US3228297A - Adapter rail restraining mechanism - Google Patents

Description

Jan. 11, 1966 oss N ETAL 3,228,297

ADAPTER RAIL RESTRAINING MECHANISM 4 Sheets-Sheet 1 Original Filed March 26, 1963 INVENTORS Robe/f L. Kassan, Robert E Car/her Lou/s H Weber, Richard H. Allen, Palmer 6. Wermadger John L. Sc/reun'e/r BY an B'erfram J Maison Br M Maw/ATTORNEY Jan. 11, 1966 KOSSAN ETAL 3,228,297

ADAPTER RAIL RESTRAINING MECHANISM Original Filed March 26, 1963 4 Sheets-Sheet 2 Jan. 11, 1966 L. KOSSAN ETAL 3,228,297

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Jan. 11, 1966 R. KOSSAN ETAL 3,228,297

ADAPTER RAIL RESTRAINING MECHANISM 4 Sheets-Sheet 4 Original Filed March 26, 1963 I l I l. MMI I I IH "I IH Hl l l l J mwm l I ll w 3, EN

United States Patent 3,228,297 ADAPTER RAIL RESTRAINING MECHANISM Robert L. Kossan, Adelphi, Md., Robert E. Carlberg, McLean, Va., Louis H. Weber, Rockville, and Richard H. Allen, Beltsville, Md., and Palmer G. Wermager, Minneapolis, John L. Scheurich, Excelsior, and Bertram J. Matson, Nlinneapolis, Minn., assigno'rs, by direct and mesne assignments, to the United States of America as represented by the Secretary of the Navy Original application Mar. 26, 1963, Ser. No. 268,496. Divided and this application May 25, 1964, Ser. No.

4 Claims. 01. s9 1.7

This application i a division of co-pending U.S. application Serial No. 268,496, filed March 26, 1963.

This invention relates to missile launchers and more particularly to an adapter rail for use in such launchers.

Heretofore, in the field of missile launchers, it has generally been found necessary to develop a different launching system for each difierent size or type of missile according to the particular needs of each missile. Variations in size of missiles has been a particularly perplexing problem because it requires not only the development of a new system but also the redesign of each individual component within the system. That is to say, when a new type of missile is developed, a launching system can be designed and constructed by using the existing components of another launching system for a different missile which is of the same or similar configuration and size. However, when a missile is developed which is not only of a different type but also of a different size and configuration, the existing components, e.g., magazine and launcher, cannot be used. Thus, it becomes necessary to develop a new system with new components for this last-mentioned missile.

A further object of the present invention is to provide an adapter rail which will mechanically restrain a given missile as the same is transported from the magazine to the launcher arm in a launching system designed for another missile and, when the given missile is positioned on the launcher arm, will remove some of the mechanical restraints until the given missile is fired and when sufficient thrust has been developed the remaining restraints will be overcome.

A further object is the provision of a restraining device that is both positive and releasable upon exertion of a predetermined amount of force therebetween.

FIG. 1 is a composite view of a launcher arm illustrating the manner in which the missile is secured to the adapter rail and the adapter rail supported by the launcher arm;

FIG. 2 is a dimetric view of a mechanical schematic of the central portion of the adapter rail;

FIG. 3 is a detail view of the arming tool and linkage means for the clamp release mechanism;

FIG. 4 is a horizontal section of the central portion of the adapter rail and showing the missile restraining mechanism;

FIG. 5 is a vertical section of the central portion of the rail and showing the missile restraining mechanism;

FIG. 6 is a section taken on line 2626 of FIG. 5 and showing pawls of the missile restraining mechanism in engagement with the aft lug of the missile;

FIG. 7 is a section taken on line 2727 of FIG. 5 and showing the engagement of the pawls with the aft lug of the missile.

The relationship of the missile C to the adapter rail 36 and the rails relationship to the track 29 of the launching system, as represented by the launcher arm 28, is shown in FIG. 1. The adapter rail 36 is constructed of a beam 40, preferably of welded steel con- 3,228,297 Patented Jan. 11, 1966 ice struction, and has forward and aft shoes 42 and 44 respectively, which shoes simulate those for missiles A and B, mounted on the top surface thereof. These upper shoes 42 and 44 are utilized to support the adapter rail and the missile C in the missile magazine and loading mechanism, not shown, 26 and on the launcher arm track 29. Shoe tracks 46, for accommodating the shoes 48 of missile C are mounted on the underside of beam 40. A cantilever beam 50 is bolted to the aft end of the beam 40 and contains two connectors for attaching an umbilical cord.

A restraining latch 250, shown in FIGS. 4 and 5, is provided on the beam 40 to engage and hold the aft shoe on missile C. Restraining latch 250 comprises a compression spring 252 mounted over a sleeve 254 which is slidable in a housing 256 attached to beam 40. A rod 258 is mounted in the sleeve 254 and has a clevis 260 integral with the right end as viewed in FIG. 5. A shoulder 262 is formed on the rod 258 at its juncture with the clevis 260 and bears against spring 252. An enlarged washer 264 is mounted on the sleeve 254 be tween housing 256 and clevis 260 and bears against the other end of spring 252.

An enlarged head 266 is threadedly attached to the left end of rod 258 as viewed in FIG. 5 and by hearing against housing 256 limits the movement of the sleeve and rod to the right. The sleeve 254 is of such length that it bears against both the shoulder 262 and head 266 and is, therefore, not movable relative to the rod 258.

A pin 276 extends through the clevis 260 and pivotally mounts two links 272 and 274 on the clevis. Links 272 and 274 are connected by means of pivot pins 280 and 278 to arms 286 and 288 respectively. The arms 286 and 288 are respectively keyed to shafts 282 and 284 which are rotatably mounted in bearings affixed to beam 40. Latch pawls 312 and 314 are integral with or rigidly attached to the lower end of shafts 282 and 284. Pawls 312 and 3-14 have projections 316 and 318 respectively which engage and restrain the aft shoe of missile C, as shown in FIGS. 6 and 7.

When the missile C is fired, the thrust will act against projections 316 and 318 and exert a moment on pawls 314 and 312 which tends to rotate them inward on the shafts 282 and 284. However, the spring 252 acting on shoulder 262 forces the clevis 260 and pin 276 to the right, as viewed in FIGS. 5 and 6. The spring force, therefore, exerts a moment, through links 272 and 274 to arms 286 and 288 and by shafts 282 and 284, on the pawls 312 and 314 which tends to force them in an outward direction. Thus, the missile C cannot be launched until the thrust exceeds the force of the spring 252, at which point the pawls will be rotated inward and the missile shoe can pass the projections 316 and 318.

A safety latch, operated by rotation of the arming socket, is provided to prevent the pawls from moving inward before the missile is fired. This safety latch comprises a latch block 320, shown in'FIGS. 2, 5 and 6, rigidly attached to a shaft 124 which is rotatably mounted in beam 40. An arm is rigidly attached to shaft 124 and pinned to one end of rod 118. The other end of rod 118 is pinned to gear section 112 by means of pin 109. Rotation of the gear section by the arming tool, as previously described, will move rod 118 to the right as viewed in FIG. 3. Rod 118 will pivot arm 120 to the left and rotate shaft 124. Latch block 320 will, therefore, be pivoted out of notches 322 and 324 in pawls 314 and 312 and permit them to pivot inward.

A manual release 325 shown best in FIGS. 2 and 4 is provided on the beam 40 for retracting projections 316 and 318 on pawls 312 and 314 to permit a missile type C to be loaded onto the adapter rail. The release 325 comprises a bar 270 pivotally mounted at a point intermediate of its ends to beam 48 by means of pin 290. The bar 270 is pivotally pinned at one end to head 266 by means of pin 340 and has a clevis 342 formed integral with its other end. A curved slot 344 is provided in clevis 342 through which a pin 346 extends. A bell crank 348 is pivotally mounted on beam 49 by means of pin 350. One arm of the bell crank is pivotally pinned to a link 352. A rod 354 is secured to beam 40 by means of member 356 and has a clevis 358 on one end. A compression spring is mounted over rod 354 between member 356 and clevis 358 and urges the rod 354 toward the left as viewed in FIG. 4. The pin 346 extends through the slot 344 in clevis 342 and is rotatably secured in the clevis 358 on the rod 354 and the link 352. The slot 344 permits the bar 370 to rotate when the release mechanism 250 is operated normally. However, when it is desired to operate the release mechanism manually, the protruding arm of the bell crank is pushed inward to the dotted position shown in FIG. 4. This causes the link 352 to move the pin 346 to the right and to compress spring 360. Since the link 352 moves beyond center, the bell crank 348 is held in this position. The pin 346 will exert a force on the right edge of the slot 344 and consequently, will pivot the bar 270 about the pin 290. The head 266 will be moved to the left retracting the rod 258 and compressing the release spring 252. Movement of the rod 258 will rotate projections 316 and 318 out of the path of the aft lug for the missile C, through the linkage means previously described.

Obviously many modifications and variations of the present invention are possible in the light of the above teachings. It is therefore to be understood that within the scope of the appended claims the invention may be practiced otherwise than as specifically described.

What is claimed is:

1. A restraining mechanism for holding a missile stationary on a launcher until a predetermined thrust has been developed thereby comprising:

a first housing mounted on the launcher,

a second housing Within said first housing,

a sleeve slidable within said second housing,

a shoulder on one end of said sleeve,

a rod fixedly attached inside of and coaxial with said sleeve and extending beyond said shoulder, a compression spring mounted over said sleeve and between said second housing and said shoulder,

limiting means on said sleeve and engageable with said housing for limiting the extent of movement of said sleeve by the bias of said spring,

a pair of pawls rotatably mounted on said first housing and engageable with the missile,

and linkage means connecting said pawls to said rod whereby said pawls are held in the path of the missile by the action of said spring until the thrust of the missile exceeds the bias force of said spring.

2. A restraining mechanism according to claim 1 in which said linkage means comprises;

a clevis attached to said rod,

a first pair of links pivotally attached to said clevis,

a second pair of links pivotally attached at one end to said first pair of links and rigidly secured at the other end to a pair of shafts, said shafts being rotatably mounted on said first housing, and said shafts being further rigidly attached to said pawls.

3. A restraining mechanism according to claim 2 and further comprising;

a bar pivotally mounted at substantially its central portion to said first housing and pivotally connected at one end to said sleeve,

a slot in and adjacent to the other end of said bar,

a bell crank rotatably mounted on said first housing,

a first link pinned to said bell crank,

a second link movably mounted on said first housing,

bias means interposed between said first housing and said second link for urging said second link toward said first link, and

a pin connecting said first and second links and extending through said slot whereby rotation of said bell crank will cause said first link to move said pin against the force of said bias means and pivot said bar to retract said pawls from the path of the missile.

4. A restraining mechanism according to claim 3 and further comprising;

a block rotatably mounted on said first housing for movement into and out of engagement with said pawls whereby said pawls are rendered immovable when said block is in engagement therewith.

References Cited by the Examiner UNITED STATES PATENTS 2,460,929 2/1949 Golf 891.7 2,690,124 9/1954 Melick 89-1] 2,809,557 10/1957 Johnson 89-15 2,831,400 4/1958 Hosli 89-1.7

BENJAMIN A. BORCHELT, Primary Examiner.

SAMUEL W. ENGLE, Examiner.

Claims (1)

1. A RESTRAINING MECHANISM FOR HOLDING A MISSILE STATIONARY ON A LAUNCHER UNTIL A PREDETERMINED THRUST HAS BEEN DEVELOPED THEREBY COMPRISING: A FIRST HOUSING MOUNTED ON THE LAUNCHER, A SECOND HOUSING WITHIN SAID FIRST HOUSING, A SLEEVE SLIDABLE WITHIN SAID SECOND HOUSING, A SHOULDER ON ONE END OF SAID SLEEVE, A ROD FIXEDLY ATTACHED INSIDE OF AND COAXIAL WITH SAID SLEEVE AND EXTENDING BEYOND SAID SHOULDER, A COMPRESSION SPRING MOUNTED OVER SAID SLEEVEE AND BETWEEN SAID SECOND HOUSING AND SAID SHOULDER, LIMITING MEANS ON SAID SLEEVE AND ENGAGEABLE WITH SAID HOUSING FOR LIMITING THE EXTENT OF MOVEMENT OF SAID SLEEVE BY THE BIAS OF SAID SPRING, A PAIR OF PAWLS ROTATABLY MOUNTED ON SAID FIRST HOUSING AND ENGAGEABLE WITH THE MISSILE, AND LINKAGE MEANS CONNECTING SAID PAWLS TO SAID ROD WHEREBY SAID PAWLS ARE HELD IN THE PATH OF THE MISSILE BY THE ACTION OF SAID SPRING UNTIL THE THRUST OF THE MISSILE EXCEEDS THE BIAS FORCE OF SAID SPRING.

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