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Publication numberUS3124040 A
Publication typeGrant
Publication dateMar 10, 1964
Filing dateFeb 26, 1962
Publication numberUS 3124040 A, US 3124040A, US-A-3124040, US3124040 A, US3124040A
InventorsWilly A. Fiedler
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Support system for tube launched
US 3124040 A
Abstract  available in
Previous page
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Claims  available in
Description  (OCR text may contain errors)

March 10, 1964 w. A. FIEDLER SUPPORT SYSTEM FOR TUBE LAUNCHED MISSILE Filed Feb. 26, 1962 INVENTOR WILL) A. F/EDLER ATTORNEYS United States Patent 3,124,040 sUProRr SYSTEM ron TUBE LAUNCHED MISSILE Willy A. Fiedler, Los Altos, Calii'., assignor, by mesne assignments, to the United States of America as represented by the Secretary of the Navy Filed Feb. 26, 1962, Ser. No. 175,853 9 Claims. (Cl. 89-1.7)

This invention relates to a cylinder that is utilized to contain a missile during logistic, pre-launch and launch phases, and more particularly it relates to a container lined with a flexible mat.

The complete missile package consists of an outer tube containing a suspension system which supports an inner tube, which latter tube directly contains the missile. The present invention deals primarily with the inner tube of this missile package.

This inner tube, usually of non-corrosive aluminum alloy, must be protected from direct contact with the missile. The method most prominently utilized is to surround the missile at a plurality of points along its vertical exterior with hand rubber stowage and launching supports or adapters. These adapters separate from the missile after ejection from the launch tube. Although such supporting means have served the purpose, they have not proved entirely satisfactory under all conditions of service for the following reasons:

(1) Underwater collision of missiles and adapters h'om prior launchings.

(2) Fall back of adapters on the submarine or ship during surface launching.

(3) Unknown contribution of the adapters to the cavitation about the missile dun'ng separation.

(4) Support at spaced points along missile allowed flexing of the missile.

Accordingly, it is an object of the present invention to provide a simple, reliable, soft support system for missile containers and launch tubes.

Another object is the provision of a support system which transfers external loads to missiles over large areas during logistic, pie-launch and launch phases.

Yet another object is the provision of a support system that remains fixed to the container and launch tnbe thus eliminating collisions and fall back, and which greatly simplifies rearming the missile system.

Still another object is to provide a support for tubelaunched missiles which will give superior load distribution during transportation and storage, especially during depth charge shocks.

Another object is to provide improved missile environment during launch ejection, eliminating danger of high local stresses.

Yet another object is to eliminate improper adapter location.

Still another object is the provision of a support system compatible with all modes of transportation and with both surface and underwater tube ejection launchmgs.

Another object is to provide a soft support system for tube launched missiles that assures damping of missile motion caused by shock and vibrations.

Other objects and many of the attendant advantages 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 FIGS. 1 through 3 show longitudinal sectional views of the inner container and the missile.

Referring now to the drawings in order:

FIG. 1 shows the inner tube 1 of cylindrical cross 3,124,040 Patented Mar. 10, 1964 See section. Centrally disposed within tube 1 is a missile 2 of cylindrical shape surrounded at its lower end by a skirt 3 of cylindrical shape. The lower end of skirt 3 has a shoulder 4 which is engaged by a yielding hold down device 5. The skirt can be flared to spread the mat to insure an air seal during launch and to prevent flexing during insertion by being surrounded by a sectional plastic ring 6 which is attached to skirt 3 by means of a latch 7 which fits into a slot 8 on skirt 3. The inner tube 1 is continuously covered by a rubber mat 9 having a large number of parallel ring protrusions 10, resulting in lips 11 which contact and support the missile along its exterior in a direction normal to its vertical axis. The outside face of the mat may be coated. with a sheet 13 of low friction material such as Teflon or nylon.

FIG. 2 shows an alternate means of spreading the lips 11 of fiexomat 9 during insertion or ejection wherein an inflatable reinforced torus 13 is attached to skirt 3 and is inflated by means of eject air (from a source not shown) through a plurality of holes 14 in skirt 3.

The lips can be of various shapes such as slightly conical, cylindrical or with thickened edge. FIG. 3 shows a flexornat 15 wherein the lips are joined together to form a closed flexomat 15 containing circumferential air pockets :16.

Sectional shape of the rings is selected to assure a good seal against launch eject pressure and to give acceptable missile support. The normal (height and/or stiffness of the rubber rings adjacent to the missiles critical loading sections and at the top of the tube may be reduced to permit passage of exterior missile proturberances.

When the missile container is subjected to lateral shock or vibratory motion the entire missile undergoes a lateral displacement relative to the container. Each rubber ring adjacent to the missile motors imposes a certain force essentially normal to the missile axis. Rings in the various port-ions of the container may have diiterent spring rates in order to reduce bending loads on the missile. The missile is protected at the fore and aft ends of the container by conventional shock absorbing devices.

Though the outer container forms no part of this invention, it is necessary to describe it to show the full advantages and operation of the disclosed invention. The outer container shell or capsule contains access ports and provisions for system checkout of the missile through umbilical plugs. The re-entry body segment of the capsule is removable. The inner container when necessary has scalable access ports and umbilical plugs to match those of the outer container. The portion of the inner tube that encloses the missile re-entry body is also removable, thus allowing separate mating of missile and re-entry body. A swivel gland is provided in the base of the inner tube to automatically mate with the eject-air inlet tube.

The outer container holds the inner tube by means of a set of air springs which consist of a pair of cylindrical pad-type springs which give transverse support to the inner liner and a pair of torroidal air springs to provide axial support in the container. These pad-type transverse springs are faced with nylon sheeting to prevent scufling and to permit sliding into the shipping container or the outer container of the submarine launch system.

The design of this system thus allows the use of the inner liner as a shipping container and launch tube since it can be designed with all the necessary hardware and transferred from an outer shipping container to the outer tube of the launching package; or the inner liner can be left in place and another missile inserted into it.

The use of an attached support in the inner tube eliminates the time consuming, critical locating of the hard point guides and sea-ls during insertion of the missile into the inner tube.

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 may be practiced otherwise than as specifically described.

What is claimed is:

1. As a soft-support system for tube-launched missiles, the combination of a cylindrical missile, a tube and a resilient, annular mat secured within said tube, said cylindrical missile being releasably retained within said tube and mat, said mat having attached thereto a plurality of flexible ring protrusions, which ring protrusions are normal to the axis of said missile and are in circumferential contiguity with said missile whereby tendencies toward excessive movement of a stowed missile within the launching tube is retarded and possible damage to the missile as a result of externally applied shocks and vibrations is obviated.

2. The comination of structure of claim 1 wherein the mat comprises rubber.

3. The combination of structure of claim 2 wherein the missile engaging surface of the mat is coated with a material selected from the group consisting of Teflon and nylon.

4. As a soft support system for tube launched missiles, the combination of a missile, a tube, a flexible mat, a missile skirt and spreading means, wherein a substantially cylindrical missile is centrally disposed within an inner tube of a missile package, said inner tube having secured therewithin and being substantially interiorly covered With a flexible mat which circumferentially engages and supports said missile, said missile being surrounded at its lower portion by a missile skirt to protect the missile motors and nozzles, means to spread said mat and increase the compression thereof interposed between and contiguous with both said missile skirt and said mat so as to insure an air seal during ejection of the missile from the tube.

5. The combination of claim 4 wherein the spreading means comprises a sectioned ring attached to said skirt and having a diameter decreasing in the eject direction.

6. The combination of claim 4 wherein the spreading means comprises an inflatable torus attached to said skirt and inflated by means of eject air communicated through holes in said skirt.

7. In an inner tube of a missile package for launching missiles terminating in a skirt section, the improvement comprising a flexible, generally cylindrically-shaped mat permanently fixed to the inner surface of said inner tube so as to exert a cushioning force normal to the axis of a missile when the same is disposed within said tube and mat, and independent spreading means having a diameter decreasing in the eject direction of a missile during launching and interposed between and sealingly engaging said mat and said skirt so as to insure an air seal during ejection and to prevent ring flexing during insertion of a missile into said tube.

8. The improvement according to claim 4 which contains a plurality of mutually spaced, annular protrusions.

9. The improvement according to claim 4 which contains a plurality of mutually spaced, generally annular chambers.

References Cited in the file of this patent UNITED STATES PATENTS 2,001,684 Johnson May 14, 1935 2,259,940 Nathan Oct. 21, 1941 2,271,777 Nathan Feb. 3, 1942 2,485,976 Main Oct. 25, 1949 2,534,811 Corlett Dec. 19, 1950 2,672,814 Dubost Mar. 23, 1954 2,727,738 Lindley Dec. 20, 1955 2,749,150 Kaiser June 5, 1956 2,874,826 Matthews et al. Feb. 24, 1959 2,928,348 Zisman et al. Mar. 15, 1960 2,996,102 Butler Aug. 15, 1961 3,030,865 Ridnour Apr. 24, 1962 3,088,374 Guyant et al. May 7, 1963 FOREIGN PATENTS 91,240 Netherlands June 15, 1959

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Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US3289533 *Apr 6, 1965Dec 6, 1966Brown Charles RMissile launching tube seal
US4324167 *Apr 14, 1980Apr 13, 1982General Dynamics, Pomona DivisionFlexible area launch tube rear cover
US4357855 *Dec 1, 1980Nov 9, 1982The United States Of America As Represented By The Secretary Of The NavyRadiation resistant projectile canister liner
US4406211 *Jul 28, 1981Sep 27, 1983Westinghouse Electric Corp.Annular shock absorbing system for a missile launcher
US4464972 *Mar 15, 1983Aug 14, 1984The United States Of America As Represented By The Secretary Of The Air ForceLateral support system for canister-launched missile
US4602552 *Jun 25, 1984Jul 29, 1986The United States Of America As Represented By The Secretary Of The Air ForceZero adhesion system
US4604940 *Feb 28, 1985Aug 12, 1986Westinghouse Electric Corp.Highly resilient polyurethane elastomer
US4646617 *Aug 30, 1985Mar 3, 1987Westinghouse Electric Corp.Shock absorbing support pad system
US4664421 *Aug 29, 1986May 12, 1987Jones William DForgiving profile pipe gasket
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US5220125 *Jan 18, 1985Jun 15, 1993Westinghouse Electric Corp.Unitized shock isolation and missile support system
US5315912 *May 11, 1984May 31, 1994Westinghouse Electric Corp.Suspended hoop seal
US5353677 *Aug 31, 1993Oct 11, 1994Westinghouse Electric CorporationShock isolation system
US5438905 *Jun 19, 1984Aug 8, 1995Westinghouse Electric CorporationMethod and apparatus for stabilizing the in-tube trajectory of a missile
US5438906 *Aug 13, 1984Aug 8, 1995Westinghouse Electric CorporationUnitized shock absorbing pad with looped fiber ring
U.S. Classification89/1.816, 285/110, 285/106, 206/3, 42/76.1
International ClassificationF41F3/00, F41F3/042
Cooperative ClassificationF41F3/042
European ClassificationF41F3/042