US3038383A

US3038383A - Missile launching apparatus

Info

Publication number: US3038383A
Application number: US9405A
Authority: US
Inventors: Tiesenhausen Georg Von
Original assignee: Individual
Current assignee: Individual
Priority date: 1960-02-17
Filing date: 1960-02-17
Publication date: 1962-06-12
Anticipated expiration: 1979-06-12

Description

June 12, 1962 Filed Feb. 17, 1960 s. VON TIESENHAUSEN V 3,038,383

MISSILE LAUNCHING APPARATUS 4 Sheets-Sheet 1 I 20 I Z P 1 Georg von Tiesenhuusen, INVENTOR.

BY $515 wj June 12, 1962 G. VON TIESENHAUSEN MISSILE LAUNCHING APPARATUS 4 Sheets-Sheet 2 Filed Feb. 17. 1960 w mm moi a INVENTOR.

June 12, 1962 e. VON TIESENHAUSEN 3,038,383

MISSILE LAUNCHING APPARATUS I Filed Feb. 17, 1960 I 4 Sheets-Sheet :s

Georg von Tiesenhausen INVEN TOR.

ay-W June 12, 1962 G. VON TIESENHAUSEN 3,038,383

MISSILE LAUNQHING APPARATUS Filed Feb. 17, 1960 4 Sheets-Sheet 4 1 J .(C) w I I w 'lfllllHlllIHIMIHIIJINIHMI States The invention described herein may be manufactured and used by or for the Government for governmental purposes without the payment of any royalty thereon.

My invention relates to apparatus to support missiles for launching thereof from a launching pad and more particularly, to such apparatus to secure the missiles thereto prior to the launching.

. Missiles originally included single engines disposed for combustion of fuel therein to produce axial thrust. The missiles were superimposed upon level surfaces of conventional pads for firing and the engines rapidly developed the value of thrust required for launching. When payloads are increased, such missiles are required to be secured to the launching pad, to provide for development by the single engine of suflicient value of thrust for launching.

For still greater payloads, missiles are provided with multiple engines disposed in clusters around the missile axes. The period of maximum thrust development varies in the individual engines'and the multiple engine missiles are required to be retained on the launching pad until the development of substantially equal thrust in the engines for launching equilibrium of the missiles.

characteristically, missiles are provided with high centers of gravity, and in shipboard application launching pads require means to secure the missiles to the launching surfaces of the pads and provide cantilever support of the missiles to compensate for the roll of the ships. The means are required to release the missiles for launching only when the surfaces are substantially horizontal.

An object of my invention therefore is to provide apparatus disposed to support missiles for launching and to secure the missiles thereto, prior to the launching.

Another object of my invention is to provide such apparatus disposed to retain missiles on the launching pads therefor for development of a predetermined thrust therein prior to the launching.

.A further object of my invention is to provide such apparatus disposed to provide cantilever support for missiles fired from ships.

' In carrying out my invention, a tailgrab includes a plurality of clamps spacedly secured to a launching pad and the clamps are pivoted between positions, of engagement with the transversely projecting tail flange of a missile to retain the missile on the launching pad, and of disengagement from the flange. Levers corresponding to the clamps are pivoted on the pad between armed positions to retain the clamps in the engagement positions and disarmed positions free of the levers. The tailgrab also includes a device for retention of the levers in the armed positions and for release of the levers responsive to the firing. The levers are disposed for displacement between the armed and disarmed positions responsive to the launching.

. A delay period of substantially 25 milliseconds from the beginning of combustion in the engines to the launching has been incorporated in the tailgrab. This period has been found sutficient for single engine-missiles with high loading and for equalization of thrust in multiple-engine missiles. However, longer time delays are contemplated for still larger missiles.

In shipboard application, the tailgrabs are disposed for cantilever support of the missiles on the launching pads to compensate for the roll of the ships.

For more complete understanding, reference is directed i atet 2 to the following description and the accompanying drawing, in which:

FIGURE 1 is a perspective view of a missile secured to one embodiment of my invention;

FIGURE 2 is an enlarged perspective view of a clamp of such embodiment;

FIGURE 3 is an enlarged elevation of the clamp in closed position;

FIGURE 4 is a view similar to FIGURE 3 with the clamp in open position;

FIGURE 5 is an enlarged elevation of a connector of FIGURE 1;

FIGURE 6 is a similar view of the connector after rupture;

FIGURE 7 is an enlarged perspective view of the embodiment with an alternate form of arming device in the armed position thereof;

FIGURE 8 is a view similar to FIGURE 7 with the arming device in the disarmed position.

FIGURE 9 is an enlarged view, partly cut away, of the separator shown in FIGURE 7; and

FIGURE 10 is "a view similar to FIGURE 9 of the separator after release.

Accordingly, a launching pad 12 is secured to a base 14 and provided with a surface 16 for engagement with a projecting tail flange 18 disposed in transverse relation with a principal axis 19 of a missile 20. The missile is provided with a power plant 21 for combustion of fuel therein to produce thrust. A tailgrab 22 is provided with clamps 24 spacedly secured to pad 12. Each of the clamps includes a transverse shaft 26 with arms 28 and a leg 30 secured to the shaft in angular relation to form a crank 32. Each shaft is rotatable in apertures 34 of a pair of spaced brackets 36 secured to pad 12. One end of a link 38 of clamp 24 is pinned at 46 to each of the legs and link 38 includes a projecting pin 42 in the opposite end thereof. Adjustable fingers 44 are respectively secured to arms 28 for engagement with flange -18.

Levers 46 respectively corresponding to links 38 are provided with semi-cylindrical grooves 48 and the levers are respectively pivoted at 50 in brackets 52 secured to pad 12. The levers operate between armed positions for engagement of shafts 26 with ends 54 of apertures 34 p and of grooves 48 with pins 42 to stress cranks 32 and apply pressure to flange 18 to secure missile 20 to surface 16, and disarmed positions out of the engagement. Safety links '56, are provided to connect links 38 and corresponding levers 46 and temporarily secure the lovers in the armed positions.

An arming device '57 for securing levers 46 in the armed positions, includes pulleys 58 rotatably secured to the free ends of levers 46, a cable 60 with portions for engagement with pulleys 58 and connectors 62 disposed to connect adjacent ends of the cable portions to retain the levers in the armed positions. Links 56 are removed when missiles 20 are to be fired.

Each of connectors 62 includes a portion 76 of reduced section and an axial bore 78 projecting into section 76. A squib 80 is disposed in bore 78 and connected by wires 82 for electrical detonation responsive to firing of missile 20 for rupture of portion 76 to release levers 46.

In the armed positions of levers 46, the centers of pins 42 are displaced towards levers 46 from the line of centers of

pins

40 and 42 by adjustable stop 84 secured to pad 12. Relief of the stress of cranks 32 rotates levers 46 to the disarmed positions responsive to the release.

Apertures 34 are elongated and shafts 26 fall in the apertures responsive to operation of levers 46 for displacement of arms 28 out of possible interference with missile 20 in launching. Cams 88 are secured to shafts 26 and stops 90 are secured to pad 12 for engagement to prevent 3 counter rotation of cranks 32 and rebound interference of the arms with missile 20.

FIGURE 7 shows abase 12 with a missile 92 supported thereon and provided with a principal axis 93 and engines 94 clustered therearound. An arming device 95 includes respective separators 96 pivotally secured at 98 to pad 12 and at 100 to the free ends of levers 46 for retention thereof in the armed positions.

Each of the separators includes

members

102 and 104 with an axial cylinder 106 in member 102 and a plurality of balls 108 radially slidable therein. A piston 110 in member 102 is biased by a spring 112 in member 104 for engagement of a flanged portion 113 of the piston to retain balls 108 between member 102 and an inwardly projecting flange 114 of member 104.

Cylinders 106 are connected through conduits 116, pipes 118 and a solenoid valve 120 to a source 122 of compressed air secured to pad 12.

Valve 120 of device 95 is electrically connected for flow of the compressed air to cylinder 106, responsive to combustion of fuel in engines 94. Piston 110 is slida ble, responsive to the air flow, for compression of spring 112 and disengagement of balls 108 from portion 113 and flange 114 for release of member 102 and consequent release of levers 46 from the armed positions. A section 124 of flange 114 is curved to facilitate the disengagement therefrom of balls 108.

Operation Tail grabs 22 are secured to launching pads 12 for time delay of the launching of missiles from the beginning of combustion of the fuel in the engines of the missiles.

In a single engine missile the delay is required for development of sufiicient thrust in the engine to lift the missile in the launching. Multiple engine missiles are delayed until the thrusts of the engines are equalized for equilibrium of the missile in the launching.

In shipboard application, a launching pad may be considered to be rotatable about a line in the missile engagement surface thereof during roll of the ship. Missiles generally are provided with high centers of gravity and launching pads are provided with tailgrabs to secure the missiles to the pad for cantilever support of the missiles during the roll.

of the roll.

While the foregoing is a description of the preferred embodiment, the following claims are intended to include those modifications and variations that are within the spirit and scope of my invention.

I claim:

1. Apparatus for launching a missile provided with a principal axis, a transversely projecting tail flange, and a power plant for combustion of fuel therein to produce thrust; comprising: a pad for supporting the missile for firing thereof provided with a surface; and a tailgrab secured to said pad and disposed for engagement with the flange to retain the missile in engagement with said surface, and disengagement from the flange to release the missile responsive to the firing, said tailgrab comprising a plurality of clamps spacedly secured to said pad and respectively provided with closed and open positions corresponding to the engagement and disengagement; levers secured to said pad and pivoted between armed positions for respective engagement with said clamps for retention thereof in the closed positions, and disarmed positions out of engagement; and an arming device disposed for engage ment to securesaid levers in the armed positions, and for disengagement from said levers responsive to the firing, each of said clamps comprising a crank with a shaft, a link having one end thereof pinned to said crank, a pair of brackets secured to said pad and provided with respective apertures for engagement therebetween of said shaft and transversely-axised rotation of said crank between the open and closed positions, and an adjustable finger Arming device 57 is provided for release of the missiles for launching at predeterminedpoints d secured to said clamp for the flange engagement; and each of said levers being disposed for engagement with the opposite end of said link in the armed position to secure the corresponding crank in the closed position.

2. Apparatus as in claim 1 with said opposite end and said lever provided with a projecting pin and a semicylindrical groove for cooperation and application of stress to said crank to apply pressure to the flange in the armed position, and with an adjustable stop secured to said pad for armed position displacement of the center of said projecting pin in the direction of said lever from the line of pivot centers of said link and arm for rotation of said levers between said armed and disarmed positions responsive to relief of the stress in said cranks.

3. Apparatus as in claim 2 with said arming device comprising pulleys secured to the free ends of said levers; a cable including portions disposed for engagement with said pulleys; connectors respectively secured between adjacent ends of said cable portions to retain said levers in the armed positions; and squibs enclosed in said connectors and disposed for electrical detonation to rupture said connectors and release said levers, responsive to the firing.

4. Apparatus as in claim 3 with each of said connectors comprising a body with a portion of reduced section and an aperture projecting therein for enclosure of said squibs; said squibs being electrically connected for detonation to rupture said reduced section portion and release said levers responsive to the firing.

5. Apparatus as in claim 4 with said bracket apertures elongated for engagement of said shafts with respective ends thereof in the closed and open positions; stops secured to said pads; and cams secured to said shafts for engagement with said pads to retain said cranks in the open positions.

6. Apparatus as in claim 5 with said tailgrabs disposed for cantilever support of the missiles on said pads.

'7. Apparatus for launching a missile provided with a principal axis, a transversely projecting tail flange, and a power plant for combustion of fuel therein to produce thrust; comprising: a pad for supporting the missile for firing thereof provided with a surface; and a tailgrab secured to said pad and disposedfor engagement with the flange to retain the missile in engagement with said surface, and disengagement from the flange to release the missile responsive to the firing, said tailgrab comprising a plurality of clamps spacedly secured to said pad and respectively provided with closed and open positions corresponding to the engagement and disengagement; levers secured to said pad and pivoted between armed positions for respective engagement with said clamps for retention thereof in the closed positions, and disarmed positions out of engagement; and an arming device disposed for engagement to secure said levers in the armed positions, and for disengagement from said levers responsive to the firing, each of said clamps comprising a crank with a shaft, a link having one end thereof pinned to said crank, a pair of brackets secured to said pad and provided with respective apertures for engagement therebetween of said shaft and transversely-axised rotation of said crank between the open and closed positions, and an adjustable finger secured to said clamp for the flange engagement; and each of said levers being disposed for engagement with the opposite end of said link in the armed position to secure the corresponding crank in the closed position, said opposite end and said lelver provided with a projecting pin and a semi-cylindrical groove for cooperation and application of stress to said crank to apply pressure to the flange in the armed position, and an adjustable stop secured to said pad for armed po sition displacement of the center of said projecting pin in the direction of said lever from the line of pivot centers of said link and arm for rotation of said levers between said armed and disarmed positions responsive to relief of the stress in said cranks, saidarming device comprising a source of compressed air secured to said pad; separators respectively secured between said pad and said levers for retention thereof in the armed positions; and a solenoid valve disposed in connected relation between said source and said separators for operation thereof to release said levers responsive to the firing.

8. Separators as in claim 7 with each thereof comprising a pair of members respectively secured to said pad and one of said levers and respectively provided with a cylinder in the connected relation and an inwardly projecting flange; balls radially sliclable in said cylinder member; and a piston disposed in said cylinder in biased relation for engagement of said balls between said cylinder member and said flange for the retention; said piston being slidably disposed for release of said flange member responsive to the solenoid valve operation.

9. A separator as in claim 8 with a spring disposed in said flange member for the biased relation.

References Cited in the file of this patent UNITED STATES PATENTS 2,831,400 Hosli Apr. 22, 1958 2,867,153 Hirsch Jan. 6, 1959 2,927,398 Kaye et al Mar. 8, 1960 FOREIGN PATENTS 914,341 France June 17, 1946