US3160061A - Tsoy k - Google Patents

Description

Dec. 8, 1964 TsoY K. MOY

R12-ENTRY BODY SUPPORT Filed Nov. 13, 1962 ...nlr-

TSOY K. MOY

Cuwu www BY M7( ATTORNEY n-h/{ENT IUnited States Patent O p Sdillei RE-ENTRY BGBY SUPPRT V'I'soy K. lVtoy, Santa Ciara, Calit., assigner, by mesu@ assignments, to the United States of America as represented by the Secretary of the Navy Filed Nov. 13, 1962, Ser. No. 237,411 1 Claim. (Cl. 89-1.7)

` ing `the time in which a missile is maintained or stored in the launching tube, it often becomes desirable to move the assemblage. This is particularly true when the launching tube is located on board a transportable launcher, such .as a seagoing vessel, and more particularly a submarine. In such an environment the launching tube structure may be iixedwith respect to the structure of the submarine o-r vessel. During such transportation of a launcher with a missile therein, the missile is often subjected to shocks and vibrations within the tube, and Vit is therefore desirable `to provide means to support and shield theV missile, especially the re-entry portion thereof. In the past, various mechanically retractable devices have been proposed, such as tensioned cables that support the missile and retain it in desired position in the tube. However, these mechanically retractable devices present certain disadvantages and shortcomings and are possessed y of undesirable features which result from the fact that they must be quickly and reliably released and completely withdrawn, Failure to do so will result in damage to the missile and possible invalidation of the launch.

Additionally, excessive shock on the re-entry body, which is generally positioned on the nose or forward end of the missile, has been encountered due tothe impact of Water upon the missile andthe high Vpressure gas 'trappedv between the inilowing vwater and the outwardly expelled missile during underwater launches. It is, thereiordan object ofthe present invention to provide newand improved instrumentalities for isolating a missile against externally induced vibration and forcesv to which it would otherwisebe subjected and supporting it in a manner whereby it will be immune to externally applied shock eiects andwhich instrumentalities do not require theV incorporation of facilities for release and Withdrawal with Vrespect theretoprior to launching of the missile.

It is a1 hirther` object lot the Vpresent invention to provide a support for a missile which Will not Vfoul the launch-A ing tube during launching as Well as afterthe missile has I Y been ejected.

v A' further obiect is theprovision of an improved vibration ,isolating and mass supporting system which is possessed of substantially all ofthe desired vkessential Vop- Verational''featuresfot Vdevicestor similar? purposes here'- tofore or Howlin-general us'eand which lobviatessubf stantially all of the" undesirablel features, or shortcomings I Ytin-rect and `which ,possesses alljbf the qualities of vcorn-v pactness, ruggedness, adaptabilityfand durability.

It is a furtherobject ofthepresent .invention to pro- ,vide a lateral supporting andf pos' ning;V structure for K y A, therein.

ibddl Patented Dec. 8, i964 lCe the missile which will effect a reduction in the peak pressure exerted on the cone section of a missile during the initial portion of a launch, especially When such launch is made underwater.

A further object of this invention resides in the provision of a vibration isolationsystem in which the ele- 'Y ments to be protected from ambient induced vibrations are so supported within a containing structure having a common or intimately disposed base with respect to the device to be protected whereby undesirable vibrations are Other objects and many of the attendant advantages of;

this invention will be readily appreciated as the same becornesV better understood by reference to the following detailed description when considered in connection with the accompanying drawings in which like reference numerals designate like parts throughout the iigures thereof and wherein:

FIG. 1 is a perspective View of a portion of a missile launching tube assembly with portions broken away showingr a missile and one modifica-tion of the supporting structure of the instant invention;

FIG. 2 is a transverse sectional View of a portion of the missile launching tube assembly taken substantially along the line 2 2 of FIG. 1 showing the missile nose and the supporting structure of the instant invention;

FIG. 3 is an enlarged exploded perspective view of the components of a portion of the missile supporting structure of the instant invention;

FIG. 4 is a transversesectional View of a portion of the launching tube assembly missile and supporting structure showing a missile access opening taken substantially along the line #i d of FIG. l, and

FIG. 5 is a transverse sectional View ot a portion of the launching tube assembly, missile and supporting structure showing otherrnissile access openings taken substantially along the line 5 5. Y l

Referring now to the drawings, a launching tube assembly i@ embodying the invention, as shown in FIG. l,

comprises an outer tube i2 secured partially or Wholly v i nular shoulder located on or near the upper, surface or the submarine. f

An inner or launching tube 16 is suspended within the outer tube by means ofv dex rods or thelike as disclosed in application Serial No. 138,534- Vibration and Noise' Control in Liquid Springs, tiled VSeptember 13, 1961, by Wilson T. Price et The space between the outer and launching tubes is sealedto prevent the entry of water This lseal' is accomplished by means of yan an? rnular sealing member ldisposedbetween the tubes at upper ends. v

A diaphrag'm 2i? is releasiably secured at thefupper end (5f-'the launching tube to 'form an enclosure for prevent ingthe entry vo t waterinto' helaunching tube, `The dia-"- phragm is secured to the tube by means of an annular flange 22 containing a suitable explosive charge, e.g. Primacord," which, upon detonation effects the release of the diaphragm.

A missile 24 is carried within the launching tube and is releasably secured within the tube by suitable clamping means normally associated with the missile skirt (not shown). The clamping structure is suspended near the lower end of the launching tube by structural arrangement which provide a limited degree of freedom of movement of the missile in order that bending stresses, vibration and shock imposed on the missile may be minimized. Additionally, resilient launch/stowage adapters (not shown) are located between the missile and launching tube at intervals along the missile body to absorb vibration and shock resulting from handling of the assembly and ship movements.

A nose cone or re-entry body 26, 2S is located on the forward end of the missile. Due to the particular components contained therein, the re-entry body is especially susceptible to damaging pressures and shocks. As pointed out hereinabove, these induced shocks on the missile may originate during handling and stowage of the missile and associated launching tube container 16, or may be caused by various maneuvers of the submarine within which the launching tube assemblies reside. A further pressure shock is imposed upon the nose cone at the moment of missile expulsion from the launching tube after the diaphragm Ztl has been released ,from the end of the launching tube. A large pressure peak is imposed along the tapered portion 26 of the cone due to the combined motion of the outwardly moving ejected missile and the inwardly directed mass of inundating water. The air or pressurizing glas within the cavity, generally `defined by tube 16, diaphragm and missile 24, is compressed between the converging missile and water mass thus generating or producing a high pressure intensity region or concentration in the area of the missile surface defined by the tapered surface 26 ofthe nose cone.

The present invention accomplishes an absorption of the concentrated energy and effects a dispersal thereof to accomplish a reduction in the pressure peak to which the nose cone is subjected to a magnitude within acceptable limits. Additionally it provides support for the nose cone during transportation and minimizes the possibility of damage thereto by absorbing shock and damping vibrations reflected inwardly by the launching tube. l

The invention comprises a rigid plastic foam spider 30, FIGS. 1-3, in the form of foam blocks 32 which extend from the launching tube radially inwardly into contact with the upper nose cone portion 2S. The spider may be constructed of any suitable rigid plastic foam material, eg., polyurethane. The sides of the blocks are provided with ta ered recesses 34 which receive adjustment wedges 36 which permits, to a limited degree, the variation of the relationship between the arcuate surface 37 of the block adjacent the tube and the arcuate surface 38 in abutment with the nose cone. Adjustability vis desirable since the tube 16 is an unmachined, generally cylindrical shaped member having inner. surfaces which may not be of exact circular configuration. Also, the missile nose 23 may not be in a perfect concentrioal relationship with the tube. Therefore, to assure full contact of the block surfaces with both the tube and cone under the above conditions, the appropriate wedge may be forced further into its mating recess while, simultaneously, the opposite wedge is withdrawn a like distance from the correspond ing recess thus bending the block along the narrow web portion 39 as required to assure full mating contact with the cone and tube surfaces.

Supporting the foam blocks at the desired position ad- CII jacent the forward end of nose cone portion 28 is a hol-""" low cylindrical member or barrel 4t) extending from the forward circumferential row of launoh/stowage adapters (not shown) to the foam blocks. The barrel member may abut the blocks along the rearwardly facing surface il adjacent the tube wall or, preferably, lthe blocks and barrel member may have a tapered joint 42 as shown in FIG. l. To insure rigidity, the blocks are secured to the barrel member by adhesive cement or other suitable fastening means. The barrel member may be composed of a number of arcuate sections, e.g. sections 40a, 4Gb, 49e, and 40d as shown in FIGS. l 'and 2, for ease in handling and shipping. The sections may be attached to form the cylindrical member at the time of installation in the launching tube by any suitable means. The barrel member is provided with appropriate holes 44S, 45, 46 and 47 or openings to permit access to the missile for electrical, umbilical and hose connections, monitoring, and the like.

ln operation, the upwardly moving ejected missile pushes the entire ifoam assembly 30 out of the launching tube. Upon expulsion of the missile from the tube, hydrodynamic forces acting on the foam assembly cause the foam members to separate from the missile. Due to the buoyant characteristics of the foam members, the pieces, after separation, will rise to the surface of the body of water and thus obviate fouling of the tube hatches.

The spokedike configuration of the spider blocks 32 emanating radially outwardly from the missile, serves t0 impede and disrupt the mass of water inundating the tube after the diaphragm is released. Thus, the initial pressure peak, normally concentrated along the nose cone portion 26 due to the convergence the missile and Water upon ejection of the missile from the launching tube, is reduced to within acceptable limits as a result of the discontinuity of the water mass developed as the water impinges upon the spider.

Therefore, it will be readily apparent that the provision of the foam spider in a launching tube assembly accomplishes the objectives of providing nose cone support against shock and vibration for a missile within a launch tube in a simple and effective manner which eliminates fouling of the launch tube and favorably reduces the initial pressures imposed on the nose cone as it is ejected into the water. While the invention has herein been disclosed by reference to the details of a specific embodiment, it is understood that the foregoing disclosure is intended to be construed in an illustrative rather than limited sense, as it is contemplated that various modifications of the construction and arrangement of the parts will readily occur to those skilled in the art, within the spirit of the invention and the scope of the appended claim.

What is claimed is:

in a missile launching tube assembly having a missile contained therein rfor launching therefrom substantially rigid missile positioning yand shock isolating and absorbing members between the missile nose and the launching tube to position said missile and shield nose cone from excessive shock and vibration, said members being constructed of a crushable material of the character displaying high resistance to applied loads up to the point of permanent deformation thereof;

said members being formed with outer and inner arcuate surfaces, said outer yarcuate surface being adjacent to and corresponding in configuration to said tube, said inner arcuate surface being adjacent to and corresponding in configuration to said nose cone, said members being formed with opposed central recesses separated by la narrow web; and

wedges insertable into said recesses, whereby in the event of misalignment said members may `be bent 'atsaid web by the insertion of said wedges into the recesses therebyA causing said inner and outer arcuate surfaces to change theirnrelative curvature and to fully mate with said nose cone and said tube,

respectively.

(References on following page) References Cited by the Examiner UNITED STATES PATENTS Hatch 217-79 Dougan 102-93 5 Shrefer.

Turechek 102-93 Alexander 102-93 Copeland 267-61 Barr 1027-93 X 10 Siegel et al. 89-1.7 Weller. Wood et a1. 89-1.7 Guyant et a1 89-1.7 Webster et al. 89-1.7

BENJAMIN A. BORCHELT, Primary Examiner.

SAMUEL W. ENGLE, Examiner.

Claims (1)

1. IN A MISSILE LAUNCHING TUBE ASSEMBLY HAVING A MISSILE CONTAINED THEREIN FOR LAUNCHING THEREFROM SUBSTANTIALLY RIGID MISSILE POSITIONING AND SHOCK ISOLATING AND ABSORBING MEMBERS BETWEEN THE MISSILE NOSE AND THE LAUNCHING TUBE TO POSITION SAID MISSILE AND SHIELD NOSE CONE FROM EXCESSIVE SHOCK AND VIBRATION, SAID MEMBERS BEING CONSTRUCTED OF A CRUSHABLE MATERIAL OF THE CHARACTER DISPLAYING HIGH RESISTANCE TO APPLIED LOADS UP TO THE POINT OF PERMANENT DEFORMATION THEREOF; SAID MEMBERS BEING FORMED WITH OUTER AND INNER ARCUATE SURFACES, SAID OUTER ARCUATE SURFACE BEING ADJACENT TO AND CORRESPONDING IN CONFIGURATION TO SAID TUBE, SAID INNER ARCUATE SURFACE BEING ADJACENT TO AND CORRESPONDING IN CONFIGURATION TO SAID NOSE CONE, SAID MEMBERS BEING FORMED WITH OPPOSED CENTRAL RECESSES SEPARATED BY A NARROW WEB; AND WEDGES INSERTABLE INTO SAID RECESSES, WHEREBY IN THE EVENT OF MISALIGNMENT SAID MEMBERS MAY BE BENT

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