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Publication numberUS3180222 A
Publication typeGrant
Publication dateApr 27, 1965
Filing dateSep 24, 1962
Priority dateSep 24, 1962
Publication numberUS 3180222 A, US 3180222A, US-A-3180222, US3180222 A, US3180222A
InventorsMoy Tsoy K
Original AssigneeMoy Tsoy K
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Simplified system to control postlaunch flooding
US 3180222 A
Abstract  available in
Images(3)
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Claims  available in
Description  (OCR text may contain errors)

April 27, 1965 Ts MOY 3,180,222

SIMPLIFIED SYSTEM TO CONTROL POST-LAUNCH FLOODING Filed Sept. 24, 1962 3 Sheets-Sheet l T50) K. M0) M WW I ATT RNEY 4 AG NT TSOY K. MQY

April 27, 1965 SIMPLIFIED SYSTEM TO CONTROL POST-LAUNCH FLOODING Filed Sept. 24, 1962 3 Sheets-Sheet 2 I WF\\\\\\ II 6 I a April 27, 1965 TSOY K. MOY 3,130,222

SIMPLIFIED SYSTEM To CONTROL POST-LAUNCH FLOODING Filed Sept. 24, 1962 3 Sheets-Sheet 3 United States Patent Ofifice alsazzz Patented Apr. 27, 1965 3,180,222 SMLIFIED SYSTEM TD CONTROL POST- LAUNCH 'FLOODING Tsoy K. Moy, Santa Clara, Calif., assignor, by rncsne assignments, to the United States of America as represented by the Secretary of the Navy Filed Sept. 24, 1962, Ser. No. 225338, 3 Claims. (Cl. 89'-1.7)

, This invention relates generally to missile launching systems and more particularly to the control of postlaunch flooding of submerged launching tubes.

The launching of missiles from within submerged vessels or platforms presents the problem of controlling the stability of the vessels due to the variation in the weightvolume relationship of the vessel before and after missile launching. Immediate post-launch flooding of the container from which the missile was ejected has been viewed as a satisfactory solution to the problem if such flooding may be controlled to limit the weight of flooding Water to that of the ejected missile. Lack of suitable control would permit the launch tubes to be rapidly filled with water thus causing a marked change in the buoyancy of the submerged vessel.

One solution to the problem of flooding control is a movable check valve within the launch tube as described in application Serial No. 165,050, entitled Post Launch invention contemplates the creation of a cavity for trapping air within the launch tube thus reducing the amount of flooded water in the tube when a light weight missile has been ejected. By means of this arrangement, the weight of the flooded water is controlled and limited to approximately that of the ejected missile.

Referring to FIGS. 1 and 2 the missile launching tube 169 is supported within an outer tube 11 by any suitable means (not shown) and the space between the tubes is isolated by a bottom seal 12 and a top seal (not shown). Normally, the tubes are carried within the hull of a vessel, e.g., a submarine, in vertical orientation.

Flooding Control Apparatus, filed January 8, 1962 by Tsoy K. Moy, now US. Patent No. 3,100,421, and assigned to the United States Government. However, the requirement of an eflective sealbetween the valve and the launch tube in addition to the requirement for locking means positioned at various locations along the tube for selectively holding the valve at predetermined levels prompted the desirability of a simple, stationary, foolproof control.

Accordingly, an object of the present invention is to provide a simple, economic apparatus for controlling the post-launch flooding of submerged missile launch tubes thereby maintaining a stable Weight within the tube before and after launch, which apparatus may be easily installed and readily varied to accommodate missiles of varying sizes and weight.

Another object of the invention is to provide means for limiting the post-launch flooding to that amount equal in weight to any one of a variety of missiles selected for launching.

Other objects and many 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 in which like reference numerals designate like parts throughout the figures thereof and wherein:

FIG. 1 is a perspective view of a portion of a missile launching tube assembly with portions broken away;

FIG. 2 is a vertical sectional view of a portion of a missile launching tube assembly and -a missile supported therein;

FIG. 3 is a perspective sectional view of another embodiment of the flex rod stool skirt;

FIG. 4 is a perspective view of the missile hold-down clamp; and D FIG. 5 is a plan view of a, portion of the missile holddown clamp showing the actuator.

Alaunching system embodying the present invention anticipates initially a launching capability of two types of missiles of diflerent weights. Since the change of weight of the vessel after missile ejection, without flooding control, would vary depending upon whether a normal weight or light missile was launched, the operation of weight compensation in the vessel is complicated. The present A missile support ring assembly 13 is centered beneath the launching tube 10 and is attached thereto by fiexure rods 16 suspended from pads 17 welded to the lower outer surface of the launching tube. The flexure rods 16 suspend the support ring 13 in the manner of a pendulum so that when the missile 20 is subjected to a side load, flexing of the rods allows the missile to move laterally Within limits, imposed by storage/ launching adapters (not shown) positioned between the missile Z0 and the tube It Bending stresses on the missile and missile skirt 21 are thus minimized. Vertical movement of the support ring, relative to the launching tube, is restrained. The support ring supports and holds down a normal weight and norm-a1 length missile in stowed position by clamping the missile skirt to the missile support flange 14 of the support ring.

A flex rod stool 30 may be used as a spacer between the missile support ring 13 and missile skirt 21 when a shorter missile 20 is to be launched. Such spacing-is re quired to eflect proper alignment of electrical and instrumentation cabling, umbilical connections and pneumatic lines from the launching tube to the missile.

The flex rod stool 30 comprises concentrically arranged inner and outer cylinders. The outer cylinder 31 rests on the support flange 14 of the missile support ring and is secured to the support ring by clamps 32 protruding from the stool skirt 40. The inner cylinder 34, to which the short missile is clamped, floats within the outer cylinder 31 on vertical flexure rods 35 suspended from the upper rim 36 of the outer cylinder. The lower ends of the flexure rods are secured to the bottom rim 37 of the inner cylinder. Under a side load, a missile is allowed the same pendulum-like lateral motion as are missiles that are clamped to the missile support ring 13, thus minimizing the bending stresses on the missile and missile skirt.

A missile hold down clamp Stl, FIGS. 4 and 5, consisting of a clamp ring 51 and an actuator, locks the missile skirt 21 to the flex rod stool inner cylinder 34 when the hold down clamp is engaged. A support flange 38 is provided at the upper end of the inner cylinder in a manner similar to the flange 14 on the missile support ring 13. The clamp ring 51, a split-ring circular segment, is engaged by drawing the two ends together. When the clamp ring is engaged, a groove 53 on the inner face of the clamp ring mates with surfaces on the missile skirt and on the stool missile support flange, preventing vertical movement of the missile within the launching tube. The clamp. structure is similar to that associated with the support ring 13 when normal missiles are used.

The actuator 52 contains two pneumatic or hydraulic cylinders 54 that control levers 55 attached tothe two ends of the clamp ring. These levers are pivotally mounted to swing inwardly when the clamping ring is being engaged and outwardly when it is being "retracted.

Associated with the clamp and stool are switches for indicating the condition of the clamp and for indicating the departure of the missile from the ring.

When the short, lighter weight missile is launched from the flex rod stool, it is necessary to provide means a for reducing the weight of water which floods the launch tube by an amount equal to the difference in weight between the normal and light-weight missiles. By so doing, the problem of weight compensation in the vessel is greatly simplified since the same compensation would be applicable after the firing of either of the above type missiles.

The instant invention accomplishes the reduction of post-launch flooding by the provision of a flex rod stool skirt 40 attached to an inwardly protruding flange 39 provided on the lower end of the flex rod stool outer cylinder 31. The skirt is formed in the shape of a hollow cylinder or funnel (FIG. 3) and, when secured to the flange by bolts 41, serves as an extension of the outer cylinder 31 below the missile support ring 13. As set forth hereinabove the stool and associated skirt are secured to the missile support ring by clamps 32 attached to the skirt by bolts 42 and extending outwardly therefrom in contact with the under surface of the missile support ring. The cylindrically-shaped skirt shown in FIGS. 1 and 2 has a generally straight-sided outer wall interrupted by an upper recess 43 for attaching the skirt to the outer cylinder and a lower recess 44 for receiving the clamps 32. The inner wall of the skirt is also a generally straight-sided wall having a beveled upper surface 45 and flaring outwardly at the bottom as at 46 to facilitate the flow of missile eject air from. a source 18 through the skirt.

When the stool 30 is positioned on the support ring 13, the depending skirt 40 forms a cavity determined by the outer tube 11, seal 12, support ring assembly 13 and the skirt 40 within which missile eject air is trapped. The air so contained prevents post-launch flooding into the cavity thereby reducing the total weight of flooded water in the launch tube relative to flooding in the absence of the stool skirt. The size of the cavity and, therefore, the amount of post-launch flooding are substantially inversely proportional and may be readily varied by altering the height of the stool skirt.

The volume of the cavity may also be varied by providing a funnel-shaped skirt 47 having outside walls 48 generally tapering downwardly and inwardly thus creating a larger cavity. The skirt 47 is provided at its lower extremity with a straight sided portion 49 and with beveled and flared portions, 45' and 46, at the top and bottom to facilitate the flow of missile eject-air. The skirt is further provided with recesses 43' and 44 for attachment to the outer cylinder flange 39 and clamps 32. Obviously, varying the vessel depth at which missiles are launched will cause a variation in the volume of the trapped air due to the changing pressure exerted on the air mass. However, tests have shown that such variation in volume of air and associated post-launch flooding, within the range of depths reasonably contemplated for missile launching, areinsigniflcant insofar as vessel compensation is concerned.

Therefore, it will readily be seen that the inclusion of the flex rod stool and skirt accomplishes the objectives of controlling post-launch flooding, when diflerent size missiles are to be ejected from a missile launch tube, in a simple, eflicient and eltective manner. While the invention has herein been disclosed by reference to the details of a specific embodiment, it is understood that such disclosure is intended in an illustrative, rather than limited sense, as it is contemplated that various modifications in 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 claims.

What is claimed is:

1. In a missile launching system having at least one vertically extending launching tube assembly comprising an outer tube, an inner tube mounted within said outer tube, means disposed between and sealing said tube, a missile support disposed within said inner tube in spaced relation with respect thereto, ring means carried by said inner tube for supporting said missile support in spaced relationship with respect to the inner tube, an annular member secured to said support and cooperating with the outer tube, ring means and sealing means to provide a cavity for entrapping gas in the lower region of said tubes upon post launch flooding of said tube assembly thereby to control the amount of post launch flooding in such a manner that the weight represented by post launch flooding equals the weight of a launched missile, said missile support comprising an outer cylinder and an inner cylinder concentrically arranged therewithin, said outer cylinder having at its lower end, an inwardly directed flange and at the upper end thereof an additional inwardly directed flange, means securing said annular member to said lower flange, said inner cylinder having an outwardly directed flange at the lower end thereof and a missile supporting flange at the upper end thereof, rod means connecting said upper flange on the outer cylinder with the additional flange on the inner cylinder whereby when a missile is seated on said missile flange and secured to said inner cylinder longitudinal movement of said missile relative to said inner tube is prevented, and a hydraulically actuated split ring for securing the missile to the inner cylinder when the missile is seated in the missile flange.

2. In a missile launching system of the type having at least one vertically extending launching tube assembly having an outer tube, an inner tube suspended therewithin, sealing means disposed between said inner and outer tubes, a support ring secured to the bottom of said inner tube, a plurality of flexure rods carried by said inner tube in engagement with said supporting ring for securing the ring thereto, a missile support and post launch flooding control comprising a stool mounted on said support ring and having an inner cylindrical member and an outer cylindrical member, means on said inner cylindrical member for receiving and supporting a missile thereon, an annular member attached to said outer cylinder member in engagement with said supporting ring and extending downwardly therefrom beyond the lower extremities of said support ring, sealing means and cylindrical members thereby providing a cavity between said supporting ring, sealing means, annular member and outer tube whereby gas may be trapped in said cavity during post-launch flooding for controlling the amount of said flooding, flange means on the inner cylindrical member, complementary flange means on said outer cylindrical member, and flexure rods connecting said flange means on the cylindrical members for supporting the inner cylindrical member in a missile supporting and receiving position.

3. The system according to claim 2 including clamping means for securing said missile to said stool comprising a split-ring encircling said missile and the inner cylindrical member and having groove means engageable with flange means on the missile and flange means on the inner cylindrical member, pivotally connected lever means having the terminal ends thereof pivotally connected to the split ring, and hydraulic means connected to said lever means for engaging said grove means with the flange means on said missile and the inner cylindrical member.

References Cited by the Examiner UNITED STATES PATENTS 1,186,023 6/16 Moore 89--5 2,981,187 4/61 Riordan et al. 102-49 3,072,022 1/63 Wood et a1. 89--1.7 3,087,386 4/63 Rung et al. 89--1.7

BENJAMIN A. BORCHELT, Primary Examiner.

ARTHUR M. HORTON, SAMUEL W. ENGLE,

Examiners.

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US1186023 *Sep 22, 1915Jun 6, 1916William Vincent MooreGun-tampion and means for actuating the same.
US2981187 *Nov 10, 1958Apr 25, 1961Baughman John EPneumatic mechanism for booster clamp ring release
US3072022 *Oct 30, 1961Jan 8, 1963Ecker Charles WMissile container suspension system
US3087386 *Mar 23, 1961Apr 30, 1963Barakauskas Edward JAdapter for missile launcher
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US3823903 *Mar 3, 1972Jul 16, 1974Menasco Mfg CoDual length pendulum shock absorbing system
US3962951 *Apr 1, 1975Jun 15, 1976The United States Of America As Represented By The Secretary Of The NavyMissile launching and hold-down device therefor
US5003909 *Jun 18, 1990Apr 2, 1991The United States Of America As Represented By The Secretary Of The NavySubmarine torpedo tube collapsible choke
US5363791 *May 11, 1993Nov 15, 1994Newport News Shipbuilding And Dry Dock CompanyWeapons launch system
US5645006 *Jan 17, 1996Jul 8, 1997The United States Of America As Represented By The Secretary Of The NavyBladder assembly for retaining fluid under pressure
Classifications
U.S. Classification89/1.81, 114/238
International ClassificationF41F3/00, F41F3/07
Cooperative ClassificationF41F3/07
European ClassificationF41F3/07