Галерея 3245318
Галерея 3245318
April 12, 1966 J. L. FINKELSTEIN ETAL 3,245,318
FLOTATION MISSILE LAUNCHER 2 Sheets-Sheet 1 Filed April 22, 1964 M Y E N U E N SWIN G VR ELO A 0 Oq m P T wa A E WE m m mGf F L V YWUM MEMS w @G 4 H g B I 2 4 F 7 3 April 12, 1966 J. 1.. FINKELSTEIN ETAL 3,245,318
FLO'IATION MISSILE LAUNCHER Filed April 22, 1964 2 Sheets-Sheet 2 INVENTORS JAY L. FINKELSTEIN EDWARD S. GRAVLIN PAUL G. ANDERSON SA ORE J. PENZA QWJ-EMEY United States Fatent G 3,245,318 FLOTATION MISSILE LAUNCHER Jay L. Finkelstein, Santa Monica, Edward S. Gravlin, Oxnard, Paul G. Anderson, Montalvo, and Salvatore J. Penza, Oxnard, Calif., assignors to the United States of America as represented by the Secretary of the Navy Filed Apr. 22, 1964, Ser. No. 361,918 2 Claims. (Cl. 89--1.7)
The invention described herein may be manufactured and used by or for the Government of the United States of America for governmental purposes without the payment of any royalties thereon or therefor.
The present invention relates in general to missile launchers and more particularly to missile launchers capable of launching a missile from a body of water wherein the launcher will permit handling and service of the missile while the missile and the launcher are waterborne.
The use of bodies of water as the medium to support the launching of missiles is becoming more desirable both because of the costs involved in comparison with land based launch pads and equipment and the lessening of damage to equipment and injury to personnel. Waterborne missile launchers currently in use include in some instances merely a float or series of floats attached to the missile itself so that the missile may be launched from a suspended position in a body of water. Other current water launching devices include structures which substantially surround the missile so as to provide protection during the immersion and other pre-la-unch stages. These latter devices have considerable limitations some of which lie in not providing protection to the body of the missile while it is being handled and transported from land to where it is suspended in the water, or, alternatively, in over-protecting the missile so as to preclude servicing or handling while the missile and launcher are waterborne. Prior missile launchers both of the waterborne and land based variety are heavy and relatively complex therefore requiring considerable effort and dexterity in handling the launcher alone or the launcher with a missile inserted in it. Some of the current launchers include closure means which are used to enclose the upper extremity of the missile whereby the missile before launching is protected from the elements and upon launching is exposed to the elements only after forcing apart the closure means before entering the atmosphere. Such protective devices impede the progress of the missile and present a possible means for causing course deviation.
The launcher of the present invention avoids many of the disadvantages of prior and current flotation launching devices and additionally provides a device which is light in weight and yet which will support the missile in a plurality of areas as well as permitting servicing and handling of the missile and guiding the missile during its launching. A primary function of the present launcher is to provide the proper buoyancy and stability characteristics to the launcher-missile ensemble so that when the ensemble is floating in a vertical attitude the angular deviation of the missiles flight path from the vertical is at a minimum value. This stability characteristic is incorporated in the physical characteristics of the launcher and is especially important where unguided missiles are launched.
Accordingly, it is an object of the present invention to provide a waterborne missile launcher which supports the missile and/ or a booster laterally as well as longitudinally both in the launching attitude and also in the handling stages prior to a launching attitude being assumed.
It is another object of the present invention to provide ings wherein the missile may be serviced throughout its I a missile launcher for accomplishing waterborne launch- 3,245,318 Patented Apr. 12, 1966 length while in the pre-launch stages or in a launching attitude.
It is a further object of the present invention to provide a missile launcher which supports the missile in a plurality of areas both during handling and launching and additionally permits the water surrounding the missile to coddle it during all stages prior to and during launching.
Other objects and many of the attendant advantages of this invention will be readily appreciated as the same becomes better under-stood by reference to the following detailed description when considered in connection with the accompanying drawings wherein like numerals throughout the figures represent like parts.
FIG. 1 is a perspective view of the launcher with a missile and booster i'nserted therein.
FIG. 2 is an enlarged view of a missile and booster adapted to be launched from the present launcher.
FIG. 3 is a top view of the missile launcher with the missile and booster omitted.
FIG. 4 is a section taken along line II of FIG. 1 with the missile and booster omitted.
FIG. 5 is a section taken along line =IIII of FIG. 1 with the missile and booster omitted.
The launcher of the present invention is basically a latticework frame which provides a minimum weight for the size and strength requirements of the launcher. The launcher includes a flotation member attached near the upper extremity thereof and a base member which may be adapted to receive missiles or boosters having one or a number of nozzles. The launcher also includes guide rails extending along the length thereof one or more of which has a guide track which precludes missile rotation during launching. The frame members are simple in form being variations of general structural shapes which provide strength, rigidity and partial damping of vertical movement of the launcher when waterborne. The frame members are joined together by longitudinal members such as tubes or structural shapes which are preferably interconnected by braces so as to form a triangular structure thereby utilizing the strongest polygonal shape for the structure.
Referring now to FIG. 1, there is shown the launcher 11 comprising longitudinal members such as tubes 12 which extend from base frame 13 to top frame 15. Longitudinal members such as tubes 12 are joined by welding or other conventional fastening means to frames 13 and 15 and a plurality of intermediate transverse frames 17 which also are generally triangular in shape and are shown in greater detail in FIGS. 3, 4 and 5. Frames 17 are basically of I beam form in cross-section, the web portion 19 performing a dual function of providing strength as well as damping vertical oscillations of the launcher, while the inner flanges 21 and outer flanges 22 thereof combine a maximum of strength with the mini mum use of material. Braces 25 connect apexes of alternate triangular points in the construction while braces 26 provide added strength in areas requiring same, namely, at the base of the structure and substantially at the mid point thereof. The flotation member 30 is preferably attached to the launcher 11 at the extreme upper portion thereof so as to provide maximum hydrodynamic stability of the structure and its contents. In the embodiment shown, flotation member 30 is of a closed-cell foam such as lightweight styrofoam and is formed, as shown in FIG. 3, in a cylinder whose outer periphery extends to the apexes of triangular frames 17. The styrofoam is extended, in the embodiment shown, to the inner flange 21 of end frame 15, the flotation member 30 being secured to the launcher by having tubes 12 and braces 25 included in the solidified foam structure. The flotation member is positioned under the web portion 19 of triangular frame 15 thereby providing sufficient surface upon which i i T the weight of the launcher may be borne and conducted to the flotation member 30. It will be appreciated that other means of flotation such as tanks may be used within the inventive concept, and that such tanks may have means for selective filling to permit towing under appropriate conditions. That is, the tanks which would replace flotation member 30 would be susceptible to partial filling so that the entire structure could be more easily towed. In such a towing operation, a sufficient amount of buoyancy would be retained in the tanks to float a great portion of the weight of the structure while the bottom or base end would be attached to the towing vessel and the weight of that end borne by the towing Howser or cable. The structure presented is compact and light in weight and therefore easily lifted and transported by surface vessel to the proposed area of launch.
A missile 31, or a booster 32 and missile 31, after being inserted into the launcher 11, are supported, when the launcher is in the vertical attitude, by base plate 33 which is shown in greater detail in FIG. 5. The base plate 33 in this particular embodiment is shown having three openings 36 whose primary function is to permit the emanation of exhaust gases from each of the motors of a three-motor booster 32. It will be appreciated that the present embodiment may be enlarged to accommodate two or more missiles, and that other embodiments may accommodate a variety of rocket motors within the scope of the invention.
Base plate 33 is supported by cross members 37 each of which extend from the inner flange 21 of triangular frame 13 to a point at the center of the triangle where they are joined. The cross members 37 also provide support for guide rails 40, 41 and 42 which, as seen in FIGS. 1 and 3, extend from the base plate 33 to the extreme upper frame 15. Guide rails 40, 41 and 42 are joined to each of the transverse frame members 17. A guide such as track 44 is included in one or more of the guide rails, in the present embodiment guide rail 41, with track 44 fitting within a groove 46 in chocks 45, shown in FIG. 2, which are attached to the missile and to the booster. Track 44 prevents rotation of the missile during the launching stage. Brackets 47, 48 and 49 (48 is not seen in FIG. 1) strengthen the upper extremities of guide rails 40, 41 and 42, respectively. Handling members such as eyelets 50 are provided where necessary.
FIG. 2 shows the missile 31 and booster 32 separated from one another to better illustrate the manner in which they are nested together in a close-fitting yet readily separable manner. To accomplish the desired nesting, booster 32 is provided with a ring 53 which is afllxed to the head portion 51 thereof by rods 52. Ring 53 has a raised tapered portion 53a which fits within a mating recess 54 in the missile 31, the tapered portion 53a and recess 54 serving to accurately and firmly position missile 31 atop booster 32. Both the missile and booster are provided with grooved chocks 45 whose groove 46 receives track 44- of guide rail 41. Chocks 45a, without grooves, are also provided on the missile and booster to build out the missile and booster to the envelope diameter of the guide rails and to accept wear from friction occasioned by movement along the guide rails 40, 41 and 42 in lieu of such wear being received by the missile and booster.
FIGS. 3, 4 and illustrate in greater detail frames 13, 17 and 15 with the missile 31 and booster 32 omitted. In FIG. 3, top frame 15 is shown to be constructed of a series of sections 57 which are welded or otherwise joined together as indicated at lines 56 to form the web portion of a composite I beam structure. The inner and outer flange portions of the composite I beam, 21 and 22, respectively, are formed of angle members welded or otherwise joined to the edges of the fiat web portion 19. It will be appreciated that the frames 13, 15 and 17 may be constructed in shapes other than that shown and described, and that these frames may be made more rigid by, for example, welding or otherwise joining angle members along some or all of lines 56, or other such lines within the inventive concept. Flotation member 30 is shown with its curved outer periphery extending to the apexes of frame 15. The inner axial periphery of the flotation member 30 extends, in this embodiment, to inner flange 21, however, it will be appreciated that flotation member 30 could be shaped and extended otherwise than as shown within the concept of the invention. It also will be appreciated that flotation member 30 may be made of other material than styrofoam, for example, of metal tanks, within the scope of the invention. The upper extremities 60, 61 and 62 of guide rails 40, 41 and 42, respectively, are curved or flared to permit some freedom of transverse movement of the missile during insertion into the launcher. Curved apex portions 64, 65 and 66 of frame 15 accommodate the fins of the missile and, in this embodiment, the booster such that the components to be launched are guided by guide rails 40, 41 and 42 with their fin structure or other extremities spaced from the launcher.
In FIG. 4, triangular frame members 17 are shown to have a different configuration from that of frames 13 and 15, the intermediate frames 17 having straight inner flanges 21 while base frame 13 has both its inner and outer flanges 21, 22 straight. Intermediate frames 17 are cut away on their inner flange at apexes 70, 71 and 72 to accommodate the fins of missile 31 and booster 32. It will be appreciated that each of the frames 13, 15 and 17 could have a common configuration within the inventive concept to further simplify construction of the launcher. It also will be appreciated that additional strength could be obtained by including longitudinal members, not shown, extending from top frame 15 to base frame 13 and connected to each of frames 17 at desired points on the outer periphery thereof within the concept of the invention. Base plate 33 is shown in FIG. 5 as receiving support from cross members 37 which, as indicated in FIG. 1, may also be of composite I beam structure. The base frame 13 may be further strengthened in support by angle members 75 which may be welded or otherwise joined to cross members 37. Guide rails 40, 41 and 42 terminate at and are joined to cross members 37, and are spaced apart a distance such that a minimum or nominal clearance of the order of inch is obtained between the outer periphery of the bodies of the missile and booster or the missile alone and the guide surfaces 77, 78 and 79, respectively, of guide rails 40, 41 and 42 as shown in FIG. 4. It is not considered essential to provide lubricants or other friction reducing matter between the surfaces 77, 78 and 79 and the missile body or the booster body.
The center of gravity of the composite of structure 11, missile 31, booster 32 and flotation member 30 is indicated at 82. This center of gravity is spaced a distance below center of buoyancy 84 of the order of 10 to 35 percent of the longitudinal dimension of the launcher to provide a metacentric height through which a desired righting moment may be transmitted to the composite structure. A proper metacentric height is essential to ensure the hydrodynamic stability required to reduce to a minimum the pitching motion of the structure due to wave or sea action, such pitching motion in this usage referring to any deviation of the longitudinal axis of the structure from the vertical.
The operation of the launcher 11 has been extensively described supra, however, what follows is included to complete the description of operation and handling. In preparing the launcher for use, a booster, if one not connected to the missile is to be used, is first inserted between guide rails 40, 41 and 42 and lowered to a position of rest on base plate 33. The missile may or may not be attached to the booster, and if not it is next lowered into position above the booster. After the missile and/or booster have been inserted in the launcher, the launcher then may be lowered into the water by crane or other means which are connected to eyelets 50 or other similar handling members. It will be appreciated that the presence of guide rails 40, 41 and 4-2 throughout the length of the launcher provides considerable lateral as well as longitudinal support for the missile thereby permitting the launcher to accommodate missiles of relatively weak construction as well as missiles more capable of being maintained in various attitudes without additional external support. In addition to such lateral and longitudinal support, when the launcher is immersed or partly immersed in water the guide rails 40, 41 and 42 provide between their guide surfaces 77, 78 and 79 space for the surrounding water to support the missile and booster thereby coddling the missile and protecting it from distortion during the pre-launch stage. The missile, booster and launcher are next lowered into the water and moved if necessary to a desired position through the use of work boats or other motive means. The lattice type of construction, as well as the spacing between guide rails 40, 41 and 42, permits ready access to a great proportion of the missile and/or booster so that they may be serviced while in the launcher whether on board ship or in the body of water from which launching is to be accomplished. The latticework construction also provides a wide variety of locations Where control and monitoring equipment such as remote radio checkout command equipment and other electronic equipment may be supported, serviced and operated. Such equipment may be positioned above or below the Waterline or have components positioned above and below the Waterline where it is necessary that some components not be submerged. Once immersed in the water, the frames 17 and base frame 13 provide, through their transverse web surfaces or portions 19 and the flanges 21 and 22, a very effective damping structure which serves to significantly reduce vertical oscillation due to wave or sea motion. Since the launcher remains in the water after the launching of the missile, it can receive and retain all excess supporting equipment including external remote firing receivers. The missile now may be launched when desired, there being no impediments in the launcher to be removed.
There is thus provided a floating missile launcher whose open structure permits handling both before and after immersion in the water and also provides support for the missile before immersion and permits hydrodynamic support and stability as well as structural support after immersion. The launcher of the present invention is particularly suited for assisting in the launching of missiles which are too weak in construction to be handled and immersed unsupported in the launching medium. Since flotation means for the missile are provided by the launcher and since the flotation means thus are separate from the missile, it will be appreciated that missile construction is simplified and. a number of such missiles may be successively fired from one launcher. The launcher of the present embodiment has been constructed in triangular shape to provide the strongest polygonal shape, however, it will be appreciated that other polygonal shapes may be used within the concept of the invention. Although a minimum of three guide rails has been disclosed in the embodiment described herein, it also will be appreciated that any number of rails may be used, the only limitation on the number of guide rails being the number and positioning of the fins of the vehicle to be inserted in the launcher. The frame members of the launcher are of corrosion resistant metal and therefore a wide variety of material is available for use in the launcher. As stated earlier, either a closed-cell foam plastic flotation member 30 may be used or a gas filled compartment or compartments may pro
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