US3106132A - Launcher - Google Patents

Description

Oct. 8, 1963 E. E. BIERMANN ETAL 3,106,132

LAUNCHER 7 Sheets-Sheet 1 Filed March 6, 1961 INVENTORS. EARL E. BIERMANN MELVIN APPELMAN A. M2 ATTOR EY.

Oct. 8, 1963 E. E. BIERMANN ETAL 3,166,132

LAUNCHER '7 Sheets-Sheet 2 Filed March 6. l961 FIG. 3.

INVENTORS. EARL E. BIERMANN MELVIN APPELMAN fl.% ATTORNEY.

FIG. 5.

Oct. 8, 1963 E. BIERMANN ETAL I 3,106,132

LAUNCHER '7 Sheets-Sheet 3 INVENTORS.

EARL E. BIERMANN MELVIN APPELMAN ATTORNEY.

Filed March 6, 1961 Oct. 8, 1963 E. E. BIERMANN ETAL LAUNCHER '7 Sheets-Sheet 4 Filed March 5, 1961 INVENTORS.. EARL E. BIERMANN MELVIN APPELMAN /z. ATTOR N E Y Oct. 8, 1963 E. E. BIERMANN ETAL LAUNCHER Filed March 6, 1961 7 Sheets-Sheet 5 FIG. I6.

Al-R PRESSURE LINE E N L c L U A R D Y H S E RM m AM L TM N N u R E w P B M m N A Lw G RL E EM T s U A H X F- EXHAUST /e. ATTORNE'Y.

Oct. 8, 1963 E. E. BIERMANN ETAL LAUNCHER Filed March 6, 1961 7 Sheets-Sheet 6 (III INVENTORS.

EARL E. BIERMANN MELVIN APPELMAN ATTORNE'Y.

Och 1963 E. E. BIERMANN ETAL 3,

LAUNCHER 7 Sheets-Sheet 7 Filed March 6, 1961 {3.7%, ATTORNEY.

EARL E. BIERMANN ME LVIN APPELMAN Unite in This invention relates to missile launchers and more particularly to shipboard launchers for launching a mis sile of the type disclosed in patent application of Orville J. Saholt et al. for Rocket Thrown Missile, Serial No. 8,201, filed February 11, 1960.

The missile referred to is an improved version of the missile briefly described in US. Patent No. 2,960,009 to Ralph F. Hereth et al. for Launcher, hereinafter referred to as the RAT launcher, difiering essentially by use of a jet motor, the thrust of which may be terminated as desired during the air trajectory, and hereinafter referred to as the ASROC (anti-submarine rocket) missile. The ASROC missile launcher, to which the present invention relates, is similar to the RAT launcher in the respect that a missile guide rail may be maintained trained in azimuth and elevation with change of ship bearing and roll. The RAT launcher, however, is in the nature of an attachment for a conventional gun mount which utilizes the gun mount training mechanism to train the launcher rail whereas in the present invention the launcher is a complete unit which is designed independent of use of preexisting equiprnent. As will subsequently appear, it differs, also, in many other respects.

As the RAT missile developed into the ASROC missile new tactical techniques became desirable among which were selectivity of the particular type of missile to be launched, for example, homing torpedo or depth charge, and increased rate of launch. In the RAT launcher the missiles are stored in a magazine and fed sequentially to the launcher rail which provides no means for selectivity of the particular type of missile to be launched. If the launcher rail contains a homing torpedo and the magazine contains a depth charge and it is desired to launch the depth charge it is necessary to launch or jettison the missiles ahead of the depth charge before the latter can be launched. This not only entails loss of time to index the desired missile into launching position on the launcher rail but also loss of expensive missiles. The RAT launcher, therefore, although conceivably capable of handling diiferent types of missiles, is not practical for such purpose. Another disadvantage of the RAT launcher is the requirement for jettisoning a defective missile to thus free the launcher rail for its succeeding missile contained in the indexing mechanism, disposed between the launcher rail and magazine. This entails loss of expensive missiles which might be rendered serviceable.

The RAT launcher evolved around the concept of utilizing preexisting equipment, a gun mount, for training a rocket launcher rail (actually, a pair of rails, one cooperating with each gun of a twin gun mount). The apparent advantage of such concept is the utilization of the gun mount for a second purpose: launching rocket missiles, without complete duplication of training mechanism and the like. When it is considered, however, that a gun equipped warship is designed to a considerable extent around its basic gun requirements it becomes apparent that the RAT launcher is not readily adaptable to ships other than the ones for which it was designed. Thus, the gun mount which forms a part of the RAT launcher is provided with gun supporting structure, sometimes referred to as a turret, which extends well below the deck of the ship. The ship, particularly in this locus,

main Patented Oct. 8, 1963 must be suitably designed to accommodate this below the deck portion of the gun mount. As will be apparent, to adapt such gun mount to some other type of ship would, in most instances, require complete redesign of below the deck structure. Such limitation thus led to the desire for a self contained launcher which could be deck mounted to any structurally adequate ship which could accommodate it on its deck. The indexing mechanism is also a hazardous part of the RAT launcher system since accidental firing of a missile motor, while the missile is in the indexing mechanism, can produce considerable damage, if not an explosion, since no provision is made to harmlessly fire the missile while in the indexing mech anism.

One of the general objects of the present invention is the provision of a launcher which obviates the disadvantages just referred to. V A more specific object is to provide a deck mount shipboard launcher for rocket propelled missiles which enables selective launching of a plurality of missiles, each missile having its independent launcher rail.

Another object is to provide a launcher of the foregoing type which is compact, light in weight and requires a minimum of power for its operation.

Still further objects, advantages and salient features will become more apparent from the description to follow, the appended claims and the accompanying drawing, in which:

FIG. 1 is front assembly perspective of the subject of the invention;

FIG. 2 is a rear perspective ofFIG. 1;

FIG. 3 is a perspective, partly in phantom, of one of the launcher housings;

FIG. 4 is an enlarged perspective of a portion of FIG. 3;

FIG. 5 is a section taken on line 55, FIG. 4;

FIG. 6 is a lower plan of the forward portion of FIG. 3 as viewed in the direction of arrow 6;

FIG. 7 is a section taken on line 7-7, FIG. 6;

. FIG. 8 is a section taken on line 8--8, FIG. 6;

FIG. 9 is a side elevation, partly in section, of a buffer arm;

FIG. 10 is a perspective, partly in section, of launcher housing clutching mechanism;

FIGS. 11 to 13 diagrammatically illustrate various positions of parts of the mechanism of FIG. 10;

FIG. 14 is a detail of FIG. 10;

FIG. 15 is a section taken on line 15-15, FIG. 14;

FIG. 16 illustrates missile restraining mechanism;

, FIG. 16A illustrates a portionof FIG. 16 with parts in a different position;

FIG. 17 illustrates the elevating drive mechanism;

FIG. 18 illustrates the train or azimuth drive mechanlsm;

FIG. 19 illustrates fire interrupting mechanism driving ly associated with FIGS. 17 and 18;

FIG. 20 is a side elevation of hose and cable loop apparatus;

FIG. 21 is a side elevation, partly in section, of a rupture diaphragm;

FIG. 22 is a transverse section through a portion of a launcher cell wall; and

FIG. 23 is an enlarged section taken on line 23-23, FIG. 22.

As will subsequently appear, the invention, in its broader aspects, involves certain requisite combinations of components and certain others which may be optionally employed as refinements thereto. To facilitate an understanding of these distinctions the invention will therefore be described in general and then in detail, some of the details being exemplary of specific modes of attaining certain requisite results and others being optional refinements which may be employed if desired.

roll.

With reference to the drawing, and particularly FIGS.

1 to 3 and 10, the invention comprises in its broader aspects a suitable support 50, affixed to the deck of a ship, which supports a launched mount 52, which may be rotated by power about a vertical axis which thus trains the mount in an azimuthal direction in the same manner as a conventional gun mount commonly employed on warships. Mount 52 carries a power operated torque shaft 54, selectively rotatable in opposite directions to which is journaled four adjacent rectangular housings 56, 56a, 56b, 566, each being divided into upper and lower cells 60, 60. Each cell is closed at the front end by a 7 pair of pivoted doors 62 and at the rear by a rupturable diaphragm 64-, the doors and diaphragrns preventing entry of sea spray,,cold air and foreign material into the cells. As best shown in FIG. 3, each cell is provided with a launching rail 66 which is slideably carried within a cell and, when actuated, moves forwardly, opening its pair of doors, providing an effective lengthening of the launcher rail travel of a missile 68 slideably supported by the rail. A clutching mechanism 70, best shown in FIG. 10, is provided for each housing which provides a mechanical connection to the torque shaft so that the housing may be trained in elevation, like the gun of a conventional gun mount, as the torque shaft is rotated. As will be apparent, any dual cell housing may be selectively clutched to the torque shaft, and when so connected, the launcher rails in the pair of connected cells may be simultaneously trained toward a target, both in azimuth and elevation, in the same manner in which conventional warship guns are maintained trained as the ship rolls or' changes bearing.

In the general operation of the device so far described it will be assumed that all launcher housings are disposed in their horizontal stowed position as shown in FIG. 2 and an underwater target is located by the ship sonar. It will also he assumed that the cells contain ASROC missiles, some of which are provided with depth charges and others with homing torpedoes and it is determined that a homing torpedo will be employed to attack the target. Assuming that, say the top cell 60 of housing 56 contains such a missile, suitable mechanism is actuated to clutch or lock housing 56 to the torque shaft which is then rotated through a suit-able angle to elevate the housing which angle will be maintained irrespective of ship Similarly, the entire mount is rotated in azimuth and maintained properly trained irrespective of changes of ship hearing. The launching rail contained within this top cell is next actuated which extends it forwardly through the front doors of the cell, opening the doors as it extends. This missile is now ready to be launched when appropriate command signals are received.

T rque Shaft and clutching Mechanism (FIGS. 10 to The torque shaft or tube 54 is journaled to mount 52 by suitable bearings disposed adjacent its ends and others disposed between the housings. Between each pair of adjacentbearings the tube journally supports a launcher housing support 72, as best shown in FIG. 10*, to which a launcher housing 56 is rigidly connected (FIG. 1). The mount is provided with a slideable pin 74 having a tapered end 76 which engages a tapered bore 78 in the tube, one bore for each housing being provided, these being in alignment. The lower end of the pin is provided with a T slot 80 which engages the T shaped upper end 8-1 of a ram 82 (FIG. 15)

which is guided for rectilinear. movement and actuated by a double acting pneumatic actuator 84, the piston rod 86 of which is connected to and forms a part of the ram. An arcuate track 88 is rigidly mounted to the mount onto which the lower T-shaped end of the pin may travel and rollers 90 are carried by the pin which engages the upper face of the track which maintains a spring 92, disposed within the pin, compressed and the tapered end of the pin in tight engagement with its mating bore in the torque tube. A bell crank 94 is pivoted to the mount, one arm 96 of which is slotted to receive a pin 97 carried by the ram and the other arm 98 being pivotally connected by a link 100 to a pivoted latch 102, provided with a slot 103 which engages a pin 1G4 carried by the mount. In the operation of the mechanism just described it will be assumed that all of the housings are disposed in their horizontal stowed positions and it is desired to elevate a particular housing. At this time latch 102 of each housing engages its mating pin 104, FIGS. 10 and 11, and all hous ings are locked against movement. One of the cylinders 84 is then actuated moving ram 82 upwardly, the ram carrying pin 74 upwardly until its end 76 engages the bore 78 in the tube. During this operation, latch 102 is rotated to unlatched position by bellcrank 94 and the housing is now captured by the torque tube for rotation with the latter, FIG. 12. The torque tube is then rotated, FIG. 13, to elevate the housing and the lower end of pin 74 moves out of engagement with the upper end of the ram and onto engagement with the arcuate track. The housing may then be elevated as desired, within its range of movement. When it is desired to return a housing to stowed position the reverse action takes place, moving pin 74 back into engagement with the ram, lowering of which unlocks or declutches the pin from the torque tube and again locking the housing in stowed position by latch 102. This mechanism thus comprises, principally, means for selectively clutching a housing to the torque tube for controlled movement by the latter, and secondarily, means forlatching a housing to the mount when the former is 1 in stowed position.

Launching Rails and Doors (FIGS. 3 to 8) Each cell contains a launcher rail 66 having parallel facing grooves 108 adjacent its lower edge which form guideways for slideably receiving a pair of longitudinally spaced launcher lugs 110, 112, FIG. 8, which project upwardly from the missile. The lugs are substantially identical except that the laterally and oppositely projecting flanges 114 on front lug are longer than the flanges 116 on rear lug 112. The lower inwardly projecting flanges, forming grooves 108, are cut away rearWardl-y from the front end of the rail for a distance equal to the spacing of the lugs so that when the front lug reaches the front end of the rail the rear lug simultaneously reaches the rear end of this cut away portion to permit the lugs to be simultaneously freed'from guidance by the rail thus preventing tipping of the missile about the rear lug due to force of gravity which would occur if the rear lug remained in the guide after the front lug had left same.

Rail 66 is supported for rectilinear movement by suitable brackets 118 supported from the roof of the cell which brackets may employ suitable gibs 119 for adjustment. A short rail portion 66A, having the same groove shape as rail 66 is fixed to the cell at the rear end of rail 66 and serves as a guide for loading a missile through the rear end of the cell onto rail 66. A double acting air operated pneumatic actuator 120 is fixed t0 the cell, its piston rod 122 being connected to an intermediate portion of the guide. As will be apparent, when the piston rod moves forwardly, the rail 66 slides forward away from fixed rail 66A, projecting forwardlyfrom the front end of the cell and when moved rearwardly returns the rail to its normal position within the cell.

A pair of hinged doors 62 are provided for closing the front end of each cell, these being actuated by movement of the rail. As best shown in FIG. 6, each door is provided with a pivoted arm 124. connected by a pivoted link 126 to the door, the arm having a roller 128 which may ride along a guideway 130 having a depression 132 at its front end and a oammi-ng surface 134 joining the recess and guideway. When the rail is in retracted position with the doors closed the roller is disposed within the recess and when the rail moves forwardly surface 134,

cams the roller 128 and arm 124 outwardly thus opening the door to the position shown. When the rail is retracted the door remains open until impact absorbing spring finger 136 engages around the roller and forces it back into the depression thus positively closing the door. It will be apparent that a spring could be employed in lieu of such fingers to close the door.

Missile Restraining Mechanism (FIGS. 3, 16, 16A) Each missile is restrained against unauthorized lateral and longitudinal movements relative to its launching rail by a snubber and detent system. The snubber system comprises fore and aft lower hydraulic cylinders 140, 140a, the pistons 142, 142a of which are atfixed to V- blocks 144, 144a which engage the lower surface of a missile and fore and aft pairs of side snubbers 146, 146a and 148, 148a which engage opposite sides of the missile. Missile engaging pads carried by the side snubbe-rs are shaped to conform to the missile somewhat above a horizontal diameter so that they urge the missile laterally and also downwardly in opposition to the upward urge of the lower snubbers. Each side snubber is supported for movement by :a parallelogram linkage 150, the linkage of a fore and aft snubber on each side of the missile being connected by links 152 connected to opposite ends of piston rods 154, forming parts of double acting pneumatic actuators 156.

The detent system comprises a double acting pneumatic cylinder 158, the piston rod 166 of which is affixed to rectilinearly movable locking pin 162 having a can ming notch 164 into which one end of a spring loaded detent 166 extends, the other end of the detent having a camming surface 168 engaging a notch 176B disposed within one of the launching lugs of the missile. Multiple position valve 172 is provided to control air pressure to the system just described and a similar valve 174 is provided to control pneumatic cylinder 12.0 which operates the extensible launching rail. Limit switches S may be provided, as desired, to indicate the position of the various moving parts or to serve as interlock switches to prevent unauthorized movement of parts.

In the operation of the mechanism just described air pressure has been applied to cylinder 158, the piston of which has been moved to one limit of movement, forcing hydraulic fluid, shown in solid black, to cylinders 140, 149a, moving the fore and aft lower snubbers into engagement with the missile. Air pressure has also moved all side snubbers 146, 146a, 148, 148a into engagement with the missile. The missile is thus firmly held by the snubbers against lateral movement relative to its launching rail and thus may not transmit undesired stresses to the launching lugs due to ship roll or pitch. Locking pin 162 also blocks movement of detent 166 which positively restrains longitudinal movement of the missile. If the missile motor were accidently fired at this time its entire thrust (20,000 lbs. tor the exemplary missile) would be imparted to the detent and the motor would burn out while restrained in the launcher. When it is desired to fire the missile, valves 172 and 174 are operated which moves piston rods 154 to the other extreme of the position shown, thus retracting .the side snubbers. Air is also applied to cylinders 149, 140a retracting the lower snubbers and forcing hydraulic fluid to return to one side of cylinder 158, as shown in PEG. 16A. At this time one end of detent 162 is aligned with notch 164 and is free to move against the urge of its spring, which in the particular example is designed to retain the missile against movement unless it develops in excess of 2000 lbs. thrust, the purpose of which is to ensure that the missile would launch to a safe distance away from the ship. Valve 174 has now been actuated, also, moving actuator 120 to the other linnMt of movement shown and extending the launching rail (FIG. 6). The missile is now ready to launch. Mechanism 176 may be provided to manually move the detent out of engagement with the Elevation alnd Bufier Mechanism (FIGS. 17, 9)

The power drive for torque tube 54 consists essentially of reduction gear mechanism, a hydraulic motor for selectively driving same in opposite directions and a friction brake for quickly arresting rotation of the various parts. FIG. 17 diagrammatically illustrates an exemplary form of mechanism comprising a sector gear 181) aflixed to one end of torque tube 54 and driven by pinion 182, the sector gear and pinion being disposed within casing 184 (FIG. 2). The pinion is driven through reduction gears 186 and reversible hydraulic motor 188. Shaft 191) is provided with a brake disk 192 which may be engaged by a stationary disc 1% which may be selectively engaged with the former by hydraulic actuator 1%. An auxiliary reversible air motor 197 may selectively drive worm wheel 198, aflixed to shaft 190, for manually rotating the torque tube. A firing interrupter power take-oil shaft 199, the purpose of which is to be subsequently described, is driven by the reduction gearing.

To prevent runaway conditions near the limits of rotation of torque tube 54, a butter arm 200 (FIG. 9) is journaled on its other end, within casing 201 (FIG. 1), with a rotary lost motion connection, sure-h as by splines 2&2, which permit approximately 82 of free rotation of the torque tube. At the end of such travel the splines engage, rotating the arm, the motion of the latter being restrained in each of opposite directions by hydraulic bullers or dash pots 294-, which control flow of liquid between opposite sides of a piston 206 which allow several degrees further rotation of the torque tube before the pistons bottom in their cylinders. The dash pots illustrated are of the type which are spring urged in one direction, the pistons being provided with tapered bleed grooves 297 to eiiect increasing resistance as they ap proach bottoming positions and check valves 208 to permit flow of liquid in one direction between opposite side-s of the pistons.

Train or Azimulzh Drive (FIG. 18)

The launcher unit is supported tor rotation about avertical axis by a training circle or ring vgear 210, rig-idly secured to ship structure, and an aanti-friction bearing 2 12 which supports a base plate 214, the latter supporting all movable structure so far described. The power drive for the launcher unit is essentially the same as the drive for the [torque tube, comprising a pinion 216 meshing with gear 210, reduction gearing 218 driven by reversible hydraulic motor 2,20, motion being arrested by brake mechanism 222, all carried by and rotatable with the base plate. A firing interrupter power take off shaft 224, to be subsequently described, is driven by the reduction gearing. An air motor 226, like motor 197, may be employed to selectively manually rotate the base plate.

Hydraulic motors 188 and 220 are supplied with liquid under pressure, each by an electric motor driven pump supported by the base plate. The pumps are of the positive displacement type, the volumes of which may be selectively varied to control operation of the respective motors.

A buffer mechanism (not shown), similar to the elevating butler mechanism previously described, and 0perated by stops carried by the base plate, may be employed to prevent runaway conditions near the ends of travel of the base plate.

Firing interrupter (FIG. 19)

Power take off shafts 199 and 224, previously referred to, provide inputs to a firing interrupter 234 which prevents launching of a missile when a launching rail is aligned with superstructure of the ship such as masts, funnels and the like. In a simplified form such device may be considered as cams 232, 234 driven by each shaft, each cam operating a switch, 236, 238 and the cam lobes being so shaped that'the switches provide a preventive circuit for launching a missile when a launching rail is in any position aligned with superstructure or other obstruction. Such devices are well known, being commonly employed With gun mounts to prevent firing'of the guns in certain positions of elevation and azimuth.

Cable and Hose Loop (FIG. 20)

As previously suggested, the rotatable launching unit must be supplied with hydraulic, pneumatic, heat exchanging and other fluid together with electrical power, control signals and the like. The sources of these are, for the mostpart, located at stationary loci on the ship. It is apparent, therefore, that communication devices are required between'relatively movable parts. The communication device employed with this invention comprises'a hollow vertical stationar'y' post 2% disposed on the vertical axis of the launcher through which or around which a plurality of flexible cables and hoses 242 extend upwardly, thence downwardly, forming loops 244 and thence to a ring 2.46 carried by and rotatable with the launcher unit. As will be apparent, when the launcher unit rotates between opposite limits of rotation the loops may rotate or twist about the post, thus compensating for the change in distance between fixed and movable portions of the cables and hoses.

Rupture Diaphragm (FIG. 21)

The rear opening of each cell is closed by a circular diaphragm 64, formed of a sheet of water resisting material, the peripheral edge of which engages a flange 250 and is'secured to the latter by a U-shaped clamping band 252, the ends of which are drawn toward each other by band'253 and a toggle clamp 254. When a missile is launched its motor blast ruptures the diaphragm. Flange 250* is integrally connected to a rectangular plate 255 which is secured at its four corners to the rear end of a cell by a plurality of con ventional quarter turn quick disconnect bolts 258. When a missile is to be loaded into the launcher this plate is removed to permit the four orthogonally arranged fins of the missile to pass through the corners of the rectangular opening 259 in the cell.

Heating and Cooling (FIGS. 22, 23)

The top and side walls of each launcher cell 56 are constructed of panels 26h formed from aluminum plates 26 2 separated by a honey-comb core 264 of corrugated thin aluminum sheets 266, the abutting portions of such sheets being bonded together by a suitable resin cement 268 and the ends of the core being similarly bonded to the plates. Hollow heat exchangers 270, 272 extending longitudinally of each cell and formed of extruded aluminum are secured, respectively, to the inner opposed side faces of each cell and to the top outer surface of the uppermost cell. Fluid, either hot or cold, is circulated through the heat exchangers to maintain the cells at a desired temperature. The top heat exchangers, when employed with heated fluid also serve as deicers to prevent accumulation of ice on the top surfaces of the uppermost cells.

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:

l. A shipboard launcher for rocket propelled missiles, comprising; a support mounted for rotation about a vertical axis, a torque shaft carried by said support for rotation about a horizontal axis, power means carried by said 3 support for selectively rotating said support and torque shaft in opposite directions, a plurality of adjacent elongated housings each journally supported :by said torque shaft, whereby said torque shaft may rotate without rotation of a housing supported thereby, said housings being restrained against movement along their longitudinal axes, each containing a launcher rail, the longitudinal asses of the rails being disposed in parallel planes, and means for selectively clutching one of said housings directly to said shaft, whereby its launcher rail may be rotated about said horizontalaxis independent of the remaining launcher rails.

2. A launcher in accordance with claim 1 wherein each of said housings comprises a pair of superposed separated cells, each containing a launcher rail.

3 A launcher in accordance with claim 2 comprising four of said housings.

4. In a shipboard launcher for rocket propelled missiles of the type having a plurality of adjacent elongated housings, each comprising a pair of superposed separated cells, each cell having a launcher rail contained within same, the longitudinal axes of the rails :being disposed in parallel planes, each cell having a movable closure at its forward end, the rail of each cell being rectilinearly movable by power means for opening the closure and extending a portion of the rail beyond the forward end of a cell, each cell having means associated therewith for selectively restraining a missile carried by its rail against lateral movements and other means for restraining the missile against movement along its rail when the missile produces less than a predetermined thrust, each cell having heat exchangers afiixed to its walls for maintaining its interior at a desired temperature, each cell having means closing its rear end adapted to be ruptured by missile blast, the improvements in combination, comprising; a support mounted for rotation about a vertical axis, a torque shaft carried by said support for rotation about a horizontal axis, power means carried by said support for selectively rotating said support and torque shaft in opposite directions, and means for selectively clutching one of said housings to said shaft, whereby the pair of launcher rails carried by its cells may be rotated about said horizontal axis independent of the remaining launcher rails.

5 A launcher in accordance with claim 1 wherein said means for selectively clutching one of said housings directly to said shaft comprises a slideable pin carried by a housing and aligned with an aperture in said torque shaft when said torque shaft is'in a predetermined position, and means for moving said pin into registry with said aperture, the torque shaft, housing and pin being thereafter rotatable together.

6. A launcher in accordance with claim 5 including an arcuate guideway disposed concentric to said axis forming an abutment engageable with a portion of said pin, for retaining said pin in registry with its mating aperture in the torque shaft. V

7. A launcher in accordance with claiinl including means for positively restraining a housing from rotation when in its lowest position about said horizontal axis, and means interconnecting the last named means with said means for selectively clutching one of said housings directly to said shaft for releasing the housing for rotation when the last named means becomes operative.

References Cited in the file of this patent UNITED STATES PATENTS Eaton June 13, 1961

Claims (1)

1. A SHIPBOARD LAUNCHER FOR ROCVKET PROPELLED MISSILES, COMPRISING; A SUPPORT MOUNTED FOR ROTATION ABOUT A VERTICAL AXIS, A TORQUE SHAFT CARRIED BY SAID SUPPORT FOR ROTATION ABOUT A HORIZONTAL AXIS, POWER MEANS CARRIED BY SAID SUPPORT FOR SELECTIVELY ROTATING SAID SUPPORT AND TORQUE SHAFT IN OPPOSITE DIRECTIONS, A PLURALITY OF ADJACENT ELONGATED HOUSINGS EACH JOURNALLY SUPPORTED BY SAID TORQUE SHAFT, WHEREBY SAID TORQUE SHAFT MAY ROTATE WITHOUT ROTATION OF A HOUSING SUPPORTED THEREBY, SAID HOUSINGS BEING RESTRAINED AGAINST MOVEMENT ALONG THEIR LONGITUDINAL AXES, EACH CONTAINING A LAUCHER RAIL, THE LONGITUDINAL AXES, OF THE RAILS BEING DISPOSED IN PARALLEL PLANES, AND MEANS FOR SELECTIVELY CLUTCHING ONE OF SAID HOUSINGS DIRECTLY TO SAID SHAFT, WHEREBY ITS LAUNCHER RAIL MAY BE ROTATED ABOUT THE SAID HORIZONTAL AXIS INDEPENDENT OF THE REMAINING LAUNCHER RAILS.

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