US2826960A

US2826960A - Missile launcher

Info

Publication number: US2826960A
Application number: US252970A
Authority: US
Inventors: Ferdinand J Schiavi
Original assignee: Individual
Current assignee: Individual
Priority date: 1951-10-24
Filing date: 1951-10-24
Publication date: 1958-03-18
Anticipated expiration: 1975-03-18

Description

March 18, 19.58

Filed OCI". 24,v 1951 FIG.

F. J. scHlAvl 2,826,960

MISSILE LAUNCHER Y 7 Sheets-Shea?l l ATTORNEYS F. J. SCHIAVI March 18, 1958 MISSILE LAUNCHER 7 Sheets-Sheet 2 Filed Oct. 24. 1951 BY QM@ (5P/2mm@ March 18, 1958 F. J. scHlAvl 2,826,950

y Mssms LAUNCHER Filed oct. 24, 195; 7 Smets-sheet s INVENTOR FERDINAND J. SGH/A Vl BY Hf/4%@ (G2/344m ATTORNEYS F. J. SCHIAVI y March 18, 1958 MISSILE LAUNCHER 7 Sheets-Sheet 4 Filed oct. 24, 19.51

INVENT-ORIk FE R17/NAND J. 5CH/ V/ v .mi

March 18, 1958 F. J. scr-NAVI 2,326,960

MIssILE LAUNCHER Filed oct. 24, 1951 '7 Sheets-Sheet 5 INVENTOR.

.l sow/Aw March 18, 1958 F. J. scHlAvl 2,826,960

MrssILE LAUNCHER Filed ont. 24, 1951 I Y 'r sheets-sheet e -IIIIIIIIIIIIIIHHHIL E I S l i E s q) l a i t Q v :s un W i W- FERDINAND J. SCH/AVI ATTORNEYS Marchy 18, 1958 FJ. SCHIAVI 2,826,960

MISSILE LAUNCHER Filedoct. 24, 1951 'r sheets-sheet# PER/NAND d. SGH/ W j@ @Kw ATTORNYS 2,826,960 Patented Mar. 18, 1958 MlSSlLE LAUNCHER Ferdinand I. Schiavi, Fails Church, Va. Application @ctober 24, 1951, Serial No. 2527ii 4 Claims. (Cl. 89 1.7)

(Granted under Title 35, U. S. Code (1952), sec. 266) This invention relates to missile launchers and more particularly to a launcher for guided missiles, rockets and similar self-powered devices.

Heretofore guided missiles and rockets of any substantial length have customarily been launched from land based launchers since shipboard launching operations are so hindered by the action of rough weather, space limitations and launcher control problems as to render them impractical. In the past, launchers for long missiles have ordinarily assumed the form of an elaborate skeletonized framework having a number of long guide rails or tracks to surround and guide the missile. These rails were normally muc-l1 longer than the missile so that the missile would be guided during a substantial portion of its launching movement. In such devices the track or guideway was ordinarily xed in elevation, or at best could only be moved very slowly and by cumbersome means and very long missiles required that the framework extend a substantial distance upwardly. It is apparent that such a massive relatively immovable structure would be unsuitable for shipboard installation and would be diiicult to reload, would not permit operation by conventional re control equipment, and would objectionally raise the center of gravity of the ship.

With the foregoing in mind, it is an object of the present invention to provide a missile launcher which is relatively short in length as compared to the missile and hence is suitable for shipboard installation.

Another object isto provide a missile launcher which may be movable in both train and elevation so as to provide a relatively stable platform for launching a missile from a ship.

Still another object is to provide such a launcher which may be remotely controlled by conventional gun control or lire director means.

Another object is the provision of a missile launcher which aiords a low ship silhouette or prole and therefore is not readily observable by an enemy.

A further object is the provision of a launcher for self-propelled missiles wherein the missile blast is directed away from the mount operating mechanisms.

A still further object is the provision of a missile launcher which may be conveniently loaded and reloaded by shipboard personnel while the ship is under way.

Still another object is the provision of a missile launcher which normally supports the missiles at a convenient height for operating personnel to make preight inspections, adjustments and repairs.

These and other objects and inherent advantages of this invention will become apparent from the following specication and drawings in which:

Fig. l is a side elevational view of one embodimentV of the invention illustrating by dotted lines a missile in its loaded position and the same missile 4elevatedto a ring or launching position;

Fig. 2 is a top plan view ofthe embodiment shown in Fig. l illustrating by dotted lines the spaced positions of a pair of missiles when mounted on the launcher;

Fig. 3 is a front elevational view of the launcher of Fig. l illustrating the manner in which the missiles are supported by the launcher;

Fig. 4 is a side elevational view of the launcher adapted for use on a land vehicle;

Fig. 5 is an enlarged sectional view taken along a line substantially corresponding to line 5 5 of Fig. 2 and illustrating details of the mount training and elevating mechanisms;

Fig. 6 is an enlarged detailed view partially in section and partially broken away taken along a line substantially corresponding to line 6 6 of Fig. 2 and showing missile supporting structure and a latch for preventing accidental forward motion of the missile;

Fig. 7 is an enlarged transverse sectional View taken along a line substantially corresponding to line 7 7 of Fig. 6 and illustrating the missile supporting railspandv the relative position of the firing contact;

Fig. 8 is a fragmentary horizontal section taken alonga line substantially corresponding to line 8 8 of Fig.. 7

limiting rearward movement of a missile; and

Fig. 9 is a vertical sectional View taken along a line substantially corresponding to line 9 9 of Fig. 8 illustrating the manner in which the tiring contact engages the missile supporting lug.

Referring now to the drawings, wherein like reference numerals designate like parts throughout the several Views, Figs. l, 2 and 3 disclose a launcher mount, designated generally by the numeral 2G, mounted for rotation on a supporting stand 21, which is aixed to a deck or platform 22 of a ship. The launcher mount is supported for rotation by suitable annular roller pads and bearings 23 (Fig. 5) on a platform 24 upon which is also mounted' suitable launcher training and elevating power drive mechanisms, such for example, as are used on U. S. Navy 40 mm. quad gun mounts which may be remotely controlled by known gun director systems.

A missile supporting frame 43, of a substantially U-shaped is mounted above the platform 24 on a stanchion or weldment 25 comprising spaced reinforced vertical plates 26 extending upwardly and rearwardly from the vertical axis 27 of the mount 20 and secured to the upper surface of the platform by bolts or other suitable means. The frame 43 is pivotally mounted on the stanchion 25 by means of a pair of short trunnion shafts 30 journaled as shown in pillow blocks 29 mounted at the top of each vertical plate 26.

The entire frame 43 and its attached missiles 47 may be moved in elevation by means of an elevating arc or sector 40 (Fig. 5) mounted on the frame and having peripheral teeth 41 in engagement with an elevating pinion d2. Since the trunnion shafts are Cif-center, 1t is apparent that when the frame is elevated only the short after end of the frame 43 will be moved toward the deck 22. This oit-center mounting of the trunnions permits the mount 2G to be positioned relatively close to the deck 22 and still be raised to a high elevation which results in a low silhouette and places the frame and missiles 47 within easy reach of shipboard personnel. Movement of the frame 43 in elevation may be limited by a suitable stop or buifer arrangement and movement in depression may be limited by a stop mechanism which in the embodiment illustrated includes a shield 43 mounted on the cross arm 44 and extending beyond the shaft 3i) to a position over a combination buler and elevation drive limit switch 49. The switch 49 is contacted by the shield 43 when the frame 43 is depressed to a predetermined point at which time the actuation of the switch will stop the elevation driving mechanism and prevent further depression of the frame.

The frame 43 includes missile supporting legs or booms 46 which, `as shown, extend forwardly .and downwardly of the center point 50 of the trunnions 30 (Fig. l) and outwardly of platform 24, and comprise two flanged box like forward and

rear sections

51 and 52 secured together at their flanged ends by bolts or other suitable means. The forward section 52 which mounts the missile supporting'and guiding surfaces may readily be removed as a unit and replaced by anotherto accommodate missiles of different design or to replace a damaged section.

As shown the missile may be supported at its after end by three suspension lugs, two forward and one aft. Each missile supporting forward section 52 includes a base plate 53 having depending walls 54--54 (Figs. 6 and 7) which extend along the length of the section and are slotted or grooved at their forward ends to form rails or guideways S for accommodating forward supporting lugs 56 mounted on the missile 47. Mounted in each of the guideways 55 at a predetermined distance from the forward end of section 52 is a stop 57 which limits the rearward movement of the lugs on the guideways. The missile 47 is further supported near its after end on the boom 46 by means of a T-shaped lug 60 mounted on the missile and in sliding contact with an after guideway 59 of similar configuration which is open at both ends and extends the length of the lower portion of a missile supporting block 5S mounted on and depending below base plate 53. The block 58 is critically mounted in the base plate 53 so that the distance from its forward end to the forward end of the guideways 55 is equal to the distance between the forward lugs 56 and the after lug 60 on the rocket or missile 47. This construction provides for a simultaneous release of the forward and after

lugs

56 and 60 from their respective supporting rails and 59 as the missile 47 is moved forward and results in what may be called a tip olf-less launching of the `missile with substantially zero length guideways relative to the length of the missile to be laimched and as compared with guideways previously employed on launchers for large size missiles. This feature of zero length tip off-less launching prevents missile tip off or tilt such as would occur if the missile supporting lugs 56 and were to be separately released, as for example where both lugs travel in the same guideway and the forward lug necessarily reaches the end of the guideway and is released before the after lug. The missile 47, as disclosed above is supported at its after end, thus as the frame. 43 is elevated a major portion of the missile moves away from platform 24. This manner of mounting the missile 47 inv combination with the off-center trunnions provides a construction having a low center of gravity and capable of movement in train and elevation independent of the length of the missile, which is highly desirable for shipboard use.

A solenoid operated latch bar 62 (Fig. 6) is provided in each forward boom section 52 for locking the missiles 47 against forward movement on the launcher. The latch bar 62 is slidably mounted in an upper central portion 61 of missile supporting block 58 and is normally urged into engagement with the after missile lug 6) by means of a coil spring 63 which acts against a flange 64 on thev latch bar and a cover plate 65 mounted onthe top surface of the upper central portion 6I of missile supporting block 58. The lower forward portion of the latch bar 62 is beveled so that the bar will be raised when the beveledface is engaged by lug 60 as the missile 47 is moved rearwardly on guideway 59 thus permitting the lug, to pass the bar. The after portion of the latch bar 62V presents a vertical face to prevent forward motion of the missile after the lug has moved past the bar and the bar itself is prevented from rotating by a keyway 6,6` milled into the bar which is inv engagement with a suitable key (not shown). on thev cover plate 65. The

4 latch bar 62 is raised to release the missile 47 for forward movement on the

guideways

55 and 59 by means of a solenoid Si) which is pivotally connected to the latch bar through a iianged link assembly 68. The link assembly 68 rises with the latch bar 62 to actuate a missile firing switch 8l which is mounted on the forward boom section 52 to one side of the latch mechanism and has an arm 82 extending over the flanged portion of theY link as sembly which is engaged thereby to operate the switch to lire the missile 47 and to further indicate through a suitable signal circuit that the latch bar has been withdrawn from the guideway 59 and the missile freed for forward movement.

ln the embodiment illustrated, an electric current for firing the missile is conducted to the missile through contact 85 located on the end of a leaf spring or similar resilient means S6 which is mounted on base plate 53 in the forward end of section 52 (Figs. 8 and 9) and electrically insulated therefrom by an insulator S7. The contact is urged downwardly through anaperture 88 in plate 53 by spring 86 and engages a Contact 89 on one of the lugs 56 of the missile. A conductor 100 is connected at one end to a terminal 101 on leafspring 86 and at the other end to a suitable firing current source (not shown). Access to the mechanism within forward section 52 for checking and maintenance is provided through an aperture 83 having a removable cover 84 which may be of transparent material if desired.

In Fig. 4 there is shown an adaptation of the mount 20 for use on a vehicle. As shown it is supported on the running gear of a 105 mm. antiaircraft mount 200 and is an illustration of the scope of use of this invention. It will be apparent that the same advantages are present in this use and that it may be remotely controlled in the same manner.

In operation missiles 47 to be launched are loaded on lift trucks (Fig. 3) which are provided with guideways 111 which slidably engage lugs 112 located on the underside of the missiles. If a missile booster unit is employed then the support lugs may be mounted upon the booster in the manner illustrated. In use missiles 47 so mounted on the trucks are transported to the launcher 20 and raised by suitable means to a position where the forward and after

missile supporting lugs

56 and 60 on top of the missile are in alignment with their respective rails or guideways 55 land 59 on undersurface of the launcher legs or booms 46. The missiles are then moved rearwardly until they are locked in place, after which the trucks 110 may be moved. Because of the low slung characteristics of the mount 20 the missiles are in a position so that preflight inspections or other work on the missile may be performed with ease. This' low slung position of the missiles obviates thenecessity of scaffolding or other similar supports to raise personnel to a position where work may be done.

After the preflight inspections and adjustments have been completed the missiles 47 are trained andV elevated lto a tiring positionin' accordance with information relating t-o a specific target and the firing circuit is closed. This energizes solenoid 80 to retract the -missile restraining latch bar 62 and link assembly 68, the upward movement of which ycloses switch 81 to lire the missiles through a` suitable firing circuit (not shown) including spring pressed contact 85 and its mating contact 89 on' one of the forward missile supporting lugs 56. Because of the outboard position of the missiles on the launcher, the take-off blast of the missiles is directed away from the operating mechanisms of the launcher, thus obviating injury to saidV mechanisms due to the tremendous heat developed by the missiles at take-olf. V'Ihrough theV use of suitable: firing circuits the missiles supported by the twin-'launcher booms may selectively be tired either consecutively or simultaneously.

While there is illustrated a preferred embodimentrof the invention, it is to be understood that the invention may be embodied in other forms without departing from the spirit and scope of the invention as defined by the following claims.

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.

What is claimed is:

1. In 'a launcher for missiles having relatively delicate radially extending vanes, a bas'e, a trainable mount supported on the base for rotation about a vertical axis comprising a stanchion extending upwardly and rearwardly from said axis, trunnion shafts on said stanchion disposed rearwardly of said axis, a horizontal transverse frame mounted on and in close proximity to said shafts for pivotal movement in elevation about said shafts, said frame having a leg extending forwardly of said shafts and spaced outboard of the base and stanchion, forward and aft guideways of equal length depending from the under* side of said leg to receive mating spaced lugs on a missile to be launched from the mount, said guideways being spaced from one another for simultaneous release of the lugs on the missile and thereby providing tip olf-less launching, said guideways also being so positioned as to support the missile adjacent its aft end to thereby allow the missile to be pivoted in elevation to any desired firing position regardless of its total length, latch means to preclude forward movement of the missiles until ready for tiring, and means to preclude rearward movement of the missile.

2. In a launching apparatus for missiles having a relatively delicate radially extending vanes, a base, a trainable mount supported on the base for rotation about a vertical axis comprising a stanchion extending upwardly and lrearwardly from said axis, trunnion shafts on said stanchion disposed rearwardly of said axis, a substantially U-shaped frame mounted on said shafts adjacent its base for pivotal movement in elevation, the legs of said frame extending forwardly and being spaced outboard of the base and stanchion, forward and aft guideways of equal length depending from the underside of said legs to receive mating spaced lugs on missiles to be launched from the mount, said guideways being spaced from one another for simultaneous release of the lugs on the missile and thereby providing tip off-less launching, said guideways also being so positioned as to support the missiles adjacent their after ends to thereby allow the missiles to be pivoted in elevation to any desired ring position regardless of their total length, latch means extending into the aft guideways to preclude forward movement of the missiles until ready for tiring, and means for conducting electric currents to the missiles for firing the missiles.

3. In a launching apparatus for missiles having relatively delicate radially extending vanes, the launching apparatus having a base, a ltrainable mount supported on the base for rotation about the vertical axis, a stanchion extending upwardly and rearwardly from said axis, trunnion shafts on said stanchion disposed rearwardly of said axis, a substantially U-shaped frame mounted on said shafts adjacent to its base for pivotal movement in elevation, and the legs of said frame extending forwardly and being spaced outboard of the base and stanchion; the combination of spaced parallel guideways of equal length depending from the underside of each of said legs adjacent the forward ends thereof to receive mating spaced lugs on missiles to be launched from the mount, a missile supporting block depending from the underside of each leg rearwardly of said guideways, said blocks each having a T-shaped slot to receive a mating lug on each missile, the axis of said slot being disposed intermediate the spaced forward lguideways the distance from the forward end of the forward guideways to forward end of the missile supporting block being equal to the longitudinal distance between the support lugs on the missile to permit tip olf-less launching of the missile, said forward and after guideways being spaced to support the missiles adjacent their after ends to thereby allow the f missiles to be pivoted in elevation to any desired tiring position regardless of their total lengths, latch means extending into the after guideways to prevent forward movement of the missiles until ready for firing, stops mounted in said forward guideways to prevent rearward movement of the missiles.

4. In a launcher for missiles having relatively delicate radially extending vanes, the launcher having a platform, a trainable mount supported on the platform for rotation ab-out a Vertical axis comprising a stanchion extending upwardly and rearwardly from said axis, pillow blocks mounted on said stanchion rearwardly of said axis, trunnion shafts journaled in the pillow blocks, a substantially U-shaped frame mounted on said shafts near its base for pivotal movement in elevation, the legs of said frame extending forwardly and being spaced outboard of the plat-form and stanchion, and each of said legs comprising a plate having depending walls extending the length of the plates; the combination of forward guideways in the forward portion of said walls, a missile supporting block mounted on the after portion of each of said plates and having a T-shaped after guideway, the .axis of said after guideway being disposed intermediate said walls, said guideways being of equal length and receiving mating lugs mounted on the after portions of missiles to be launched from the mount, the distance from the forward end of the' after guideways to the forward end of the forward guideways being equal to the longitudinal distance between the lugs on the missiles to permit tip olf-less launching of the missiles, said missiles being supported exclusively adjacent their after ends to thereby allow the missiles to be pivoted in elevation to any desired firing position regardless of their total lengths, latch means mounted on said support blocks and extending into the after guideways to preclude forward movement of the missiles until ready for tiring, stops mounted in said forward guideways to preclude rearward movement of the missiles at all times.

References Cited in the lc of this patent UNITED STATES PATENTS 409,943 Emmens Aug. 27, 1889 1,351,649 Holecek Aug. 31, 1920 1,377,292 Thomas May 10, 1921 2,414,579 Anderson et al. Jan. 2l, 1947 FOREIGN PATENTS 455,576 Great Britain Oct. 23, 1936 970,202 France June 14, 1950