US3087386A - Adapter for missile launcher - Google Patents

Description

April 30, 1963 R. D. RUNG ETAL 3,087,386

ADAPTER FOR MISSILE LAUNCHER Filed March 23, 1961 2 Sheets-Sheet 1 [7 a L x I 1 I m i 19 I j FIG.

INVENTORS R. 0. RUNG FIG. 2 EDWARD J. BARAKAUSKAS QKQ.

M MW BY M 95 AGENT April 30, 1963 R. D. RUNG ETAL ADAPTER FOR MISSILE LAUNCHER 2 Sheets-Sheet 2 Filed March 25, 1961 INVENTORS R. D. RUNG EDWARD J. BARAKAUSKAS AT RNEYS 6.

AGENT 3,087,386 Patented Apr. 30, 1.963

f flee 3,087,386 ADAPTER FOR MISSILE LAUNCHER Robert D. Rang and Edward J. Barakauskas, Saratoga, Caiif., assignors, by mesne assignments, to the United States of America as represented by the Secretary of the vy Filed Mar. 23, 1961, Ser. No. 97,980

3 Claims. (Cl. 891.7)

The present invention relates generally to missile launcher-s and more specifically to means for adapting a launcher to missiles of various sizes.

With the advent of ballistic missiles came the need for the method of making the missile launching complex invulnerable to surprise attack by enemy missiles and aircraft. Without such invulnerability it would be possible for ballistic missile capability to be completely destroyed before missiles could be launched in a retaliatory action. Further, without means to protect these launching complexes from destruction by enemy attack, they would be unable to fill the primary function of acting as a deterrent to possible enemy surprise attack.

Accordingly, several expedients have been the subject of extensive research and development. The three most prominent of these are firstly, the hardening of launching sites as, for example, by building concrete silos below ground level; secondly, by launching the missile from an airborne aircraft; and thirdly, by launching the missile from a moving ship or land vehicle. This invention finds use primarily in missile launchers of the third category. However, it cannot be said that this invention is inapplicable to the other two categories as it is possible that such a device could be uilized in conjunction with the launching of any ballistic or guided missile.

The missile launching system which is mounted in a vehicle, such as a submarine or truck, is usually provided with a supply of missiles supported in a position which permits rapid firing. Such a vehicle may have a tube launching system which includes one or more missile launching tubes, each having a missile positioned therein. The tube acts as a storing and conveying means as well as launcher. Such launching systems may be constructed in a manner to permit the launching of a relatively large long range missile. However, in certain instances it is desirable for the launching system to launch a missile having a shorter range. Consequently, these missiles are lighter in weight and have a configuration which is shorter than the longer range missiles. Such a missile is constructed with the same diameter of the large missile in order that it may be properly ejected from the missile launching tubes. However, since these missile launching tubes have access doors which are designed to provide an access to the missile guidance package it is necessary to provide means which will raise the smaller missile from the lower end of the launching tube in order that access doors may be aligned with the guidance package of the smaller missile. Further, when the launching vehicle is a submarine, submerged below the surface of the water, it is necessary to constantly maintain the center of gravity of the ship at a common point. Normally, the sea water which fills the tube system subsequent to the launching of a large missile adequately compensates for the weight of the missile. However, when using a smaller missile it is necessary to take aboard a smaller amount of ballast in order not to over-compensate for the weight of the missile.

Accordingly, an object of the present invention is to provide an improved launching system which will permit the launching of various size missiles.

Another object of the present invention resides in the provision of a means which will compensate for a missile height differential in a missile launching system.

Still another object of the present invention is to provide a missile launching system which compensates for the differential in Weight between various size missiles.

A further object of this invention is to provide a missile launcher which will compensate for weight and height differentials in various missiles.

A further object of this invention is to provide a compensating means which is simple in construction, relatively inexpensive in cost, and reliable in operation.

Other objects and many of the attendant advantages of this invention will be readily appreciated as the same becomes better understood by reference to the following detailed description when considered in connection with the accompanying drawings wherein:

FIG. 1 is a transverse cross-sectional view of a typical ballistic missile launching vehicle;

FIG. 2 is a sectional view of the lower portion of a launching tube system;

FIG. 3 is a view partially in section taken substantially along the line 33 of FIG. 2;

FIG. 4 is a perspective view of another embodiment of the present invention; and

FIG. 5 is a sectional view taken substantially along the line 5-5 of FIG. 4.

FIG. 1 illustrates one embodiment of the present invention and, more specifically, it discloses a cross-sectional view of a ballistic missile launching submarine 11. As each of the missile launching systems 12 in the submarine 11 are identical, the description which follows hereinafter will describe a single launching system.

A missile 13 is positioned in the launching system 12 which has its upper portion covered by a hatch 14. Missile launching system 12 includes an outer tube 15 which has resiliently mounted therein an inner tube 16. The inner tube 16 and the outer tube 15 are provided with an opening 17 which is utilized to gain access to the missile guidance package through opening 18 in the missile skin. The missile 13 is ejected from the inner tube 16 when high pressure fluid is released from a fluid flask 19. This fluid pressure is controlled by a fluid valve system, not shown, positioned in the conduit 21 which connects the fluid flask 19 with the chamber 22 in the lower portion of the launching system 12. Hydraulic springs 23 resiliently support the inner tube 16 within the outer tube 15 thereby isolating the missile 13- trom sudden and severe shocks as, for example, from shocks created by the detonation of depth charges.

FIG. 2 illustrates in greater detail the adapter 31 which is utilized to adapt the launching system 1 2 to accommodate a small missile 13. Missile 13 is shorter in height and lighter in weight than the largest missile which may be launched by system 12. The inner tube 16 has a support ring 32 positioned adjacent its lower end 33. Sealing means 34 forms a fluid tight chamber 22 below the missile and assures that the entire fluid pressure from fluid flask 19 will be utilized to eject the missile 13 from the inner tube .16. T he adapter stool 31 comprises a short tubular shaped section 35 having a flange portion 36 at its upper end. The flange portion 36 supports the missile 13. The adapter stool '31 is in turn supported by the support ring 32. The clamps '30 are utilized to lock the adapter stool 31 to the support ring 32. The support ring 32 is resiliently connected to the inner tube 16 by any suitable means.

FIGS. 2 and 3 illustrate the one-way valve means 37 of the adapter stool. The flapper valves 38 are hinged at 39 to permit the upward passage of eject air. However, when fluid attempts to pass downwardly through the valve means 37 in the direction of arrow 41, the valves 38 automatically close and substantially prevent the passage of fluid therethrough.

FIGS. 4 and 5 illustrate another embodiment of the present invention. Only the lower portion of the adapter stool apparatus is illustrated. Ribs 51 are provided on the lower end of the stool to provide structural support therefor. 'Flapper valves 52are pivoted about axis .53 and permit the passage of fluid therethrough in an upward direction butsubstantially prevent the flow of fluid in .the downward direction as indicatedby arrow 41.

In operation, when it is desired to launch a relatively large missile from the'launching system, the adapter stool 31 is completely removed by retracting the. clamping means 30 and vertically removing the adapter stool 3 1 from the launching system '12. The large missileis lowered directly into the innertube 16 and is supported directlyby the support ring 32. However, when a smaller missileis to'be launched by the system 12, the adapter stool 31is placed in the inner tube .16 adjacent to and supported by the support ring 32 in a manner shown in FIG. 2. This support ring compensates for the varying height of the'smaller missile by moving it upwardly by an amount necessary to insure that the guidance package opening 18 in the missile .13. can be reached through the access 17. In order to compensate for the weight differential between the smaller and larger typemissile, the adapter stool provides valve means 37 which function as a false floor in the launching system to decrease the amount of ballast water taken into the launching system after the ejection of a'missile. Thatis, after the missile is.ejected,-sea water completely :fills the .inner tube 16 but is prevented from reaching the chamber 22 by the one-way valve means illustrated in FIGS. 2 and 4. By taking aboard an amount of water which is equal in weight to that of the ejected missile the submarine substantially maintains the same center of gravity after launch that .it had before launch and, therefore, its stability remains substantiallyconstant.

It is pointed out that should the missile launching system be mounted in a truck where it is not absolutely necessary to compensate for the difference in weight, the one-way valve means could be eliminated. Further, the length of the tubular shaped section 35 above the support ring 32 can be varied in order to compensate for any height differential between the larger and smaller missiles. Still further, the amount of ballast-which is taken aboard subsequent to missile launching can be varied by positioning the one-way valve means anywhere within the height of the tubular shapedsection 35. That is, the valve could be lowered in the adapter stool to permit more ballastwater or raised to permit less ballast water to be taken aboard. It is only necessary that the valve means 37 not have its operation obstructed by the lower end of the missile 13. The valve need not be completely fluid tight because after the missile is launched the ballast water quickly fills the inner tube 16 and the hatch -14 is immediately thereafter closed. Should the ballast water then seep down through the valve means this would not alter the weight of the ballast, as the batch is closed tight, or effectively change the center of gravity of the submarine.

Both of the above-described embodiments of the present invention permit the launching system to eject both large and small missiles having varying weight and height. It is seen that this invention can be utilized in situations where it is necessary to compensate for only one of these two factors. That is, the adapter stool can be used to compensate for height differential, weight. differential or both of these diiferentials.

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.

What is claimed is:

1. In a missile system mounted in a submarine and operable while submerged to vertically launch a large missile, said system comprising an outer tube vertically mounted in said submarine, an inner tube resiliently mounted within said outer tube, said tubes having their upper ends projecting outwardly from said submarine, a hatch operable to open and close said upper ends of said tubes, a support ring adjacent and resiliently supported by the lower end [of said inner tube, said support ring being operable to vertically support said large missile, an access pasagew-ay through said tubes operable to permit access to the guidance opening of said large missile, an air eject system operable to eject said 'large missile from said inner tube, said eject system including a chamber below the lower ends of said tubes; thecombination of an adapter stool operable to convert said system insa manner to permit the .iaunching of a small missile, saidsmall rnissile being shorter in h'eightand lighter in weight than said large missile, said adapter stool being operably interposed between said support ring and small missile in a manner to compensate for the difference in height of said small missile in a manner topermit alignment of said access passageway with the guidance opening of said small missile, said adapter havinga one-way valvemeans operable-to permit eject air to pass .therethrough [from said chamber to eject said small missile and to prohibit fluid flow reversely therethrough.

2. A'missile launching apparatus for missiles of varying length and identical diameter comprising a vertically disposed outer tube, a second inner tube of a diameter substantially less than said outer tube, the inner diameter of said inner tube being substantially equal to the diameter of the missiles, said inner tube terminating short of the bottom of said outer tube, a sealing means between said inner and outer tubes located substantially at the bottom of the inner tube to provide a cylindrical compartment below said inner tube of a size to regulate the water taken in after firing the missile, said water serving as ballast to equal the weight of the tired missile, said water normally filling said inner tube and said cylindrical compartment after firing the longest possible missile, a

support ring secured to the lower end of said inner tube to support the longest possible missile, and a removable adapter stool fitting within said inner tube and seated on said support ring and projecting downward below the bottom of said inner tube, said stool also extending upward within said inner tube to support missiles of a length less than the longest missile, said adapter stool having means permitting fluid flow upward-within said inner tube and restricting fluid flowdownward from said inner tube to restrict the flow ofballast water and prevent said ballast water from entering said cylindrical compartment after firing a missile shorter than the longest possible missile.

3. A missile launching apparatus according-to claim 2 and including an external shoulder on said adapterstool,

said shoulder engaging the support ring to support said adapter stool a predetermined distance below'the bottom of said inner tube to limit the weight of water admitted as ballast, in the inner tube and the adapter stool. I

ReferencesCited in the'file of this patent UNITED STATES PATENTS Bialy Sept. 5, 1961

Claims (1)

1. IN A MISSLE SYSTEM MOUNTED IN A SUBMARINE AND OPERABLE WHILE SUBMERGED TO VERTICALLY LAUNCH A LARGE MISSILE, SAID SYSTEM COMPRISING AN OUTER TUBE VERTICALLY MOUNTED IN SAID SUBMARINE, AN INNER TUBE RESILIENTLY MOUNTED WITHIN SAID OUTER TUBE, SAID TUBES HAVING THEIR UPPER ENDS PROJECTING OUTWARDLY FROM SAID SUBMARINE, A HATCH OPERABLE TO OPEN AND CLOSE SAID UPPER ENDS OF SAID TUBES, A SUPPORT RING ADJACENT AND RESILIENTLY SUPPORTED BY THE LOWER END OF SAID INNER TUBE, SAID SUPPORT RING BEING OPERABLE TO VERTICALLY SUPPORT SAID LARGE MISSILE, AN ACCESS PASSAGEWAY THROUGH SAID TUBES OPERABLE TO PERMIT ACCESS TO THE GUIDANCE OPENING OF SAID LARGE MISSILE, AN AIR EJECT SYSTEM OPERABLE TO EJECT SAID LARGE MISSILE FROM SAID INNER TUBE, SAID EJECT SYSTEM INCLUDING A CHAMBER BELOW THE LOWER ENDS OF SAID TUBES; THE COMBINATION OF AN ADAPTER STOOL OPERABLE TO CONVERT SAID SYSTEM IN A MANNER TO PERMIT THE LAUNCHING OF A SMALL MISSILE, SAID SMALL MISSILE BEING SHORTER IN HEIGHT AND LIGHTER IN WEIGHT THAN SAID LARGE MISSILE, SAID ADAPTER STOOL BEING OPERABLY INTERPOSED BETWEEN SAID SUPPORT RING AND SMALL MISSILE IN A MANNER TO COMPENSATE FOR THE DIFFERENCE IN HEIGHT OF SAID SMALL MISSILE IN A MANNER TO PERMIT ALIGNMENT OF SAID ACCESS PASSAGEWAY WITH THE GUIDANCE OPENING OF SAID SMALL MISSILE, SAID ADAPTER HAVING A ONE-WAY VALVE MEANS OPERABLE TO PERMIT EJECT AIR TO PASS THERETHROUGH FROM SAID CHAMBER TO EJECT SAID SMALL MISSILE AND TO PROHIBIT FLUID FLOW REVERSELY THERETHROUGH.

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