Search Images Maps Play YouTube News Gmail Drive More »
Sign in
Screen reader users: click this link for accessible mode. Accessible mode has the same essential features but works better with your reader.

Patents

  1. Advanced Patent Search
Publication numberUS2981152 A
Publication typeGrant
Publication dateApr 25, 1961
Filing dateMar 5, 1959
Priority dateMar 5, 1959
Publication numberUS 2981152 A, US 2981152A, US-A-2981152, US2981152 A, US2981152A
InventorsDietz Victor J, Miller Jr Arthur H, Shipley Donald M
Original AssigneeDietz Victor J, Miller Jr Arthur H, Shipley Donald M
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Missile handling and launching device
US 2981152 A
Images(3)
Previous page
Next page
Description  (OCR text may contain errors)

April 1961 A. H. MILLER, JR., EI'AL 2,981,152

MISSILE HANDLING AND LAUNCHING DEVICE Filed March 5, 1959 5 Sheets-Sheet l FlG.l.

INVENTORS. A. H. MILLERJR. D. M. SHiPLEY V. J. DIETZ ATTORNEY-S A ril 25, 1961 A. H. MILLER, JR.. ETAL 2,981,152

MISSILE HANDLING AND LAUNCHING DEVICE Filed March 5, 1959 3 Sheets-Sheet 2 INVENTORS. A. H. MILLER JR. D. M. SHIPLEY V. J. DIETZ BY CQ/aW ATTORNEYJ A ril 25, 1961 A. H. MILLER, JR., ETAL 2,981,152

MISSILE HANDLING AND LAUNCHING DEVICE 3 Sheets-Sheet 3 Filed March 5, 1959 @W wfmrggggg ground launchingv capsule.

2,981,152 MISSEE HANDLING AND LAUNCHING DEVICE Arthur H. Miller, Jr., and Victor J. Dietz, Silver Spring, and Donald M. Shipley, Hyattsville, Md., assignors to the United States of America as represented by the Secretary of the Navy FiledMar. 5, 1959, Ser. No. 797,552 Claims. (Cl. 891.7)

The present invention relates to a missile handling and launching system, and more particularly to such a system in which novel handling equipment is integrated with a novel arrangement of multiple launchers.

The inherent advantages of multiple launcher systems over single firing units are well known and include increased fire power, reliability, reservation until the last possible instant for choice of type missile, high degree of automaticity, etc. The present invention utilizes all these advantages in providing a missile handling and launching system including a plurality of underground launchers and; offers, additionally, thefeature of safe ready stowage. whichienables the missiles to be safely stored underground in a maximum degree of readiness since warmup power can be supplied directly to themissiles in their respective. launchers. The underground aspect of this system also allows eachv launcher to act as its own dud disposal area. In the unlikely. chance of adud, no action by anyone is necessary to dispose of it and another missile may be launched immediately. Y

It will therefore be recognized as the object and purpose of the present invention to provide a missile handling and launching system of underground launchers which, by novel integral handling means, will permit, with aminimum personnel requirement, a high degreeof fire power, last minute selectivity of type missile to befire d,

safestorage in a maximum state of readiness, and minimum effort for the disarming and removalfof duds.

Qther objects and many of the attendant advantages of this invention will be readily appreciated as the same becomes understood by reference to the following detailed description when considered in connection with the accompanying drawings. i

"Briefly, the present invention contemplates a handling and launching system in which an aerial missile is carried, on a unique dolly through various final'assembly stages in a ready area. When the missile has been com pletely assembled, the dolly and missile are drawn onto a novel vehicle fortransfer to a vertically disposed under- Means are provided on the vehicle for tilting the dolly and missile into a vertical; attitude and for lowering the dolly and missile into the launching capsule. In the launching capsule, means are provided for automatically disengaging the missile from the dolly in order that the dolly may be retrieved.

In the drawings:

F ice sile and a portion of the transfer vehicle in raised position in preparation for-the lowering operation.

Fig. 6 is an end elevation of the releasable clamping means on the dolly;

Fig. 7 is a section taken on line 77 of Fig. 6.

Referring now to the drawings in greater detail, Fig. 1 shows the general layout of the missile handling and launching system constituting the present invention in which missiles 10 are assembled in a ready area 12. The ready area 12 is generally surrounded by appropriate walls and a roof conforming to certain provisions of established military safety standards. In Fig. 2, it can be seen that each of the missiles 10 are carried horizontally through the final assembly phases on a dolly 14 that rides on tracks 16. The tracks 16 are secured to the floor of the ready area 12 and are formed from I-beams. As best seen in Fig. 3, the wheels of the dolly ride between the upper and lower flanges of the track so that the dolly is constrained to move longitudinally of the tracks 16.

The missile 10 is held in coupled relationship with the dolly 14 by a pair of shoes 18 on the missile which engages a rail 20 on the dolly. The pair of shoes 18 is conventionally provided on the periphery of the missile to facilitate handling and launching and comprises a fore and an aft shoe. A similar pair of shoes 19 is positioned diametrically opposite the pair 18 and likewise is provided for handling and launching purposes. Each shoe of the pairs 18 and 19 is provided with outwardly depending fianges 22, those of the pair 18 engaging longi: tudinal, slots 24 in the rail 20 to constrain the missile 10 to longitudinal movement with respect to the dolly 14. For the purpose of controlling this longitudinal movement, a simple releasable clamp 25, shown in Figs. 6 and 7, is provided on the rear of the rail 20 which engages one of the rear, shoeslS on the missile 10 and comprises an arm 26 pivotally mounted in a bracket 27 and a trippinglever 28 When the missile 10 is completely. assembled, it and the dolly Mare moved to a loading platform in the ready area 12 in preparation for removal therefrom by a transfer vehicle 30. Referring, once again to Fig. 2, it is seen that the vehicle 30 is a modified standard truck chassis and carries tracks 32 which mate with the tracks 16. of the ready area 12, For the purpose of drawing the dolly 14 and missile 10 directly onto the vehicle, a power winch 34 is provided on the vehicle. The tracks 32 are Fig. 1 is a perspective. showing; the general arrangemounted on a bed 36 which is pivotable in a vertical plane about a shaft 38 journalled in frame. 40 of the vehicle 30, so that the missile 10v and dolly 14 can be elevated into a vertical attitude by a hydraulic lift 42. As can be seen in the drawings, the hydraulic lift 42 is simi lar to th e. type used in dump trailers and is mounted on the frame 40. of the vehicle 30, one end of the lift engaging a bracket 44. on the pivotable bed 3 6.

After the missile 10 and dolly 14 are drawn onto the transfer vehicle 30, they are transported to a launching area 50 comprising a plurality of vertically disposed underground launching capsules 52 As seen in. Fig. l, the launching capsules 52 are arranged preferably in a plurality of rows, each row being centered between tracks 54, which, as will be seen, aid in positioning the transfer vehicle 30 over the capsules,

' As shown in Fig. 4, the vehicle 30 is provided with a second set of wheels 56 which are mounted on axle extensions 58 outboard of the vehicles regular wheels. The wheels 56 may be standard railroad wheels or other wise flanged so that they will engage the tracks 54 to guide the vehicles 30 in position over the launching capsules 52.

, Referring to Fig. 5, it can be seen that the launching capsules 52 are located underground in a vertical position, each being provided with a hinged counter-balanced P tented Apr. 25 1961 cover 66. The walls of the capsule 52 may be fabri cated of steel plate or, as shown in the drawings, formed of concrete. For the purpose of inducing the most efficient flow of exhaust gases from the capsule 52 at launch, the bottom of the capsule is provided with across section substantially in the form of a double concave 'surface. i t

In order that the missile and dolly 14 may be guided into the capsule 52, handling tracks 68 are secured longitudinally to the inner wall of the capsule and are of the same cross section as the tracks 32 onthc vehicle 30. The upper end 70 of the tracks 68 are cut at an angle complementary to the end of the tracks 32 so that when the latter is pivoted into the vertical attitude the ends of the two tracks will mate thereby allowing the missile 10 and dolly 14 to be lowered into the proper position in the capsule 52. a a a Located diametrically opposite the tracks 68 in the capsule 52 is a launching rail 72 that is rigidly secured to the inner wall of the capsule 52. The launching rail 72 is provided with slots 74 which engage the flanges 22 of the missile shoes of the pair 19 in the same manner as the slots 24 of the rail on the dolly 14 engage the shoes of the pair 18. Thus in addition to being supported by the dolly 14, the missile 10 is also sup portedin the capsule 52 by the launching rail 72.

.The lowering of the missile lfl into the launching capsule 52 is accomplished by first bringing the loaded vehicle 30 into position at-the capsule, this being considerably simplified by the fact that the tracks 54 in the launching area 12 guide the vehicle along one centerline of the capsule. Next, the pivotable tracks 32 on the vehicle 30 and bearing the missile 10 and dolly 14 are elevated into a vertical attitude by the hydraulic lift 42. Final positioning is done by moving the vehicle 30 along the tracks 54 to bring the pivotable tracks 32 into aligned mating position with the handling tracks 68 in the launching capsule 52. The dolly 14 carrying the missile 10 and which is now suspended on the vertically inclined pivotable tracks 32 by the winch Men the vehicle 30, is lowered into the launching capsule 52 by the same winch. By virtue of the alignment of the two tracks 32 and 68, the loaded dolly 14 is transferred smoothly from the vehicle 30 to the capsule 52. i

It is seen that as the missile 10 enters the capsule 52, the shoes 19 on the missile engage the launching rail 72 in the capsule to afiord concurrent support of the missile. This then permits the dolly 14 to be relieved of its burden once it has served its purpose of lowering the missile 10 into position in the capsule 52. To effectuate this, a member 76is provided in the capsule 52 and is so located that just as the missile 10 is arriving at its final position in the capsule, the member will engage the tripping lever 28 of the releasable clamp of the dolly 14 to uncouple the missile 10 from the dolly. Once having been thus freed from the missile 10, the dolly 14 may be withdrawn from the capsule 52 by the same means that was used for lowering it into the capsule, namely, the winch 34. The dolly .14 and the vehicle 32 are then available forhandling and loading another missile into another launching capsule.

Provision is also made in each of the launching capassumeprime role as a launcher, the capsule 52 also functions the scope of the appended claims, the invention may be practiced; otherwise than as specifically described.

What is claimed is: V

.1.1. Inan underground missile launching system including a missi e having a plurality of pairs of flanged launching shoes thereon, a tube vertically disposed in the ground for launching said missile, said tube having a launching rail therein and crigageable with one pair of said launching shoes, said launching system also including a vehicle for transporting and loading said missile into said tube;

I the combinationtherewith of an improvement, comprisclamping means on said dolly forcontrolling longitudinal movement of said missile relative to said dolly, wheels.

on said dolly, handling tracks onsaid vehicle and engageable with said dolly wheels .to maintain said vehicle and dolly in lateral locked relationship, said tracks being pivotable into a vertical attitude, restraining means on sules 52 for additional conventional associated equipment such as warm-up power and launching power said vehicle and engageable with said dolly to control longitudinal movement of said dolly relative to. said handling tracks, second handling tracks in said tube and engageable withsaid first handling tracks in aligned relationship, said second handling tracks also being engage,- able with said dolly wheels in the same manner as said first handlingltracks, and means in said tube and engageable with said releasable clamping means to release said dolly for longitudinal movement relative to said missile. 2. The combinationas recited in claim 1 wherein said dolly support rail includes a longitudinal slot to receive the flanges of said missile launching shoes to maintain said missile and dolly in laterallocked relationship.

3. The combination as recited in claim 1 wherein each of said first and second handling tracks include upper and lower flanges to form a channel therebetween to receive said dolly wheels whereby said dolly is maintained in lateral locked relationship with said handling tracks.

4. The combination as recited in claim 1 wherein said restraining means includes a crble winch on said vehicle, the free end of the cable winch being engageable with said dolly. 5. The combination as recited in claim 1 wherein said last-mentioned means includes a member fixedly mounted in said tube and engageable with said releasable clamping means on said dolly.

References Cited in the file of this patent UNITED STATES PATENTS 2,735,391

Buschers Feb. 27, 1956 2,763,447 Carrau Sept. 18, 1956 2,814,453 Trimble et al. Nov. 26, 1957 2,882,795 Bergner et a]. Apr. 21, 1959 OTHER REFERENCES Missiles and Rockets, October 27, 1958, pages (Front Cover). (Copy in Div. 10.)

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US2735391 *Jul 25, 1952Feb 21, 1956 H buschers
US2763447 *Aug 10, 1954Sep 18, 1956Carrau Mario JHigh altitude observation means
US2814453 *Mar 14, 1952Nov 26, 1957Glenn L Martin CoAir base
US2882795 *Mar 15, 1956Apr 21, 1959Alco Products IncErecting and launching apparatus
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US3088612 *May 26, 1961May 7, 1963Aluise Robert RMethod of handling stores
US3132562 *May 16, 1961May 12, 1964Dow Chemical CoLaunching system for rocket driven devices
US3155248 *Dec 31, 1962Nov 3, 1964Seatrain Lines IncVehicle-container
US3284888 *May 9, 1963Nov 15, 1966Charles B AllenMethod and apparatus for assembling and erecting a rocket or missile
US3338433 *Sep 28, 1964Aug 29, 1967Martin Marietta CorpAdjustable support arrangement
US3822800 *Nov 4, 1971Jul 9, 1974Leszczynski SApparatus for transporting transformers and the like
US4363257 *May 28, 1980Dec 14, 1982Fmc CorporationStrikedown service mechanism for a vertical launching system
US5924648 *Oct 3, 1997Jul 20, 1999Lockheed Martin CorporationSystem for upending/reclining launch vehicles
US6610971 *May 7, 2002Aug 26, 2003The United States Of America As Represented By The Secretary Of The NavyShip self-defense missile weapon system
DE1259738B *May 18, 1963Jan 25, 1968Boelkow GmbhVorrichtung zum Starten von Raketen von einem auf einem Drehgestell hoehenrichtbar gelagerten Schlitten
EP0042978A2 *May 27, 1981Jan 6, 1982Fmc CorporationStrikedown service mechanism for a vertical missile launching system
Classifications
U.S. Classification89/1.805, 414/728, 414/286, 414/350, 29/429
International ClassificationF41A9/00, F41A9/87, F41F3/04, F41F3/073, F41F3/00
Cooperative ClassificationF41F3/073, F41A9/87, F41F3/04
European ClassificationF41F3/073, F41A9/87, F41F3/04