottom volume of the container with gases from the powder pressure accumulator. 2. A device for launching a rocket from a transport and launch container, including an obturator installed in the bottom of the rocket and a powder pressure accumulator installed in the bottom of the container, a high-pressure cylinder with a pyrovalve, characterized in that the cylinder with a pyrovalve made by the shut-off valve is connected to the axillary the volume of the container by a pipeline through the obturator, which is made of profiled from elastic material with the possibility of bypassing the boost gas from the axillary to the bottom volume of the container nera, while the container pressurization system is equipped with a pressure switch installed in the bottom volume of the container with a docked pipe, the opposite end of which is located in the under-liner of the container, and the pressure switch is electrically connected to the start-off valve.

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