US3158062A

US3158062A - Missile container and launcher

Info

Publication number: US3158062A
Application number: US845752A
Authority: US
Inventors: Alfred M Feiler
Original assignee: Pneumo Dynamics Corp
Current assignee: Pneumo Dynamics Corp
Priority date: 1959-10-12
Filing date: 1959-10-12
Publication date: 1964-11-24
Anticipated expiration: 1981-11-24

Description

Nov. 24, 1964 A. M. FEILER 3,158,062

MISSILE CONTAINER AND LAUNCHER Filed Oct. 12, 1959 3 Sheets-Sheet 1 INVENTOR.

ALFRED M. FEILER ATTORNEY Nov. 24, 1964 A. M. FEILER 3,158,062

MISSILE CONTAINER AND LAUNCHER Filed Oct. 12, 1959 3 Sheets-Sheet 3 INVENTOR Y ALFRED M. FEILER ATTORNEY United States Patent Office 3,158,962 MHSSILE CUNTAHNER AND LAUNCHER Alfred M. Feller, Palisades, Qalih, assignor, by ruesne assignments, to Pneumo Dynamics Corporation, Cleveland, Ohio, a corporation of Belaware Filed Oct. 12, 1959, Ser. No. 845,752 6 Claims. (Cl. 89-1.?)

This invention relates generally to missile handling devices and more particularly to a new and improved unitary transporting and launching combination in which a missile can be transported to a submerged firing location and thereafter fired.

It is an important object of this invention to provide a unitary missile transporting and launching device.

It is another important object of this invention to provide a missile transporting device suitable for transporting missiles on land or submerged in water.

It is another important object of this invention to provide a missile transporting and launching device capable of launching a missile from a submerged position in the ocean and the like.

It is another important object of this invention to provide a missile transporting and launching device including means to maintain an internal pressure within the launcher which is substantially equal to the pressure of the surrounding environment.

It is another important object of this invention to provide a missile transporting and launching device ineluding means to eject the missile from the launcher when both are submerged.

Generally, self-propelled missiles are transported in sealed containers which are constructed to be capable of resisting expected loads and shocks which may be applied during the handling and transportation of the cargo in air-borne or surface-borne vehicles. When preparing the missile for launching, the missile is usually transferred from the sealed container into a launching means which may be a submerged or submersible launching tube. This requires special handling of the missile in preparation for the firing.

In a transporting and launching device according to this invention, the special launching means are eliminated and all of the launching functions are performed by and in association with the transporting container.

According to this invention, the transporting and launching device includes a launching tube which is constructed to resiliently support and protect the missile during air transport and during surface transport by land vehicle or ship. The launching tube is further constructed to be capable of supporting and protecting the missile While the tube is being towed to sea either on the surface or submerged. Means are provided to resiliently support the missile cargo Within the launching tube against surface or submarine shocks. Due to logistics considerations, the missile and its transporting devices should be as light as possible commensurate with the primary functions of the system. In transporting the launching devices according to this invention, a substantial reduction of Weight of the transporting component or fluid tight housing is achieved by the use of means which maintain the hydrostatic pressure within the housing substantially equal to the exterior pressure on the housing. The balancing of the two pressures permits the construction of the launching device in the lightest possible manner since it is not required to withstand substantial external hydrostatic pressure.

Further objects and advantages will appear from the following description and drawings, wherein:

FIGURE 1 is a side elevation illustrating the missile transporting and launching device in a submerged position prior to the firing of the missile;

33,158,062 Patented Nov. 24, 1964 FIGURE 2 shows the missile after it has been ejected from the launcher prior to the firing of the missile rockets;

FIGURE 3 is a View similar to FIGURES 1 and 2 showing the rocket after it has passed through the surface of the water under the power of its propulsion rockets;

FIGURE 4 is a side elevation in longitudinal section illustrating the structure of the missile transporting and launching device with the missile contained therein;

FIGURE 5 is an enlarged fragmentary View of the control system used to balance the internal pressure of the missile launcher with the exterior environment pressure;

FIGURE 6 is an enlarged fragmentary view illustrating one form of the connecting cable used to supply data to the missile prior to the launching and to control the operation of the launching mechanism; and

FIGURE 7 is an enlarged fragmentary view of the system used to eject the missile from the launcher during the firing operation.

Referring to FIGURES 1 through 3, the launcher includes a housing 9 comprising a cylindrical body 10 closed at one end by a hinged nose cap 11 and at the other end by a conical end member 12. The body It? is provided with four longitudinally extending rails 13 each or" which is connected to the body It by spaced struts 14. The rails 13 can be used for the handling and shipping of the launcher and as a travelling stand.

In normal towing operations, a tow line is connected to a swivel eye 18 on the conical end member 12. When the missile 21 is to be launched, it is anchored in a vertical submerged position as shown in FIGURE 1. When the launcher is in the submerged and anchored position, the launcher remains substantially vertical so that the hinged nose cap 11 is at the upper end. In order to insure that the submerged housing will float in a vertical position, the mechanism is constructed so that its center of gravity G is horizontally aligned with the lateral center of pressure P and the center of buoyancy B is axially displaced above the center of gravity.

An anchoring yoke 17 is pivotally connected to trunnions 15 so that it can pivot about an axis 16' which passes through the center of gravity G. The yoke 19 is in turn connected to suitable anchor means by a cable 19. Therefore, the device will remain in the vertical position shown regardless of whether or not ocean currents are present. The yoke 17 is provided with arms having a length greater than one-half of the length of the housing below the trunnions 15 so the housing is able to oscillate freely about its center of gravity. In FIGURES 1 through 3, the launcher is shown as it would be anchored in a relatively strong current.

When the missile 21 is to be fired, the hinged nose cap 11 is opened and a charge of compressed air ejects the missile from the launcher. Because the launcher is submerged in the ocean, it moves downward as the missile moves upward. After the missile 21 is clear of the launcher, the missile propulsion rockets are fired to propel the missile up through the surface of the ocean as shown in FIGURE 3.

The general structural arrangement of the transporting and launching device is shown in FIGURE 4. A launching tube 22 is resiliently suspended within the housing 9 for limited movement relative thereto. This cushions the missile 21 so that it is not damaged by impacts on the housing. To provide resilient support of the launching tube, a plurality of S-shaped leaf springs 23 are connected between the main cylindrical body 10 and the launching tube 22. The interior of the main cylindrical body 1d and the exterior of the launching tube 22 is formed with

stiffening ribs

24 and 26 respectively. Preferably, the springs 23 are connected between adjacent rib sections on the cylindrical body ill and the launching L) tube 22. By using springs of the type shown, the launching tube 22 can move in all three planes relative to the cylindrical body 10.

Thenose cap 11 is hinged to the cylindrical body 10 for rotation about a hinge pivot 27 and is secured in the closed position by a series of explosive bolts 23 which extend through

co-operating flanges

29 and 31 on the cylindrical body 10 and the nose cap 11 respectively. A seal 32, shown in FIGURE 5, prevents leakage between the cylindrical body 10 and the nose cap 11. In order to insure that the nose cap 11 will pivot clear of the end of the launching tube 22 during the firing sequence, a tension spring 33 is located within one of the rails 13 and is connected between its associated rail 13 and a pull 7 i-c1134. The pull rod 34 is pivotally connected at 36 to an.

arm 37 formed on the nose cap 11. Once the explosive bolts 28 are fired to release the nose cap, the spring 33 operates to pull the nose cap to the open position shown in FIGURES 2 and 3.

In order to maintain the internal pressure within the transporting launcher at a pressure substantially equal to the environmental pressure, an automatic system, shown best in FIGURE 5, is used. The nose cap 11 is formed with an inner wall 38 which co-operates with an outer wall 39 to define a high pressure chamber 41. This chamber is charged with a suitable gas or liquefied gas and provides a reservoir for pressurizing the interior of the device. A pressure regulator 42 is mounted on the outer wall 39 and connects through a tube 43 to the interior of the cylindrical body 10.

Various types of pressure regulators could be used;

however, the type shown in FIGURE is one simple version which would adequately perform the required function. The illustrated pressure regulator includes a housing 44 mounted on the outer wall 39 and a flexible diaphragm 46 which co-operates with the housing 44 to define a regulating chamber 47. The outside of the diaphragm 46 is exposed to the environmental pressure through an opening 48 in the outer wall 39. The tube 43 connects the regulating chamber 47 to the interior of the cylindrical body 10. Therefore, one side of the diaphragm is exposed to the pressure within the cylindrical body and the other side is exposed to the environmental pressure. A valve member 49 is mounted on the diaphragm 46 and is formed with a head which engages an exterior valve seat 51 on the housing 44. When the pressure within the regulating chamber 47 exceeds the environmental pressure, the diaphragm 46 moves the valve member 49 into engagement with the valve seat-51 which prevents flow from the high pressure chamber 41 into the regulating chamber 47. However, when the pressure within'the regulating chamber 47 drops below the environmental pressure, the diaphragm 46 moves the valve member 49 away from the valve seat 51 and permits flow from the high pressure chamber 41 into the regulating chamber 47 and into the interior of the cylindrical body 10.

The regulator 42 can only operate to increase the pressure within the cylindrical body 10 as the environmental pressure surrounding the launcher increases which occurs when the depth of submersion of the housing is increased. If the pressure within the launcher exceeds the environmental pressure which occurs when the submerged depth of the launching device is decreased, a check valve 52 mounted on the nose cap 11 opens to bleed off the excess pressure. The co-operation between the check valve 52 and the pressure regulator 42 insures that the internal pressure of the launcher will be maintained at substantially the same pressure as the environmental pressure. Because the internal and external pressures are maintained substantially equal, the cylindrical body and the other portions of the launcher are not exposed to either bursting or crushing stresses so a very light cylindrical body can be used.

A control cable receptacle 53, shown in FIGURE 6,

is mounted on the cylindrical body It) to provide a watertight connection with a flexible control cable 54. An 0- ring seal 56 prevents leakage between the control cable 54 and the receptacle 53 and a suitable clamp 57 secures the control cable to the receptacle. The control cable 54 is used to feed firing data to the missile 21 and to control the operation of the various mechanisms within the launcher from a remote control station.

The remote control station would normally be the controlling submarine which would be nearby during the firing operations. As an alternate, the cable 54 could connect to a submersible buoy which is adapted and equipped with means to receive control and programming signals and transmit them through the control cable to the laupching mechanism. This buoy could incorporate surfacing means adapted to render the buoy buoyant at regular intervals or upon receipt of an external command which may be embodied in a pre-arranged sequence of submarine sonic vibrations. The buoy may further be adapted to submerge either by command or automatically at a given period of time at the surface. It will be understood that when the buoy is surfaced, the required control signals may be applied by either radio means or by direct contact control which is temporarily connected to the buoy. The control cable is shown connected to the missile 21 by a detachable lead 58 and to control elements 59 mounted on the lower end of the launching tube 22. This mounting of the control elements 59 provide the shock protection of the resilient mounting of the launching tube 22 within the cylindrical body 10.

In order to axially secure the missile 21 within the launching tube 22, the missile is provided with an axially extending tubular projection 61 threaded into an inner wall 62 at 63 on the launching tube 22. The inner wall 62 co-operates with an outer wall 64 to define a high pressure chamber 66 in which pressurized gas is stored. This gas is used during the firing sequence to eject the missile 21 from the launching tube 22. Normally, the rocket motors within the missile 21 will not be fired until the missile is completely free of the launching mechanism. In order to carry the axial stresses of supporting the missile 21 and to provide a passage for high pressure gases, a centrally located tube 67 extends between the inner wall 62 and the outer wall 64 and is open to the tubular projection 61 on the missile 21.

An explosive operated valve 68, of the type shown in the co-pending application Serial No. 775,281 filed November 20, 1958, now US. Patent No. 2,997,051, assigned to the assignee of thisinvention, is mounted on the inner wall 62. This valve, when operated, connects the pressurized chamber 66 to an ejection chamber 69 between the inner wall 62 and an ejection piston 71. The ejection piston 71 is provided with a seal 72 which prevents leakage between the piston 71 and the inner wall of the launching tube 22. The piston is also provided with an annular skirt 73 which engages the lower end of the missile 21 to distribute the ejection load through the missile.

When the compressed gas is admitted into the ejection chamber 69, a force is developed on the piston 71 which causes the piston and missile 21 to move upwardly along the launching tube out of the launching mechanism. The tubular projection 61 is formed with a frangible section within the ejection chamber 69 which is sheared by detonation of a primer cord 74. The valve 68 and the primer cord 74 are detonated at the same time so that operation of the valve results in the pressurization of the ejection chamber 69 and of the interior of the tube 67 simultaneously.

During the handling of the missile and the transportation thereof to the launching site, it is necessary to permit relative axial movement between the launching tube 22 and the cylindrical body is but during the firing, the launching tube should be axially locked relative to the cylindrical body. The mechanism for accomplishing the locking function includes a cylinder 76 integrally formed on the launching tube and a co-operating piston 77 axially movable within the cylinder. The piston is connected through a piston rod 78 to a tie bar 79 by a ball socket joint 81. The other end of the tie bar 79 is connected by a similar ball socket joint 82 to the conical end member 12. The use of a tie bar with ball socket joints is necessary because the launching tube 22 and in turn the piston 77 must be free to move radially relative to the cylindrical body 10. The piston rod 78 extends through the piston 77 into the tube 67 so that both sides of the piston 77 will have the same eifective area. Glands 83 are mounted on each end of the cylinder 76 to provide a fiuid seal with the piston rod 78.

The two ends of the cylinder 76 are connected through passages 84 and a flow restricting orifice S6. The cylinder 76 is filled with oil and in normal operation, axial movement of the piston 77 displaces oil through the passages 84 and the orifice 86. Therefore, the cylinder 76 and the piston 77 co-operate to provide a hydraulic damper which normally resists axial movement between the launching tube 22 and the conical end member 12. In order to prevent any axial movement between the launching tube 22 and the conical end member 12 during the ejection of the missile 21 from the launching tube, a hydraulic lock is provided. This includes a pneumatically operated valve 87 which moves into engagement with the orifice 86 to prevent flow between the two ends of the cylinder 76 during the ejection of the missile 2E. The valve 87 is formed with a head 88, the rearward side of which is connected to the interior of the tube 57 through a passage 8?. A spring 91 normally maintains the valve 87 in the position shown in FIGURE 7 displaced from the orifice 86 but when the pressure within the chamber 66 is admitted into the interior of the tube 67, the valve 87 is displaced against the action of the spring 91 to close the orifice 86 and provide the necessary hydraulic lock.

In operation, the missile 21 is stored within the launching tube 22 as shown in FIGURE 4. The missile can be transported by land, air, or sea to the launching site and submerged below the surface of the ocean. Prior to the launching of the missile 21, the necessary control data is fed into the control system of the missile through the control cable 54. The operation of the pressure regulator 42 and the check valve 52 maintains an internal pressure within the launcher equal to the environmental pressure thus preventing excessive pressure strains from being applied to the housing.

When the missile is to be launched, a series of simultaneous operations take place. The explosive bolts 28 are detonated to release the nose cap 11 so that it can be opened by the tension spring 33. At the same time, the valve 68 is operated and the primer cord 74 is detonated to release the axial connection between the missile 21 and the launching tube 22. The pressure within the ejection chamber 69 causes the ejection piston 71 to move the missile 21 out of the launching tube 22. At the same time, this pressure operates the valve 87 to hydraulically lock the piston 77 so that the launching tube 22 cannot move relative to the cylindrical body 10. When the missile 21 is clear of the launching tube 22, the rocket motors of the missile 21 are fired. This causes the piston 71 to be ejected from the end of the missile so that the missile is completely free of the launching mechanism.

Those skilled in the art will recognize that the use of a transporting and launching device according to this invention eliminates the necessity of special handling to transfer the missile from the transporting device to a launching device and provides a unitary system to perform the entire handling and launching functions.

Although a preferred embodiment of this invention is illustrated, it will be realized that various modifications of the structural details may be made without departing from the mode of operation and the essence of the invention. Therefore, except insofar as they are claimed in the appended claims, structural details may be varied widely without modifying the mode of operation. Accordingly, the appended claims and not the aforesaid detailed description are determinative of the scope of the invention.

I claim:

1. A missile transporting and launching device comprising an elongated fluid tight housing capable of being submerged, support means in said housing for receiving a missile, ejection means in said housing operable to eject the missile from said housing while said housing is submerged, resilient means in said housing for resiliently mounting said support means and said missile in said housing and lock means operably connected to said housing and said support means preventing relative axial motion therebetween only when said missile is being ejected.

2. A missile transporting and launching device comprising an elongated fluid tight housing capable of being submerged, means in said housing automatically maintaining the internal pressure thereof substantially equal to the external pressure thereon, support means in said housing for receiving a missile therein, ejection means cooperable with said support means and effective to eject the missile from said housing while said housing is submerged, resilient means disposed in said housing for re siliently mounting said support means and said missile therein in said housing and lock means connected to said support means and said housing preventing relative axial motion therebetween only when said missile is being ejected.

3. A missile transporting and launching mechanism comprising an elongated fluid tight housing, a normally closed hinged end cap on one end of said housing movable to an open position clear of the end of said housing, a launching tube in said housing, and resilient means between the housing and launching tube resiliently supporting the launching tube in said housing for limited movement relative thereto in all directions, a chamber in said launching tube filled with compressed fiuid, valved means operable to release said fluid from said chamber to eject a missile from said tube when said end cap is opened, and lock means between said tube and housing including means operated by release of fluid from said chamber to prevent relative axial movement between said tube and housing.

4. A missile transporting and launching mechanism comprising an elongated fluid tight housing, a normally closed hinged end cap on one end of said housing mayable to an open position clear of the end of said housing, a launching tube in said housing, and resilient means between the housing and launching tube resiliently supporting the launching tube in said housing for limited movement relative thereto in all directions, a first chamber filled with compressed fluid, regulating means connected to said housing and first chamber operable to vent fluid from said first chamber into said housing to maintain the internal and external pressure thereon substantially equal, a second chamber filled with compressed fluid, and valved means operable to release said fiuid from said second chamber to eject a missile from said tube when said end cap is opened.

5. A missile transporting and launching mechanism comprising an elongated fluid tight housing, a normally closed hinged end cap on one end of said housing movable to an open position clear of the end of said housing, a launching tube resiliently supported in said housing for limited movement relative thereto in all directions, a first chamber in said end cap filled with compressed fluid, regulating means connected to said housing and first chamber operable to vent fluid from said first chamber into said housing to maintain the internal and external pressure thereon substantially equal, a second chamber on said launcher filled with compressed fluid, valved means operable to release said fluid from said second chamber to eject a missile from said tube when said end cap is opened, andlock means between said tube and housing 0perated by release of fluid from said second chamber to prevent relative axial movement between said tube and housing.

6. A missile launching device comprising a launching tube adapted to receive and support amissile, a fluid tight housing completely enclosing said tube, shock means between said housing and tube resiliently supporting said launcher within said housing for limited movement relative thereto, pressure means automatically maintaining the internal pressure in said housing substantially equal to the pressure outside said housing, ejection means in said housing operable to open one end thereof and eject said missile from said tube, and lock means connected to the housing and the launching tube and operable during the ejection of the missile from said tube to prevent relative axial movement between said tube and housing.

8 References Cited in the file of this patent UNITED STATES PATENTS 425,574 Lassoe Apr. 15', 1890 467,793 Elliott Ian. 26, 1892 952,450 Leon Mar. 22, 1910 1,216,221 Erickson et a1 Feb. 13, 1917 1,707,112 Browne May 26, 1929 1,985,184 Methlin Dec. 18, 1934 2,060,670 Hartman Nov. 10, 1936 2,349,009 Schwab May 16, 1944 2,705,919 Semon Apr. 12, 1955 2,903,124 Carver Sept. 8, 1959 2,956,478 Ream Oct. 18, 1960 OTHER REFERENCES Aviation Week, Apr. 21, 1958, p. 31, Compressed Air

Claims

3. A MISSILE TRANSPORTING AND LAUNCHING MECHANISM COMPRISING AN ELONGATED FLUID TIGHT HOUSING, A NORMALLY CLOSED HINGED END CAP ON ONE END OF SAID HOUSING MOVABLE TO AN OPEN POSITION CLEAR OF THE END OF SAID HOUSING, A LAUNCHING TUBE IN SAID HOUSING, AND RESILIENT MEANS BETWEEN THE HOUSING AND LAUNCHING TUBE RESILIENTLY SUPPORTING THE LAUNCHING TUBE IN SAID HOUSING FOR LIMITED MOVEMENT RELATIVE THERETO IN ALL DIRECTIONS, A CHAMBER IN SAID LAUNCHING TUBE FILLED WITH COMPRESSED FLUID, VALVED MEANS OPERABLE TO RELEASE SAID FLUID FROM SAID CHAMBER TO EJECT A MISSILE FORM SAID TUBE WHEN SAID END CAP IS OPENED, AND LOCK MEANS BETWEEN SAID TUBE AND HOUSING INCLUDING MEANS OPERATED BY RELEASE OF FLUID FROM SAID CHAMBER TO PREVENT RELATIVE AXIAL MOVEMENT BETWEEN SAID TUBE AND HOUSING.