US3182554A - Missile ejection method and apparatus - Google Patents

Description

United States Patent Ce 3,182,554 MFSSELE EB'ECTEGN METHGD AND APPARATUS Edward J, Baralraushas, Saratoga, Quilt, assignor, by mesne assignments, to the United States of America as represented by the Secretary of the Navy Filed Earn. 17, 1964, Ser. No. 338,54il 3 Claims. (Cl. 89-4.?)

The present inventionrelates to a method and apparatus for bringing about the substantially vertical ejection of a missile from a launching tube carried by a submarine or other underwater vessel.

At the present time it is strategically desirable to launch missiles from a vessel travel ng below the surface of the ocean or other body of water. Numerous advantages accrue from such a procedure, since countermeasures can not readily be taken by an enemy due to the mobile nature of the vessel on which the launching apparatus is carried.

One method by which a launching of this type has been accomplished includes the provision of a source of compressed air, which is programmed into the launching tube at the time that ejection of the missile is to be eifected.

Obviously drawbacks to this expedient include not only the considerable weight of the air storage equipment, but also the fact that extended periods of time may elapse between the installation of the apparatus on the vessel and the actual lauching of the missile. This involves a necessity for maintaining the pressure of the air during this interval, as well as maintaining a constant check on the status of the equipment associated therewith.

The foregoing method, in which air under compression is stored in a tank or cylinder and then discharged into the missile launching tube through a programmed control valve, while yielding generally acceptable results, nevertheless is subject to the disadvantages above enumerated. It would be desirable if the source of compressed air could be eliminated, as this would materially reduce the weight which the vessel must carry and thus add to its range and maneuverability. In accordance with a feature of the present disclosure, the compressed air source is replaced by a gas generator which preferably includes a fuel in solid form which is not ignited until the time where the launching is to be actually carried out. One advantage of such an arrangement is that the volume of such fuel is but a minor fraction of that represented by the compressed air source which it replaces. In addition, there is no problem of maintaining air pressure over extended periods of time, nor of air leakage due to a malfunction of the storage or transfer equipment.

Gne necessary characteristic of a system such as set forth herein is that the generated gas possess a temperature (in the region of the missile, or, in other words, in the launching tube) below that at which the possibility of ignition of the missile propellant per so might occur. The present disclosure produces a working fluid at a temperature sufficiently low so that no such premature ignition of the missile propellant can take place. Furthermore, the fluid of the present disclosure has relatively uniform characteristics when it pressurizes the launching tube chamber, and thus a successful launching operation is more likely to result.

Previous attempts have been made to utilize gas pres sure generators to achieve an objective somewhat analoguns to that desired herein. One technique which has been so employed is to provide for the passage of gas from the generator to a tank of some coolant (such as water) to pressurize the latter. The coolant is then sprayed into the exhaust stream from the gas generator. This procedure, however, is not completelysatisfactory, because the pressure tap significantly changes the exhaust nozzle area and thus the burning rate of the gas generator.

3,13825lii Patented li ay ii, 19%5 In addition, it is necessary to form an efiective seal for the water or other coolant within the nozzle or nozzles, and this seal must be of a type which completely ruptures as soon as the gas generator becomes operative. Still further, the injection apparatus is subject to malfunction by blockage of either the line employed to pressurize the water reservoir or by failure of the means used to seal the nozzles.

Another technique which has been subject to experiment is that designated as the so-called puddle. In this system, the exhaust from the gas generator impinges directly upon the surface of a pool of water. The latter is vaporized and enters into the launching tube where it acts to eject the missile when a certain pressure level has been reached. While this method is not subject to serious malfunctions from a mechanical standpoint, nevertheless the vaporization action is irregular and the cooling characteristics are not uniform. Consequently, it is ditlicult to predict with accuracy the precise instant at which the missile will be ejected. Since the flight characteristics of the missile depend at least in part on its orientation at the instant when it leaves the launching tube, it is extremely important that this time instant coincide with that programmed by the operator.

The present concept does not include the undesirable features of the above-mentioned techniques. Instead, it incorporates the production of a series of pressure drops, or steps, in the exhaust region of the gas generator. These pressure steps are made use of to create a corresponding series of pressure variations for ejection of the coolant into the launching tube itself. In this fashion, the coolant can be emitted at a continuous rate into the region where it mixes with the pressurized gas from the source and thereby yields an essentially uniform mixture the characteristics or" which can be predicted with a high degree of accuracy. Thus the launch point can be determined by the operator without introducing the possibility of sending the missile on an incorrect course due to a premature or delayed firing.

One object of the present invention, therefore, is to provide an improved form of method and apparatus for launching a missile from an underwater vessel such as a submarine.

Another object of the invention is to provide for the substantially vertical ejection of a missile from a launching tube carried by an underwater vessel through'the action of a pressurized fluid produced at the timethat the launching operation is carried out.

A further object of the invention is to provide for the ejection of a missile from a launching tube by means of a pressurized mixture of gas and water vapor, which is maintained below a temperature at which premature ignition of the missile propellant might otherwise occur.

A still further objector" the invention is to provide a missile firing apparatus for an underwater vessel, such apparatus eliminating the necessity of maintaining a source of fluid under pressure for what might be ex tended periods of time.

Other objects, advantages, and novel features of the invention will become apparent from the following detailed description of the invention when considered in conjunction with the accompanying drawings wherein;

FIG. 1 is a partly sectional View of a preferred form of missile ejection apparatus designed in accordance with the present invention, illustrating the condition thereof prior to the time that ejection of the missile is to take place; and

FIG. 2 is a view of the apparatus of FIG. 1, illustrating its condition when an ejection of the missile is taking place.

Referring now to the drawing, there is shown a launching tube which is carried by, and mounted on, some underwater vessel such as a submarine. This tube, generally identified in the dr'awingby the reference numeral 10, is

. so oriented on the vessel as to support therewithin a missile 12 in a generally upright or vertical position. As shown in the drawing, missile 12 is maintained within the launching tube 19 so as to create a lower chamber 14 which is initially at ambient temperature and pressure prior to the time that the ejection apparatus of'the invention becomes operative. It should be noted that the missile 12 incorporates one or more exhaust nozzles 16 which lie within the chamber 14 and open directly thereinto. Missile 12 is heldaway from direct contact with the inner wall of tube byan annular seal 18,'which acts to preclude any fluid which may subsequently, fill chamber 14 from being exhausted therefrom through the opening between missile .12 and the inner wall of the launching tube.

As further illustrated, the lower chamber 14 of the launching tube ltl'is connected by a conduit 20 with the fluid-generatingapparatus of the present invention. This apparatus is generallyidentified by the reference numeral 22, and consists of two basic partsnamely, a gas generator. 24 and a mixing unit 26 by means of which some coolant such as water is added to the gas from generator 24 prior to the time that such gas is supplied to the chamber 14 through the conduit 20.

Reference to FIG. 1 of the drawings will bring out the conditions which prevail insthe system prior to a missile launching. At this time, the chamber 14 and conduit it) are each at ambient temperature and pressure, and no l the conduit 20 by any suitable means such as welding or a plurality of bolts (not shown). The tank 28 is designed shape. The fuel 44 may be similar in nature to 'a rocket propellant, and is enclosed within a tubular housing 46 to include a tubular standpipe 38 which is mounted coaxially within the tank and is supported at its lower end by a retaining member 32. At the upper end of the standpipe 30 is formed a plurality of openings 34 which are circumferentially spaced around the tube and which have a function which will later be described. The lower portion of standpipe 30 has formed therein a further plurality :of openings 35 which function as nozzles.

These openings 35, like the openings 34, are circumferentially spaced, and provide communication between the interior of the 'standpipe 30'and thatregion 36 which lies between the outer Wall: of the standpipe and the inner wall of thetank 28. Such region isfilled with a liquidcoolant 37 ,(suchas water) 'to a level 38 below the openings 34.

Nozzles 35 are designed to be continuously open, and to eject thefcoolant 37"therethrough when a pressure differential is created between the two open ends of each nozzle. However, prior'to launching the missile 12, coolant 37 reaches'the same level 38 in both the standpipe 30 and in the region exterior thereof.

Theretainin'g member 32, in addition to supporting the standpipe- 30, also positions a diaphragm 39' which acts to 37 is precluded from entering into the conduit 24);

The upper end of the standpipe 3% is closed by a cap '40; Also supported by the upper end of the standpipe is one of a plurality of baflies 42 which lie intermediate the mixing unit 26-and the gas generator 24; The particular structure for supporting these bafiles 42 in position forms no part of the present invention, and it is only necessary that the bailles be sospaced apart as to create an indirect path for gas entering the tank' region 36 from the generator 24.

The generator 24is designed to contain therewithin a fuel 44 which isin solid form and of generally cylindrical which is attached to and supported by the tank 28. These two cylindrical containers 28 and 46 are secured together in any suitable fashion, such as by a plurality of bolts (not shown). The means for supporting and positioning the fuel 44 within the housing 46 is not fully illustrated, but includes a support 47 having an axial opening 48extending therethrough by means of which gas can flow from I I the generator 24 to the interior region 36 of the tank 28 any suitable means for bringing about va burning of the fuel 44 may be utilized as long as the action of thiscontrol mechanism is essentially instantaneous.

Prior to'the time that the missile 12 is to be ejected from the launching tube 10, the chamber 14 is unpres surized, as is the conduit 20. Also devoid of any pressurized fluid is the interior ofthe fuel housing 46, the passageway t8, and the region between the bafiles 42. This condition is illustrated in FIG. l,"which also shows the coolant 37 as reaching the commonlevel 38 within both the tank'28 and thestandpipe 30. v 7

If now it is desired to eject the missile 12 from the tube It), the control operator on the vessel gives a firing signal which brings about an energization of the conductor 52 and in turn activates the ignitor 50. .At this point,

the. fuel 44 begins to burn, and immediately forms gas under pressure'within the housing 46. The gas thus produced flows through the passageway 48, and a portion 54 of this gas enters the standpipefit) through the apertures 34 to create a pressure upon the surface of that portionof the coolant 37 which is within the 'standpipea As soon as this pressure reaches a predetermined level determined by the characteristicsof the diaphragm 39, the latter ruptures, and the coolant within the standpipe is ejected into, the conduit 20. At the same/time, another portion ofthe gas from the'generator 24 follows a path between the baflles 42 to come in to contact with the coolant in the region 36 of tank 28. This gas pressure forces such cool-' ant through the circumferentially-spaced nozzles 35, since the interior of the standpipe is now empty of liquid and hence a pressure differential is present between one end of each nozzle 35- and the opposite end thereof." Since the'nature of the nozzle is such that water passes continuously therethrough when a pressureldrop'exists thereacross, the amount of such coolant that enters the standpipe 30 is determined by the structural design of thenozzles. By properly sizing the openings 34 in the upper portion of the standpipe 30, a large pressure drop is created from the outside of the standpipe to the inside thereof. 7

When the actions just described have taken place, the

condition of the system is such as shown in FIG. 2. The standpipe 30, as illustrated, is filled with gas at, high temperature, and the conduit 20 filled with a mixture 'of'gas and water at a lower temperature; This gas-water'mixture is supplied to the chamber 14' of the launch tube 10,

where it exerts a launching pressure against the lower surface of the missile 12 to eject it from the tube. The, pressure build up in chamber 14 is made possible by the presence of the annular seal 18, which precludes any leakage of the pressurized mixture between theouter surface 7 of the missile and the inner wall of the launch tube.

It has been stated above that one of the important characteristics of the present invention is that the pressurized mixture which comes into contact with the missile exhaust nozzles 16 is ata sufficiently low temperature so that it will not cause premature ignition of the missile propellant per se. This has not been capable of achievement in systems heretofore employed for ejection purposes. In addition to this feature, however, certain other important advantages of the present disclosure should be emphasized. These include (1) the major portions of the coolant is injected into the gas at a controlled continuous rate, so that the inconsistent action of previous arrangements which utilize a so-called puddle of liquid is no longer present, (2) it is impossible with the present arrangement to inject gas at an excessively high temperature into the launching tube without rupturing the water seal, (3) passage of the hot gas through the water tank in itself creates the pressure which is utilized for injection of the coolant, and (4) the water ejection nozzles are always open and hence any potential malfunction of a control valve can not occur.

Although the invention has been illustrated as comprising a particular physical association between the tank in which the coolant is contained and the gas generator, it should be understood that alternative forms of each of these structures may be employed and their physical interrelationship modified without changing the principles of operation of the apparatus.

Obviously many modifications and variations of the present invention are possible in the light of the above teachings. It is therefore to be understood that within the scope of the appended claims the invention may be practiced otherwise than as specifically described.

I claim:

1. In an apparatus designed to be carried by an underwater vessel and controllable by an operator so as to effect the launching on an essentially vertical trajectory of a missile toward a target, said apparatus comprising:

a launching tube within which said missile is vertically supported and positioned so as to establish a closed chamber at the lower end of said tube which, prior to a launching operation, is at substantially ambient temperature and pressure;

a gas generating unit including a cylindrical housing;

a solid gas-producing fuel contained within said housing;

a mixing chamber also of generally cylindrical form and connected to said gas generator;

at body of liquid within said mixing chamber;

a substantially tubular standpipe located Within said mixing chamber, of smaller diameter than said chamher, and disposed in coaxial relationship therewith,

said standpipe containing a first plurality of apertures at that end thereof proximate to said gas generator and a second plurality of apertures at the other end thereof;

a tubular conduit connecting that end of said mixing chamber opposite to said gas generator to the closed chamber at the lower end of said launching tube;

a frangible closure element extending across the end of said tubular standpipe between said second plurality of apertures and said conduit, said closure element acting to retain said body of liquid within said mixing chamber prior to the ignition of said fuel; and

means controlled by said operator for igniting said fuel;

whereby, when said fuel is ignited, the gas generated thereby will pass into said mixing chamber and divide into two portions, one of which portions impinges the surface of that portion of said body of liquid exterior of said standpipe and the other of which portions enters the first plurality of apertures in said standpipe to pressurize the liquid therewithin and thereby rupture said closure element, so that the fluid initially in said standpipe enters said conduit in a body, and whereby the portion of said gas which impinges that portion of said body of liquid exterior of said standpipe also pressurizes the latter and forces such liquid through the said second plurality of apertures into the interior of said standpipe to mix with the gas passing therethrough from said generating unit, following which such mixture passes through said conduit to enter the chamber at the lower end of said launching tube where it effects the launching of said missile, the temperature of the mixture reaching the said launching tube chamber being lower than the temperature of the gas generated by the burning of said fuel due to the addition to such gas of the liquid ejected thereinto during passage of the gas through said standpipe.

2. The combination of claim 1, further comprising a plurality of gas-deflecting partitions disposed between said gas generating unit and said mixing chamber for conducting that portion of the generated gas which impinges the surface of that portion of said body of liquid exterior of said standpipe over a path which is longer than the linear distance between the point at which the gas is generated and the surface of the said body portion of liquid.

3. The combination of claim 2, in which the housing forming part of said gas generating unit has contained therein an igniting device in direct contact with said fuel, and means for energizing said igniting device to initiate an essentially instantaneous combustion of said solid fuel.

References Cited by the Examiner UNITED STATES PATENTS 886,199 4/08 Flaig 39.57 1,828,784 10/31 Perrin 6039.59 2,644,364 7/53 Nass 89-1.7 2,989,899 6/61 Siegel 89 1.7 3,064,902 11/61 Moore et a1 6039.48 X

BENJAMIN A. BORCHELT, Primary Examiner.

SAMUEL W. ENGLE, Examiner.

Claims (1)

1. IN AN APPARATUS DESIGNED TO BE CARRIED BY AN UNDERWATER VESSEL AND CONTROLLABLE BY AN OPERATOR SO AS TO EFFECT THE LAUNCHING ON AN ESSENTIALLY VERTICAL TRAJECTORY OF A MISSILE TOWARD A TARGET, SAID APPARATUS COMPRISING: A LAUNCHING TUBE WITHIN WHICH SAID MISSILE IS VERTICALLY SUPPORTED AND POSITIONED SO AS TO ESTABLISH A CLOSED CHAMBER AT THE LOWER END OF SAID TUBE WHICH, PRIOR TO A LAUNCHING OPERATION, IS AT SUBSTANTIALLY AMBIENT TEMPERATURE AND PRESSURE; A GAS GENERATING UNIT INLCUDING A CYLINDRICAL HOUSING; A SOLID GAS-PRODUCING FUEL CONTAINED WITHIN SAID HOUSING; A MIXING CHAMBER ALSO OF GENERALLY CYLINDRICAL FORM AND CONNECTED TO SAID GAS GENERATOR; A BODY OF LIQUID WITHIN SAID MIXING CHAMBER; A SUBSTANTIALLY TUBULAR STANDPIPE LOCATED WITHIN SAID MIXING CHAMBER, OF SMALLER DIAMETER THAN SAID CHAMBER, AND DISPOSED IN COAXIAL RELATIONSHIP THEREWITH, SAID STANDPIPE CONTAINING A FIRST PLURALITY OF APERTURES AT THAT END THEREOF PROXIMATE TO SAID GAS GENERATOR AND A SECOND PLURALITY OF APERTURES AT THE OTHER END THEREOF; A TUBULAR CONDUIT CONNECTING THAT END OF SAID MIXING CHAMBER OPPOSITE TO SAID GAS GENERATOR TO THE CLOSED CHAMBER AT THE LOWER END OF SAID LAUNCHING TUBE; A FRANGIBLE CLOSURE ELEMENT EXTENDING ACROSS THE END OF SAID TUBULAR STANDPIPE BETWEEN SAID SECOND PLURALITY OF APERTURES AND SAID CONDUIT, SAID CLOSURE ELEMENT ACTING TO RETAIN SAID BODY OF LIQUID WITHIN SAID MIXING CHAMBER PRIOR TO THE IGNITION OF SAID FUEL; AND MEANS CONTROLLED BY SAID OPERATOR FOR IGNITING SAID FUEL; WHEREBY, WHEN SAID FUEL IS IGNITED, THE GAS GENERATED THEREBY WILL PASS INTO SAID MIXING CHAMBER AND DIVIDE INTO TWO PORTIONS, ONE OF WHICH PORTIONS IMPINGES THE SURFACE OF THAT PORTION OF SAID BODY OF LIQUID EXTERIOR OF SAID STANDPIPE AND THE OTHER OF WHICH PORTIONS ENTERS THE FIRST PLURALITY OF APERTURES IN SAID STANDPIPE TO PRESSURIZE THE LIQUID THEREWITHIN AND THEREBY RUPTURE SAID CLOSURE ELEMENT, SO THAT THE FLUID INITIALLY IN SAID STANDPIPE ENTERS SAID CONDUIT IN A BODY, AND WHEREBY THE PORTION OF SAID GAS WHICH IMPINGES THAT PORTION OF SAID BODY OF LIQUID EXTERIOR OF SAID STANDPIPE ALSO PRESSURIZES THE LATTER AND FORCES SUCH LIQUID THROUGH THE SAID SECOND PLURALITY OF APERTURES INTO THE INTERIOR OF SAID STANDPIPE TO MIX WITH THE GAS PASSING THERETHROUGH FROM SAID GENERATING UNIT, FOLLOWING WHICH SUCH MIXTURE PASSES THROUGH SAID CONDUIT TO ENTER THE CHAMBER AT THE LOWER END OF SAID LAUNCHING TUBE WHERE IT EFFECTS THE LAUNCHING OF SAID MISSILE, THE TEMPERATURE OF THE MIXTURE REACHING THE SAID LAUNCHING TUBE CHAMBER BEING LOWER THAN THE TEMPERATURE OF THE GAS GENERATED BY THE BURNING OF SAID FUEL DUE TO THE ADDITION TO SUCH GAS OF THE LIQUID EJECTED THEREINTO DURING PASSAGE OF THE GAS THROUGH SAID STANDPIPE.

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