US2978959A

US2978959A - Self-aligning guide for loading in missile launching systems

Info

Publication number: US2978959A
Application number: US357937A
Authority: US
Inventors: Robert E Carlberg
Original assignee: Individual
Current assignee: Individual
Priority date: 1953-05-27
Filing date: 1953-05-27
Publication date: 1961-04-11
Anticipated expiration: 1978-04-11

Description

April 11, 1961 Filed May 27. 195;

FIG. I

R. E. CARLBERG SELF-ALIGNING GUIDE FOR LOADING IN MISSILE LAUNCHING SYSTEMS 2 Sheets-Sheet 1 I4 I6 2% i U 2:9 32 '33 52 L i 26 25 22 2o 39 40 31, as 45 LOADING DIRECTION FIRING DIRECTION "III ROBERT E. CARLBERG BY ZLMM Q/BMW ATTORNEY S A ril 11, 1961 R. E. CARLBERG 2,978,959

SELF-ALIGNING GUIDE FOR LOADING IN MISSILE LAUNCHING SYSTEMS Filed May 27, 1953 2 Sheets-Sheet 2 INVENTOR ROBERT E. CARLBERG 3a 7 BY SELF-ALIGNING GUIDE FOR LOADING IN MISSILE LAUNCHIN G vSYSTEMS Robert E. Carlberg, Falls Church, Va., assignor to the United States of America as represented by the Secretary of the Navy The invention described herein may be manufactured and used by or for the Government of the United States respectively.

of America for governmental purposes without the paymerit of any royalties thereon or therefor. j The invention relates to improvements in load handling equipment and more particularly to improved muzzle loading equipment formissile launchers handling elongate missiles of the type supported by fore and aft suspension lugs.

V The muzzle loading of long,-'heavy missiles provided with rigidly fixed fore and aft suspension lugs onto stationary grooved supporting rails'or guides of a missile launcher requires the exercise of a considerable amount of care not only in the preliminary alignment of the fore and aft suspension lugs forwardly of the front and rear launcher rails or guides preparatory to attachment of the missile to the launcher, but also in bodily moving 7 the missile backwardly underneath the launcher rails and maintaining parallelism of the missile and launcher arm while the missile is being supported on a cart or the like. An important object of the present invention is to pro- Pendently connected by fore and aft sets of

linkage

18, 19 to the fore-anddaft crossheads is a missile loading rail or bar 20 provided on its underside with forward and aft male and

female guides

21, 22 respectively.

The floating rail or bar 20 is supported during missile loading so as to havef-reedom of motion in all directions, angularly and linearly except forward and aft and in the down direction. To this end, the fore and aft sets of linkage are provided ,at their upper end portions with

universal joints

23, 24 and at their lower end portions with hinge joints 25, 26 and a ball joint 27 connected to the top side of the rail and having aligning

hinge pins

28, 29 and socket 30 disposed above and longitudinally of the rail. Instead of using the rigid rod 31 shown in the drawings for linking the universal joint 24 and ball joint 27' of the aft set of linkage, the use of a flexible cable (not shown) is optional. Hingedly connected to the aligned

forward hinge pins

28, 29 at a lower edge 32 is a plate 33 having a cylindrical swivel housing 34 rigidly aflixed to its forward end and normal to'the lower edge 32. The lower end of the universal joint 23 includes a shaft 35 swiveling in the housing 34. The missile 36 is anelongate rocket provided with a pair of upwardly projecting relatively long rigidly attached

forward suspension lugs

37, 38 having inturned vide equipment facilitating the loading of a heavy missile v i of the type provided with fore and aft suspension lugs onto the guide rails of the launcher. I

Another important object of the invention is the provision of means facilitating the loading of a heavy missile supported on a moving cart or the like into a muzzle loading launcher.

. A. further object is to provide improved missile supporting fixtures for a launcher handling elongate missiles of the type provided with fore and aft suspension lugs.

' A still further object is the provision ofimproved mis- 4 sile supporting and lifting equipment for a launcher of the above-described character.

The invention also aims to provide improved floating missile suspension equipment for a launcher of the characterdescribed.

Additionally, the invention aims to provide a missile launcher having the above-described floating missile suspension equipment with means firmly securing the missile suspension equipment against floating action during launching of the missile.

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 is a side view of the missile loading equipment 2 showing a missile in loaded position; and v Fig. 2 is a perspective view of the equipment with parts thereof shown in lowered position ready for suspension of a missile thereon. 1

In the drawings, which for the purpose of illustration show only a preferred embodiment of the invention, and wherein similar reference characters denote corresponding parts throughout the several'views, 10 designates the launcher arm or carrier member. of a

missile fingers

39, 40, and a single upwardly projecting relatively short rigidly attached aft suspension lug 41 having outturned

fingers

42, 43. On the underside of the floating rail or bar 20 at its forward end is a tapered male guide 44 'provided with

side grooves

45, 46 slidably receiving the inturned

fingers

39, 40 of the missile forward suspension lugs. Also on the underside of the floating rail or bar but at its after end is a female guide 47 provided with a rearwardly convergent throat 48 leading to a T-shaped groove 49 slidably receiving the aft missile suspension lug 41. i Projecting upwardly from the forward and aftend portions of the 'floating bar are triangular, preferably

integral wedge members

50, 51, arranged to firmly engage against

re-entrant surfaces

52,53 and 54, 55 of seats formed in the launcher arm. When the missile is to be muzzle loaded onto the launcher, the rail is lowered to a free swinging position so that the forward and

aft guides

44, 47 may be readily positioned to receive the suspension lugs of the missile being loaded from a cart, and will be automatically selfaligning with the suspension lugs of the rigidly supported missile on the cart as the cart is drawn rearward-1y under the launcher rail. v By the system of

hydraulic cylinders

12, 13 and sets of

linkage

18, 19, the rail and missile are then raised to bring the

wedge members

50, 51 into firm engagement with the respective seating surfaces 5255 whereby all motion of the floating rail 20 is prevented during firing.

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 maybe practiced otherwise than as specifically deseri bed. 7

' What: is claimed is: Y Y

1. A launcher for an elongate missile having fore and aft suspension lugs, said launcher comprising a carrier member disposable in a sub'stantially horizontal position above the 'missile for loading, a bar below the car;

rier member having fore and aft portions equipped with subjacent fixtures for connection with the respective fore and aft suspension lugs of the missile, fore and aft lift members carried by said carrier member, fore and aft sets of linkage respectively connecting the fore and aft portions of said bar to said fore and aft lift members, said sets of linkage including joints permitting lateral and angular movement of said bar relative to said carrier member whereby alignment of the fixtures subjacent the bar with the fore and aft suspension lugs of a missile disposed for instance in skew relation below said carrier member during loading is facilitated.

2. A launcher for an elongate missile having fore and aft suspension lugs, said launcher comprising a carrier member disposable in a substantially horizontal position above the missile for loading, a bar below the carrier member having fore and aft portions equipped with subjacent fixtures for connection with the respective fore and aft suspension lugs of the missile, fore and aft lift members carried by said carrier member, fore and aft sets of linkage respectively connecting the fore and aft portions of said bar to said fore and aft lift members, said sets of linkage each including a universal joint whereby independent operation of said fore and aft lift members is permitted and a swivel joint whereby said bar may be disposed in skew relation to said carrier member.

3. A launcher for an elongate missile having fore and aft suspension lugs, said launcher comprising a carrier member disposable in a substantially horizontal position above the missile for loading, a bar below the carrier member having fore and aft portions equipped with subjacent fixtures for connection with the respective fore and aft suspension lugs of the missile, fore and aft lift members carried by said carrier member, fore and aft sets of linkage respectively connecting the fore and aft portions of said bar to said fore and aft lift members, said sets of linkage including joints permitting lateral and angular movement of said bar relative to said carrier member whereby alignment of the fixtures subjacent the bar with the fore and aft suspension lugs of a missile disposed below said carrier member during loading is facilitated, and means interengaging said carrier member and bar upon lifting of said bar to firmly secure said bar against movement relative to said carrier member during firing of the missile.

4. A muzzle loading launcher for an elongate missile having fore and aft suspension lugs, said launcher comprising a carrier member disposable in a substantially horizontal position above the missile for loading, a bar below the carrier member having fore and aft portions equipped with subjacent longitudinal guides having forward ends for slidably receiving the fore and aft suspension lugs of the missile, fore and aft lift members reciprocably slidably guided in said carrier member, fore and aft sets of linkage respectively connecting the fore and aft end portions of said bar to said fore and aft lift members, said sets of linkage each including joints permitting lateral and angular movement of said bar relative to said carrier member whereby alignment of the fixtures subjacent the bar with the fore and aft suspension lugs of a missile disposed in skew relation below said carrier member during loading is facilitated.

5. A muzzle loading launcher for an elongate missile having fore and aft suspension lugs, said launcher comprising a carrier member disposable in a substantially horizontal position above the missile for loading, a bar below the carrier member having fore and aft portions equipped with subjacent longitudinal guides having forward ends for slidably receiving the fore and aft suspension lugs of the missile, fore and aft lift members reciprocably slidably guided in said carrier member, fore and aft sets of linkages respectively connecting the fore and aft end portions of said bar to said fore and aft members, Said, Sets of linkage each including joints permitting lateral and angular movement of said bar relative to said carrier member whereby alignment of the fixtures subjacent the bar with the fore and aft suspension lugs of a missile disposed in skew relation with said carrier member during loading is facilitated, andmeans interengaging said carrier member and bar upon lifting of said bar to firmly secure said bar against movement relative to said carrier member during firing of the missile. i i

6. A muzzle loading launcher for an elongate missile having fore and aft suspension lugs, said launcher comprising a carrier member disposable in a substantially horizontal position above the missile for loading, a bar below the carrier member and having fore and aft portions equipped with subjacent longitudinal guides for receiving the fore and aft suspension lugs, respectively, of the missile, fore and aft lift members reciprocably slidably guided in said carrier member, fore and aft sets of linkage respectively connecting the fore and aft end portions of said bar to said fore and aft lift members, said sets of linkage each including a universal joint and a sWiVel'jOint arranged to preclude forward, aft and downward movement of said bar relative to said carrier member while permitting lateral and angular relative movement thereof to facilitate alignment of' the fore and aft suspension lugs of a missile below the bar with said longitudinal guides during loading, said carrier member and bar being provided with mating surfaces interengageable upon lifting of said bar thereby to secure said bar against movement relative to said carrier member during firing of the missile.

7. A self-aligning guide for loading a rocket missile having a pair of mutually spaced lugs on the front end and a substantially T-shaped lug on the rear end thereof onto a carrier, said guide comprising a rail, hydraulic cylinders depending from the carrier, having piston rods fromwhich the rail is suspended, a tapered male guide on front of the rail and terminating in a pair of mutually spaced grooves for receiving the lugs on the front end of the missile, a tapered female guide on the rear of the rail and terminating in a substantially T-shaped groove for receiving the T-shaped lug on the rear end of the missile, linkages connecting the rail to the piston rods, said linkages being movable by said piston for moving said rail and articulated where joined to the rail and to the piston rods to permit freedom of motion of the rail with respect to the oncoming missile, a pair of mutually spaced wedge shaped recesses formed in said carrier, and a pair of complementary wedge shaped locking members integrally formed with said rail for locking the rail to the carrier as said wedgeshaped members are moved into engagement with said recesses by said movement of the rail by the linkages.

8. A self-aligning guide for loading a rocket missile having a pair of mutually spaced lugs on the front end and a substantially T-shaped lug on the rear end thereof onto a carrier having a plurality of wedge shaped recesses formed therein, said guide comprising a rail, hydraulic cylinders depending from the carrier, having piston rods from which the rail is suspended, a tapered male guide on front of the rail and terminating in a pair of mutually spaced grooves for receiving the lugs on the front end of the missile, a tapered female guide on rear of the rail and terminating in a substantially T-shaped groove for receiving the T-shaped lug on the rear end of the missile, linkages connecting the rail to the piston rods, said linkages being articulated where joined to the rail and to the piston rods to permit freedom of motion of the rail with respect to the oncoming missile, and a plurality of complementary wedge shaped members formed on said rail interengaging said recesses in the carrier upon lifting of said rail for locking said rail to said carrier against movement relative to said carrier during firing of the missile.

(References on following page) Referencs Cited in the file of this patent UNITED STATES PATENTS Maxim Nov. 11, 1913 Anderson et a1. Ian. 21, 1947 Wardwell Dec. 19, 1950 Meadowcroft 1 Aug. 3, 1954 France Feb. 6, 1952