US2792757A - Missile launcher - Google Patents

Description

y 1957 R. E. 'CARLBERG EI'AL 2,782,757

MISSILE LAUNCHER Original Filed Sept. 1, 1950 v 18 sheets -sheet 1 INVENTOR ROBERT E. GARLBERG FRANK W S/EVE R0600 DEMAS/ jaw/WW y 1 1957 R. E. CARLBERG ETAL 2,792,757

' MISSILE LAUNCHER Original Fi led Sept. 1. 1950 18 Sheets-Sheet 3 I] IF IF II II II ll INVENTORS ROBERT E. mm 95% FRANK w. SIEVE Roam DEMAS/ ATTORNE YS 21, 1957 R. E. CARLBERG- ETAL [22395757 MISSILE LAUNCHER I Original Filed Sept. 1. 1950 q 18 Sheets-Sheet 4 I02 NV EN'IORS ROBERT E. amwma FRANK w $IEVE ROOGA 05mm ATTORNEYS 21-, 1957 R. E. CARLBERG T MISSILE LAUNCHER 18 Sheets-Sheet 5 Original Filed Sept. 1. 1950 INVENTORS ay 21, 1957 R. E. CARLBERG ETA!- 2,792,757

MISSILE LAUNCHER Ori ginal Filed Sept; 1. 1950 18 Sheets-Sheet e FIG. I!

INVENTORS ROBERT E. GARLBE'RG FRANK W. S/EVE R0000 DEAS/ ATTORNEYS y 7 R. E. CARLBERG ET AL 2,792,757

MISSILE LAUNCHER 1 Original Filed Sept. 1. use 18 shets -shjew 7 lNVENTORS ROBERT E. OARLBERG FRANK w. 315 v5 R0600 DEMASI ATTORNEYS y 7 R. E. CARLBERG ETAL MISSILE LAUNCHER 18 Sheets-Sheet 8 .INVENTORS HUBER? E. OARLBERG FRANK W 5751/5 R0000 @EMAS/ Original Filed Sept. l. 1950 I a? a ATTORNEYS y 1, 1957 R. E. CARLBERG ETAL 2,792,77

MISSILE LAUNCHER Original Filed Sept. 1. 1950 1s Sheets-Sheet 9 ROBERT E. aARl. BERG FRANK R. S/EVE R0600 omwsl ATTORNEYS May 21, 1957 R. E. CARLBERG ET AL MISSILE LAUNCHER Original Filed Sept. 1, 1950 18 Sheets-Sheet l0 FIG. 75

SAF mo INVENTORS ROBERT E. OARLBERG FRANK W S/EVE R0060 DEM/15! BY W/Z WW ATTORNEYS 21,v 1957 R. E. CARLBERG ET L 2,792,757

MISSILE LAUNCHER Original Filed Sept. 1, 1950 18 Sheets-Sheet ll Fm. W

INVENTORS ROBERT E. OAHLBERE FRANK W. S/EVE R0000 DEMAS/ KMQWZR BY /3- W ATTORNEYS R. E. CARLBERG. ETAL MISSILE LAUNCHER m m m m t -E 2 w m 9 n 0 E! 0 m m M n 2 w w 0E A w m m/m h F. .D w WW0 1 EN 4 W RFR Y B Original Filed Sept. 1, 1950 FIG. l9

May 21, 1957 R. E. CARLBERG ETAL 2,7 2,

MISSILE LAUNCHER Original Filed Sept. 1, 1950 v l8 Sheets-Sheet 13 FIG. 22

' INVENTORS ROBERT E. GARLBERG FRANK W S/El/E R0000 DEMA SI FIG. 2/

y 1, 1957 R. E. CARLBERG ET AL.

MISSILE LAUNCHER 18 Sheets-Sheet 14 Original Filed Sept. 1, 1950 INVENTOR ROBERT E GARLBERG FRANK W. S/EVE R0660 DEMAS/ X14. 0&7; BY Q/Z W ATTORNEYS May 21, 1957 R. E. CARLBERG E 2,792,757

' MISSILE LAUNCHER Original Filed Sept. 1. 1.950 v 18 Sheets-Sheet 15 iNVENTORS ROBERT E. OARLBERG FRANK W. S/EVE R0600 DEMAS/ QB W ATTORNEYS May 21, 1957 R. E. CARLBERG ETAL. 2,7

MISSILE LAUNCHER Original Filed Sept. 1, 1950 18 Sheets-Sheet 16 INVENTORS ROBERT E. OARLBERG FRANK. w, S/EVE Rocco ommsl 1Q Q/ZA AT ;ORNEYS y 7 R. E. CARLBERG ETAL 2,792,757

MISSILE LAUNCHER Original Filed Sept. 1, 1950 I 18 Sheets-Sheet 17 RAISE HOIST DEPRESS GUIDE FIR-E ELEVATE GUIDE LOWER HOIST INDEX R.S DRUM TIME CYCLE OF OPERATIONS INVENTORS ROBERT E. CAR/.5596 FRANK w. S/EVE FIG. 29 R0600 DEMAS/ ATTORNEYS NHSSILE LAUNCHER Robert E. Carlberg and Frank W. Sieve, Falls Church, and Rocco De Masi, Arlington, Va.

(Priginal application September 1, 1959, Serial No. 132,696, new Patent No. 2,745,317, dated May 15, 1956. Divided and this application February 16, 1954, Serial No. 410,470

11 Claims. (Cl. 891.7)

(Granted under Title 35, U. S. Code (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 application is a division of application Serial No. 182,696, filed September 1, 1950, now U. S. Patent No. 2,745,317, for Missile Launcher, which is directed to a combination of several inventions by joint inventors Arthur I. Stanton, Robert 'E. Carlberg, Robert K. Bole, Frank W. Sieve, William Danziger, and Rocco De Masi.

This invention relates to missile launchers and more particularly to missile launchers which are automatic in operation and may be controlled from a remote firing station.

In the art of modern warfare the use of self-powered missiles such as rockets has been receiving increasing attention, however, difiiculties have been encountered in the handling and launching of such missiles particularly when it is desired to launch a number of them in rapid succession.

Heretofore, devices for launching a multiplicity of rockets have beeen in the form of relatively simple construction comprising a rack or frame for supporting a number of rockets side by side and means for firing all of the rockets substantially simultaneously whereupon they are broadcast in the general direction of the target. When adapted for shipboard use such devices ordinarily could not independently be moved in train or elevation and their firing accuracy depended upon directing the ship toward the target and arriving at a prescribed range before the missiles were released. that to obtain repeated firing with such an arrangement it was necessary for the launcher to be loaded by hand from above-deck with exposed personnel and this loading step had to be repeated before the launcher could again be fired.

The risks attendant to the exposure of large numbers of rockets and personnel above-decks is readily apparent.

In order to avoid hazard to shipboard personnel loading rockets in an exposed position, there have been developed gravity fed or mechanically fed rocket launchers which fire rockets one by one through a firing trough. However, in such arrangements ordinarily the supply of rockets still must occupy an exposed position and hence is vulnerable to a hit by the enemy.

A further problem, particularly with large rockets, arises out of the tremendous heat generated by the rocket blast as it is fired. Because of the tremendous heat and' blast effects of the rocket as it is launched, it is important that the launcher be automatically loaded and capable of being operated in train and in elevation by remote control means such as the conventional gun director employed aboard ship.

The missile launcher of the present invention overcomes the above and other limitations of prior art devices and is particularly adapted for use on naval'vessels where space limitations are important, however,'it will;

It will be apparent;

2,792,757 I Patented May 21, 1957 2 be understood that it is not limited to such use but may be used in other installations where a launcher of this character is desired.

Accordingly, it is an object of the present invention to provide an improved missile launcher design which provides optimum control of the missile during launching, is rapid in action and avoids the hazards incident to the use of conventional missile launchers.

A further object of the present invention is to provide a missile launcher that may be completely automatic in operation and may be controlled from a remote station by suitable control equipment.

Still another object of the present invention is to provide a launching guide tube having a loading position and a launching position and means for moving the guide tube between the loading and the launching position.

Another object of the present invention is the provision of improved loading means whereby missiles may be supported in a magazine disposed beneath the launcher mount and under the deck structure and carrying a supply of missiles such as rockets which are individually positioned adjacent a vertical hoist for movement into the missile launcher guide.

A further object is the provision of an improved missile launcher installation wherein the structural relationship between the above-deck mount and below-deck magazine and hoist may be varied to conform with structural and space limitations of various naval vessels upon which it may be installed.

Another object is the provision of means for safely conveying an unfired missile from the launcher guide back to the missile magazine.

A-further object is to provide apparatus to facilitate the lowering of missiles from above-deck into a ships stowage magazine.

A still further object is to provide means for loading missiles from the ships stowage magazine into a launcher ready service magazine.-

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 vertical side elevation with portions removed. showing one embodiment of the present invention in stowed condition;

Fig. 2 is a similar view from the opposite side but with the parts arranged in loading position;

Fig. 3 is a side elevation with the launching tube disposed in firing position;

Figs. 4 to 9, inclusive, are schematic views illustrating the positions of the launching tube, launcher hoist,

and ready service magazine. during loading and firing operations;

Fig. 10 is a top plan view with the launching tube in load position and the deck surface removed to show the ready service magazine located in one position relative to the launcher mount;

Fig. 11 is an enlarged front elevation view of a por-- tion of the launcher mount of the present invention;

Fig. 12 is an enlarged rear elevation view of a porit appears from above;

Fig. is an enlarged detailed sectional view of the upper portion of the rear missile end of the guide tube and illustrating the forward and rear restraining latches;

Fig. 16 is a perspective view partly broken away of the operating mechanism located in the upper portion of a suitable blast shield and showing the linkage employed to manually withdraw the forward restraining latch; v

' Fig. 17 is a detailed view showing the bearing means whereby the launcher mount is supported for movement in train;

Fig. 18 is 'a schematic perspective view of the launcher hoist operating means employed to raise missiles from the ready service magazine into the guide tube;

Fig. 19 is a detailed vertical section through a portion of the ready service magazine bearing means showing the drive pinion and ring gear arrangement;

Fig. 20 is a top view of the ready service latch showing latch receiving notches therefor in the inner periphery of the ring gear; V I

Fig. 21 is an enlarged detailed vertical section through the lower portion of a magazine stall showing details of the ready service magazine missile support latch and stall loaded indicator mechanism;

Fig. 22 is a perspective view as it appears looking from within a stall and showing the latch and indicator mechanism of Fig. 20;

Fig. 23 is a perspective view partially broken away of the stowage hoist and tray used to load missiles from below into the ready service magazine;

Fig. 24 isan enlarged detailed perspective view of the missile holding clamp employed to clasp the missile and hold it on the tray during tray movement;

Fig. 25 is an enlarged detailed view of a stowage hoist upper limit interlock cam and switch;

Fig. 26 is an enlarged detailed view of a stowage hoist lower limit interlock cam and switch;

Fig. 27 is an enlarged perspective view of the stowage hoist tray latch mechanism together with tray closed indicator and interlock switches;

Fig. 28 is an enlarged schematic perspective view of the stowage hoist tray pivot bearings together with a tray loaded interlock and tray position indicators;

Fig. 29 is a time chart showing the relative movement of the launcher hoist, the launcher guide and readyser'vice magazine during one complete cycle of automatic operation; and V Fig. is a schematic view showing the method of lowering missiles from above-deck to the ready service magazine and thence by the stowage hoist to the missile stowage magazine or locker.

The present invention is shown as a shipboard type of missile launcher installation wherein all components except the launcher guide tube are protected by enclosure within a shield or by location below-deck. The launcher may be remotely controlled and automatically operated by connection to a suitable control system forming no part of the present invention.

In the embodiment illustrated, a single launcher guide tube is supported by trunnions for pivotal movement from an upright loading position to an inclined firing position at which time it is lowered to some angle between 0 and Y60" of elevation as determined by a signal received from the ships gun director. This guide tube and its trunnions are mounted upon a carriage supported upon a mount which is similar to the conventional 40 mm. gun mount and includes the necessary apparatus for moving the guide tube both in train and elevation in response to director signals received from conventional fire control equipment. By this means the mount may be moved in train and in elevation so that it may bear upon the target up to the very instant of firing.

A second component of this launcher is a hoist mech anism which operates to deliver rockets o'r'otherl missiles from a below-deck ready service magazine into the launcher guide tube when it is at its 90 elevated or load ing position. i

A third component is a below-deck ready service magazine in the form of a large upright drum having a plurality of missile receiving stalls spaced about its periphery. By suitable means the drum may be rotated to successively present missiles to the launcher hoist for loading into the guide tube.

A fourth component of the present invention is the provision of a stowage hoist whereby missiles may be supplied to the stalls of the ready service magazine from a remote missile stowage compartment so as to replenish the supply of missiles in said ready service magazine during a period when the launcher is not in automatic operation. This stowage hoist 'embodies'transfer means including a tray upon which the missiles may be loaded and which tray then tilts to transfer the missiles from a horizontal stowed position to an upright position in alignment with the stowage hoist whereupon they may be moved into empty stalls of the ready service magazine.

The first three components above set forth work together during automatic firing operation to automatically and continually load and fire missiles until the supply in the ready service magazine has been exhausted or until a cease the order is given. Thereafter the last component works to reload the ready service magazine so that it Will be ready for another burst of automatic fire. These operations may be carried on in timed relationship underthe control of suitable electrical and hydraulic interlocks, the details of which form no part of this invention but which may be employed, if so desired, to assure the completion of each step before the start of the next.

In normal service, operation of the missile launcher may be remotely controlled by a director fire control system. When the launcher is in operating condition, and is following the director, the entire magazine supply of 22 missiles may be loaded and launched in succession simply by closing the firing circuit and holding it closed. During this automatic loading and launching operation, no action isrequired of launcher personnel. The firing of the launcher may be controlled remotely, as aforementioned, and successive loading of missiles from the ready service magazine may be performed automatically by the missile hoist. Hence, under these conditions personnel are not stationed in or about the mount abovedeck during firing operation.

Local control features of train and elevation are not incorporated in the launcher, however, handwheels are provided to move the mount manually in train and elevation for the performance of stowing and casualty operations and to facilitate service or maintenance work. Local control of the firing circuit may be provided at a below-deck control station as an alternative to director firing.

In the embodiment of the invention illustrated, and referring particularly to Figs. 1 to 12, inclusive, the present missile launcher is shown as it may be installed on a naval vessel with an above-deck mount generally designated 100, a below-deck ready service magazine 101 and a missile hoisting mechanism 102 adapted to convey missiles from the magazine directly into a missile guide tube 103 carried by the mount.

The above-deck mount is provided with a suitable protective shield 104 resting upon a shield base 1 15. Within the shield is mounted a carriage 166' having spaced cheeks 107 and 108 mounting trunnion bearings 109. The guide tube 103 has trunnions 110 supported in the bearings 109 about which the tube may pivot from an upright loading position to an inclined firing position, the tube103 being provided with a gear sector 111 which may beengaged by: the usual drive pinion to move the tube in elevation.

'In the embodiment illustrated the device is shown supported upon deck 114' by' means of a flanged roller bear-

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