US3340767A - Missile flotation ejection means - Google Patents

Description

A Z N E P I s MISSILE FLOTATION EJECTION MEANS 5 Sheets-Sheet 1 Filed Nov. 29, 1965 INVE/VTO/P. SA LVATORE J. PENZA BYC y-AGfNT 2% ATTORNEY EQW- s. J. PENZA 3,340,767

MISSILE FLOTATION EJEGTION MEANS Filed Nov. 29, 1965 5 Sheets-Sheet 3 i 52--- 4O INVENTOR.

SALVATORE J. PENZA BY @fW QJ'5WW A r Tom/E r 3,34%,767 V Patented Sept. 12, 1967 3,340,767 MISSILE FLOTATION EJECTION MEANS Salvatore J. Penza, Oxnard, Califi, assignor to the United States of America as represented by the Secretary of the Navy Filed Nov. 29, 1965, Ser. No. 510,471 7 Claims. (Cl. 891.809)

ABSTRACT OF THE DISCLOSURE A releasable flotation means for water-launched missiles, rockets and other vehicles wherein the vehicle is hung from the flotation means at a point well below the center of buoyancy of the flotation material. At the time of launch, this flotation material is held against the vehicle only by the force of buoyancy. When firing occurs and the vehicle begins to rise, the flotation means first falls a short distance and then is ejected outwardly away from the vehicle body so as not to interfere with the launching operation.

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.

This invention relates to means for suspending a missile or other object for launch from a body of water, and more particularly to means for releasing such object from the suspension means as it is launched.

Missiles are being launched from the water with increasing frequency because of the many advantages of water over land launching. However, in most instances, missiles launched from water require supplemental flotation and support means of various forms and ordinarily these help provide missile stability and limit the rolling and bobbing of the missile in its water environment.

Such flotation means must however be jettisoned from the missile as the missile is launched from the water, and to accomplish this without interfering with missile flight requires effective disconnect means and methods. One example of prior external flotation means is the use of a doughnut shaped buoyant mass surrounding and connected to the upper portion of the missile. Such flotation means may comprise a buoyant jacket formed of several segments which are normally secured together around the missile and upon launch can be forcibly ejected away from the missile by explosive means. These doughnut shaped flotation means have been found to provide little vertical stability to the missile and the lack of positive attaching means between the flotation means and the missile introduces serious handling problems, especially in rough seas. The use of explosive means to insure positive separation of the float from the missile has definite limitations in that electrical circuits generally are required thereby introducing the possibility of malfunction both in the electrical circuit and in the burning of the explosive.

The present invention provides a releasable flotation means which eliminates the need for explosive devices, electrical circuits and complicated release mechanisms to free the missile at launch. Flotation release occurs positively and automatically when the weight of the missile is relieved from or transferred from the flotation material. According to the principle of the present invention the missile is hung from the suspending flotation at a point well below the center of buoyancy of the flotation material. At the time of launch the flotation material therefore is held against the missile only through the force of buoyancy acting through a lever arm determined by the displacement of its center of buoyancy from the composite center of gravity of missile and flotation. Immediately upon launch the missile starts upwardly through the flotation material to direct the latter outward due to the flotation suspension arrangement and its anchoring means. It is therefore an objective of the present invention to provide means for supporting a suspended object wherein the support means is propelled away from the object by relative movement of the parts.

Another objective of this invention is to provide buoyant suspension means for suspending objects in which an oflset center of gravity of the buoyant means is utilized to enhance its separation from the object.

A further objective of the invention is to provide a flotation device which provides missile vertical stability while floating in the water and includes means actuated by the force of gravity alone for clearing the missile as it rises above the water.

Other objectives and many of the 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 numerals designate like parts throughout and wherein:

FIG. 1 is a perspective view from above showing a missile supported by the flotation device of the present invention;

FIG. 2 is an enlarged side elevation showing how the float means of FIG. 1 is connected to the missile;

FIG. 3 is a side elevation showing how the buoyant material is propelled clear during missile launch;

FIG. 4a is an enlarged detailed perspective view showing the position of the missile to flotation gear disconnect assembly when the missile is being supported in the water;

FIG. 4b is a similar view with the missile starting to move upwardly during launch;

FIG. 40 is a view showing the relationship of the parts when the flotation gear is substantially clear of the missile; and

FIG. 4d shows the final step of actual disengagement of the flotation gear.

Referring to the drawings, there is shown in FIG. 1 a conventional missile 11 adapted for launching from a body of water 12 Missile 11 is provided with flotation means 13 in the form of buoyant material divided into sections each of which is normally held against the missile when providing missile buoyancy during towing procedures as well as during pre-launch phases up to the time of launching. The buoyant sections are each anchored at the bottom by rod assemblies 16 and during towing and pre-launch phases the buoyant material may ba secured at the top by a quick-release retaining band such as strap 17 shown in FIG. 2. Also during towing and pre-launch phases the missile may, if desired, be provided with aft flotation means, not shown, which when removed permit the missile to orient itself vertically in the water.

As seen in FIGS. 1 and 3, missile encircling flotation means 13 may comprise a plurality of buoyant sections 18 and in the embodiment illustrated each section is a quadrant. The buoyant material may be a hollow chamber, a block of plastic or other suitable buoyant material. Sections 18 are shown symmetrically disposed about the missile with each section releasably connected to the missile in at least two locations, one at the top and one below. In the upper location the sections preferably are provided with tongues 20 each of which rests in a U- shaped bracket or keeper 21 mounted on the missile. Adjustable retaining band 17 passes over each tongue to hold it in its keeper and may be provided with a turnbuckle or toggle 24 for tightening the band to a desired tension. This toggle may readily be released and the band removed after the missile is waterborne and in a vertical position. Wing bolts 25 may be employed to take up slack and apply initial tension on band 17. Any suitable number of flotation sections 18 may be employed and they may vary somewhat in shape within the concept of this invention. In the embodiment illustrated, flotation sections 18 rest against the missile on their inner surfaces and have substantially parallel upper and under surfaces 27 and 28, respectively.

Anchoring of the lower portion of the flotation sections is accomplished through four sets of rods 16, three such sets being shown in FIG. 2, each set of rods is joined at their lower ends by a coupling 29 and are pivotally connected at their upper ends to the under surface 28 of sections 18 by longitudinally adjustable clevis ends 30. Pad eyes 31 on under surface 28 are connected to the clevis ends by pins 32. Three rods are shown comprising each assembly 16 but it will be appreciated that a different number of rods may be employed if desired. A T-bolt 33 having a threaded stem 34 and a crossbar 35 extends from each coupling 29 and is secured thereto by nut 36. Crossbar 35 normally is received in the upper flange 38 of a missile mounted anchor plate 37, flange 38 being cut away at slot 39 to receive stem 34. Anchor plate 37 has a lower flange 40 which in this embodiment is spaced a greater distance from the adjacent surface of missile 11 than upper flange 38. Flotation 13, rod assemblies 16, coupling 29 and anchor plate 37 are shown in FIG. 2 as they appear when carrying the weight of missile 11. Anchor plate 37 is provided with side panels 41 and is secured at an acute angle A to the missile by brackets 42, the size of angle A being determined by the weight and volume of the missile and flotation and the trajectory desired of jettisoned flotation sections 18. Anchor plate 37 may have a continuous face 44 along which crossbar 35 slides during jettisoning as will be explained in the description of operation.

FIG. 4a presents the flotation disconnect assembly as it is the instant before flotation 13 ceases to support the missile and is an enlarged detailed view of anchor plate 37 and T-bolt 33 as they are shown in FIGS. 1 and 2. FIG. 4b illustrates the position of T-bolt 33 relative to anchor plate 37 a short time after the missile has begun to rise, the flotation and its connecting assemblies remaining in the water. Arrow 45 indicates the direction of motion of crossbar 35 along surface 44 and arrow 46 indicates the initial rotary movement of stem 34 about the longitudinal axis of crossbar 35. In FIG. 40 crossbar 35 has been forced upward from the extreme downward position shown in FIG. 3. The condition shown in FIG. 3 exists only momentarily since the buoyant sections are rotated outward and downward as flanges 40 urge crossbars 35 upward. Continued upward movement of anchor plate 37 produces an upward movement of crossbar 35 indicated by arrow 48 and an increased downward movement of stem 34 as indicated by arrow 48 and an increased downward movement of stem 34 as indicated by arrow 49. FIG. 4d shows T-bolt 33 being flipped away from the missile by the action of flange 40 as indicated by arrows t) and 51, the movement of the crossbar out of the anchor plate being indicated by arrow 52.

In operation, flotation 13 preferably is attached to the missile at a desired location either on land or aboard ship before the missile and flotation are lowered into the water. Tongues 20 on the forward end of the flotation will have been secured into keepers 21 on the missile and crossbar 35 of T-bolt 33 will be retained in place under flange 38 of anchor plate 37. When the missile is ready for firing, strap 17 is released after which the missile is held suspended by the force of buoyancy which urges cross-bar 35 into upper flange 38. When firing occurs and the missile begins to rise the sections fall away from the missile and by engagement of the crossbar 35 with lower flange 40 the sections are rotated sideways outwards. Side panels 41 inhibit tipping of crossbar 35 in the anchor plate during flotation section ejection processes.

It will be recognized that 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. Iclaim: 1. A device for releasing material suspending a missile in water when the weight of the missile is removed from the material comprising:

suspension means releasably attached to said missile, said suspension means being formed into at least two sections oppositely positioned about the missile;

said suspension means retained at its upper extremity .against said missile during pre-suspension phases of missile handling;

receiving means on said missile for releasably receiving the lower extremity of said suspension means during suspension phases of missile handling;

said receiving means adapted to slidably direct the downward movement of the lower extremity of said suspension means for a predetermined distance when the weight of the missile is removed therefrom;

said receiving means adapted to induce rotary movement of said suspension means by causing upward movement of the lower extremity thereof at the termination of the downward movement directed by said receiving means;

the upper portion of the sections of said suspension means comprising buoyant material and the lower portion of said sections comprising means engaging the buoyant material with the receiving means at a point spaced from the lower extremity of the buoyant material;

said engaging means being adjustable for securely positioning the buoyant material about the missile while the buoyant material is retained at its upper extremity against the missile; whereby said suspension means is jettisoned away from the vicinity of said missile when the weight of the latter is removed from the suspension means; and

wherein said engaging means includes at its lower extremity a member in the form of a crossbar disposed transverse to the longitudinal axis of the missile;

said member precluding rotation of said buoyant material about axes substantially parallel to the longitudinal axis of the missile.

2. The device as defined in claim 1 wherein said transverse member is disposed a substantial distance with respect to the distance between the upper and lower extremities of the buoyant material from the lower extremity of said buoyant material.

3. The device as defined in claim 2 wherein said engaging means includes a plurality of connector assemblies connecting spaced portions of the lower extremity of said buoyant material to a coupling means remotely spaced from such lower extremity; and

means connecting said coupling means to said transverse member.

4. The device as defined in claim 3 wherein said receiving means has upper weight supporting means disposed a selected distance from the longitudinal axis of said missile and lower intercepting means for urging said transverse member away from the vicinity of the missile after the weight of the missile has been removed from said sections of buoyant material.

5. The device as defined in claim 4 wherein said intercepting means is disposed at greater distance from the longitudinal axis of said missile than said selected distance.

6. The device as defined in claim 5 wherein said receiving means includes a surface disposed at an angle to the adjacent surface of said missile and adapted to slidably receive the lower etxremity of said engaging means.

8,340,767 5 6 7. The device as defined in claim 6 wherein said re- References Cited ceiving means has a flat intermediate portion, upper weight UNITED STATES PATENTS supporting means in the 'form of a downwardly-curved 3 208 346 9/1965 Penza et a1 89 1 809 flange on said receiving means and lower intercepting 3 249 014 5/1966 Daughenbaugh means in the form of an upwardly curved flange on said 5 receiving means. SAMUEL W. ENGLE, Primary Examiner.

Claims (1)

1. A DEVICE FOR RELEASING MATERIAL SUSPENDING A MISSILE IN WATER WHEN THE WEIGHT OF THE MISSILE IS REMOVED FROM THE MATERIAL COMPRISING: SUSPENSION MEANS RELEASABLY ATTACHED TO SAID MISSILE, SAID SUSPENSION MEANS BEING FORMED INTO AT LEAST TWO SECTIONS OPPOSITELY POSITIONED ABOUT THE MISSLE; SAID SUSPENSION MEANS RETAINED AT ITS UPPER EXTREMITY AGAINST SAID MISSILE DURING PRE-SUSPENSION PHASES OF MISSILE HANDLING; RECEIVING MEANS ON SAID MISSILE FOR RELEASABLY RECEIVING THE LOWER EXTREMITY OF SAID SUSPENSION MEANS DURING SUSPENSION PHASES OF MISSILE HANDLING; SAID RECEIVING MEANS ADAPTED TO SLIDABLY DIRECT THE DOWNWARD MOVEMENT OF THE LOWER EXTREMITY OF SAID SUSPENSION MEANS FOR A PREDETERMINED DISTANCE WHEN THE WEIGHT OF THE MISSILE IS REMOVED THEREFROM; SAID RECEIVING MEANS ADAPTED TO INDUCE ROTARY MOVEMENT OF SAID SUSPENSION MEANS BY CAUSING UPWARD MOVEMENT OF THE LOWER EXTREMITY THEREOF AT THE TERMINATION OF THE DOWNWARD MOVEMENT DIRECTED BY SAID RECEIVING MEANS; THE UPPER PORTION OF THE SECTIONS OF SAID SUSPENSION MEANS COMPRISING BUOYANT MATERIAL AND THE LOWER PORTION OF SAID SECTIONS COMPRISING MEANS ENGAGING THE BUOYANT MATERIAL WITH THE RECEIVING MEANS AT A POINT SPACED FROM THE LOWER EXTREMITY OF THE BUOYANT MATERIAL; SAID ENGAGING MEANS BEING ADJUSTABLE FOR SECURELY POSITIONING THE BUOYANT MATERIAL ABOUT THE MISSILE WHILE THE BUOYANT MATERIAL IS RETAINED AT ITS UPPER EXTREMITY AGAINST THE MISSILE; WHEREBY SAID SUSPENSION MEANS IS JETTISONED AWAY FROM THE VICINITY OF SAID MISSILE WHEN THE WEIGHT OF THE LATTER IS REMOVED FROM THE SUSPENSION MEANS; AND WHEREIN SAID ENGAGING MEANS INCLUDES AT ITS LOWER EXTREMITY A MEMBER IN THE FORM OF A CROSSBAR DISPOSED TRANSVERSE TO THE LONGITUDINAL AXIS OF THE MISSILE; SAID MEMBER PRECLUDING ROTATION OF SAID BUOYANT MATERIAL ABOUT AXES SUBSTANTIALLY PARALLEL TO THE LONGITUDINAL AXIS OF THE MISSILE.

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