US3249014A

US3249014A - Flotation and launching harness for water launched missiles

Info

Publication number: US3249014A
Application number: US378079A
Authority: US
Inventors: Raymond S Daughenbaugh
Original assignee: Individual
Current assignee: Individual
Priority date: 1964-06-25
Filing date: 1964-06-25
Publication date: 1966-05-03
Anticipated expiration: 1983-05-03

Description

May 3, 1966 R. S. DAUGHENBAUGH FLOTATION AND LAUNGHING HARNESS FOR WATER LAUNCHED MISSILES Filed June 25, 1964 Fig. 3

IN VEN TOR.

RAYMON D S. DAUGHENBAUGH Cim fr0/m15? United States Patent fce 3,249,014 Patented May 3, 1966 3 249,014 FLOTATION AND LUNCHlNG HARNESS FOR j WATER LAUNCHED MISSILES Raymond S. Daughenbaugh, Oxnard, Calif., assignor to the United States of America as represented by the Secretary of the Navy Filed June 25, 1964, Ser. No. 378,079 12 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.

This invention relates to a floatable launching apparatus for water launched missiles, and more particularly to s uch an apparatus having flotation means which is separable fro`m the missile mechanically upon launch.

j The feasibility of launching Hydra-type missiles from a body of water is well established by U.S. Patent No. 3,077,143 of February l2, 1963 issued to Draim and Stalzer. In most instances, any conventional missile requires external flotation means, in the form of a jacket or the like, for the purpose of floating the missile upright, and Iwith sufficient rolling and dippingV stability in the water to provide a proper launch environment. Since any external flotation means must be discarded from the missile at the start of the launch phase as the missile commences to lift out of the water, some effective disconnecting means must be so provided. The aforementioned patent illustrates two such external flotation means, one

Vbeing doughnut shaped and relying solely on the weight of the missile through braces to support the missile to the flotation means. It has been found that a doughnut shaped flotation means provides little dipping stability to the missile while flotating in the water, and the lack of any positive attaching means between flotation means and missile has limitations during handling and in rough i seas.

Another flotation means heretofore used comprises -an Aelongate jacket formed in segments and secured together around the missile by explosive bolts Venergized at the time of launch to eject apart the segments. Explosive separation is most effective but has certain limitations in that the explosive bolts require an electrical circuit which has to be maintained in a water tight condition, and requires initiation from a remote control station. Accidental forcing of the bolts when the missile is floating in the water in a standby condition will cause loss of the missile, or, on the other hand, failure to release when themissile is launched will probably cause an aborted ,Y flight.

, The present invention provides a flotation and launching harness that eliminates the need for electrical circuits, and the waterproof protection that is necessary in a water A environment. In addition, the instant invention flotation release is accomplished automatically upon a successful missile firing, which provides a safety feature, and avoids possible loss of missile. The harness comprises a flotation jacket constructed of material which is readily severable, i.e. foam plastic, which is supported concentrically to the upper end of the missile. A plurality of circumferentially spaced wires are detachably anchored at one end to the missile and extend. up longitudinally between the missile and the flotation jacket, and around the top of the flotation jacket outwardly and downwardly and anchored at the other end to a plate extending across the nozzle end of the rocket motor. When the rocket motor is ignited the pressure of the exhaust exerted on the plate forces the wires downwardly cutting through the flotation jacket to effectively segmentize the jacket, which segments float free of the missile as it is propelled through the water. The nozzle plate serves also as a sea anchor to provide the missile with dipping stability. Longitudinal straps may be provided having one end anchored to the top of the flotation jacket and the other end anchored to the stabilizing plate for pulling the segments away from the missile path after being cut by the wires, the straps and flotation segments thereafter floating the stabilizing plate and harness for recording purposes.

One object of this invention is to provide a simple flotation and separation apparatus for water launched missiles that eliminates the need for electrical circuits and explosive devices.

Another object of this invention is to provide a simple flotation and separation apparatus for water launched missiles wherein separation occurs automatically when the rocket motor is ignited and builds up a predetermined pressure.

Still a further object is to provide la flotation and separation apparatus wherein the flotation segments are pulled clear of the missile fins, and a corollary object is to permit said flotation segments to enable salvage of the separation apparatus.

A further object is to provide a flotation and separation device which provides vertical stability to the missile while floating in the water.

Other objects, advantages and novel features of the invention will become apparent from the following detailed description of the invention 'when considered in conjunction with the accompanying drawings wherein:

FIG. l is a perspective view of a water launchable missile having attached thereto the flotation and separation apparatus in accordance with the teaching of this invention;

FIG. 2 is an enlarged elevation view, partially in tion, of the stabilizing plate; and

FIG. 3 is an enlarged sectional view taken through the flotation member showing the details of mounting the missile.

Referring to the drawings where like reference numerals designate similar parts throughout the several views, there is shown in FIG. 1 a conventional rocket missile 10 adapted to be launched from a body of water 12. Missile 10 is provided with a flotation jacket 14 which snugly hugs the missile for floatably supporting the missile upright in the water in a launching position, and for floating the missile for towing purposes. Jacket 14 is constructed of a flotation material such as cork or foam plastic which is capable ofV being severed-for a purpose later to be described. Jacket 14 can be constructed in the form of an integral sleeve or ring which can be assembled on the missile by sliding over the nose, or fabricated in segments and assembled around the missile and made integral by cementing etc., or in segments with separable connections.

To secure jacket 14 at the predetermined longitudinal position on the missile, jacket 14 has imbedded at the lower end a plurality of spaced fingers 16 each having a free end which projects beyond the lower end of the jacket and engages a ring 18 encircling the missile skin and secured thereto. Individual lugs could also be used instead of the ring. Fingers 16 and ring 18 perform a dual function, firstly, as a stop to restrain any downward movement of the flotation jacket, and secondly, to provide a hinge joint for the separation procedure that will be later described. Instead of ring 18 or lug, a recess could be provided in the missile skin to receive each free end of fingers 16 which could be bent inwardly, providing a camming action for the hinge connection.

The flotation jacket 14 is pulled downwardly against ring 18 by a harness 20 which also serves to sever the flotation jacket in several segments and eject them from the missile path. Harness comprises a plurality of cutting SeC- cables 22, four being illustrated, equally spaced around the missile periphery. Each cable 22 has one end terminating in a hook 24 which loosely engages the end of the missile skin or any other anchoring mean that may be provided for this purpose. Each cable extends longitudinally up along the missile skin preferably spaced between fingers 16 and missile fins 25 to avoid interference, each cable continuing around the top of jacket 14 and back down to a stabilizing plate or sea anchor 26 where it is hingedly connected to the periphery by means of a pin and eye connection 2S through a turnbuckle 29. A plurality of chafing pads 3f) are applied to flotation jacket 14 at each bearing area where the cutting cables engage the jackets, namely at both ends of the jackets. Pads 30 can be made of fiberglass or the like cemented to the jacket, the pads possessing a predetermined shear strength sufficient to resist any cutting action of the cables during normal handling operations or while floating in the Water, however, the pads being shearable by the cutting cables when the missile is launched. At this time, a sufficient tension is applied on the cutting cables to shear the flotation jacket into a plurality of segments 31, indicated by broken lines, as the missile moves through the water.

Stabilizing plates 26 extends across the mouth of nozzle 32 of the rocket motor preferably extending laterally beyond the nozzle. This construction will proved a sea anchor effect to give the missile dipping stability while floating in the water, and act as a piston on which the exhaust gases react. Plate 26 is preferably configured to be dish-shaped, and may be provided with spaced lugs 34 on the concave inside surface for centering the plate to the nozzle. Stabilizing plate should be symmetrical and centered with respect to nozzle 32 to assure a uniform tension in all of cables 22 during the severing action. A sealing ring 36 can be provided between the nozzle rim and plate 26 to seal against the egress of Water, although such a nozzle will normally be provided with an internal nozzle plug (not shown) for this purpose.

To facilitate the removal of flotation jacket segments 31 from the missile path after the severing action, a plurality of straps 38, at least one for each segment 31 may be provided. Each strap is secured at one end to eyes 40 on the periphery of stabilizing plate and the other end of the strap extends over the top of the flotation jacket and is embedded therein in any suitable manner. Each strap is preferably provided with a series of folds 41 created by stitching 42 having a predetermined strength. When unfolded, folds 41 provide sufficient slack in the straps at the initial thrust build up of the missile to enable the severing actions of cables 22 to be completed before the straps yank segments 31 free of the missile path.

Flotation jacket 14 and harness 20 are assembled to missile prior to being lowered into the water, the necessary adjustment in the tension in cutting cables 22 being performed through turnbuckles 29. If it is necessary to tow the missile and flotation and separation apparatus in the water to the launch site, the entire assembly should be towed with the stabilizing plate being forward. As the missile floats in the water at the launch site, the stabilizing plate provides a restraining force on the vertical dipping motions of the missile assembly. Any force exerted by the holding action of the cutting cables on the top of the flotation jacket as the missile bobs in the water is resisted by bearing pads 30. When the rocket motor is fired, downward thrust of the exhaust gases is exerted on stabilizing plate 26 forcing cutting cables 22 downward to overcome the resistance of pads 30 and commence slicing or tearing the flotation jacket into segments 31, while at the same time the upward movement of the missile moves the flotation jacket away from the cables. If desired the flotation jacket could be partially scored to facilitate the severing action. The tension on straps 38 starts to rip stitching 42 to unfold the slack strap material until the segments are completely severed at which time the tension on the straps flips the segments laterally outwardly, each segment pivoting on fingers 16. At this time the absence of tension in cutting cables 22 enables the hooks 24 to fall free of the missile as the missile is propelled upwardly in the water free of the flotation jacket.

The flotation jacket sevments 31 still being connected to stabilizing plate 26 through straps 38 permit the entire harness to float and be recovered and reused.

The instant flotation and severing `apparatus of this invention provides a simple and reliable manner of disconnecting the flotation means from a water launched missile. Reliability is greatly enhanced by the absence of any electrical circuitry, and the need to waterproof such equipment, for either transmitting or initiating the separation action. The flotation jacket cannot be accidentally released unless the rocket motor is fired and a sufficient thrust developed to sever the jacket. The flotation jacket will remain assembled about the missile and in operable condition if accidentally damaged as long as a major portion of the jacket remains about the missile. Salvage of the harness components provides a bonus in savings of operational costs.

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.

I claim:

1. In combination with a water launchable missile having a rocket nozzle and a propellant charge for exhaust through said nozzle, a launching apparatus comprising:

flotation means encompassing sa-id missile;

said flotation means being constructed of material at least a portion of which is severable by a predetermined force;

separable means for supporting said flotation means on the missile;

severing means for separating said flota-tion means into segments; and

means operable by the force generated -by the exhaust gases from said missile propellant charge for actuating said severing means; whereby the flotation means can be separated from the missile upon missile launching.

2. The combination of claim 1 wherein said severing means includes a plurality of cutting cables.

3. The combination of claim 2 wherein said severing means includes a plate positioned in the path of the nozzle exhaust to which an end of each cable is anchored.

4. The combination of claim 1 wherein means are provided for ejecting said segments from the missile.

5. In combination with a water launchabile missile having a rocket nozzle and a propellant charge for exhaust through said nozzle, a launching apparatus comprising:

a flotation jacket encompassing said missile;

said jacket being constructed of material being severable by a predetermined force;

separable means for supporting said flotation jacket to the missile;

a plurality of severing cables for separating said jacket into segments; and

means operable by the force generated by the exhaust gases from said missile propellant charge to actuate said severing means; whereby the flotation jacket can be separated from the missile upon missile launching.

6. The combination of claim 5 wherein said separable means comprises hinge members at the lower end of said jacke-t, at least one pair of hinge members for each segment.

7. In combination with a water launchable missile having a rocket nozzle, a launching apparatus comprismg:

a flotation jacket encompassing said missile; said jacket being constructed of material being severable by a predetermined force; separable hinge means for supporting said flotation jacket at the lower end to the missile; cable means for sep-arating said jacket into segments; each segment having a hinge means; a stabilizing plate; said cables having one end connected to the stabilizing plate and the other end extending around the upper end of the jacket and detachably anchored to the missile for supporting the plate against the nozzle; whereby the force generated by the nozzle exhaust gases will exert a downward force on the plate forcing the cables to sever said dotation jacket.

8. The combination of claim 7 wherein said stabilizing plate has means for seating the mouth of the nozzle. 9. The combination of claim 7 wherein a plurality of straps are provided, the ends of each strap being anchored to the plate and to each jacket segment respectively.

10. The combination of claim 8 wherein each strap has means for a predetermined extension of its length. 11. A launching apparatus for a water launchable missile having a rocket exhaust nozzle comprising in combination:

a flotation jacket for encompassing said nozzle; said jacket being constructed of material being severable by a predetermined force; a plurality of cables for separating said jacket into segments; a stabilizing plate adapted to be held against the mouth of sa-id rocket nozzle; one end of each cable secured in spaced relation around the periphery of said plate; the other end of each cable having detachable means for securing to the missile. 12. The launching apparatus of claim r11 wherein a plurality of straps are connected between the stabilizing plate and the flotation jacket.

References Cited by the Examiner UNITED STATES PATENTS 2,831,400 4/1958 Hosli 89-1.7 2,876,678 3/1959` Lyon 89-1.7 3,077,143 2/ 1963 Draim et al 89-l.7

BENJAMIN A. BORCHELT, Primary Examiner.

SAMUEL W. ENGLE, Examiner.

Claims

7. IN COMBINATION WITH A WATER LAUNCHABLE MISSILE HAVING A ROCKET NOZZLE, A LAUNCHING APPARATUS COMPRISING: A FLOTATION JACKET ENCOMPASSING SAID MISSILE; SAID JACKET BEING CONSTRUCTED OF MATERIAL BEING SEVERABLE BY A PREDETERMINED FORCE; SEPARABLE HINGE MEANS FOR SUPPORTING SAID FLOTATION JACKET AT THE LOWER END TO THE MISSILE; CABLE MEANS FOR SEPARATING SAID JACKET INTO SEGMENTS; EACH SEGMENT HAVING A HINGE MEANS; A STABILIZING PLATE; SAID CABLES HAVING ONE END CONNECTED TO THE STABILIZING PLATE AND THE OTHER END EXTENDING AROUND THE UPPER END OF THE JACKET AND DETACHABLY ANCHORED TO THE MISSILE FOR SUPPORTING THE PLATE AGAINST THE NOZZLE;