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Publication numberUS3373657 A
Publication typeGrant
Publication dateMar 19, 1968
Filing dateDec 28, 1964
Priority dateDec 28, 1964
Publication numberUS 3373657 A, US 3373657A, US-A-3373657, US3373657 A, US3373657A
InventorsGuin Joel B
Original AssigneeJoel B. Guin
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Open water missile and cargo launching systems
US 3373657 A
Abstract  available in
Images(4)
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Claims  available in
Description  (OCR text may contain errors)

March 19, 1968 5, sum 3,373,657

OPEN WATER MISSILE AND CARGO LAUNCHING SYSTEMS Filed Dec. 28, 1964 4 Sheets-Sheet 1 1N%NTOR J. B. GUIN March 19, 1968 OPEN WATER MISSILE AND CARGO LAUNCHING SYSTEMS 4 Sheets-Sheet 2 Filed Dec. 28, 1964 March 19, 1968 J. B. GUIN 3,373,657

OPEN WATER MISSILE AND CARGO LAUNCHING SYSTEMS Filed D60. 28, 1964 4 Sheets-Sheet 5 INVENTOR March 19, 1968 J. B. GUIN 3,373,657

OPEN WATER MISSILE AND CARGO LAUNCHING SYSTEMS Filed Dec. 28, 1964 4 Sheets-Sheet 4 75 lllllllq 65 JUNE INVENTOR tates 3,373,657 ()PEN WATER MISSILE AND CARGO LAUNCHIN G SYSTEMS Joel B. Guin, 148 E. 48th St., New York, N.Y. 10017 Filed Dec. 28, 1964, Ser. No. 421,218

6 Claims. (Cl. 891.81)

Risk of low-level abortion (due to some minor defect in 7 equipment, adjustment, checking or timing, or position of the submarine, or due to an obstruction in the water) which could endanger the submarine or crew;

Short range, since so much fuel is wastefully consumed in reaching Mach 2 to 3 that remaining space precludes carrying fuel for a long flight.

Suggested improvements in the Polaris system require costly shafts extending downward, in order to utilize the hydrostatic pressure inherent in deep columns of Water.

'It is therefore an object of this invention to provide an open water missile or cargo launching system which will obviate the objections noted; which will prevent tumbling, avoid excessive fuel consumption, reduce friction, decrease low-level abortions and increase missile range.

Another object is to save the cost of deep water shafts and reduce the costs of heavy stabilization, navigation, and fuel-container equipment;

A further object is to simplify both stabilization and navigation equipment and procedures and to increase target accuracy by imparting such a strong impulse to the missile that it attains a speed of Mach 2 or 3 before its own fuel is ignited, thus conserving fuel to permit navigation corrections much later, even up to the target area.

Other objects are:

To furnish a launching system using hydrostatic waterpressure as the launching force;

To use a vessel e.g. aircraft carrier, barge, cruiser, drydock, floating do-nut, on which the system is based;

To provide a guidance and stabilization means with a beam comprising extensible and, retractable, telescoping, hollow cylindrical sections, directed down from the vessel vertically into the water, and having a heavy steel sphere attached at the bottom, said sphere containing motors, winding drums, compressors, etc.;

To provide a series of cylinders, starting with booster cylinders above the steel sphere, a container cylinder holding the missile and/or cradle and/ or platform, and one or more water-displacing cylinders reaching toward the surface;

To fasten all or most of said cylinders to running along the vertical hollow beam;

To stabilize the missile in flight by imparting to it a thrust sufiicient to accelerate it to Mach 2 or 3 before its fuel is ignited and/ or spinning it like a top by fastening it to a turntable that rotates at increasing r.p.m.s during launch operations;

To provide an electrical and/or electronic control and telemetry center on the floating vessel; to coordinate operations with an instrumented range (e.g. that extending southeast from Cape Kennedy).

A still further object of this system is to save money and help modernize the fleet by converting old vessels gliding devices free such as outmoded submarines, aircraft carriers, cruisers, barges, etc. now in or ready for the moth-ball fleet to enable them to perform a quite up-to-date mission.

Additional objects will be apparent when specifications are considered in connection with details of the attached drawings:

FIG. 1 is a top view of the launching section, cut out of the launching vessel.

FIG. 2 is a horizontal view taken along the line 2-2, showing a vertical section through the launching part.

FIG. 3 is a view of the heart of the launching system, a vertical hollow beam extending downward, with gliding devices to which missile container and other cylinders are connected.

FIG. 4 is a cross section of the lower part of the hollow beam shown in FIG. 3.

FIG. 4A is a top view of cylinder 6 in FIGS. 1 and 2.

FIG. 5 is a side view of U-shaped guiding beam 23 of FIGS. 1 and 2.

FIG. 6 is a detail view of collapsed parts of FIG. 5.

FIG. 7 is a detailed side-view of two sections of the U-shaped beam in FIG. 5.

FIG. 8 is a top view of a horizontal cross section taken on line 4-4 in FIG. 7.

FIG. 9 is a vertical cross-section taken along line 5-5 in FIG. 7. v

The essential operational concept of this invention is:

To place an extensible and retractable telescoping hollow beam vertically into the Water; to extend said beam straight down into the water; to stabilize said beam by a heavy steel sphere at the bottom, said sphere containing essential equipment such as motors, winding drums, compressors, etc; to place one or more missiles within missile containers; to insert one or more booster cylinders between the steel sphere and the missile container and one or more water-displacing cylinders above the missile container; to fasten these cylinders to gliding devices moving freely on the beam; to stabilize all cylinders by one or more guiding beams, which are also extensible, retractable, and telescoping.

System stabilization may be provided by heavy weights and/or anchors attached to the lower sections of the vertical hollow beam. If continued launching is to be made from the same area, semipermanent heavy anchors could be placed on the ocean bottom, with heavy cables between them which could be engaged by hooks on cables extending from the bottom section and/or intermediate sections of the hollow beam. Stabilization can also be provided by one or more guiding beams made of one or more extensible and retractable telescoping sections directed downward parallel to the hollow beam, and/or one or more series of girders extending horizontally from the hollow beam and /or the guiding beam, along with wires of cables threaded through the outer ends of said girders horizontally and pullled taut to give a suspension bridge effect. Two such cables through girders on opposite sides of the same beam would look like two suspension bridges back to back, but positioned vertically.

The boosters, comprising two or more expansible and collapsible cylinders may contain air at even higher pressure than the water at the level they are placed, with catches timed to release when additional thrust is most needed.

Further thrust may be given by igniting fuel contained in or near the booster cylinders. Boosters may also contain chemicals. Other boosters may comprise various mechanical devices, e.g. cables over rollers with multiple pulleys and weights, etc.

Means for readily expanding and collapsing booster cylinders and water-displacing cylinders and/or raising or lowering the pressure to that required at each level must be provided, comprising appropriate compressors,

plumbing, valves, controls, signals, etc. Also useful would be ways of making the hollow beam and/or the gu1d1 ng beam more rigid, such as a series of girders extending horizontally from two or more of the sections of one or both beams, with wires or cables stretched tautly through loops near the outer ends of said girders and fastened near the top and bottom of said beam or beams.

A means for deflecting the water-displacing and booster cylinders, and the missile or cargo container cylinder over the side away from the vessel must be provided. Choice of such means will be determined by the number, size, weight, length, and diameter and speed of the cylinders, the number and frequency of launchings, the height and width of the ship, the presence or absence of connections between cylinders, etc. Deflection means available include: runners, grooves, channels, fins, levers or compressed air jets, one or more of which may be used to start the deflection of each cylinder. The speed will be sufficient to shoot them far out into the water.

Fastening all water-displacing cylinders by ropes or cables, and all booster cylinders by ropes or cables will aid in deflecting them properly, in preventing them from colliding unduly in the air or water and in gathering them from the water after each launching.

All above means are known: no new technology is involved.

Referring now to the drawings, FIG. 1 shows a top view of the launching section, cut lengthwise out of the launching vessel and FIG. 2 is a horizontal section taken on the line 22 in FIG. 1 and showing a vertical cut through the launching section.

A hollow cylindrical beam 1 extends vertically through the ship and incloses a second hollow beam 2 which fits slidably within it. Other beams may be included and similarly operated, if required. The tubes are collapsed (as described in FIG. 4) by two ropes 4 which are fastened at 5. Hollow beam 1 is rigidly held by supporting structure 9 connected to cylinder 6. Structure 9 is fastened to hollow beam 1 at 8 and to the outside cylinder 6 at 7. One design is shown in FIG. 1, a cross configuration, the four quarters of Which inclose four launching areas 14 numbered I, II, III and IV. Objects are launched through these, one to four at a time. A part of one top cylinder 3, in dotted lines, is rotated into the section plane. To avoid free rotation around hollow beam 1, one or more U- shaped guiding beams 23 extend downward from the bottom rim of cylinder 6, and runners or other guiding devices extend from its open side to the ascending top cylinder (see FIG. 3). Each beam 23 is collapsible into one of the open spaces 25 in upper cylinder 6. In FIG. 2, a guiding beam 23 is rotated into the section plane.

Cylinder 6 is connected with ship 20 over a universal joint whose inner bearings 10 are movably mounted between cylinder 6 and gimbal ring 11, and outer bearings 12 are movably mounted between ring 11 and ship structure 20, 90 removed from bearings 10. Cylinder 6 is connected with the ship body 20 by flexible structure 13, thus keeping water out of the bearing section.

Annular pressurized air container ring 15 has outer circumference 16 and inner circumference 17.

Hull 18 of the ship supports upper deck 22, below which is storage space 21. While cruising (all beams collapsed, all cylinders stored) hole 19A in the bottom of ship 20 is covered by a plate 19 that is brought into position through openings 24.

FIGS. 3 and 4 show the essential launching arrangement in which objects are driven upwards and guided along a hollow cylindrical beam 2 in the middle (1, 2, etc. in FIG. 2). Only one object is shown but two or more can be launched together as in FIGS. 1 and 2.

Object container 26 with object 27 is held in position by guiding devices 32 which fit around hollow beam 2 and are attached to the cylinders above and below container 26. The middle beam consists of several parts fitting into each other as described in FIG. 2, being separated at limits 34: the scale is too small to show the telescoping of progressively larger beam sections. If more than one object is to be launched at one time, devices 32 are changed accordingly. Any desired number of light expanslble cylinders, such as 28 and 29, filled with pressurized gas, are placed above container 26. Below container 26 other collapsible booster cylinders, such as 30 and 31, also filled with compressed gas, are placed, if required to increase buoyancy. Cables 35 are used to collapse hollow beam 2.

One design for the lower part of the launching system is shown in FIG. 4. Heavy steel sphere consisting of two half-spheres 44 and 45, screwed together at 46 and containing motor unit 43 to which energy is supplied over circuit lines 47 from the launching vessel is attached below beam 36. The sphere contains a set of winding drums 40 and 42, one for each object to be launched. When beams 36 (1, 2 in FIG. 2) are collapsed the sphere fits into hole 19A in the launching vessel (FIG. 2). To extend collapsed beams 36, plate 19 is removed; then the sphere whose weight pulls the middle beam down, is released. As the sections are extended, they are locked in place by conventional means such as catches. Each launching unit, including booster cylinders below, object container, and water displacing cylinders above, are pulled down by rope 38 which in turn is Wound up on drum 42, driven by motor unit 43. During a launch the winding drum rotates freely. To retract hollow beams 36 the catches which lock all sections are released and drum 40 driven by motor unit 43 winds up cable 39, which is an extension of cable 35 in FIG. 3. This draws the sphere upward and collapses the beam (see FIGS. 59 for guiding and stabilizing means).

FIGS. 4A to 9 show the guiding beam system, the preferred design consisting of four U-shaped telescoping steel beams. FIG. 4A is a top view of cylinder 6 of FIGS. 1 and 2 in the launching vessel, with installations of four leading beams 51, 51A, 51B, and 51C within which the guiding U-beam sections ascend and descend.

FIG. 5 shows three telescoping U-beam sections 52, 54, and 56 of guiding beam 23 with vertical sections through supporting rings 53 and 55 which encompass all four beams indicated in FIG. 4 and are fastened to the beam sections. If desired, the encompassing support rings may be eliminated and the beams stabilized by weights, anchors, etc.

FIG. 6 shows the way beam section 54 and support ring 55 fit under the next section 52 above. Thus all support rings fit together when collapsed.

FIGS. 7 to 9 show two U-beam subsystems: the extension catch and the cylinder guiding device.

FIG. 7 is a side view of the two U-beam sections 60 and 61 with a section through support ring 62 described in FIG. 5. As section 61 glides down catch 67 is in rectangular depression 73 but springs out, driven by spring 68, when it reaches depression 69, to prevent further extension of part 61. The convex lower edge of catch 67 helps to push it back into depression 73 when the beams are retracted.

The cylinder guiding device prevents free rotation and excessive horizontal movement of cylinders. To prevent horizontal movement, curved steel plate 63 fastened to a piston-like bar 64 is pressed by spring 66 against the inside of U-beam 60. Both bar 64 and spring 66 move within plunger structure 65 which is fastened to the outside of launching cylinders, object containers, etc. Bevel 74 at the top of each section facilitates gliding along the back wall.

FIG. 8, a horizontal section along line 4-4 in FIG. 7 shows part of the guiding device that prevents free rotation of the cylinders. Steel plates 70, mounted on structure 65, are pressed against the side walls of the U-beam 60 by springs 71. The closer the U-beam side walls come together the more the springs are pressed inward: in the lowest part of the U-beam plates 70 lie in depression 75.

FIG. 9, a vertical section along line 5-5 in FIG. 7, the beveling 72 of both edges of the U-beam facilitates gliding of plates 70' along the sidewalls, plates 70 also being beveled.

A missile launching might proceed thus: All checks made, countdown ends; booster, missile container and water-displacing cylinders are unloosed, in that order; momentum attained, pressure of first air booster is let go, then the second, third, etc.; cylinders start deflecting over the sides; water acceleration slowing, first steam booster ignites, then the second, etc., throwing flames into water container, producing steam that is forced downward through nozzles; missile flames may be fired into a water container below surface or later in flight, depending on speed desired; last cylinders are deflected; launch completed, cylinders are gathered, collapsed, and prepared for next launching. Plumbing, valves, releases, controls, etc. are conventional: for simplicity they have been omitted and will not be claimed.

I claim:

1. A missile launching system comprising:

A floating vessel, a cylindrical hollow beam having a plurality of extensible and retractable telescoping sections suspended downwardly into the water from said vessel, means mounting said hollow beam on said vessel, means for extending and collapsing said telescoping sections, a closed contanier for holding the missile to be launched, guiding means on said container and cooperating with the surface of said hollow beam sections, said closed container for said missile displacing a suflicient volume of water to thereby provide a buoyant missile launching container, means mounted on the lower end of said hollow beam for lowering said closed container for said missile and means for releasing the container whereby the container with the missile therein is propelled upward by the hydrostatic pressure of the surrounding water to thereby launch the missile.

2. A missile launching system according to claim 1 having inserted below said floating vessel and above said container for a missile to be launched, one or more water-displacing cylinders, each having a plurality of expansible and collapsible sections, the uppermost cylinder being streamlined and the bottom of each cylinder fitting closely over the top of the cylinder below it, for the purpose of reducing water friction.

3. A missile launching system according to claim 2 wherein said means for lowering said container for the missile to be launched and for releasing said container consists of a spherical member which holds and in which are mounted motors, compressors, and winding equipment for lowering and releasing, said spherical member being mounted upon the lower end of said hollow beam.

4. A missile launching system according to claim 2 in combination with additional guiding means comprising:

A guiding beam formed of a plurality of extensible and retractable U-beam sections that telescope into each other, the topmost section being mounted upon the lower part of said floating vessel, the entire guiding beam being directed downward into the water, parallel to said hollow beam from which it is separated by said closed container for the missile to be launched and said water-displacing cylinders;

Gliding devices movably attached on one side to said guiding beam and fixedly attached on the other side to said closed container and said water-displacing cylinders which are thereby guided and prevented from turning with respect to the hollow beam as said container and cylinders descend and ascend in the Water;

Means for limiting the descent of the guiding beam consisting of depressions in the rear of each U-beam section near its top end, matching holes in the front of each section near its lower end, and catches attached to springs in the depressions in such way as to be forced into the holes as the lower sections slide down along the upper sections, thereby locking them in place;

Means for facilitating the glide of said catches, consisting of bevelled lower edges of the catches and bevelled bottoms of said holes; means for minimizing horizontal radial movements of said closed conta'nier and said water-displacing cylinders consisting of curved steel plates fastened to piston-like bars that are pressed by steel springs against the inside of said U-beam sections, both the bars and springs moving within holding structures fastened to the outside of the closed container and said water-displacing cylinders, the top of each said U-beam section below the uppermost being bevelled to facilitate the gliding over of said curved steel plates as said closed container and water-displacing cylinders to which they are fastened ascend during the launching of said missile.

5. A missile launching system according to claim .3 in combination with collapsing means comprising cable means running through said hollow beam to said steel sphere where it is wound upon one of said winding drums contained therein which is rotatable by one of the motors contained therein so as to force said collapsible sections of the water-displacing cylinders together prior to the launching of said closed container with the missile therein.

6. A missile launching system according to claim 4, in combination with means for damping wave motion and stabilizing the system, comprising:

A universal joint with outer bearings interposed between said floating vessel and a gimbal ring, and inner bearings interposed between the same gimbal ring and an upper cylinder which constitutes said means mounting the hollow beam on said vessel, said vessel having a hole in its bottom through which the hollow beam and the guiding U-beam sections are extended downward and retracted upward;

And means for floating said vessel while said hole is open, comprising: an air filled annular ring surrounding the launching assembly and a flexible structure, impervious to water, interposed between the annular ring and the launching assembly.

References Cited UNITED STATES PATENTS 3,122,057 2/1964 Kubit 891.7 3,135,162 6/1964 Kamalian 891.7 6/1964 Brown 89--1.7

SAMUEL W. ENGLE, Primary Examiner. BENJAMIN A. BORCHELT, Examiner.

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US3122057 *Feb 17, 1961Feb 25, 1964Kubit Theofile TMeans for launching space vehicles
US3135162 *Nov 27, 1961Jun 2, 1964Neubar KamalianWater-borne missile launcher
US3137203 *Jan 31, 1962Jun 16, 1964Joseph BrownUnderwater missile launching system
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US3513750 *Jun 24, 1968May 26, 1970Us NavyFloating missile launcher
US4916999 *Oct 27, 1988Apr 17, 1990Rowan Companies, Inc.Offshore launching system
US7451680 *Oct 20, 2006Nov 18, 2008The United States Of America As Represented By The Secretary Of The NavySubmarine steam generator missile ejection system
US8887614 *May 14, 2013Nov 18, 2014The United States Of America As Represented By The Secretary Of The NavyStacked buoyant payload launcher
DE1928794C1 *Jun 6, 1969May 3, 1979Dornier System GmbhAbwehrwaffe fuer ein U-Boot zur Bekaempfung von UEberwasser-,Land-oder Luftzielen
Classifications
U.S. Classification89/1.81
International ClassificationF41F3/00, F41F3/07
Cooperative ClassificationF41F3/07
European ClassificationF41F3/07