RU2728878C1 - Transport-launching container - Google Patents

Abstract

FIELD: astronautics.SUBSTANCE: invention relates to rocket equipment, and more specifically to transport-launching containers (TLC). TLC includes a barrel tightly closed by upper and lower covers. Upper cover of the cartridge is attached to the barrel by means of tear-off elements. Inside the shell there can be installed a rocket with a nose fairing, with possibility of performance of the upper cover of the cartridge. In the lower part the obturator is installed. Powder pressure accumulator is arranged in bottom volume of TLC. Bottom volume of TLC is connected to ventilated volume of TLC with the help of gas duct. Area of minimum flow section of the latter is selected based on the following inequalities: P< P< P, where Pis value of the static pressure of water at the maximum depth of the start; Pis attic pressure in TPK screen at the time of depressurization when starting with a maximum depth; Pis magnitude of permissible pressure on side surface of missile.EFFECT: enabling higher reliability.1 cl, 1 dwg

Description

The invention relates to rocketry and can be used in transport and launch containers (TPK) located in launchers of submarines (mainly), surface ships and ground carriers.

Known TPK (here and below, TPK means TPK assembled with a rocket), given in the description of the invention to the patent "Transport and launch module", RU 2245503, F41F 3/04, application from 03.11.2003, published 27.01.2005 It contains a beaker hermetically sealed with top and bottom lids. A rocket with a nose fairing, which is also the top cover of the glass, is installed inside the glass. The top cover of the glass is fastened to the glass using tear-off elements. An obturator is installed on the rocket in its lower part, which divides the internal free volume of the TPK into two parts: the under-roof volume of the TPK (this is the volume of the annular gap between the rocket and the glass in the section from the obturator to the top cover of the glass) and the bottom volume of the TPK (this is the volume enclosed between the bottom cover of the glass, the bottom cut of the rocket and the obturator). The bottom volume contains a pressure cylinder with a pyrovalve and a powder pressure accumulator.

The launch of a rocket from the considered TPK is as follows. At the beginning, the pyrovalve of the pressurized cylinder is triggered, the gas from which creates some pressure in the bottom volume of the TPK. Next, the powder pressure accumulator is turned on, as a result of which the pressure in the bottom volume of the TPK rises, at a certain value of this pressure, the tear-off elements break, and the rocket, together with the top cover of the glass, begins to accelerately move in the glass and leaves it.

The main disadvantage of the considered TPK is as follows. When the rocket moves in the glass during its launch, the top cover of the glass comes out of it, as a result of which the under-cover volume of the TPK loses its tightness. At this moment, the pressure in the indicated volume is ≈1 atm. Since when the rocket is launched from a great depth, the seawater pressure significantly exceeds 1 atm, in this case the seawater begins to intensively enter the under-roof volume of the TPK. The incoming water causes vibration loads that negatively affect the stability of the rocket, and water hammer, which can lead to the destruction of the rocket.

Another TPK is known, given in the description of the invention to the patent "Method for launching a rocket from a transport-launch container and a device for its implementation", RU 2544253, F41F 3/04, application dated 10.24.2013, published 03.20.2015, in which seawater does not enter the under-roof volume of the TPK. This TPK is the closest in terms of the set of essential features to the proposed TPK and is chosen as the closest analogue prototype. Known TPK contains a glass, hermetically sealed with top and bottom lids. The top cover of the glass is fastened to the glass using tear-off elements. A rocket with a nose fairing, which is also the top cover of the glass, is installed inside the glass. An obturator is installed on the rocket in its lower part, which divides the internal free volume of the TPK into two parts: the under-roof volume of the TPK and the bottom volume of the TPK. The obturator is made with the possibility of bypassing gas from the under-lid to the bottom volume of the TPK. In the bottom volume of the TPK, a powder pressure accumulator, a high-pressure cylinder with a start-cutoff valve and a pressure indicator are installed. The cut-off valve and the pressure indicator are connected to the under-lid volume of the TPK by pipelines through an obturator, while the pressure indicator is electrically coupled with the start-cut off valve.

The first disadvantage of the prototype is a rather complex system for pressurizing the TPK under-roof volume (this system means all the elements and connections between them, which ensure the pressure of the TPK under-roof volume). This system reduces the reliability of the TPK operation, and also reduces the volume of the rocket that can be placed in this TPK and has a significant cost.

The second disadvantage of the prototype is that the pressurization of the under-roof volume of the TPK is performed before the launch of the rocket, which increases the time of the pre-launch preparation of the rocket.

The aim of the proposed invention is to improve the reliability of the TPK, increase the volume of the rocket that can be placed in this TPK, reduce the cost of the TPK and reduce the time for prelaunch preparation of the rocket.

This goal is achieved by the fact that in the TPK, which contains a glass, hermetically sealed by the top and bottom covers, the top cover of the glass is fastened to the glass using tear-off elements, a rocket with a head fairing is installed inside the glass, which is also the top cover of the glass, on the lower part of the rocket an obturator is installed, and a powder pressure accumulator is placed in the bottom volume of the TPK, the following new elements have been introduced: the bottom volume of the TPK is connected to the under-roof volume of the TPK by means of a gas conduit, the minimum flow area of which is selected from the condition of the following inequalities:

P _st <P _pr <P _d ,

where P _st is the value of the static water pressure at the maximum launch depth; P _pr is the value of pressure in the under-roof volume of the TPK at the time of its depressurization at the start from the maximum depth; R _d - the value of the permissible pressure on the side surface of the rocket.

The proposed technical solution is illustrated by a drawing. FIG. 1 schematically shows the TPK, general view, longitudinal section:

1 - glass;

2 - the top cover of the glass;

3 - the lower cover of the glass;

4 - tear-off element;

5 - rocket;

6 - obturator;

7 - powder pressure accumulator;

8 - gas conduit;

"A" is the under-lid volume of the TPK (this is the volume of the annular gap between the rocket 5 and the nozzle 1 in the section from the obturator 6 to the upper lid of the nozzle 2);

"B" is the bottom volume of the TPK (this is the volume enclosed between the lower cover of the glass 3, the bottom cut of the rocket 5 and the obturator 6).

TPK contains a glass 1, which is hermetically closed by the upper cover of the glass 2 and the lower cover of the glass 3. The upper cover of the glass 2 is fastened to the glass 1 using tear-off elements 4, which can be made in various forms, for example, in the form of explosive bolts, in the form of explosive screws as shown in FIG. 1. Inside the glass 1 there is a rocket 5 with a head fairing, which is at the same time the upper cover of the glass 2. On the rocket 5 in its lower part there is an obturator 6 made, for example, in the form of a rubber ring. A powder pressure accumulator 7 is installed in the bottom volume of the TPK "B" 7. The bottom volume of the TPK "B" is connected to the under-roof volume of the TPK "A" by means of a gas duct 8. The gas duct 8 can be made in different ways, for example, in the form of a pipeline, as shown in fig. 1, or in the form of a hole in any element of the rocket 5. The area of the minimum flow area of the gas conduit is selected from the condition of the following inequalities:

P _st <P _pr <P _d ,

where P _st is the value of the static water pressure at the maximum launch depth; P _pr - the value of pressure in the under-roof volume of TPK "A" at the time of its depressurization at the start from the maximum depth; R _d - the value of the permissible pressure on the side surface of the rocket 5.

It is possible to choose the minimum flow area of the gas duct 8 that satisfies the above inequalities experimentally or by calculation, for example, as follows.

With the known under-roof volume TPK "A", thermodynamic parameters of the gas of the powder pressure accumulator 7 and the parameters of the gas in the bottom volume of the TPK "B", the relationship between the minimum flow area of the gas conduit 8 and the pressure in the under-roof volume of the TPK "A" is expressed by the following system of equations:

where P _p is the gas pressure in the under-roof volume of TPK "A";

S is the minimum flow area of the gas conduit 8;

Р _don - gas pressure in the bottom volume of TPK "B";

ρ _don - gas density in the bottom volume of TPK "B";

V is the value of the undercoat volume of TPK "A";

Q - second mass flow rate of gas through area 5;

k is the gas adiabatic index;

t is time;

max is a function that returns a value equal to the largest of its arguments.

The above system of equations is solved from the moment the powder pressure accumulator 7 starts up to the moment of depressurization of the under-lid volume of the TPK "A" and thus:

where t _p is the time from the start of the powder pressure accumulator 7 to the moment of depressurization of the under-lid volume of the TPK "A".

Time t _p is determined by the formula:

t _p = t _o + t _in ,

where t _o - the time from the start of the powder pressure accumulator 7 until the separation of the rocket 5 from the glass 1; t _{at the} time from the moment of separation of the rocket 5 from the glass 1 to the moment of depressurization of the under-roof volume of the TPK "A".

Time t _in is determined from the equation:

where h is the distance that must be covered by the rocket 5 from the moment of its separation from the glass 1 to the depressurization of the under-lid volume of the TPK "A", this distance is equal to the depth of the entry of the upper cover of the glass 2 into the glass 1;

F is the area of the bottom cut of the rocket 5;

R _st - the value of the static water pressure at the maximum launch depth;

m is the mass of the rocket 5;

g - acceleration of gravity.

Additionally, it should be noted that for clarity, in FIG. 1 gas conduit 8 and the gap between the rocket 5 and the glass 1 are greatly increased.

The proposed TPK works as follows. At the start command, a signal is given to start the powder pressure accumulator 7, as a result of which the powder gases begin to flow directly into the bottom volume of the TPK "B" and through the gas duct 8 into the under-roof volume of the TPK "A". As the propellant gases enter, the pressure in both volumes increases, while the pressure in the bottom volume of the TPK "B" increases more intensively than in the under-roof volume of the TPK "A". Under the influence of pressure in the bottom volume of the TPK "B" tear-off elements 4 break, and the rocket 5, together with the upper cover of the cup 2, breaks away from the cup 1. When the rocket 5 moves relative to the cup 1 by the amount of the entry of the upper cover of the cup 2 into the cup 1, the under-roof volume is depressurized TPK "A". At this point, with the selected area of the minimum flow area of the gas conduit 8, the pressure in the under-roof volume of the TPK will always exceed the value of the static water pressure at the launch depth, therefore the seawater cannot intensively enter the under-roof volume of the TPK "A", which excludes the occurrence of vibration loads and water hammer. Under the influence of pressure in the bottom volume of the TPK "B", the rocket 5 continues to exit the glass 1 and exits it, while it is possible that even in the process of the exit of the rocket 5 from the glass 1, its starting engine is started (this engine is not shown in the drawing) ...

When the launch depth in the proposed TPK changes, the pressure in the under-roof volume of the TPK changes at the time of depressurization of this volume. The maximum value of this pressure is reached at the start from the maximum depth, and the minimum value - at the start from the surface of the water or at the ground start.

Although very hot gas enters the undercover volume of the TPK "A", it cannot significantly heat the rocket skin, since with the accepted area of the minimum flow area of the gas duct 8, the amount of gas entering the undercover volume of the TPK is small. The calculations carried out by the authors of this invention showed that even at a start from the maximum depth, when the maximum amount of gas enters the under-roof volume of the TPK, the additional heating of the rocket skin will not exceed 50 ° C.

In the proposed TPK, the task of pressurizing the under-roof volume of the TPK is performed by a gas conduit. It is simple, reliable, compact and cheap. In the prototype, this task is performed by a rather complex system, which has a relatively large volume, relatively low reliability and relatively high cost. In the proposed TPK, the under-roof volume of the TPK is pressurized during the launch of the rocket, and in the prototype, before the launch of the rocket. The following conclusion can be drawn from the above.

The use of the proposed technical solution makes it possible to increase the reliability of the TPK operation, increase the volume of the rocket that can be placed in this TPK, reduce the cost of the TPK and reduce the time for prelaunch preparation of the rocket in comparison with the prototype.

Claims (3)

A transport and launch container (TPK) containing a glass, hermetically sealed by the top and bottom lids, the top cover of the glass is fastened to the glass using tear-off elements, a rocket with a head fairing can be installed inside the glass with the possibility of performing the function of the upper cover of the glass and having a lower part of the installed obturator, in the bottom volume of the TPK there is a powder pressure accumulator, characterized in that the bottom volume of the TPK is connected to the under-roof volume of the TPK by means of a gas conduit, the minimum flow area of which is selected from the condition of the following inequalities: P _st <P _pr <P _d where P _st is the value of the static water pressure at the maximum launch depth; P _pr is the value of pressure in the under-roof volume of the TPK at the time of its depressurization at the start from the maximum depth; R _d - the value of the permissible pressure on the side surface of the rocket.

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