US3173334A - Missile launching system - Google Patents

Description

March 16, 1965 s. LANDSTROM MISSILE LAUNCHING SYSTEM 4 Sheets-Sheet 1 Filed 001;- 22, 1958 INVENT OR SVEN LANDSTROM A). w- BY ATTORNEYS March 16, 1965 LANDSTROM 3,173,334

MISSILE LAUNCHING SYSTEM Filed Oct. 22, 1958 4 Sheets-Sheet 2 mmmnu|mn|1|m|mm||unmmmmunum llllllIllllllllll[IllIllllHlllllllmllllllllllll IIIIllIlI|llllmlllllllllllllllll nmnmlllll HHHHHHH FIG. 2

llllllllHlHllllllllllllllllllllllllllllllllllllllll I! nl |m|||||m|||ulIllulllllllllllllllllllllllllllllll INVENTOR svew ANDS mou M By ATTORNEY8 March 1955 s. LANDSTROM 3,173,334

MISSILE LAUNCHING SYSTEM Filed Oct. 22, 1958 4 Sheets-Sheet 3 FIG. 3

INVENTOR 8 l/E/V l. A/VD S TRON March 1 Filed Oct FIG. 4

S. LANDSTROM MISSILE LAUNCHING SYSTEM 4 Sheets-Sheet 4 Illlllllllllllllllllllllllllllllllllll Illllllllllllllllllll BY dQm ATTORNEYS United States Patent 3,173,334 MISSILE LAUNCHING SYSTEM Sven Landstrom, Stockholm, Sweden, assignor to the United States of America as represented by the Secretary of the Navy Filed Oct. 22, 1958, Ser. No. 76%,042

2 Claims. (ill. 89-1.7)

(Granted underTitle 35, US. ode (1952), see. 266) The invention described herein may be manufactured and used by or for the Government of the United States of America for governmental purposes Without the payment of any royalties thereon or therefor.

This invention relates to an improved system for launching guided missiles and more particularly to an improved system and methods of use thereof for the launching of guided missiles from a land base.

Experience with launching methods and apparatus systems designed for launching guided missiles has demonstrated the need for a new type equipment for magazining, handling and launching present day guided missiles. In my copending application, Serial No. 769,045, filed Oct. 22, 1958, l have disclosed a system and a method of use thereof suitable for handling the complex weapons usable today for national defense. The instant invention is an improvement of my aforementioned system and methods.

The difiiculties encountered in effectively using todays guided missiles stem from the excessive size and Weight of the missiles coupled with their inherent structural and operational delicacies. To successfully assemble and maintain adequate supplies of present day missiles in a ready status and to launch those missiles in the most expeditious fashion when the occasion arises, requires a complete departure from previous thinking in the magazining, handling and launching techniques used with former conventional weapons.

Accordingly, it is an object of the present invention to provide an improved magazining, handling and launching system and method of use thereof for guided missiles which allows selectability of missiles for launching according to desires as to warhead type, guidance system and propulsion means, from a roundhouse magazine.

A further object or" the invention is to provide an improved launching system for either surface-to-surface or surface-to-air guided missiles which is adapted for single or salvo firing.

Another object resides in the provision of a launching and magazining system which overcomes the shortcomings of prior art fixed lauching systems while providing substantially all the desirable practical functional and safety features of apparatus for this purpose heretofore or now in general use.

Still another object of the invention is to provide a safe, simple and expeditious method and system for handling, storing and launching guided self-propelled missiles.

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 plan view of approximately one-half of a launching system incorporating the present invention with the roof being omitted from the circular magazine to more clearly illustrate details of the invention;

FIG. 2 is an enlarged elevational view with parts shown in section and as viewed from a line substantially corresponding to line 2-4. in FIG. 1;

FIG. 3 is a perspective view showing a missile transporting cart; and

FIG. 4 is a side elevational view with parts shown in section, the section being taken through the launching "ice pit along a plane corresponding to the direction of the ramming rail of the magazine and with the launcher in loading position.

In FIG. 1 is illustrated one half of a system incorporating this invention, it being understood that the other half, comprising a mirror image of FIG. 1 may be located along the broken away left side of FIG. 1. As there shown acircular magazine 14 incorporates a plurality of radially disposed individualmissile stowage cells 15 in which assembledmissiles 23 are stored with the warhead ends directly outwardly. Theindividual cells 15, each contain afeeder rail 20 and are separated from each other byspaced walls 16 the space therebetween being provided with a blast dissipating substance 22, such as sand, to contain any premature explosion in as small an area as possible. The inner periphery of thecircular magazine 14 is formed by individual blast closures ordoors 17 isolating each missile stowage cell .15 from the turntable area located centrally within the magazine. At the center of the magazine is provided apivot post 19 about which themagazine turntable 12 rotates. The outer periphery of the circular magazine is bounded by an external wall 11, which like the other structural components of the magazine may be formed of reinforced concrete or the like.

Theindividual blast doors 17 located on the inner periphery of the magazine are mounted to reciprocally move alongstanchions 18 which form the supporting structure for theroof 43. Theloading rail 2 connectsassembly area 27 with the interior ofcircular magazine 14 while the rammingrail 25 connects thelaunching area 26 with the interior of the magazine.Suitable blast closures 34 and as are located at the outer extremity of the rail passages to isolate the interior of the magazine from any blast effects.

Located centrally within the launching well 26 is alaunching device 13, while adud area 30, remote from themagazine 14, and common to both halves of the system, communicates with the launching well, through ablast door 35. Theassembly area 27, adjacent themagazine 14, houses a turntable 40 which serves to turn the missiles for introduction to either magazine after assembly, or as herein after more fully explained, may be used to cross-feed missiles from the magazine illustrated to an identical counterpart magazine, not shown. A missilecomponent receiving area 38 is provided externally of theassembly area 27 and communicates therewith throughclosure 39, through which missile components may be introduced into the assembly area where they are assembled and checked out intesting area 28. The missiles are then mounted on carriages orcarts 80, FIG. 3, as will become clear as the description proceeds, and are introduced to the magazine throughclosure 34, across loading rail 24 and onto amagazine turntable 12. Theturntable 12 is then rotated to select any desired cell for storage of themissiles 23. The missiles may be all of the same type, as illustrated, or may comprise a mixture of missiles having difierent characteristics. For example, the guidance system, propulsion unit and warhead type may be varied as desired so that a variety of types of missiles is stored in the magazine.

Acontrol area 33 is located externally of the system proper and serves to house necessary control equipment, personnel, electrical power sources and the like.

Underneath themagazine 14 there is provided an emptycart stowage cellar 32, which as explained more fully hereinafter, serves to store empty missile carrying carts after the missiles are launched.

It should be noted that themissiles 23 are shown stowed with the warhead ends directed outwardly. This, it will be observed, places the most lethal part of the missile adjacent the widest portion of the safety barrier 22 separating each reinforced concrete cell 1 5. This feature is primarily a safety feature so that should one or more of the stowed missiles explode prematurely, the detonation will be contained in as small an area as possible. In this connection, it should be noted in passing that the roof of thecells 15 may be constructed of any material which will provide a relatively soft structure, such, for example, as a sand barrier, to aid in restricting the premature detonation or" a missile to as local an area as possible.

Since theassembly area 27 with its rotatable turntable 40 is advantageously located between themagazine 14 and its counterpart, should equipment fail in one half of the system, it is possible to cross feed ready missiles from one magazine to the other. For example, if a casualty occurred in thelaunching device 13 of the illustrated system half, missiles frommagazine 14 could be transferred via the assembly area turntable 40 to the operative launcher system half, not shown. It is obvious that the flexibility and reliability of the overall launching system is considerably enhanced by this feature.

Referring now to PEG. 2, aready missile 23 is illustrated as stowed within acell 15. The missile is mounted on cart till which rests onfeeder rail 20. The cell is surrounded by the outer wall 11, aroof 43, which as previously mentioned, may be padded with a non-frangible r blast attenuating material, and the runway orfloor 45.Tne blast door 17 is shown in a closed position and another missile, illustrated in phantom, is shown in the position it would occupy uponmagazine turntable 12. Thepivot post 19 of themagazine turntable 12 may if desired serve as a central support for theroof 43 as well as the center of rotation of the magazine turntable. Within themagazine turntable 12 is carried anextendable chain ram 42 which is operated by a hydraulically drivensprocket 44. Any conventional extendable chain ram may be used, such as the one disclosed in US. Patent 2,779,246, and rammer in itself, forms no part of this invention.

A pair ofcircular tracks 55 supported by theroof 43 serves tocarry an electrically drivencable drum 54. The circular tracks extend peripherally around themagazine turntable area, just inside thecell doors 17, so that the cable drum may be positioned upon the tracks adjacent any selected missile stowage cell. The cabledrum 54 carries a hook 56 which is engaged in a loop or pad eye connected to the top of each closure 17 (not shown) to hoist the closure to a closed position after the cell is loaded. In order to open the cell, theturntable 12 is rotated to align itself with the selected cell. Acircular guide ring 58, also continuous around the periphery of the turntable area, serves to guide the end of the turntable romote from its pivot post during its rotation by supporting turntable roller 71. Upon proper alignment with the selected cell, a hole in circular rail registers with aplunger 60 positioned in a fluid actuated cylinder 59 which is carried on the underside ofturntable 12.

Upon actuation,plunger 60 of cylinder 59 is extended through 'the registering hole in circular rail '58, to lock the turntable in proper-position, and further extension of theplunger 60 causes deflection of the lever 61 so that throughlinkage 49,latch 57 is retracted from beneathdoor catch 50. Gravity then acts upondoor 17 causing the door to fall intodoor pit 51. A safety door buffer 52 is positioned at the bottom of the pit to cushion the impact. During door descent,carnrned surface 76 engages cam roller 77 to move the latter to theleft thereby moving pivoted link 75 and rod 74 to the right. This movement actuatesovercenterlink 73 to the right around "its-pivot 79, moving support '72 to the right and down- 30 (see FIG. 3) rides onto the feeder rail Zil to its stowed position. The hoisting hook 56 is engaged into a pad eye on thedoor 17 and the door is raised. On closing thedoor 17,carnrned surface 76 again engages cam roller 77, which in this instance, moves the cam roller to the right, which action, through link 75, pushes rod 74 to the left. This pivotsovercenter link 73, left aroundpivot 79, and through its action, positions support 72 underneath the forward section of themissile 23 and in supporting engagement therewith. Forward support '72 is provided so that long periods of stowage will not cause the forward section of the missile to sag due to its unsupported weight.

When thedoor 17 is fully closed, the door catch is again engaged bylatch 57. Just prior to closing the door 1'7, pressure in hydraulic cylinder 59 is partially released allowingcatch 57, which may be spring loaded, to engagecatch 50. The hydraulic cylinder 59 which had previously been partially unloaded so as to release lever 61 from the influence of plunger 68 is now fully retracted, thus retrieving theplunger 69 from its locking position extending through circular guide ring 53 and the turntable is free to rotate to any position, the cell having been loaded with a ready missile. As previously mentioned the turntable roller 71 merely serves to aid the turntable in rotating on the top surface ofcircular guide ring 58.

The sequence of operation during the loading of a cell proceeds as follows: The arrival of themissile carrying turntable 12 at a given cell position is followed by activation of hydraulic cylinder 59, causing projection of theplunger 60 to lock the turntable in that position on the circular guidering. Further projection of theplunger 60 causes a rocking of the linkage 61 to retractlatch 57 from engagement with catch Sll. The door drops to the open position and throughcam 76 causes actuation of the push-pull rod 74 which results in displacement of theforward support 72 thereby releasing the missile for retraction from its stowage cell.

In FIG. 3 there is shown amissile 23 suspended over a typical missile-carrying carriage orcart 80 to more clearly illustrate the structural relationship of parts. As is usual in largermissiles, a set of handling lugs 65 is affixed to the booster section of the missile. These lugs serve to facilitate handling the missile in all the operations required prior to launching. The after lug is normally T-shaped and positioned on the longitudinal axis of the missile while the forward lugs are normally attached one on each side of the booster section. When such is the case, the surface of the carrying cart 8!) is preferably provided withkeyways 66 adapted to receive their respective handling lugs. Suitable latching, means 67 are preferably provided for firmly securing the missile to the cart. The latch shown, which, it should be understood, is merely illustrative of one suitable type of latch, has two positions open and closed, either of which is maintained positively by engaging resilient pin 68 in either ofholes 69 or 70. Shoulder 78 provides a positive stop against which forward lug 65 is abutted before closing latching means 67.

Themissile 23 is placed on thecart 80 in the assembly area 2.7 with handling lugs 65 engaging theirrespective keyways 66 and latched in place. Avane 100 is then cocked, as by means of atension spring 99, to cooperate with the launching device, as will be explained hereinafter, to remove the forward portion of the cart from the trajectory path of the missile on launching.

The cart wheels 98 run on the inner surface of loading rail 24 (as is also the case with the other rails of the system) as shown. Each cart used in the system is provided with arecess 97 on each end in which is positioned acam block 113 which is engaged by therammer hand 96 to pull the cart. The rammer hand is carried by the working extremity ofextendable rammer chain 42 while therammer drive sprocket 44 is carried interiorly of the magazine turntable 12 (FIG. 2). The rammer hand is so shaped as to allow it to act to pull cam block 113 with its inner face, while the lower surface of the hand is adapted to permit it to push against the lower surface of the cart. A release button or detent 114 is reciprocally mounted incam block 113 and may be actuated in any desired manner to release or disengagerammer hand 96 fromcam block 113.

Referring now to FIG. 4, thelauncher 13, located centrally in the launchingpit 26, is shown in loading position with a missile in place. Apedestal 88, mounted on launching pit floor 46 carriestrunnion support 87 and allows train of the launcher in conventional fashion. Ayoke 86, rotatable on the trunnions, is integral withyoke extension 85 and permits conventional elevation of the launcher in response to firing orders.

To load a missile, thelauncher 13 is trained to alignment withrammer rail 25 and elevated to place launchingrail 82 in horizontal relation. A substantially continuous path for cart travel is thus provided fromrammer rail 25, through its extension 31, across fixedrail spur 112 ontolauncher rail 82. The cart is preferably secured to the launcher rails by suitable latching means not shown. For purposes of clarity, the launching well door 36 is not shown in FIG. 4.

In order to load the missile, launching rail 02 is supported horizontally by floating element 83 which is integral therewith. Floating element 83 is pivotally connected toyoke extension 85 by means ofpin 84. The forward end of element 83 is slidably supported by link 103 connected toroller 104 which bears against the upper surface ofslot 105. The bottom end of link 103 is pivotally connected toyoke 86. A push-pull rod 102 is pivotally pinned to the middle of link 103 at one end and connects to a link 101 at its other end. Link 101, in turn, is pivotally connected midway of its length to floating support 83. At its extremities, link 101 is acted upon sequentially by spring loadedvane 100 and reset plunger 108.

When themissile 23 is to be fired, the missile is preferably connected, as is conventional to an external source of power, such as a backscratcher, (not shown) to arm the booster, warm up electronic components, and the like. The launcher is trained and elevated as desired and the missile is launched by detonating the booster.

It has been discovered that in launching missiles, it is desirable to remove the launching rails from the trajectory path of the missile substantially immediately after the firing of the missile. This practice is followed in order to prevent the missile handling lug on the after end of the missile from striking the forward part of the launching rails and thereby canting the missile into an undesirable trajectory path or attitude of flight.

In the instant invention, the missile is preferably fired directly from the carryingcart 80. However, by means of the launcher mechanism disclosed, the cart can be pulled down out of the projected missile path to avoid the undesirable eifects outlined above.

Just prior to launching, the latching means 67 should be opened to allow the missile lugs 65 to pass through keyways 6n without interference. As the missile is launched and travels forwardly, the spring loadedvane 100 is released from contact with the underside of the booster casing and, due to its spring biasing, it rotates clockwise, as viewed in FIG. 4, to thereby strike link 101. The link 101 is rotated counterclockwise, FIG. 4, moving push-pull rod 102 to the right. This rocks link 103 clockwise and consequentlyroller 104 acting onslot 105 pulls floating element 83 down.Cart 80, carried onrail 82 which is integral with floating element 83, is pulled down at the same time allowing the missile to leave the launcher without interference from any of the associated launcher structure. The cart, of course,

6 remains on the launcher rails, and must of necessity be removed to reload the launcher.

The launching well door (not shown), closed during firing, is opened to reload the launcher. The launcher is again trained to alignment with therammer rail 25 and elevated to cause fixedrail spur 112 to align withspur extension 107 of empty cart track 47. The empty cart track 47, as shown, leads down under the level of therammer rail 25 and themagazine floor 45. The empty cart track 47 leads to empty cart stowage cellar 32 (FIG. 1) in which the carts are stowed till again required for use.

Simultaneously with the alignment of fixedrail spur 112 withspur extension 107, reset plunger 108 registers withcylinder 109 formed insupport housing 115.Cylinder 109 is connected to any suitable source of pressurized fluid so that reset plunger 108 may be forced to the left into cylindrical cavity 111 as shown in FIG. 4. This action is transmitted through push-pull rod 102 to reposition link 103 in its normal position thereby raising the forward portion of floating element 83. If the cart has been secured to thelauncher rail 82, as mentioned hereinbefore, these securing means should be released so that the empty cart, under the influence of gravity, rolls down the launcher rails 82, acrossspur extension 107 and onto empty cart track 47 whence it rolls down toempty cart cellar 32 for stowage.

To lock the launcher in load position the launcher is slightly depressed until a spring loaded detent 110, also carried insupport housing 115, enters cylindrical cavity 111, which is now empty due to the movement of reset plunger 108. The launcher is now clear and locked in load position with thelauncher rail 82 horizontal and ready for receipt of another rammed missile.

To load another missile the magazine turntable is rotated to select a cell in which is stowed the desired type missile. The door is dropped, as aforementioned, the rammer hand is run out to pull a carted missile onto the turntable. The turntable is then rotated to alignment withrammer rail 25 and the cart with its missile is rammed across the rammer rail onto the previously prepared launcher rail.

Should a missile booster fail to detonate or for any other reason should a missile be determined to be a dud it is removed from the launcher to dudarea 30. In such an event, the launcher, is trained and elevated to alignment with suitable rails within the dud area, anddoors 35 and 36 are opened to permit therammer 42 to push the cart carrying the dud from the launcher to the dud area. Suitable dud removal doors may be provided at the exit side ofdud area 30 to facilitate removal to a remote area for disposal.

The above-described system, as has been mentioned, is approximately one half of an integrated launching system. The same operations may have been performed simultaneously or sequentially at the counterpart units of the system half, not illustrated. Thus it will be understood that missile salvos of two missiles or single coordinated or uncoordinated fire from each launcher is possible. Also, because of the ease of selectablility of the stowed missiles from the roundhouse magazine, it is obvious that different types of missiles can be selected for tire to accomplish different purposes. t is possible, for example, to fire a ram jet powered, air-to-air missile with a conventional warhead from one launcher at the same time with a completely different type missile from the other launcher. Also to be noted, is the magazine cross feed flexibility possible with the disclosed system by the employment of both loading rails 24 and the assembly area 2'7 therebetween.

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 G the scope of the appended claims the invention may be practiced otherwise than as specifically described.

What is claimed is: 1, A guided missile launcher movable in azimuth and elevation comprising:

rotatable base and trunnion means for providing variable azimuth positioning; yoke means pivotally mounted on said trunnion means to provide variable elevation positioning; launcher rail means including an aft end and a forward end, defined with respect to the respective ends of a missile mounted thereon, pivotally mounted at the aft end thereof to said yoke means and adapted to support at both ends thereof a missile on the launcher; said launcher rail means having its pivotal mounting axis on said yoke means parallel to the pivotal mounting axis of said yoke means on said trunnion means; and means responsive to the initial movement of a missile launched from the launcher for pivoting the forward end of said launcher rail means away from the missile. 2. A system for slowing and launching guided missiles comprising:

circular annular magazine means including a ramming compartment and a plurality of missile stowage com- ReterencesCited by the Examiner UNITED STATES PATENTS 1,925,442 9/33 Fournier 214-1611 2,735,391 2/56 Buschers 89-l.7 2,745,317 5/56 Stanton et al. 89-46 2,843,020 7/58 Bertagna et al. 89l.7 2,984,157 5/61 Johnstone u 89-l.7 2,985,072 5/61 Carlberg et al'. 89--l.7 3,113,486 12/63 Kongelbeck 89l.7

BENJAMIN A. BORCHELT, Primary Examiner.

SAMUEL W. ENGLE, Examiner.

Claims (1)

1. A GUIDED MISSILE LAUNCHER MOVABLE IN AZIMUTH AND ELEVATION COMPRISING: ROTATABLE BASE AND TRUNNION MEANS FOR PROVIDING VARIABLE AZIMUTH POSITIONING; YOKE MEANS PIVOTALLY MOUNTED ON SAID TRUNNION MEANS TO PROVIDE VARIABLE ELEVATION POSITIONING; LAUNCHER RAIL MEANS INCLUDING AN AFT END AND A FORWARD END, DEFINED WITH RESPECT TO THE RESPECTIVE ENDS OF A MISSILE MOUNTED THEREON, PIVOTALLY MOUNTED AT THE AFT END THEREOF TO SAID YOKE MEANS AND ADAPTED TO SUPPORT AT BOTH ENDS THEREOF A MISSILE ON THE LAUNCHER; SAID LAUNCHER RAIL MEANS HAVING ITS PIVOTAL MOUNTING AXIS ON SAID YOKE MEANS PARALLEL TO THE PIVOTAL MOUNTING AXIS OF SAID YOKE MEANS ON SAID TRUNNION MEANS; AND MEANS RESPONSIVE TO THE INITIAL MOVEMENT OF A MISSILE LAUNCHED FROM THE LAUNCHER FOR PROVIDING THE FORWARD END OF SAID LAUNCHER RAIL MEANS AWAY FROM THE MISSILE.

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