DE2923755A1 - 2-WAY COLLECTING CHAMBER FOR ROCKET EXHAUST GAS TO SUPPRESS COMBUSTION - Google Patents

Description

2-way collecting canister for rocket exhaust for suppression of combustion processes

The present invention relates to exhaust gas collection systems with control} elements and in particular an arrangement for controlling the ι

Flow of the exhaust gases from a collecting chamber, which is called the collecting j line for a variety of missile launch tubes is used. J

If a missile is launched in a launch tube, its j Exhaust gases must be directed to a safe place. This is a particular problem when the missiles are below deck in a ship j or are arranged below the surface of the earth. The exhaust gases are picked up by a manifold which leads them to a safe Place from where they can be released into the atmosphere. The exhaust gases flow during a normal launch process through the launch tube into the manifold until the missile has risen to a considerable height above the launch tube.

The rocket exhaust is generally rich in hydrogen and carbon monoxide. These gases react with the air in the manifold, creating heat of combustion and possibly an explosion develop. In both cases the pressure in the manifold is higher than desired.

ι Show different constructions according to the state of the art

; Means on / to control and guide the rocket exhaust, for example Security doors or gas valves that are operated to let the exhaust gases into an associated manifold, after a missile has been detonated. The prior art also teaches a large open ended exhaust gas collection

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conduit for missiles arranged differently than in a launch tube, which allows a safe launch of the rocket by significantly reducing the exhaust pressure in the large manifold. A Compensation of the exhaust gas reaction forces can be achieved by releasing the gases in opposite directions at the same time. Furthermore, constructions are known from the prior art which lead or distribute rocket or projectile exhaust gases or - in one case - suppress the sound generated by recoil engines. None of those known in the prior art However, constructions solves the problem raised here.

The present invention sc. Creates a plenum chamber structure for rocket exhaust gases to suppress undesirable combustion of the raw exhaust gases in a manifold with a plurality of rocket launch tubes arranged in a line, a generally horizontally running continuous collection chamber along the line of launch tubes with means to which the launch tubes with their lower end are connected and with means to releasably close each launch tube at its lower end against the plenum chamber, the latter devices can be opened when a rocket is launched in the associated launch tube to let the exhaust gases of the missile into the plenum chamber, and the launch tube close under all other circumstances. Furthermore, a pair of upwardly standing exhaust gas ducts are provided, each of which is arranged at the two ends of the collecting chamber and is dimensioned so that its cross-sectional area corresponds approximately to that of the collecting chamber.

The two upright exhaust ducts can be connected to the collecting chamber via continuously curved elbows. Furthermore, the exhaust gas ducts can be arranged in a straight line next to one another or along a curved collector duct.

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Each of the launch tubes is where it opens into the collection chamber, provided with a protective seal. This closure is preferably a retractable door mechanism and can be controlled to ensure that the door is closed at all times, except when the missile is fired in the associated launch tube will. This arrangement serves to prevent the escape of hot exhaust gases from a missile on one located in a launch tube another missile (a very dangerous situation) or through a launcher tube from which a missile has already been shot down (again, this is an undesirable situation). When closed, the doors lock the launch tube so that it cannot act as a blind mass of air with which the exhaust gases of another rocket mix and create an explosive one Mixture can form.

As a beneficial result of using an arrangement in accordance with the present invention, the exhaust gases that are generated mix upon ignition a certain rocket are pressed into the collection chamber, deal with the air present there and direct another Incineration in the immediate vicinity of the first delivered Gas, as the still unburned hydrogen and carbon monoxide react with the available oxygen. But while further exhaust gas then flows into the collection chamber from the launch tube in which a rocket was ignited, form two gas fronts, one on each side of the firing missile. These fronts consist of the exhaust gas that was first sent by the rocket into the collection chamber, mixes very quickly with the existing air and continues to burn, until the mixture can no longer sustain combustion. These fronts are now given a separation between the exhaust gases that are driven further into the collection chamber by the firing missile, and those in the collection chamber and remaining air in the duct system. During these fronts by the launch tube containing the firing missile

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The further exhaust gases are driven away, they push the remaining air out of the plenum chamber and out of the end channels at their ends, while the air and the fuel-rich exhaust gases that are later expelled from each other kept separate. After the air has been forced out of the plenum and the duct system, there is there is no longer any risk of explosions in the system as a result of the reaction of unburned hydrogen and other combustible hydrogen Products occur in the exhaust gases.

The special configuration of the arrangement from the collection chamber and the exhaust ducts are not considered critical; certain design factors: but must be taken into account. Although they do not necessarily have to be round in cross-section, all of the elbows are curved profiles sufficient radii of curvature so that the exhaust gases flow undisturbed to the outlet ends of the upwardly directed exhaust ducts can. Sharp angled knees and pockets should be avoided where possible. The total cross-sectional area of the exhaust duct should remain relatively low. This area depends on the maximum expected exhaust gas flow, with the Amount of exhaust gas is divided more or less evenly between the two exhaust ducts. As it is desirable, a proportionate To maintain low pressure in the manifold of about 15% more than ambient pressure, the cross-sectional area should be designed for a flow rate of about Mach 0.5 in the stabilized state. Discontinuities in the ducts constant cross-sectional area should be kept to a minimum because a stagnant volume is a potential pocket in which a combustible mixture can collect can.

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Preferably, the cross-sectional area of the exhaust duct is in kept essentially constant; at least the area with the distance from the actual collection chamber should be slightly grow. If the flow area decreases significantly with distance from the collection chamber, the collection chamber acts as a Accumulator so that the fuel-rich exhaust gases and the air mix thoroughly near the missile. Takes the flow J If the area increases too quickly with the distance from the collection chamber, the volumetric efficiency decreases. If you choose a structure in which the cross-sectional area with distance from the collection chamber ' increases, the enlargement should occur behind the last rocket in ι the series, so that the air from the actual collecting i Chamber can be removed before it can mix with the exhaust gases significantly. Furthermore, the shape of the cross section may be varied to meet certain spatial requirements or other restrictions, provided that the above with regard to the Cross-sectional area specified aspects are taken into account.

; The main point is to have a large volume collection space with a relatively stagnant and turbulent mixed mixture of fuel-rich exhaust gas and existing air in one Prevent area with throttled outlet for this exhaust mixture. If this situation cannot be prevented, it will

; the resulting mixture is likely to burn and / or

explode, so that a sudden high increase in pressure ^up: occurs. The pressure increase generated by the heat of combustion can; several orders of magnitude higher than the static pressure without combustion. The explosion pressures are 5 to 18 times atmospheric pressure and can be even higher. ι

In a specific arrangement according to the present invention

a multitude (two or more) missiles and launch tubes lie spatially in a line above a generally horizontal one associated collection chamber that runs the entire length of the line. At opposite ends of the collecting

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chamber there is a pair of upright exhaust ducts, which are connected to the collection chamber by gradually and steadily curved elbows. The cross-sectional area of each exhaust duct is approximately the same as that of the collecting chamber itself, i.e. at least in the area where the collecting chamber enters the exhaust gas duct transforms. In a variation of the present invention, the walls of the exhaust duct are slightly widened so that the cross-sectional area gradually increases from the inlet end at the collection chamber to the mouth.

In another arrangement in accordance with the present invention, the missile launch tubes are in the shape of a relative to one another Arranged horseshoe. The collecting chamber runs continuously in a horseshoe shape under the launch tubes. Farther the plenum extends beyond the horseshoe arrangement of the launch tubes to the locations of the two upwardly directed exhaust ducts at the ends of the legs of the horseshoe. As with the straight line arrangement of the launch tubes and the chamber-duct exhaust system, As described above, the amount of exhaust gas from one of the rockets in the horseshoe divides more or less evenly and flows to the exhaust ducts at both ends, so that the two gas fronts or barriers arise, as described above, and push the rest of the air out of the system in front of you and through the respective duct.

During the transition period after detonating a missile in one the launch tubes and before the air is completely out of the system has been pushed out, there are three gas phases: (T) the air that is pushed out, (2) the combustion products, which form when the fuel-rich exhaust gases react with the adjacent air to form the gas barrier, and (3) the actual ones Exhaust gases that are still flowing out of the rocket and the gas barriers or fronts through the system from close to the firing missiles outwards, driving the rest of the air out of the chamber and exhaust duct sections in front of you. at

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For most missiles firing in a system according to the present invention, the first transition period is very fast and may only take 1o to 1oo milliseconds. Select i During this short period of time, the problem to which the present invention is directed occurs. Without the arrangement according to j The protection afforded by the present invention, the initially inflowing exhaust gases can be stored in an otherwise open collecting chamber Mix with air or collect in standing bags or chambers and cause a dangerous explosion.

The invention will now be described in detail with reference to the accompanying drawings using exemplary embodiments.

Fig. 1 is a side elevation of a particular arrangement in accordance with the present invention;

Fig. 2 is a side elevation of another specific arrangement in accordance with the present invention;

Figure 3 is a top plan view of an assembly in accordance with the present invention showing certain details of the missile launch tubes shows, and

Figure 4 is a top plan view of another arrangement in accordance with the present invention Invention

Fig. 1 shows a system 10 according to the present invention schematized as a side elevation. It has a collecting chamber 12 below a pair of missile launch tubes 14, 16 to which it is connected. The launch tube 14 contains a rocket 18 in the storage condition; the tube 14 is closed at its upper end with a cap 2o and at its lower end against the collecting chamber 12 closed by a protective closure 22. The lock 22 can be a door mechanism such as that of US Pat. No. 4,044,648 disclosed.

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A missile 24 is located inside the launch tube 16. The missile 24 is currently firing, namely in the initial phase of one Launch, and their exhaust gases are down and into the plenum 12 directed into it. The shutter 22 at the lower end of the The launch tube 16 is open; the cover - for example 20 at the upper end of the launch tube 16 is removed.

At the left and right ends of the collecting chamber 12 there are two upright exhaust gas ducts 26, 28 over elbows or curved line sections 3o, 32 connected. The system 1o, as shown, is for installation on board a ship or under the earth's surface provided; the deck height is with the dashed Line 34 indicated. The collection chamber 12 and the exhaust ducts 26, 28 are designed in such a way that a smooth, continuous inner surface with minimal discontinuities results. to for this purpose the elbows 3o, 32 have a constant radius. Where discontinuities are unavoidable, such as at the lower ends of the launch tubes 14, 16, the chambers created in this way are kept as flat as possible, by placing the closures 22 of a closed launch tube as close as possible to the transition from the launch tube to the sanunel chamber arranged and the corner 38 at this transition angled, widened or otherwise disguised in the wall of the collection chamber 12 transferred. As shown in FIGS. 1 and 2, the corners 38 are continuously curved at the transitions to the collecting chamber 12. This avoids and eliminates dormant pockets in which a combustible mixture of exhaust gases and air can collect could.

An exhaust gas flow E is shown as it comes from the rocket 24 from the Launch tube 16 enters collection chamber 12. As shown in Fig. 1 and 2, rocket 24 has practically begun to burn. The gas barriers or fronts marked with B are formed on both sides of the exhaust gas stream E and begin to disperse the air (with the

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Arrows shown) in front of you from the collection chamber 12 and the associated To drive out exhaust channels 26, 28, while the Abqase E in both directions laterally from the vicinity of the Missile 24 propagate.

Figure 2 is a similar schematic elevational view of an alternative arrangement 40. Here are the same parts as in Fig. 1 with the same reference numerals. The system 4o of Fig. 2 is, as shown, with regard to the rocket and launch tube assembly and associated collection chamber 12 identical to that of FIG. The system 4o is different differs from that of FIG. 1 in that the exhaust ducts 42, 44, which over the elbows 3o, 32 at .das the left and right end of the Collection chamber 12 are connected to expand slightly so that the cross-sectional area of the exhaust gas channels 4o, 42 with the Distance from the knees 3o, 32 gradually increases. As shown in Fig. 2, the exhaust ducts 42, 44 are in configuration and the dimensions are identical to one another, although this is not necessary. For example, you can do one of these widened exhaust ducts - for example 42 - with one of the constant surface exhaust ducts such as 28 of Fig. 1 combine. However, for the reasons already discussed, it is important that the cross-sectional area not be significantly reduced over the length of the exhaust duct.

Figure 3 is a top plan view of a system 10A in accordance with the present invention Invention. This system corresponds essentially to the system 1o of FIG. 1, but with three. are shown instead of just two. The corner portions 38A connect the launch tubes to the plenum at shallow angles, see above that no congestion areas can occur in these areas. In the two launch tubes 14 of FIG. 3, the covers 2o put on. However, the cover is removed from the central launch tube 16 and the missile normally located there removed; the elements visible in the tube 16 are the two doors 46 at the lower end of the launch tube together with the side

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tenteilen 48, which together with the doors 46, the launch tube
close tightly at the bottom. This arrangement is described in detail in US Pat. No. 4,044,648. The combination of the doors 46 with the side parts 48 represents a specific embodiment
of the closure construction 22, which is indicated in FIGS. 1 and 2. ;

4 shows a further arrangement in plan view
of the present invention having a plurality of launch tubes 14 corresponding to those shown in FIG. Fig. 4 shows
a system 5o with a larger number - ie five - launch tubes 14 arranged in a horseshoe shape suitable for
The same number of firing channels is more compact than the straight-line arrangements of FIGS. 1-3. In FIG. 4, the same elements as in the preceding figures bear the same
Reference number. Individual parts of the collecting chamber 12 under corresponding launching tubes 14 are connected to the curved collecting chamber sections 12B in a continuous curve.

The mode of operation of this system 5o is essentially the same ^! before, as described for the systems of FIGS. So if a given missile is launched (for example, the one in the launch tube on the far left of the exhaust duct 26), splits
the exhaust gas flow opens up when entering the collecting chamber 12 and gas barriers or fronts are formed as above, which lead to the | left and right exhaust duct 26 and 28, respectively. \ As the distances from the launch tube 14 j un- to the exhaust ports are the same, it is expected that the gas barrier from the one side reaches the closer channel before the gas barrier
arrives at the other channel from the other side. Because of the difference in distance, the respective dynamic pressures can also be different. However, the differences are not that great \

that there are significant differences in the way of working or in the] Effect of the gas fronts when expressing the initially front j

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which air from the respective collecting chamber part and exhaust gas duct [ result; so that the mixing of the air mass with the '

Exhaust gases and thus the formation of a potentially explosive;

ι Mixing are prevented. i

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Claims (1)

Paten tansp rü cn e Π A Sanunel cannon construction for missile delivery for suppressing undesired burns of the delivery in a collecting line, characterized by a plurality of rocket launching tubes erected next to one another in a line, a generally horizontal continuous Sanunel chamber running along the row of launching tubes with means for connecting each of the launching tubes at its lower end, a device to close each launch tube at its lower end against the collection chamber, which device can open when a missile is fired in the associated launch tube in order to let the rocket exhaust gases into the collection chamber, and close the launch tube in all other circumstances, and through a A pair of upright exhaust ducts connected to opposite ends of the plenum and dimensioned so that their cross-sectional area approximately corresponds to that of the plenum. 030083/0013 READY TO DO 2 ^ \ .- construction-ortach Ansptuch- 1>marked; through ^; Means, uip, the lUnfceren; Ends of the exhaust ducts mit.'iegen-ontspifecfeenden der; Sansnelkammer ss tetig continuous' to -connect. 3. Construction according to claim 2, cdasstigekeniiz & ichHet that the connecting means a pair of continuous continuous knees, tücjke -. and indeed j «of a per exhaust duct s.are belonging to ? Exhaust duct with corresponding end of the sanitary oil chamber 4. Construction naüh.tAnspruch 3, thereby ^ ketmz € ic% n * et that each elbow has a substantially constant radius and extends over an angle of about 90 °. 5. Construction according to one of the preceding claims, characterized in that the channels over their length a substantially have constant cross-sectional area. 6. Construction according to any one of claims 1 to 4, characterized in that that at least one of the exhaust ducts has a .altering cross-sectional area, which with the distance from Inlet at the plenum increases towards the outlet end. 7. Construction according to claim 6, characterized in that both exhaust ducts are designed the same and that their cross-sectional area increases from the inlet to the outlet. 8. Construction according to one of the preceding claims, characterized in that the cross-sectional area of the exhaust ducts over, their total length is not less than the minimum cross-sectional area of the plenum chamber. 9. Construction according to one of the preceding claims, characterized Exhaust ducts are continuous throughout to avoid the formation of pockets or to prevent dormant sections in which there is a - explosive mixture ^ - of .. exhaust gases and air. could accumulate. ... "_ BATH ORIGINAL SUBMITTED 1ο. Construction according to one of the preceding claims, characterized in that the launch tubes, the plenum chamber and the exhaust ducts are arranged substantially below the deck of a ship, the launch tubes and the exhaust ducts after
protrude above the deck and open out above it. 11. Construction according to one of the preceding claims, characterized characterized in that the collection chamber is provided with a cross-sectional area which corresponds to a flow velocity of the exhaust gases of about Mach 0.5 in the steady state during the launch of a missile from its launch tube. 030063/0013