KR830001722Y1 - Rocket Exhaust System - Google Patents

Abstract

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Description

Rocket Exhaust System

1 is a front view of a specific facility according to the present invention.

2 is a front view of another specific equipment according to the present invention.

3 is a plan view of a plant according to the present invention showing the details of the rocket launch tube.

4 is a plan view of another installation according to the present invention.

The present invention relates to a flow-controlled exhaust manifold device, and in particular to an apparatus for controlling the flow of exhaust gas from a plenum chamber serving as a common exhaust manifold for a number of rocket launch tubes. It is about.

When ignited inside the rocket launch tube, the exhaust gases must be discharged to a safe place. This is a particular problem when rockets are installed under the ship's deck or underground. Exhaust gases are collected and directed to exhaust using an exhaust manifold installed under the rocket exhaust nozzle. The exhaust manifold controls and seals the exhaust to a safe place and releases it into the atmosphere.

During regular firing, the exhaust flows through the launch tube into the exhaust manifold until the rocket leaves the launch tube smoothly.

Rocket exhaust is usually high in hydrogen and carbon monoxide. These gases react with the air in the exhaust manifold, causing combustion heat and explosive potential. They also generate higher manifold pressures than desired.

Various structures are well known for controlling and directing rocket exhaust gas, such as safety doors or gas valves, which operate to return the exhaust gas into the associated manifold when the rocket is ignited. In addition, exhaust manifolds with large open ends are known for rockets stored in other ways than launch tubes, allowing for safe explosion of such rockets by greatly reducing the exhaust pressure in the large manifolds. The balance of the exhaust reaction force is achieved by simultaneously releasing the gas in the opposite direction. Structures for safely guiding and diffusing rocket or missile exhaust, or in some cases for suppressing the noise of the reaction engine, are also known in the prior art. However, none of the conventional structures have dealt with the problems contained herein and at least not in the manner described below in connection with the present invention.

The invention contemplates a rocket launch tube arranged in close proximity to each other, a continuous exhaust manifold having a horizontal extension along the ship's shipboard and means for connecting to each launch tube at the base, and each launch tube from communication with the exhaust manifold. At both ends of the exhaust manifold, and sealing means adapted to seal releasably near the base and to open the exhaust gas from the rocket into the exhaust manifold after ignition of the rocket in the associated launcher and to seal the launcher under all other conditions. Provided is a rocket pleium exhaust device which is connected to each other and is composed of a pair of upright open air ducts and the like whose cross-sectional area is approximately equal to the cross-sectional area of the exhaust manifold, and which suppresses undesirable combustion of exhaust gas in the manifold.

The pair of upright exhaust conduits may be connected to the exhaust manifold via a gentle curve. The exhaust pipes may also be linearly aligned with one another or may be spatially arranged along the horseshoe exhaust manifold.

Each of the launch tubes is provided with a protective seal at its connection to the exhaust manifold. The seal is preferably a retractable door mechanism and controlled such that the door mechanism is always closed except at the ignition of the rocket in the associated launching tube. This facility serves to prevent hot exhaust gases from other rockets from passing through the rockets stored in the launch tubes as extremely dangerous events, or undesirably releasing the rockets through already launched launchers.

The door closes the launch tube when closed so that the launch tube cannot act as a sealed air pocket. The air in the pocket may mix with the exhaust from other rockets and form explosive compounds.

As a result of the use of the structure of the present invention, when a particular rocket is first ignited, the exhaust gas entering the exhaust manifold mixes with the air and burns further in the vicinity of the gas first exhausted by unburned hydrogen and carbon monoxide reacting with oxygen. . However, when the exhaust gas continues to enter the exhaust manifold from the launch tube from which the rocket is being launched, two gas barriers are formed, one on each side of the rocket being launched. Their barrier consists of exhaust gases that are first released by the rocket into the exhaust manifold and mix very rapidly with air and continue burning until the mixture can no longer continue combustion.

These barriers maintain a separation between the exhaust gases that continue to enter the exhaust manifold by the rocket under launch and the residual air in the exhaust manifold and conduit. When they are moved away from the launch tube containing the rocket being launched by the additional exhaust gas emitted from the rocket being launched, the barriers later maintain the separation between the combustible exhaust gas emitted and the air throughout the exhaust manifold. Exhaust residual air out of the exhaust manifold and out of the most conduit. Once the air is discharged out of the exhaust manifolds and conduits, there is no longer a risk of explosion due to the reaction of unburned hydrogen with other combustible materials in the exhaust.

The specific shape of the structure, including the exhaust manifold and exhaust conduit, is not considered important, but certain design elements must be considered. Even though the cross section is not necessarily rounded, all corners or bends are curved to a large radius of curvature so that the exhaust gas flows toward the outlet end of the upwardly extending exhaust conduit without disturbing it. Avoid angled corners and pockets as much as possible. The cross-sectional area of the entire exhaust conduit should be relatively small. This cross-sectional area depends on the maximum expected displacement, assuming that the exhaust is split approximately equally between the two exhaust conduits. Since it is desirable to maintain a relatively low exhaust manifold pressure of about 15% above the external atmospheric pressure, the cross-sectional area should be sized for a speed of approximately Mach 0.5 at steady state. Discontinuities in conduits with a constant cross-sectional area should be reduced to a minimum because any stagnant volume is a potential pocket for combustible mixtures.

It is desirable to keep the exhaust conduit cross section constant or to increase the cross sectional area in small increments at least in proportion to the distance from the exhaust manifold. Otherwise, if the flow area is significantly reduced in proportion to distance, the exhaust manifold tends to act as an accumulator and mixes much more combustible exhaust and air near the rocket. If the flow area increases too quickly in proportion to the distance, the volumetric efficiency is lost. If a structure is chosen that provides an increase in exhaust conduit cross-sectional area proportional to distance, the expansion occurs as it passes through the back of the rocket so that the air in the exhaust manifold is swept out before it is sufficiently mixed with the exhaust. In addition, the shape of the cross-sectional area may be changed to suit the required conditions or limitations of the specific space.

The main concern is to prevent large amounts of relatively static and turbulent mixed flammable exhaust gases and air from occurring within areas with limited outlets for their mixed exhaust manifold gases. If such a situation is not avoided, the resulting mixture burns and or explodes resulting in severe pressure rise. The pressure due to combustion heat pressure can be several times higher than the steady state pressure without combustion. The explosion pressure is approximately 5-18 atm and may be higher.

In one particular configuration configuration in accordance with the present invention, a plurality (two or more) of rockets and rocket launch tubes are spatially arranged in series over a horizontal associated tubular exhaust manifold extending over the entire length. At both ends of the exhaust manifold, a pair of upright exhaust conduits are connected to the exhaust manifold by a portion that is gently and continuously curved. The cross-sectional area of each exhaust conduit approximates the cross-sectional area of the exhaust manifold itself at least near the region where the exhaust conduit and the exhaust manifold are connected to each other. In one variation of the invention, the walls of the exhaust conduit are slightly inclined so that the cross-sectional area gradually increases from the inlet end to the outlet end connected to the exhaust manifold.

In another particular installation according to the present invention, each rocket launch tube is arranged to form a general horseshoe shape with respect to each other, the exhaust manifold extending under a continuous horseshoe manifold under all the launch tubes. The exhaust manifold extends past the horseshoe shape of the rocket launch tube and to the point where there is an upward swelling airway, one at each end of the horseshoe. With the above-described arrangement of the rocket launch tube and the high-pipe manifold exhaust system, the exhaust from any one rocket in the horseshoe is split approximately equally and proceeds to the two exhaust conduits at both ends, and the two gas barriers as described above. Form and push the remaining air in the exhaust to the front of the barrier and out of each conduit.

After a rocket in one of the launch tubes begins to ignite and during the time the air is released out of the exhaust system, the three gas phases within the exhaust system are: (1) air being expelled, (2) gas barrier Combustion products formed by the reaction of the fuel-containing exhaust gas to be formed with adjacent air, and (3) act to expel the gas barrier to the outside through the exhaust device away from the vicinity of the rocket being discharged from the rocket, There is an original exhaust gas that extrudes the remaining air out of the exhaust conduit.

For most rockets launched in the device according to the present invention, the first transition is completed in a very short time, such as 10-100 milliseconds. However, the problem addressed by the present invention remains large for that short time and can be mixed in open exhaust manifolds or accumulated in stagnant pockets and chambers without mitigation to that problem as provided by the facility according to the present invention. Early exhaust gases can cause dangerous explosions.

It will be described in more detail below with reference to the accompanying drawings for a detailed understanding of the subject innovation.

In FIG. 1, a device 10 according to the present invention is schematically shown, which device 10 has an exhaust manifold 12 located below and connected to a single rocket launch tube 14 and 16. The launch tube 14 incorporates a rocket 18 in a stored state, and the launch tube 14 has an upper end thereof closed by a cap 20 and a lower end thereof by a protective seal 22. Blocked from The seal 22 may also be comprised of a door mechanism as described in US Pat. No. 4,044,648.

Shown within the launch tube 16 is a rocket 24. The rocket 24 is in ignition, which can be thought of as the beginning of the firing process and its exhaust is descending into the exhaust manifold 12. The seal 22 at the bottom of the launch tube 16 is open and the top cap 20 is removed.

A pair of upright exhaust pipes 26 and 28 is connected to the exhaust manifold 12 at the left and right ends of the exhaust manifold via curved pipes 30 and 32. The device 10 as shown is designed for ship or underground installation and the deck height is indicated by a dashed line 34. The shapes of the exhaust manifold 12 and the exhaust conduits 26, 28 are formed to provide a smooth and continuous internal surface with minimal discontinuity. For that purpose, the bends 30 and 32 have a constant radius of curvature. Where discontinuities are inevitable, such as the bottoms of the launch tubes 14 and 16, the seal 22 of the sealed launch tube is positioned as close as possible to the connection between the exhaust manifold and the launch tube, and the connecting edge 38 of the exhaust manifold 12 You can bury the chamber as thinly as possible by opening it up or smoothing it at an angle to the wall. As shown in FIGS. 1 and 2, the edge 38 is gently curved at the connection with the exhaust manifold 12. In this way, stagnation pockets capable of accumulating flammable mixtures of the source and air are prevented and removed in advance.

The rocket exhaust gas entering the exhaust manifold 12 from the rocket 24 of the launch tube 16 is denoted by E. As shown in Figures 1 and 2, the rocket 24 has just started to burn. The gas barriers or wires B formed on both sides of the exhaust gas E are shown and used as the exhaust gas E diffuses from the vicinity of the rocket 24 to both sides, so that the barrier is exposed to the air indicated by the arrows in front of them. It begins to push out of the exhaust manifold 12 and the associated exhaust ducts 26 and 28.

FIG. 2 schematically shows an apparatus 40 different from that shown in FIG. Identical components are denoted by the same numerals. Thus, the apparatus 40 of FIG. 2 has the same rocket and launch tube installations and associated exhaust manifolds 12 as those of FIG. The device 400 is slightly inclined to the exhaust conduits 42 and 44 connected to the left and right ends of the exhaust manifold 12 by the bent portions 30 and 32 so that the cross-sectional areas of the exhaust conduits 40 and 42 are curved portions 30 and 32. It is different from that of Fig. 1. The exhaust conduits 42 and 44 are the same in shape and size, although not necessarily, as shown in Fig. 2. One of the trumpeted exhaust conduits, such as (42), may be replaced by one of the exhaust conduits having a constant cross section, such as (28) in Figure 1. However, for the reasons already described, the cross-sectional area along the length of the exhaust conduit It is important that there is no significant reduction.

3 is a plan view of the apparatus 10 according to the present invention. This is essentially similar to the apparatus 10 of FIG. 1 except that three rocket launchers 14, 16 instead of two are shown. The corner portion 38A connects the launch tube to the exhaust manifold at a shallow angle to prevent any stagnation of pockets in the area. Two launch tubes 14 in FIG. 3 are provided with a cap 20. However, the central launcher 16 has a cap removed and the elements visible within the launcher 16 are a pair of doors 46 at the bottom of the launcher, with the side 48 engaging the door 46 in closure upon closure. to be. A more detailed description of this structure is described in US Pat. No. 4,044,648. The combination of the door 46 and the side 48 includes one particular embodiment of the seal 22 structure shown in FIGS. 1 and 2.

4 shows, in plan view, another particular arrangement according to the invention, which shows a number of launch tubes 14 similar to those shown in FIG. 4 shows an apparatus 50 consisting of a plurality of rocket launch tubes 14 arranged in more compact horseshoe shapes than the straight lines of FIGS. 1 to 3 for the same number of launch tubes. have.

In FIG. 4, like elements are denoted by the same numerals as in the above drawings. Each portion of the exhaust manifold 12 under the corresponding launch tube 14 is connected by an exhaust manifold 12B that is curved into a smooth continuous curve.

The operation of the device 50 is the same as described for the devices of FIGS. 1 and 2.

Thus, for example, when the rocket is fired, which is contained in the launch tube closest to the left exhaust conduit 26, the exhaust gas enters the exhaust manifold 12 and divides to form a gas barrier or wire. As before, the gas barrier is discharged toward the left exhaust conduit 26 and the right exhaust conduit 28, respectively. Since the distances from such launch tubes 14 to the exhaust conduits are different, it can be expected that the gas barrier from one side will reach the near exhaust conduit before the other gas barrier reaches the other exhaust conduit. The difference in distance also makes each back pressure slightly different. However, the differences are notable for significant differences in the described operators or the effectiveness of the gas barriers that prevent the mixing of air and exhaust gases that form the explosive confusion by cleaning the exhaust manifolds and exhaust conduits of the air that were initially contained. It is not such a macro to cause.

For illustrative purposes, a two-way rocket exhaust manifold and a combined exhaust conduit and measurement equipment for combustion suppression according to the present invention have been described, but it will be appreciated that the present invention is not so limited. Accordingly, all modifications and changes by those skilled in the art can be made within the scope of the present invention as described in the appended claims.

Claims (1)

A number of rocket launchers arranged in close proximity to one another, a continuous exhaust manifold extending horizontally along the lines of the launchers and having a means for connecting to each launcher at the base, close each launch tube from communication with the exhaust manifold. Sealing means, exhaust manifolds, adapted to seal releasably from the rocket and open to allow exhaust gases to enter the exhaust manifold from the rocket after the ignition of the rocket in the associated bright tube and to seal the launcher under all other circumstances. In a conventional rocket exhaust system for suppressing undesired combustion of an original exhaust gas in a manifold composed of a pair of upright exhaust pipes connected to both ends, the exhaust conduits 26 and 28 are approximately equal to the cross-sectional area of the exhaust manifold 120. It has a corresponding cross-sectional area and is substantially perpendicular from the exhaust manifold 12. Rocket exhaust system for combustion yeokje, characterized in that the the extension.