US3262664A - Universal missile adapter - Google Patents

Description

July 26, 1966 w. PARASKEWIK UNIVERSAL MISSILE ADAPTER 2 Sheets-Sheet 1 Tiled Oct. 30. 1.964

INVENTOR. WILLIAM PA ASKEWIK ATTORNEYS July 26, 1966 w. PARASKEWIK UNIVERSAL MISSILE ADAPTER 2 Sheets-Sheet 2 Filed 061;. 30, 1964 INVENTOR.

WILLIAM PARASKEWIK ATTORNEYS United States Patent 3,262,664 UNIVERSAL MISSILE ADAPTER William Paraskewik, Lansdale, Pa., assignor to the United States of America as represented by the Secretary of the Navy Filed Oct. 30, 1964, Ser. No. 407,933 5 Claims. (Cl. 248-119) 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.

The present invention relates to a device for transporting heavy loads and more particularly to a handling apparatus for securing various diameter missiles to a wheeled dolly for the subsequent transportation of the missile from one location to another.

Heretofore several types of devices have been employed for performing the function of retaining missile loads, such as guided missiles, torpedoes or the like, upon dollies for the purpose of facilitating the transportation of such missiles. Screw down clamps have been used in some of these devices while in others cable lashings have been employed. These prior art missile-securing assemblies have not been altogether satisfactory in the handling of modern thin-shell weapons since they have caused damage to the shell of the missile even when extreme caution and low speeds were used during transport.

The need for a satisfactory clamping device which will hold a missile without slippage while the missile is being transported from a storage point to a subsequent location has been emphasized by the growing complexity of modern missiles, as well as the sensitivity or explosive nature of the various components employed therein. Consequently, missiles of the present day types must be transported and handled without even slight damage thereto if malfunctions are to be avoided. At the same time, however, missiles must be handled efficiently and with rapidity and the handling personnel must not be placed at a disadvantage in performing their duty of efiicient handling by being required to either exercise extreme caution while handling the missiles or to transport the same at extremely low speeds.

Most present day missiles are designed with suspension lugs which are longitudinally spaced at 14 inch or 30 inch intervals. It is through these lugs that the missile is removably secured, through hooks or the like, to a carrier aircraft. Furthermore, the lugs are employed in the handling of the missile as the same proceeds through the logistic flow cycle. In a previou proposal, it was found desirable to utilize the suspension lugs in lieu of the screw down clamps and cable lashings to retain the missile upon the transportation vehicle. The missile was placed on the vehicle with the suspension lugs in an upwardly facing position and an attempt was then made to rotate the missile on its cradling structure for purposes of moving the suspension lugs adjacent to fastening means located at the bottom of the cradle. Rotation of the missile was found to be extremely difiicult because of the weight thereof, and more particularly because of the many appendages formed on the missile: these appendages, for example, are used to secure the guiding and stabilizing wings and fins.

With the foregoing in mind the present invention provides a cradle or handling adapter which may be integrally or removably fastened to a wheeled supporting structure. The adapter of the present invention cradles the missile, anchors the same to permit transportation thereof, and provides unconstrained 360 rotation for purposes of moving the missiles suspension lugs to any desired position, such as downward for latching the mis- "ice sile, and upward for allowing simple removal of the missile from the cradle by a collateral handling device.

It is an object of the present invention to provide a cooperating cradle and clamping device for a transporting vehicle whereby a load may be secured to the cradle in a positive manner eliminating all possibility of slippage or looseness.

Another object of the present invention is to provide a cooperating cradle and clamping structure which will retain aload without damage .to the surface thereof and without employment of additional clamps or securing means.

A further object is to provide a clamping device for retaining a load on a transportation vehicle, the device being capable of actuation in a rapid and positive manner.

Still another object of the present invention is to provide a combination cradle and latching means which permits a load, such as a missile, to sustain high G load without damage thereto when in the latched condition.

A' still further object of the present invention is to provide a cradle which permits a load to be easily rotated 360 when situated thereon.

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: Y

FIG. 1 shows a plan view of an embodiment of the present invention;

FIG. 2 illustrates a more detailed plan view of the In the illustrated embodiment of the invention and with particular reference to FIG. 1 it will be observed that a pair of cradles or handling adapters, generally designated by reference numerals 10, are secured to a supporting structure such as the wheeled dolly 11 in a manner to be described more fully below. Since the adapters 10 are identical in all respects, only one adapter of the pair will be specifically described below. As best illustrated in FIGS. 1 and 4, the supporting structure 11 includes a pair of upwardly extending longitudinal rails 13 perforated along the longitudinal length thereof at 13a for selectively positioning both the cradles 10 and a cooperating pair of latching mechanisms generally designated by reference numerals 60. The cradles 10 and latching mechanisms 60 are particularly arranged to support a cylindrical load such as a missile M longitudinally of the length of the supporting structure 11 and at the same time prevent the load from shifting in any direction relative to the cradle.

Reference'is now made to FIGS. 2, 3 and 4 for a more detailed description of the cradle assembly 10. The cradle comprises a U-shaped channel member or frame 20 positioned transversely of the rails 13 with a pair of slots 22 formed in the base 20a thereof for receiving the rails 13 of the supporting structure 11. The channel member 20 is additionally formed with transversely extending arms 23, seen more clearly in FIG. 4, each having apertures at the ends thereof for alignment withthe perforations 13a of the rails 13. Appropriate fasteners 24 pass through the apertures in the arms 23 and rails 13 to thereby anchor the cradle 10 to the wheeled supporting structure 11.

As viewed in FIGS. 2 and 3, the frame 20 includes an outer pair of bearing blocks 25 and an inner pair of bearing blocks 26 appropriately secured to the sidewalls of frame 20 for rotatably receiving a shaft 27 therethrough. Shaft 27 is reversely threaded along the length thereof between each outer bearing block and inner bearing block 26 and includes tool receiving portions 28 at the ends thereof.

Positioned between each outer bearing block 25 and inner block 26 and threadably engaged by shaft 27 is a traveling block or traveler generally indicated at 39. Each block 30 includes a base portion 31 for receiving the reversely threaded portions of shaft 27, the base being further constructed with guide slots 33 for engaging corresponding guide rails 34 formed on the sidewalls of channel member 20. Each traveler 30 includes upwardly extending ears 36 having an aperture extending therethrough for rotatably supporting a pin 37 in a bearinglike manner. Pin 37 projects from and may be formed integrally with a load abutting roller member 38, the roller portion thereof being constructed of soft rubber or like material of such characteristics that injury to the missile M is precluded. As viewed more clearly in FIG. 3, pins 37 extend outwardly beyond the ears 36 of each block 30 and extend into oblong slots 40:: formed in link arms 40. Bearing assemblies 43 are appropriately fitted to these extensions of pins 37 and abut against the edges of the slots 40a to facilitate movement of each pin relative to the link arms 40 upon sliding movement of block 30 in response to rotation of shaft 27.

Pivot pins 45 integrally secured or otherwise formed with channel member 20, pivotally connect the lower ends of the link arms 40 to the frame 20 and a lower wheel 47 is additionally supported for rotation on each pivot pin 45. As viewed in FIG. 4 the upper end of each of the link arms includes an outwardly projecting spindle portion 48 rotatably receiving an upper wheel 49. An endless belt 50 is applied about the lower and upper wheels 47 and 49, respectively, to provide a soft flexible support for the missile M which extends transversely thereof. By reason of the belt and Wheel arrangements the missile M may be rotated with facility to bring hoisting lugs M formed on the missile M into engagement with the latching mechanism shown in FIGS. 1 and 5.

Latching mechanism 60 includes a top plate 61 extending transversely of the rails 13 and an access opening 61a formed therein. Plate 61 includes downwardly depending flanges 62 at the extremities thereof and an additional pair of downwardly depending plates 63 extending adjacent the inside of the rails 13. Flanges 62 and plates 63 are formed with apertures corresponding to-the spacing of the apertures 13a in rail 13 and a fastener 64 passes through these apertures to anchor the latching mechanism at the proper location along the rails 13. The position of the latching mechanism will be determined by the lug spacing on the missile M. g

A lug engaging hook 65 including base portion 65a and hook camming surface 65b is pivotally connected intermediate the depending plates 63 to a shaft 66 secured to the sideplates 63 and the hook 65 is freely pivotal betweenthe solid line or unlatched position A and the dotted line or latched position B. In order to maintain the hook 65 in the latched position B, a releasable hookretaining mechanism is pivoted adjacent hook 65 to a shaft 69 journaled in sideplates 63. Retainer 70 includes a retainer camming surface 70a for camming engagement with the base 65a of hook 65, a shoulder portion 79b for engaging the base of the hook, and a flange 700. A coiled spring mechanism is secured to pin 76 which in turn is anchored to the sidewalls 63 and includes'a one end 75:: thereof engaging the flange 700 of retainer 70 and urging the same to pivot in a counterclockwise direction. The other end 75b of spring 75 engages the hook 65 and urges the same toward the unlatched position A.

The latching mechanism operates in a manner now to be described. Prior to the introduction of the lug 55M into the'access opening 61a of plate 61, the spring elements 75a and 75b urge the retaining mechanism 70 and the lug engaging hook 65 to the respective solid line 4 position A. Upon introduction of the lug 55M within opening 61a and the engagement thereof with the hook camming surface 65b, the hook 65 rotates in a counterclockwise direction about pivot pin 66 toward the dotted line position B. This rotative movement causes the base 65a 01f the hook 65 to engage the retainer camming surface 70a and to rotate the same in a clockwise direction against the action of spring elements 75a. When the base portion 65a passes the camming surface 70a, that is, assumes the dotted line position B, the spring element 75a urges the retainer 70 to the illustrated position wherein shoulder 70b engages the base 65a of the hook thereby precluding any movement thereof toward the unlatched position A. In order to unlatch the lug 55M, the retainer 76 is pivoted in a clockwise direction about shaft 69 by an application of a force at an outer extremity thereof, for example at 70d.

Describing now the operation of the adapter 10 in combination and cooperation with the latching mechanism 60, reference is now made to FIGS. 2, 3 and 4. In the initial position, that is prior to the introduction of the missile M on the conveying vehicle, the traveling blocks 30 and associated rollers 38 are positioned adjacent the outer bearing blocks 25. It should be noted that rotation of the shaft 27 at either end thereof will cause the traveling blocks 34 to move in opposite directions in View of the reverse threading of the shaft. In this position the rollers '38 and the upper wheels 49 are in substantial alignment and the endless belt 50 is in its least slacken'ed condition. The missile M is unloaded from a preliminary carrying vehicle and hoisted from the preliminary carrier to the cradles 10 of supporting structure 11. This missile M is placed transversely of the cradles it) and rest on the two pairs of belts 50. It should be noted that the missile in this position does not engage any rollers or other restraining surfaces. Due to the hoisting of the missle, the lugs 55M extend upwardly in a direction opposite to the location of the latching mechanism 69. By reason of the cradle arrangement of the present invention the missile M may be rotated by hand to bring the lugs 55M adjacent the latching mechanism location. The rotation of the missile is accomplished with facility since the belt moves over the wheels 47 and 49, is flexible, and offers no resistance to any appendages, such as fittings or projections that may extend fromthe missile. When the lug SSM is adjacent the latching mechanism 60, the shaft 27 is rotated in a direction to cause the traveling blocks 30 to move inwardly. Due to the engagement of pin 37 and roller bearing assembly 43 with the sides of the oblong slot 40a, inward movement of the block 30 causes link arm 40 to pivot upwardly about pivot pin 45. Oblong slot 40a is angularly related to the central axis of link arm 40 extending between pivot pins 45 and 48 and, thereby, maintains the wheels 49 by contacting the missile M as the sliding block 30 moves inwardly. That is, the configuration of oblong slot 40a is such that a greater slack is permited in the belt 5t) without wheels 49 engaging the missile. It is readily seen in FIG. 3 that inward movement of the traveling block 30 causes the pivoting of link arm 40 and slackening of belt 50 which thereby permits the missile and associated lugs 55M to move downwardly toward engagement with latching mechanism 60. Wheels 49 do not engage the missile at this time which factor allows the final rotative adjustment of the missile and associated lug into the access opening 61a. Continued inward movement of traveling block 30 further slackens the belt 50, thereby causing lug 55M to initiate the latching mechanism 60 in a manner described above. When the hook 65 and retainer 70 are in the latched position, shaft 27 is further rotated to continue the inward movement of traveling block 30. This movement causes the soft rubber roller 38 to engage the missile and urge the same upwardly against the retaining hook 65. At this time, the belt 50 partially envelops the missile M and thereby provides side support thereto.

In order to remove the missile M from the cradle 10, the retainer 70 is depressed as described above with reference to the discussion of the latching mechanism 60. If necessary, the traveling block 30 is then moved inwardly, by rotation of shaft 27, to lift suspension lug 55M from opening 61a. The missile M is now freely rotatable with belt 50 and the lugs 55M are easily upwardly positioned to allow simple removal of the missile from the cradle by a collateral handling device.

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 device for supporting, positioning and transporting a cylindrical ordnance missile having securing means associated therewith comprising:

a wheeled supporting structure;

fastening means adjustably positioned on said supporting structure for engaging the securing means;

a cradle including a frame adjustably positioned on said supporting structure for supporting and positioning the missile;

belt means mounted on said frame, said belt means providing the sole support for the missile and having continuous movement transverse of the length of the missile, whereby the missile can be rotated about the longitudinal axis thereof Without incurring any substantial resistance thereto for positioning the securing means with respect to said fastening means; and

means mounted on said frame for moving said belt means between an unslackened and a slackened condition to thereby raise and lower the position of the securing means on the missile with respect to said fastening means.

2. The combination as defined in claim 1 wherein said fastening means includes:

hook means pivotal between a latched and unlatched position, said hook means being moved to the latching position by the securing means.

3. The combination as defined in claim 2 wherein said belt moving means includes roller means for engaging the missile after the missile has been engaged by said fastening means for urging the missile away from the said fastening means.

4. The combination as defined in claim 3 further including:

a pair of arms on each side of said frame having one end thereof pivotally connected to said frame;

Wheel means rotatably secured to each end of said arms for receiving said belt means thereabout;

said belt moving means operatively engaging said arms and moving said belt means positioned thereabout between a slackened and unslackened condition.

5. A device as defined in claim 4, and including:

a threaded shaft journaled in said frame,

said belt moving means threadably secured to said shaft for movement in response to rotation thereof.

References Cited by the Examiner UNITED STATES PATENTS 2,463,383 3/ 1949 Hokanson 26912 2,514,293 7/1950 Rumsey 2141 2,5 7 6,127 11/ 1951 Lefiler 144-208 2,669,364 2/1954 Aronson 2l4l 5 CLAUDE A. LE ROY, Primary Examiner.

R. P. SEITTER, Assistant Examiner.

Claims (1)

1. A DEVICE FOR SUPPORTING, POSITIONING AND TRANSPORTING A CYLINDRICAL ORDINANCE MISSILE HAVING SECURING MEANS ASSOCIATED THEREWITH COMPRISING: A WHEELED SUPPORTING STRUTURE; FASTENING MEANS ADJUSTABLY POSITIONED ON SAID SUPPORTING STRUCTURE FOR ENGAGING THE SECURING MEANS; A CRADLE INCLUDING A FRAME ADJUSTABLY POSITIONED ON SAID SUPPORTING STRUCTURE FOR SUPPORTING SAID POSITIONING THE MISSILE; BELT MEANS MOUNTED ON SAID FRAME, SAID BELT MEANS PROVIDING THE SOLE SUPPORT FOR THE MISSILE AND HAVING CONTINUOUS MOVEMENT TRANSVERSE OF THE LENGTH OF THE MISSILE, WHEREBY THE MISSILE CAN BE ROTATED ABOUT THE LONGITUDINAL AXIS THEREOF WITHOUT INCURRING ANY SUBSTANTIAL RESISTANCE THERETO FOR POSITIONING THE SECURING MEANS WITH RESPECT TO SAID FASTNING MEANS; AND MEANS MOUNTED ON SAID FRAME FOR MOVING SAID BELT MEANS BETWEEN AN UNSLACKENED AND A SLACKENED CONDITION TO THEREBY RAISE AND LOWER THE POSITION OF THE SECURING MEANS ON THE MISSILE WITH RESPECT TO SAID FASTENING MEANS.

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