Combustion suppressor

Method and apparatus for preventing combustion of exhaust gases in rocket launch systems using a plurality of launch tubes connected to a plenum including pressure sensors in each launch tube, a control system sensitive to atmospheric pressure and launch tube pressure which provides a signal to an inert gas supply flow controller to initiate flow of gas into the plenum when pressure in a launch tube, after launch of a rocket, reaches a predetermined level.

BACKGROUND OF THE INVENTION 
1. Field of the Invention 
The present invention relates to suppression, if not prevention, of exhaust 
gas combustion in a multiple rocket exhaust plenum. More particularly, the 
present invention relates to a system for providing controlled flow of 
inert gases to a rocket exhaust plenum to prevent intake of oxygen which 
renders the exhaust mixture combustible. 
2. Description of the Prior Art 
For military applications rockets, missiles or other exhaust-gas propelled 
vehicles are often stored in closely adjacent magazines, chambers or 
launch tubes. In these cases, exhaust gas ducts are normally provided to 
convey rocket exhaust gases generated during rocket ignition to a safe 
location. Where available space is at a premium, as for example on board 
ship, manifolding of a number of closely adjacent launch tubes or chambers 
into a common exhaust manifold or plenum chamber is often necessary. 
Various problems may develop if ducts connecting launch tubes to a common 
exhaust manifold are normally open before launch of the vehicles. If one 
or more of the rockets is intentionally or accidentally ignited, portions 
of the resulting exhaust gases, which may have temperatures as high as 
6,000.degree. F., can be circulated through the common manifold, into the 
connecting ducts and into other launch chambers. This could ignite other 
rockets. Also, the warheads in the launch chambers could be detonated by 
these hot gases. At a minimum, the gases could damage the rocket, 
associated equipment and hold-down devices. Thus accidental or intentional 
ignition of one rocket could render a whole ship or launching system 
ineffective. In addition, if the some of the launch tubes are open at 
their upper ends, exhaust gases entering the chambers through the 
connecting ducts could escape through the open outer ends. 
More importantly, when a rocket is launched from a multiple rocket canister 
with a common plenum, a fuel rich exhaust gas mixture containing hydrogen 
and carbon monoxide is present in the empty launch tube and plenum. This 
can present a potential explosion hazard if air containing oxygen, e.g. 
from the atmosphere, is mixed into the system prior to the next rocket 
launch. Since these exhaust gas residuals are initially quite hot, up to 
6,000.degree. F. as noted, cool-down will naturally occur in the interval 
following launch and the internal pressure of the system will decrease. 
Even after the system is closed following the launch, it contains hot 
residual exhaust gases and other outgases from the system components, for 
example ablative materials, which are rich in hydrocarbons, carbon 
monoxide and hydrogen. As the pressure decreases external air can be drawn 
into the system, for instance, through the launch tube of the next 
launched rocket since it must be uncovered in order to allow the rocket to 
be launched. Thus, a system for preventing production of combustible 
mixtures in the plenum and in empty rocket launch tubes is needed. 
The prior art discloses many different systems for utilizing a single 
plenum for the multiple firing of rockets from tubes. For instance, U.S. 
Pat. Nos. 4,044,648, 4,134,327 and 4,173,919 of the inventor herein all 
disclose systems utilizing a common exhaust duct to discharge exhaust 
gases produced by the firing of multiple rockets. 
The need to detect fires and provides a means to control them is recognized 
in U.S. Pat. No. 3,052,303 of Lapp which discloses a system to extinguish 
inadvertently ignited rockets in a storage area by utilizing the pressure 
produced by the rocket exhaust to open a clapper valve and force water 
into the rocket's chamber until the ignition is extinguished. Glendinning 
et al. in U.S. Pat. No. 2,693,240 disclose another system to detect an 
explosion in aircraft during its initial phase and suppress the explosion 
by use of fire extinguishers. 
It is also known in the prior art to utilize recirculated combustion 
exhaust materials, which are relatively inert, in order to provide a 
noncombustible atmosphere in closed containers. For instance, see U.S. 
Pat. Nos. 2,756,215 of Burgess et al. and 3,103,296 of Gour. 
In another area of art, numerous patents have been issued which deal with 
methods of extinguishing fires or suppressing combustion after a fire has 
been initiated. Generally, these methods deal with the dilution of 
available air using some inert gas delivery method. For example, the 
following references are of interest: U.S. Pat. Nos. 649,923 of Febiger, 
1,312,224 of Wotherspoon, 1,993,695 of Allen et al., 2,050,687 of Allen, 
2,543,362 of Getz, 3,468,562 of Goodloe et al., 3,830,307 of Bragg et al. 
and 3,893,514 of Carhart et al. 
SUMMARY OF THE INVENTION 
In accordance with the present invention, apparatus is disclosed for 
sensing the pressure within each launch tube of a multiple rocket 
launching system having a manifold or plenum for exhausting gases from a 
plurality of rockets and providing an inert gas, such as nitrogen or 
carbon dioxide, to the plenum in order to keep the totality of the system 
slightly above atmospheric pressure and prevent entry of sufficient oxygen 
from the atmosphere to produce a combustible mixture in the launch tubes 
or the plenum. The launch tubes are provided with separately actuatable 
controllers which, for example, may be activated by signals corresponding 
to pressure decreases which occur during cooldown of the gases contained 
in a tube. The pressure sensor is connected to a control system which also 
receives a signal corresponding to atmospheric pressure outside the launch 
system. The control system is interconnected with, for example, a one-way 
valve which opens when provided with a signal from the controller. The 
one-way valve is provided in a conduit which communicates with a pressure 
regulator and a supply of pressurized gas, such as nitrogen. The 
pressurized gas is retained at a pressure sufficiently higher than the 
plenum pressure at the point of delivery to the plenum to facilitate rapid 
dispersion of the gas into the system. 
The result of this system is the prevention of oxygen flow from the 
external atmosphere into the plenum system, since the pressure in the 
system is maintained above atmospheric. Thus, small leaks and openings, 
such as the cover for the rocket which has been launched, do not present 
the problems relating to fire hazards which have previously existed.

DESCRIPTION OF THE PREFERRED EMBODIMENTS 
The system of the present invention is basically directed to the provision 
of positive pressure inside the launch tubes and the plenum of a multiple 
launch tube system for firing rockets or missiles. This is accomplished by 
sensing the pressure in the launch tube from which a rocket has been fired 
and in the interconnecting plenum and initiating the input of an inert 
gas, such as nitrogen or carbon dioxide, into the plenum chamber and 
launch tube prior to the admission of sufficient oxygen from the 
atmosphere to produce a combustible mixture. The overall pressure in the 
system is maintained at a sufficient level that the gas in the system 
tends to flow out of the exhaust plenum after firing of the rocket and, 
thus, prevents entry of external gases into the system. 
Referring now to the drawing, and more particularly to FIG. 1, there is 
schematically illustrated a rocket launching installation which includes a 
plurality of launch tubes 10, 11, 12 and 13. It will be understood that 
the number of launch tubes is arbitrary and that more or fewer tubes may 
be provided. 
The launch tubes are connected to a common duct or plenum chamber 15 for 
conducting the exhaust gases created by firing the rockets in launch tubes 
10-13 away from the launch tubes. It will, of course, be understood that, 
instead of rockets, missiles or other exhaust-propelled vehicles may be 
utilized. Launch tube 10 illustrates a rocket 16 disposed therein. The 
rockets may be held by suitable hold-down devices (not shown), such 
devices being well known to those skilled in the art. The rocket is 
provided with an exhaust nozzle 17 through which the hot exhaust gases 
emerge. 
The bottom of launch tube 10 is closed with a frangible cover 20. However, 
other rear closure systems known to those skilled in the art may be 
utilized. The cover is secured to the walls 21 of launch tube 10 by any 
suitable manner, for example, by welding or suitable fastening devices. 
The frangible cover 20 is shown in various stages of destruction by the 
exhaust of the rockets in tubes 11, 12 and 13. 
In tube 11, rocket 35 has been ignited and nozzle 36 is emitting exhaust 
plume 38 which is exiting into plenum 15 producing pressure and exhaust 
gas flow as indicated by arrows 37. The rocket is yet to be released from 
its hold-down device, and thus cover 44 is still in position, as is cover 
44 of tube 10. 
In tube 12 cover 46 is open and rocket 40 is proceeding upward while 
emitting an exhaust plume 42 from nozzle 41. This also results in gas 
pressure in plenum 15, as indicated by arrows 37. The temperature of the 
exhaust plume 42 is quite high, up to about 6,000.degree. F., and, due to 
the downward flow of gases produced by plume 42, external atmospheric 
gases indicated by arrows 47 may begin to enter tube 12. In tube 13, 
rocket or missile 40 has exited the tube and is adjacent open cover 48. At 
this point plume 49 impinges upon tube 13 in the area of sensor 56 and 
will be drawing external atmospheric gases into tube 13 as indicated by 
arrows 47. During this time, the atmospheric oxygen may cause burning of 
some of the exhaust gases 49, thus merely increasing the normal combustion 
of the exhaust gases without adding to the problem of preventing 
combustion of residual fuel-rich gases after the launch is completed. 
Tubes 10, 11, 12 and 13 are provided with pressure sensors 50, 52, 54 and 
56, respectively. Each pressure sensor is connected via lines 58, 60, 62 
and 64, respectively, to a controller for activation in the system of the 
present invention. A sensor 57 is also connected to the control/actuate 
stage 66 for providing an indication of atmospheric pressure for 
comparison purposes. For purposes of illustration, line 64 from sensor 56 
is shown connected to controlling and actuating unit 66. It is to be 
understood that a single multifunction control unit may be utilized for 
all of the pressure sensors, or individual circuitry may be provided for 
each unit. The control and actuation unit 66 is connected, as shown by 
line 68, to control valve 76 in gas line 78 which is interconnected 
through regulating valve 80 to inert gas supply 82. 
As illustrated, valve 70 would be connected through line 84 to a control 
unit, not shown, which would receive signals from line 58 attached to 
sensor 50 in tube 10. Valve 72 would be interconnected through line 86 to 
a control unit, not shown, which would receive signals from line 60, 
connected to sensor 52. Likewise, valve 74 would be actuated by 
interconnection with line 88 to a control unit which receives signals from 
line 62 connected to sensor 54. 
The opening of any of valves 70, 72, 74 and 76 provides inert gas from 
supply 82 through feed lines 78. Lines 78 are provided with regulators 80 
to control the pressure of the inert gas contained in supply 82 and 
transmitted to plenum 15. Exemplary inert gases include nitrogen and 
carbon dioxide, both of which do not provide a combustible mixture when 
mixed with exhaust gases from the rockets. Generally, the rocket's exhaust 
contains hydrogen and carbon monoxide; thus it is necessary to prevent 
oxygen from entering the system and, especially, to prevent any mixtures 
containing hydrogen and oxygen from reaching the very high temperatures 
present in the exhaust plume of a rocket, since these high temperatures 
could result in a violent combustive reaction occurring. 
It is to be understood that due to factors such as the number of launch 
tubes and the length and direction of flow of the gases in plenum chamber 
15, different feed positions for the gas may be provided. In fact, sensors 
50, 52, 54 and 56 may be connected to a single control and actuator device 
which opens a single regulated valve if such a system will provide the 
required safety, i.e. prevent sufficient oxygen from reaching the plenum 
chamber to produce a combustible mixture. 
Further, it is to be understood that the launch tube covers shown open in 
this drawing, i.e. covers 46 and 48, will close and seal after firing of 
the rocket, and the plenum will close and seal through use of appropriate 
cover(s), not shown. It is further understood that if the launch tube rear 
cover is closed after firing the rocket, a pressure sensor in the plenum 
would be incorporated to function as sensors 50, 52, 54, 56 and in 
addition to them. 
FIG. 2 schematically illustrates the preferred control and actuating 
circuitry of the present invention. In the figure, a pressure signal is 
generated at sensor 56 and carried by line 64 to comparator 102. 
Atmospheric pressure is represented by a signal from pressure sensor 104 
and carried by line 106 to adder 96 which sums the signal with an 
adjustable signal provided to adder 96 by psi adjuster 98. As illustrated, 
psi adjuster is variable both in the positive and negative directions to 
result in either an increase or decrease in the signal received from 
sensor 104. In the preferred form the psi adjuster 98 would be set at +1 
psi and the output signal from adder 96 carried in line 100 would be the 
atmospheric pressure plus 1 psi. Adder output in line 100 is provided to 
comparator 102 which also receives a signal representative of launch tube 
pressure from pressure sensor 56 through line 64. The signal carried in 
line 64 would be connected to the comparator, such that when the 
atmospheric pressure, plus 1 psi, is greater than the launch tube 
pressure, comparator 102 provides a signal through line 108 to valve 
actuator 110 which opens valve 76 and allows gas to pass through line 78, 
as indicated by the arrows. In this manner, the system will operate to 
feed inert gas into plenum chamber 15 when the pressure at sensor 56 is 
equal to or less than 1 psi above atmospheric pressure. 
In an optional system, the atmospheric pressure sensor 104 could be 
eliminated, and the comparator provided with a fixed base signal for 
comparison, i.e. 14.7 psi. This system, of course, would function quite 
well for situations where the variations in atmospheric pressure are not 
sufficiently great to necessitate the comparison. Additionally, in this 
optional system, then, the adder which enhances a portion of the signal 
could be eliminated, as well, and the fixed signal provided to the 
comparator could be adjusted upwardly or downwardly to provide for the 
desired pressure differential. For instance, a fixed signal provided to 
the comparator could be set at a level corresponding to a pressure of 15.7 
psi, and thus the comparator would provide a signal to the actuator when 
the pressure in the associated launch tube was less than or equal to 15.7 
psi. 
In systems with which the present invention may be associated, only a 
decrease in the system pressure below the atmospheric pressure plus, say, 
1 psi causes air (oxygen) to flow into the system and possibly result in 
combustion of the residual exhaust gases. The inert gas is needed in the 
system when the system pressure decreases. The inert gases are arranged to 
flow into the system at any time that the pressure is less than 
approximately 1 psi above atmospheric pressure. 
Although there have been described above specific arrangements of a 
combustion suppressor for a multiple launch tube rocket system in 
accordance with the present invention for the purposes of illustrating the 
manner in which the invention may be used to advantage, it will be 
appreciated that the invention is not limited thereto. For example, 
although the invention has been disclosed in the association with four 
launch tubes and a manifold system therefor, the principles of the 
invention are equally applicable to any comparable system for the enclosed 
firing of rockets or the like. Accordingly, any and all modifications, 
variations or equivalent arrangements which may occur to those skilled in 
the art should be considered to be within the scope of the invention as 
defined in the appended claims.