05/097686

07/03/1973

12/14/1970

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89/1.807

89/1.819, 89/1.814, 89/1.812, 89/1.817, 89/1.815

F15B11/076; F15B15/22; F15B15/26; F41F3/042; F41F3/052; F15B11/00; F15B15/00; F41F3/00; F41F3/04

89/1.8-1.819,30,31 160/1.88,238

3096726

Retractable rails

July 1963

Johnson et al.

Engle, Samuel W.

What is claimed is

1. A missile launcher including a body having side and bottom walls, a floor spaced above the bottom wall and an open forward end,

2. The invention of claim 1, including additionally means on the body for preventing aft movement of such missile prior to arming and firing thereof.

3. A missile launcher as recited in claim 1,

4. A missile launcher as recited in claim 1, wherein said actuating means includes a pneumatic actuator.

5. A missile launcher as recited in claim 4,

6. A missile launcher as recited in claim 4,

7. A missile launcher as recited in claim 6,

8. The invention as recited in claim 7,

9. The invention as recited in claim 8,

10. In a missile launcher as recited in claim 1,

11. A missile launcher as recited in claim 10,

12. The invention as recited in claim 1,

13. The invention as recited in claim 12,

14. The invention as recited in claim 1,

15. The invention as recited in claim 14,

16. The invention as recited in claim 14,

17. A missile launcher as recited in claim 1,

18. A missile launcher as recited in claim 1,

19. A missile launcher as recited in claim 1,

20. A missile launcher as recited in claim 1,

21. A missile launcher as recited in claim 20,

22. A missile launcher as recited in claim 21, wherein said latch includes a housing having a cylinder therein,

23. A missile launcher as recited in claim 21,

24. A missile launcher as recited in claim 23,

25. The invention as recited in claim 23,

26. The invention as recited in claim 23,

27. The invention as recited in claim 1,

28. A missile launcher including a body of oblong rectangular contour and comprising a frame having spaced forward, intermediate and aft frame sections and top, side and bottom walls,

29. The invention as recited in claim 28,

30. The invention as recited in claim 28,

31. The invention as recited in claim 28,

32. The invention as recited in claim 28,

33. The invention as recited in claim 32,

34. A missile launcher as recited in claim 28,

35. A missile launcher as recited in claim 28, including additionally

36. A missile launcher as recited in claim 35,

37. The missile launcher as recited in claim 28,

38. The missile launcher as recited in claim 37,

39. A missile launcher including a body of oblong rectangular contour and having a frame having spaced forward, intermediate and aft frame sections and top, side and bottom walls,

40. The invention as recited in claim 39,

BACKGROUND OF THE INVENTION

The present invention relates to missile launching apparatus. More particularly, it pertains to an improved missile launcher which is of elongated rectangular configuration.

The threat of simultaneous, omnidirectional attacks by numbers of enemy aircraft at high and low altitudes makes it essential that missile ships have a capability for launching large numbers of missiles within short periods of time. While an existing guided missile launching system is capable of firing a salvo each ten seconds, it is generally recognized that this firing rate is insufficient for adequate defense against highly probably modes of enemy aircraft attack.

Existing launchers are of the fully automatic magazine type, in which missiles must be transferred from a below-deck magazine onto the launch rails before firing. The interval between salvos is, to a considerable extent, determined by the time required to orient the launcher into loading position, to transfer the missile from the magazine to the launch rails and return the launcher to firing position. For magazine launchers of this type it is not anticipated that the time necessary to complete these operations can be significantly reduced. It is, therefore, important that missile launchers be developed from which a substantial number of missiles can be launched in rapid-fire sequence. Such rapid-fire rates can be achieved through the use of box-type launchers where a number of missiles are stored in a cluster of individual "boxes" or "cells" mounted on a launcher turret in ready-to-fire condition. With a box launcher, firing rates of one missile every 2 seconds or less is entirely feasible.

The use of box-type launchers has been limited by large size, heavy weight, and a small complement of missiles, as a result of the inordinately large cells required to clear the span of the missile aerodynamic surfaces. Through the development of a reliable, foldable, self-erecting tail fin for TARTAR type missiles, it has become possible in a TARTAR/STANDARD missile box launcher to achieve substantial reductions in the launcher cell cross-sectional dimensions compared with the cell size required for missiles with non-folding fins. The smaller cells make possible a decrease in launcher weight and an increase in missile complement.

One important object of the present invention, therefore, is to provide a missile launcher which is of simple box-like construction and which is made of lightweight materials capable of withstanding the effects of rocket motor blast, exhaust pressure and external loads.

As another object, the invention provides a missile launcher which, because of the employment of means for accommodating missiles having initially folded fins, is capable of receiving a larger number of missiles in a smaller space than a launcher for missiles having rigid fins.

A further object of the invention resides in the provision of a missile launcher which includes guide rails for restraining the initially folded fins until the missile leaves the launcher, when said fins will erect automatically.

As a still further object, the invention provides a missile launcher which, being of box-like configuration, may be deployed singly or as a battery with a plurality of missiles in position ready to fire.

Still other objects of the invention are to provide a missile launcher having a unique forward door construction, a launcher rail having a forward section that is movable to provide clearance between the aft end of the missile and said launcher rail as said missile leaves the launcher, a mechanism to arm and fire the missile on remote command, which mechanism also includes a mechanically interlocked inadvertent fire restraint that blocks forward movement of the missile until it is armed, and means for preventing fore and aft motion of the stowed missile until its rocket has been ignited.

Additional objects of the invention are to provide a missile launcher which has a low cost, one-shot, launcher-to-missile electrical contactor which may be easily replaced after each missile firing, a self-contained pneumatic control system for the forward door, forward rail section and the arming and firing mechanism employed, and a frangible rear wall which can withstand external gun blast and "green sea" loads but will be easily ruptured by rocket blast when a missile is launched.

Further objects of the invention will become evident as the description thereof proceeds.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a perspective showing a single cell launcher according to the invention as it would appear mounted on a turret launcher;

FIG. 2 is an enlarged perspective of the single cell launcher;

FIG. 2a is an enlarged detail section on the line 2a--2a of FIG. 2;

FIG. 2b is an enlarged detail section on the line 2b--2b of FIG. 2;

FIG 2c is an enlarged detail section on the line 2c--2c of FIG. 2;

FIG. 2d is an enlarged detail section on the line 2d--2d of FIG. 2;

FIG. 3 is a view similar to FIG. 2 but showing portions of the walls of the launcher broken away to show structural details;

FIG. 3a is an enlarged detail section showing one of the springs mounted in the upper rail of the door frame to cushion the shock of the closing of the forward door of the launcher.

FIG. 4 is a perspective showing a two-cell launcher, the walls of the upper cell being broken away to show a missile in place on the launching rail and portions of the forward door and operating mechanism therefor;

FIG. 4a is a perspective view of the missile launching rail;

FIG. 4b is a perspective, with parts shown in phantom and other parts shown fragmentarily, particularly illustrating the dual track in the launching rail aft section with forward and aft missile shoes therein;

FIG. 5 is an enlarged detail perspective showing the major components of the forward door and its operating mechanism, portions of the frame being shown schematically;

FIG. 5a is a detail plan view, partly in section, showing six of the door elements and portions of the connecting cables employed;

FIG. 6 is an enlarged detail section of the forward end portion of the launcher, the forward door being shown in closed position;

FIG. 7 is a perspective of the launcher, looking from the forward end toward the aft end thereof and with the floor and one of the side walls removed, particularly showing the forward door operating mechanism, the air storage compartment, and one of the fin guide rails employed;

FIG. 8 is an enlarged detail section showing the latch and other details in the forward portion of the door actuator;

FIG. 8a is a view similar to FIG. 8 but showing the aft portion of the door actuator;

FIG. 9 is a perspective of the aft end of the launcher cell and particularly showing the electrical connector connected to a missile in the launcher;

FIG. 10 is an exploded elevation of the missile connector of FIG. 9, portions of the connector housing being shown in broken lines;

FIG. 11 is an enlarged detail section showing the aft end portion of the launcher with the frangible aft closure in place, and showing a portion of the electro-pneumatic control system in its housing;

FIG. 12 is a perspective - showing some of the electro-pneumatic control system components in the housing therefor;

FIG. 13 is a diagrammatic view showing, in top plan, the missile fin guide rails;

FIG. 14 is a section on the line 14--14 of FIG. 13;

FIG. 15 is a section on the line 15--15 of FIG. 13;

FIG. 16 is a section on the line 16--16 of FIG. 13;

FIG. 17 is an enlarged detail perspective particularly showing the forward end of the forward section of the launcher rail and the release mechanism therefor;

FIG. 18 is a perspective view looking aft from the forward end of the launcher, and showing a missile in position for launching;

FIG. 19 is a detail longitudinal section showing the latch mechanism for the forward launcher rail section in latching position and said launcher rail section in its lowermost position;

FIG. 20 is a view similar to FIG. 19 but showing the latch mechanism as it would appear immediately following release and the rail section in partial retracted position;

FIG. 21 is a view similar to FIGS. 19 and 20 but showing the forward launcher rail section in fully retracted position;

FIG. 22 is an enlarged side elevation of the forward launcher rail section latch mechanism with its housing cover removed to show the several spring biased levers and the indicator switch employed;

FIGS. 22a through 22d are side elevations generally similar to FIG. 22 but showing the positions of the several springs and levers during movement of the missile forward shoe into and out of engagement with the rail section latch mechanism;

FIG. 23 is a front elevation of the forward launcher rail section latch mechanism, partly broken away and shown in section;

FIG. 24 is a top plan view, partly in section, of the forward launcher rail section latch mechanism;

FIG. 25 is an enlarged longitudinal section, partly in elevation, showing the actuator for the rail section latch mechanism;

FIG. 26 is a detail perspective, looking upward, showing a portion of the aft launcher rail section with the forward and aft restraining latches employed mounted therein;

FIG. 26a is an enlarged detail perspective partly broken away, of the aft latch;

FIG. 26b is a similar view showing the forward restraining latch;

FIG. 26c is an elevation showing the aft end of the launcher rail;

FIG. 27 is an enlarged diagrammatic view showing the forward restraining latch and aft latch in engagement with the aft shoe of a missile in the launcher, said shoe being shown in broken lines;

FIG. 28 is a view similar to FIG. 27 but showing the forward restraining latch as it would appear as the aft shoe moves forwardly, following ignition of the rocket of the missile;

FIG. 29 is a diagrammatic view of the safety and arming mechanism as it would appear in safe position prior to missile launch;

FIG. 30 is a view similar to FIG. 29 but showing the safety and arming mechanism in armed position;

FIG. 30a is an enlarged detail perspective, looking upward, of the arming lever with stop wall of the shoe thereof in engagement with the pin of the arming switch on the missile;

FIG. 31 is a view similar to FIGS. 29 and 30 but showing the safety and arming mechanism after missile launch has been effected;

FIG. 32 is a front elevation showing diagrammatically the safety and arming mechanism in armed condition with the arming contacts in engagement with the firing contacts on a missile, other portions of the launcher having been omitted for the sake of clarity;

FIG. 33 is a detail perspective looking upward toward the safety and arming mechanism, the same being in post-firing condition;

FIG. 34 is an enlarged longitudinal section of the actuator for the safety and arming mehcanism;

FIG. 35 is a fanciful showing of a single cell launcher connected to a control console;

FIG. 36 is an enlarged front view of a typical control console;

FIG. 37 is a chart showing the sequence of steps taken to effect a missile launch and the times needed for said steps;

FIG. 38 is a schematic of the hydraulic circuit of the launcher;

FIGS. 39 and 39a are schematic views which, when considered together, provide a showing of the electric circuit of the launcher;

FIG. 40 is a perspective view showing a multi-cell launcher, according to a modified embodiment of the invention; and

FIG. 41 is a perspective showing a rig by the use of which, under certain conditions, a missile may be loaded into the launcher.

DESCRIPTION OF THE INVENTION

The launcher of the present invention comprises an oblong rectangular body to contain a missile for launching. The body is closed at its forward end by an articulate forward door which is structurally capable of withstanding external green sea loads in its closed position. The door is movable to open position on command before missile launch, in which said position it is contained in a compartment above the bottom wall and beneath a floor in the forward end portion of the body. The door itself includes a plurality of preferably steel tubular elements which are square in cross-section and are connected for articulating movement by cables that pass through bushings in said tubes near their opposite ends. The forward door is guided at its opposite edges by tracks which are located in the forward frame section and have lower end portions extending through a 90° arc to confront a storage area below the floor. The door is connected with a double acting pneumatic actuator by a carriage which is located between the floor and the bottom wall of the launcher. The carriage transmits motion of the actuator to the door when the door is opened or closed and maintains alignment of the articulated tubular elements to prevent cocking and binding thereof in the tracks.

Opposed rails are mounted within the body on the side walls thereof and function to guide the fins of a missile as it moves through the body during a launching operation, said fins erecting automatically as the missile leaves the launcher. A launcher rail, having a forward section which is movable upwardly to clear the aft end of the missile as it leaves the launcher, is employed, and an arming and firing mechanism and restrainer latch and aft latch structure, to arm and fire the missile and prevent fore and aft movement thereof until rocket ignition occurs, are also provided. The forward door, movable rail section and arming and firing mechanisms are controlled by linear actuators powered by high pressure gas, while the restrainer latch is actuated by movement of the missile as it is launched. Storage tanks for the high pressure gas and controls for the linear actuators are mounted in compartments in the bottom of the body. The operating system for the launcher is electropneumatic and is controlled from a suitable console located in a position remote therefrom.

Referring to the drawings in detail, and first to FIGS. 2 and 3, the launcher A of the present invention comprises an oblong rectangular body which comprises a frame 10 having forward, intermediate and aft frame sections 12, 14 and 16, respectively. The frame is of welded construction and utilizes tubing of square and rectangular cross-section, flat bar, and angle bars. The frame sections are connected at each side by base rails and upper and lower side rails. More specifically, to provide a rigid structure, only one side of which is shown in FIGS. 2 and 3, lower side and base rails 18 and 20, respectively connect the sections 12 and 14 at their corresponding lower ends. To protect the frame sections 14 and 16 from rocket blast, deflectors 14a and 16a are provided. As best seen in FIG. 2a, each side rail 18 forms a part of a bracket 21, which supports one side of a floor 22 and the lower end of a side wall or panel 23. a clamping strip 23a cooperates with the rail 18 for securing the wall 23 in place. Each base rail 20 is of oblong rectangular tubing and is welded to the bracket 21 at its upper edge. At its lower edge the base rail has a foot plate 24, said plate 24 forming part of a bracket 25 to which is secured one side margin of a bottom wall 26 which extends throughout the length of the frame.

Mounted on the inner wall of the base rail 20 between the brackets 21 and 25 is a guide rail 27 which cooperates with a similar guide rail on the opposite side of the frame to define a track for the forward door, which structure will be described in detail hereinafter.

At their upper corners the sections 12 and 14 are connected by an upper side rail 28 which, as best seen in FIG. 3, is of angle construction. A cap rail 28a co-operates with the rail 28 for clamping the upper end of the side wall 23 and one side margin of a top wall 30 in place. Forward and aft flat bar rail elements 32 and 34 are welded to the upright portions of the frame sections 12 and 14 and to the upper and lower side rails to provide further support for the side wall 23.

The intermediate frame section 14 is connected to the aft frame section 16, at each side, by a base rail 36 and a lower side rail 38. As best seen in FIG. 2b and FIG. 3, the structure is generally similar to that employed for connecting the forward and intermediate frame sections, except for the omission of the guide rail 27 and for the provision of an enlarged aft end portion 40 for the side rail 38. A clamping strip 42 secures the lower end of a side wall or panel 44 which is similar to the panel 23. The enlarged portion 40 defines a side wall for a housing 46 within the aft end portion of the frame 10. The housing 46 contains electrical and pneumatic control devices, to be described hereinafter, and includes a top wall 48 and an inclined forward wall 50, the top wall terminating at the aft end of the frame and the forward wall extending between the forward end of said top wall 48 and the floor 22. Beneath the floor 22 and forwardly of the housing are mounted a plurality of air storage containers 52. Also mounted beneath the floor, forwardly of the air storage containers, is the actuating mechanism for the forward door, to be described presently hereinafter.

Closing the top of the frame 10 between the frame sections 14 and 16 is a top wall 54 which is held in place at each side of said frame by an upper side rail 56 and a cap rail 58 which are similar to the rails 28 and 28a.

The forward door and the mechanism for operating it are best seen in FIGS. 3, 5, 5a, 6 and 7, and reference is now made particularly to these views. The forward door is shown generally at 60 and comprises a plurality of elements 61 which are square in cross-section and are arranged transversely of the body to move in tracks 61a provided in side rails of a door frame 62, mounted on the front face of the forward frame section 12, in an arcuate connecting channel 63 in the bottom rail of said forward frame element, and in the guide rails 27 (FIG. 2a). The opposite ends of the elements 61 are closed by guide caps 64, and the top and bottom walls of said elements are apertured, near their opposite ends, to receive preferably Nylon bushings 65 through which extend cables 66. The cables 66 extend between the uppermost and lowermost of the elements 61 and are of such length that flexure of the door will be permitted. In operation the door is moved, by means to be described, from a closed position as shown in FIG. 6, with the elements 61 in the frame 62 (and in the channel 63) to an open position as shown in FIG. 3 and in phantom in FIG. 5, with the elements in the rails 27 and in the space between the floor 22 and the bottom wall 26.

Movement of the forward door to open or closed position is effected by a pneumatic actuator 68 which comprises a cylinder and a piston rod. As best seen in FIG. 3, the actuator 68 is mounted in the frame 10 between the forward and intermediate frame sections 12 and 14 and beneath the floor 22. The aft end of the cylinder is secured to the bulkhead which is defined by the bottom rail of the intermediate frame section 14, and the piston rod has its forward end secured to the bight portion 72 of a U-shape carriage 73. As best seen in FIG. 4, the carriage includes parallel legs 74 which are connected to the bight portion 72 and have rollers 75 mounted in recesses 76 near their free ends. Rollers 77 are mounted in casters 78 which are secured to each side of the carriage at the forward ends of the legs 74. Spaced yokes 80, mounted on the forward face of the bight portion 72, are connected to the lowermost of the rail elements 61. The rollers 75 and 77 mount the carriage for rolling movement in the guide rail 27, the carriage providing an effective connection between the piston rod of the actuator 68 and the door 60. It should be particularly noted that the four-point contact between the carriage and the guide rail, i.e., two spaced rollers at each side, prevents cocking or binding of the door elements 61 during movement of the door toward open or closed position.

High pressure air is supplied to the forward or aft ends of the actuator cylinder by air lines 82 and 83, respectively, which are connected to an air supply and control valves, to be described hereinafter. Since the actuator 68 is believed to possess novel features, it has been shown in detail in FIGS. 8 and 8a.

Referring particularly to FIG. 8, the actuator 68 includes a latch 81 having a cylindrical wall 81a to which is attached a latch housing 84. The wall 81a is closed at its forward end by an end wall 85 which is apertured to receive a hollow piston rod 86, the rod 86 having a fitting 87 for connection to the carriage 73. A packing gland 88 surrounds the piston rod 86 within the forward portion of the latch 82.

The latch housing 84 includes a base 89 which has a sleeve 90 that extends through an opening 91 in the wall 81a, and a cylinder 92 in which is mounted a piston 93. The piston 93 is mounted for sliding movement in the cylinder 92 and is sealed against leakage by an O-ring 94, the inner piston wall, the wall of the cylinder 92 and the outer wall of the sleeve 90 defining an air chamber 95.

Mounted on the inner wall of the piston 93 is a latch bolt 96 which has a beveled inner end face 97, and an axial bore 98 that communicates between the chamber 95 and the interior of the latch 81. Stops 99 are formed on the inner surface of the piston 93 at each side of the latch bolt and are engageable with the base 89 for limiting inward travel of said bolt. The piston 93 has a stem 100 which extends outwardly within the latch housing 84 axially thereof and has its outer end portion slidable in an opening in an end wall 101, said end wall having a guide flange 102 surrounding said opening. A cap 103 clamps the end wall 101 in place and is formed with a recess 104 to receive the outer end of the stem when the latch bolt is in retracted position, as will be described hereinafter. A coil spring 105 surrounds the stem 100 within the outer portion of the latch housing and between the end wall 101 and the outer surface of the piston 93 and urges said piston inwardly. Formed in the wall 81a of the latch opposite the bolt 96 is a service opening 107 to which is connected the high pressure air line 82 to admit or discharge high pressure air.

The actuator 68 has a main cylinder 110 which is connected to the aft portion of the latch 81. More specifically, the forward end portion of the main cylinder is reduced in diameter and the aft end portion of the wall 81a of the latch is recessed so that said cylinder and latch may be fitted tightly together. An O-ring 111 and suitable lock nut and washer, 112 and 113, respectively, are used to assure a tightly sealed connection.

Mounted for sliding movement in the main cylinder 110 and connected to the aft end of the piston rod 86 is a main actuator piston 114. The main actuator piston 114 is formed with a reduced forward end portion 115 which defines a shoulder 116, for engagement with a straight side wall of the latch bolt 96, and a tapered forward end 117 for engagement with the tapered end wall 97 of said bolt, as will be described hereinafter.

The actuator piston 114 is hollow throughout its length and has a striker 118 mounted in its aft end, said striker comprising a hollow sleeve 119 and a flange 120, the latter substantially covering the aft end of the piston. As been seen in FIG. 8a, the piston 114 receives the forward end portion of a buffer rod 121, said buffer rod extending through the sleeve 119 and into the hollow piston rod 86. A head 122 is fixed to the forward end portion of the buffer rod 121 and is engageable with the forward end of the striker sleeve 119 during a portion of the travel of the main actuator piston 114.

The aft end portion of the main cylinder 110 is reduced to fit tightly into a coupling sleeve 124 which serves to connect a hydraulic buffer unit 125 to said cylinder. As best seen in FIG. 8b, the coupling sleeve 124 has a service port 126 to which is connected one end of the air line 83, that portion of the wall of the sleeve which is adjacent the service port being reduced in thickness to define an annular manifold 127 that communicates with the interior of the main cylinder 110 near its lower end through openings 128 which are arranged in an annular series.

The hydraulic buffer unit 125 includes a cylindrical buffer body 130 to the aft end of which is secured a mounting plate 131 for mounting the aft end of the actuator 68 on the bottom rail of the intermediate frame section 14, as previously described. Mounted in the body 130 is a buffer piston 132 which has a piston rod 133 and a stem 134. The forward end of the body 130 is secured to the aft end of the coupling sleeve 124, said body being provided with a wall 135 having a relatively wide annular sump 136 substantially medially of the body and a relatively narrow annular sump 137 near its aft end. Between the sumps the wall 135 is gradually increased in thickness, toward the aft end of the body 130, to define a tapered section 138 and a chamber within said tapered section.

The aft end of the buffer unit 125 has a plug 140 mounted therein, the plug being screwed into position, being apertured to receive the stem 134 therethrough, and having packing 141 surrounding said stem. As will be seen in FIGS. 8 and 8a, the stem 134 has an axial bore 142 and ports 143 which communicate between the chamber 139 and the exterior of the buffer unit 125 at its aft end. The bore 142 and ports 143 permit the introduction of hydraulic fluid to the interior of the chamber 139. A cap 144 closes the bore 142 at its aft end, and a by-pass 145, having a check valve 146, extends between the sumps 136 and 137.

A buffer piston rod 133 is of larger diameter than the buffer rod 121 and is provided with a stepped in diameter socket 147 which receives a stepped in diameter aft end portion 148 of said rod 121. A pin 149 connects the two rods 121 and 133. The forward end portion of the piston rod 133 is reduced in diameter to define a shoulder 150, and surrounding said reduced portion and bearing against said shoulder is the driven element 151 of a primary buffer 152. The buffer 152 includes, in addition to the driven element 151, a driving element 153, a cushioning disk 154 on the forward end of the driving element, and a plurality of stacked "Belleville" springs 155. The cushioning disk 154 is of relatively soft material, such as "Teflon." The driving element 153 is slidable on the aft end portion of the buffer rod 121 and has a longitudinally extending slot 156 which receives a coupling pin 157 on said buffer rod. The slot and pin arrangement permits limited movement between the buffer rod 121 and the driven element 153. A recess 158 in the aft end of the driving element 153 slidably receives the forwardmost portion of the buffer piston rod 133.

The operation of the forward door 60 will now be briefly described. Let it be assumed that, as shown in FIG. 6, the door is initially in closed position. In such position it will be prevented from opening accidentally by engagement of the bolt 96 of the latch 82 with the shoulder 116 of the main actuator piston 114, since the piston is secured to the piston rod 86 and said rod is connected to the door by the fitting 87 and carriage 73.

When it is desired to open the door 60 to allow a missile to leave the launcher, air under high pressure is admitted to the interior of the latch 81 from the line 82 through the service opening 107. This high pressure air will pass through the bore 98 in the latch bolt 96 into the chamber 95 and will act on the piston 93 for forcing it outwardly in the cylinder 92 against the compression of the coil spring 105. This piston movement will withdraw the bolt from behind the shoulder 116, thus allowing the actuator piston 114 to move in the main cylinder 110.

The high pressure air that operates the latch 81, as above described, also, and upon release of the latch, moves the main actuator piston 114 aft in the main cylinder 110, and about the buffer rod 121, for moving the door elements 61 downwardly in the frame 62, through the connecting channel 63 and aft along the guide rails 27. The position of the carriage 73 when the door 60 is in full open position is shown in broken lines in FIG. 5.

Under normal operating conditions, with air at 250 psi acting on the main actuator piston 114, the total door opening time is 0.750 second. To cushion the shock the rapidly moving door would otherwise have on the launcher, the buffer unit 125 (FIG. 8a) is brought into play. More specifically, when the piston 114 approaches the aft end of its travel, the striker 118 thereon engages the driving element 153 of the primary buffer 152 and moves it toward the driven element 151, against the compression of the Belleville springs 155. The driven element 151, acting against the shoulder 150, moves the buffer piston rod 133 and the buffer rod 121, which is secured thereto, in an aft direction, within the limit of travel imposed by the coupling pin 157 in the slot 156, for moving the buffer piston 132 aft in the tapered section 138 of the buffer unit 125. Movement of the buffer piston 132 will cause hydraulic fluid, shown at 160, to flow about said piston and into the forward end of the buffer unit, the tapered section 138 acting on the piston, which is of uniform diameter, to provide progressively increasing restriction of the hydraulic fluid flow to enhance buffering action. The buffering of the door mechanism takes place during the last 0.250 second of the stroke time over a distance of 2 inches, the total distance of travel of the door being, typically, slightly less than 2 feet.

Closure of the forward door 60 takes place after the missile has left the launcher. The length of time required for the door closing stroke is not critical, however, since once a missile has been fired from the launcher, there is no urgency in closing it before a missile in an adjacent launcher is fired. Typically the door closing stroke takes place in approximately two seconds. To close the forward door 60 high pressure air is switched to the air line 83 by appropriate valves. From the air line 83 air flows through the service port 126 into the manifold 127 and into the aft end of the main cylinder 110 where it will act on the main actuator piston 114 and move it forwardly in said cylinder about the buffer rod 121. As the piston 114 approaches the forward end of its stroke the sleeve 119 of the striker 118 will engage the head 122 on the buffer rod, within the hollow piston rod 86. Further movement of the piston 114 will then shift the buffer rod forwardly for moving the buffer piston in the buffer unit 125 for effecting buffering action at the forward end of the door closing stroke. As the main actuator piston 114 moves to its forwardmost position, the tapered forward end 117 of the reduced portion 115 will engage the beveled inner end face 97 of the latch bolt 96 and cam said bolt outwardly against the compression of the spring 105. When the piston 114 is in its full forward position the bolt will return to latched position with its outer end in engagement with the shoulder 116.

To cushion the impact of door closing on the door frame 62, leaf springs 62b, one of which is shown in FIG. 3a, are attached to the upper rail 62a of said frame near each end thereof and are engaged by the uppermost of the door elements 61 when the door is moved to full closed position. In practice the door will move initially into full engagement with the springs 62b and then retract a short distance.

As previously mentioned, on-board storage for high pressure gas (air) is provided by the containers 52 which are mounted in the aft section of the body between the floor 22 and the bottom wall 26. The output of the containers is controlled by valves 164 which are solenoid operated and are mounted in the housing 46. Also mounted in the housing 46 are electrical control relays 165 and a firing transformer 166. As best seen in FIGS. 9 and 11, the aft end of the launcher is provided with a connector for external high pressure air 167 and one for external electric power 168. A missile connector 170 is mounted on one side rail of the aft frame section 16. The valves 164, relays 165 and transformer 166 will be referred to hereinafter, in connection with the description of operation, and the missile connector 170 will be described in more detail.

Attention is now directed to FIG. 4 wherein a missile is shown at 171, and to FIG. 4a wherein there is shown the launcher rail for operatively supporting the missile in the launcher ready for launching. The launcher rail is shown generally at 172 and comprises an aft section 173 which is rigidly mounted in the aft portion of the launcher, an arming housing 173A which is secured to the forward end of the aft section, and a forward section 174 that is hingedly connected to the forward end of the arming housing by a pin 175. The launcher rail 172 extends from the aft toward the forward end of the launcher and is connected to the respective top rails of the aft, intermediate and forward frame sections 16, 14 and 12. The rail 172 forms a continuous guide track for the shoes of a missile during missile loading and launching operations.

In more detail, the forward section 174 of the rail 172 terminates short of the forward end of the launcher and has secured thereto a tripper unit 176 which includes a tripper mechanism 177 and a latch plate assembly 178 having a latch plate 179. As will be described in more detail hereinafter, the tripper mechanism is actuated by the forward shoe of the missile 171, as said missile moves outwardly upon firing thereof, for unlatching the forward end of the rail section 174 from the latch plate, when a pneumatic jack, also to be described, will raise said forward end a short distance so that the aft end of the missile will clear said rail as it leaves the launcher.

The missile 171 is supported in tracks formed in forward and aft rail elements 181 and 182, which are secured to the bottom walls of the rail sections 174 and 173, respectively. As best seen in FIG. 4a, the aft rail section 173 has a forward support rail element 183 mounted on the arming housing 173A and with its forward end in alignment with the aft rail element 182, and an aft support rail element 184 in alignment with the aft end of said rail element 182. Aft of the support rail element 184 is an attach bracket housing 185 having spaced yokes 186 for connection to a loading beam (see FIG. 41), and a rail extension 187 in alignment with the aft support rail element 184.

The aft rail element 182, the support rail element 184 and the extension 187, have dual tracks. That is, as seen in FIGS. 4b, 26 and 26c, said aft rail element 182 and its associated support rail element 184 and the extension have relatively wide outer tracks, one shown typically at 188, to accommodate, during loading, a relatively wide forward shoe 189 on the missile 171, and relatively narrow inner tracks, one shown typically at 190, to receive a relatively narrow aft shoe 191. It should be understood that the support rail elements 183 and 184 are of harder material and of heavier weight than the rail element 182. Further, the tracks in said support rail elements are slightly narrower than those in the rail element 182. The purpose of the heavier construction is to provide support for the missile when in storage or during transport, said heavier construction and narrower tracks being better able to withstand shocks due to rough handling.

Mounted in the aft rail section 173 are latches for engaging the aft missile shoe 191 are preventing unintended movement of the missile 171 in the launcher. These latches are seen in FIGS. 11, 26, 26a, 26b, 27 and 28 of the drawings. An aft latch, for preventing displacement of a missile in the launcher from the aft end thereof, is shown at 192. The aft latch 192 includes a latch element 193 which is pivotally mounted between the rail members of the aft support rail element 184 by a pin 194 and has an upstanding lever 195 to the upper end portion of which is secured the forward end of an actuating rod 196. The rod has a hollow aft end and extends into the attach bracket housing 185 and terminates in stepped sections 197, 198 and 199, the section 199 being slidable in an end wall 200 of the attach bracket housing 185. Spaced spring receivers 201 and 202 are mounted on the sections 197 and 199, respectively, and have a spring 203 confined therebetween.

The latch element 193, as best seen in FIG. 26a, has an inclined bottom wall 204 which extends upward and aftward and terminates in a stop 205 which is engageable with a stop wall 206. It will be seen by referring to FIG. 27 that the aft shoe 191 is movable into camming engagement with the wall 204 when the latch element 193 will be rocked about the pin 194 and against the compression of the spring 203, as shown in broken lines, until said aft shoe clears said latch element. When this happens, the spring 203 will return the latch element to the position shown in full lines, i.e., behind the shoe 191, for preventing aft movement of the missile 171.

To restrain forward movement of the missile until the rocket thereof has been fired and has generated a predetermined amount of thrust, a restrainer latch is employed. This restrainer latch is shown generally at 208 in FIGS. 26, 26b, 27 and 28, and comprises a restrainer element 209, a tension spring 210, a stop 211 and links 212 and 213 connecting the spring to an anchoring point on the aft rail section 173. A pivot pin 214 mounts the restrainer element 209 between the rails of the inner track 190 of the aft support rail element 184, and a clevis pin 215 connects the upper end portion of said element 209 to the link 213. The element 209 extends above the link 213 to define a stop lug 216 which is engageable with the stop 211. The restrainer latch element 209 is provided with curved surfaces 217 and 218 which meet to form a notch 219. As best seen in FIGS. 26b, 27 and 28, the surfaces 217 and 218 adjacent the notch 219 are so shaped that when the element 209 is in its lowermost position, as shown in FIG. 27, that portion of the surface 217 which forms a part of the notch 219 will confront the forward edge of the aft missile shoe 191. The tension spring 210, acting through the links 212 and 213, will maintain the element 209 in its lowermost position and thus restrain the missile against unintended forward movement in the launcher. Ignition of the missile rocket will result in the generation of sufficient thrust to overcome the effect of the tension spring 210, when the aft missile shoe will rock the restrainer latch element 209 to the position shown in FIG. 28 and permit the missile to move from the launcher when other latches, to be described hereinafter, are actuated. The tension spring 210 is preloaded so that the aft shoe of the missile must exert a force of, say, one-half g before the element 209 will be moved to allow said shoe to pass.

It should be emphasized that since the aft latch 192 and the restrainer latch 208 are mounted in the aft support rail element 184, they, together with the support rail element 183 with the shoe 189 therein, provide a convenient means for limiting movement of a missile in the launcher during storage because, as stated hereinabove, said rail elements 183 and 184 are formed of harder material than the rail elements 181 and 182 and the tracks therein are narrower and thus more snugly engage the shoes 189 and 191.

The missile arming and firing mechanism is indicated generally at 220, is mounted partially in the aft rail section 173 near its forward end and partially in the arming housing 173A (FIG. 4a), and is shown in FIGS. 29 through 34, FIGS. 29 through 32 being diagrammatic. The arming and firing mechanism, which also includes an inadvertent ignition latch, consists of a plurality of cooperating elements including a pneumatic jack 221 having a cylinder 222 and piston rod 223. Referring first to FIG. 34, the cylinder 222 has a main piston 224 slidable therein, and an inner piston 225 slidable in the main piston. The aft end portion of the piston rod 223 extends slidably through the forward wall of the main piston 224 and is reduced in diameter to receive a sleeve 226 having an annular recess to receive the hub of the inner piston 225 thereon, said inner piston and said sleeve being held in place on the piston rod by a nut and lock washer combination 227. The inner piston 225 has a skirt 228 which cooperates with the aft end of the sleeve 226 to define a cup to receive the aft end of a compression spring 229 which surrounds said sleeve and is confined between the surface of the forward wall of the main piston 224 and said cup. The aft end of the main piston 224 is closed by an aft end wall 230, and air under pressure is selectively admitted to the forward and aft ends of the cylinder 222 through ports 231 and 232, respectively.

The cylinder 222 has its aft end mounted for limited pivotal movement within the aft rail section 173 in any suitable manner, as by a bracket 233, and the forward end of the piston rod 223 is provided with a fitting 234 for pivotal connection to a clevis 235 on the upper end of an arming lever 236 by a pin 237. At its lower end the arming lever carries an arming shoe 238 which, as shown in FIGS. 30a and 30b, has a cam surface 239 that terminates in a stop wall 240. The arming shoe 238 is movable by the piston rod 223 from the position shown in FIG. 29 to that shown in FIG. 30, in which latter position said shoe will engage an arming pin 241 on an arming switch 242 on the forward shoe 189 of the missile for moving said switch and arming the missile. In a manner to be described in more detail, in connection with the description of the operation of the complete arming and firing mechanism, the arming shoe 238 is held in engagement with the arming switch until the missile 171 moves forward in the launcher in response to rocket thrust.

Medially of its length the arming lever 236 is provided with a hub 243 through which is extended a cam shaft 244. The cam shaft is rigidly connected to the arming lever and, as best seen in FIGS. 29, 30, 31 and 32, extends at each side of said lever and has a crank 245 at each end, each said crank having a crank pin 246 which is movable in an arcuate cam slot 247 in the upper end of a contact plunger 248. Each of the plungers 248 carries a contact 249 at its lower end and each said contactor is engageable with a contact button 250 on the missile 171. In FIGS. 4a and 33, the plungers 248 are shown slidably mounted in guide sleeves 250A.

Associated with the cam shaft 244 at each side of the hub 243 between said hub and the crank 245 is a latch 251. The latches 251 are identical, so that a description of one will suffice for both. Each of the latches 251 includes a positive motion cam 252 which has a driving element 253, fixed on the shaft 244, and a driven element 254 which has its forward end pivotally connected to a bracket 255 secured in the launcher rail 172. Formed on the driven element 254 is a downwardly extending latch member 256 which, in its lowered position, is engageable with the forward edge of the aft shoe 191 for retaining the missile against undesired forward movement.

The operation of the arming and firing mechanism 220 is as follows. When it is desired to arm and fire the missile 171, air under pressure is admitted to the forward port 231 of the cylinder 222 for forcing the main piston 224 to its aftmost position in said cylinder. Such movement of the main piston will shift the arming lever from the position shown in FIG. 29 to that shown in FIG. 30, i.e., with the arming shoe 238 in engagement with the arming switch 242 and the pin 241 in engagement with the stop wall 240. In this position the piston rod 223 will have moved aft about one-half of its travel distance, said rod being limited as to further movement, as shown in FIG. 30, by engagement of the pin 241 with the arming shoe 238. Since the piston rod 223 is held in mid-position, as stated, the inner piston 225 will also be held against movement. It will thus be seen that shifting of the main piston 224 to its aftmost position will compress the spring 229 between the inner surface of the front wall of said piston and the inner piston.

At the same time the arming lever 236 is moved to engage the shoe 238 with the arming switch 242 and pin 241, as above described, for arming the missile, the cam shaft 244 will be rocked for partially rotating the driving elements 253 of the positive motion cams, for shifting the latch members 256 from their latching positions in front of the forward shoe 189, as shown in FIG. 30, and for moving the cranks 246 in their slots 247 for driving the contactors 249 into engagement with the contact buttons 250, also as shown in FIG. 30.

Engagement of the contactors 249 with the contact buttons 250 will cause ignition of the missile rocket and since the latch members will have been moved from in front of the aft shoe 191, and the restrainer latch 208 will release, the missile will move forwardly in the launcher. Such forward movement of the missile (and the aft shoe 191) will disengage said shoe from the arming shoe 238, when the spring 229 will move the piston rod to full aft position and, as shown in FIG. 31, move the arming shoe to its forwardmost position. Simultaneously the contactors will be raised and the latches 256 displaced. The arming and firing mechanism 220 is returned to pre-armed condition by admitting air under pressure through the port 232 into the aft end of the cylinder 222 for forcing the main piston forwardly in said cylinder and moving the piston rod 223 to its forwardmost position, as shown in FIG. 29.

AS will be seen in FIGS. 4a and 33, the forward end of the arming housing 173A forms the fixed part of the hinge that connects the forward and aft rail sections 174 and 173. As shown particularly in FIG. 33, the forward support rail element 183 has a guide track for the forward missile shoe 189, which track spans between the track 182 in the aft rail section and the track 188 in the forward rail section. The rails are so arranged that as the missile forward shoe leaves the forward rail section guide track at the front of the launcher, the aft shoe 191 simultaneously drops off of its guide track at the forward end of the aft rail section, that is, at the junction between said aft rail section and the arming housing. Thus, the forward support rail element 183, on the bottom of the arming housing 173A, has a guide track for the forward shoe only.

Referring again to the tripper unit 176, which functions to elevate the forward end portion of the rail section 174 so that it will be cleared by the aft end of a missile moving out of the launcher, said unit includes a housing 258 in which the tripper mechanism is mounted. The tripper unit 176 is shown in FIGS. 4a, 6, 17, 19, 20, 21, 22a through 22d, 23, 24 and 25. A latch plate assembly 178, shown in FIGS. 6 and 17, is associated with the unit 176. FIGS. 19, 20 and 21 show the tripper mechanism schematically and reference is first made to these views.

The upper rail of the forward frame section 12 is provided with a clevis 260. In schematic views 19, 20 and 21 the clevis 260 is shown, for convenience, attached to the upper wall of the launcher. The clevis is pivotally connected to a crank 261, mounted in the housing 258 and having its aft end connected to the forward end of a piston rod 262. The piston rod is movable in a cylinder that is mounted in the forward end of the forward rail section 174. The piston and cylinder comprise parts of an actuator 263 which will be described in more detail hereinafter. At this point, however, it should be stated that immediately prior to a missile launching operation air under pressure is supplied to the actuator 263 for urging the piston rod aftward for biasing the forward rail section 174 upwardly against restraint imposed by the latch mechanism now to be described.

Also mounted in the housing is a pair of latches 264. The latches are mounted side-by-side and are identical in construction, so that a description of one will suffice for both. Each of the latches 264 is pivotally mounted in a yoke 265 on the front of the housing and comprises a tongue 266 and a detent 267. The tongue 266 is initially engaged beneath a keeper 268 and is held in this position by engagement of the aft end of the detent 267 in a notch 269 which is formed in a sear 270 that is pivotally mounted on the bottom wall of the housing 258, the sear being initially held in latching position by one of a pair of trippers now to be described.

The pair of trippers mentioned hereinabove is mounted in the housing 258 on the bottom wall thereof, one at each side of said housing (see FIG. 23) and in position for engagement by the forward missile shoe 189 as it leaves the track 188. The trippers are shown generally at 271 and are identical, so that a description of one will suffice. The trippers cooperate with the sears which, in turn, cooperate with the latches 264, to the end that said latches will be released from their keepers, in a manner to be described hereinafter. In more detail, each of the trippers is mounted in a yoke 272 in the housing 258 and comprises a lever 273, a stop 274 and a buffer spring 275. The lever 273 is of substantially O-gee shape, as is the buffer spring 275, said buffer spring being of heavy sheet metal and being spaced from said lever. Engagement of each of the latches 264 with its keeper 268, as shown in FIG. 19, will be maintained by engagement of the detent 267 in the notch 269 in the sear 270, as stated hereinabove, and by the engagement of the stop 274 of the tripper 271 in an aft notch 276 in said sear. In FIG. 19 the buffer spring 275 of the lever 273 is shown immediately prior to contact therewith by the forward shoe 189. In FIG. 20 the shoe 189 has engaged the lever 273 for shifting the stop 274 out of the notch 276 for releasing the sear 270 and, thus, the latch.

As stated hereinabove, the forward section 174 of the launcher rail 172 is biased in an upward direction by high-pressure air in the cylinder of the actuator 263, acting on the piston rod 262, said upward movement, however, being restrained by engagement of each of the tongues 266 with its keeper 268. It should be noted that when the latch tongues engage their keepers, the vertical center lines of the latches will be located slightly aft of the center lines of the clevises 260. Thus, when the latches are released, as shown in FIG. 20, the tongues thereof will be withdrawn from their keepers by the upward biasing action of the actuator 263. In FIG. 20 the forward end portion of the forward rail section 174 is shown as it starts to move upwardly, and in FIG. 21 said forward end portion is shown in its fully elevated position and with the forward shoe 189 clear of the launcher.

Attention is now directed to FIGS. 22, 23, and 24 of the drawings wherein an actual, rather than schematic, embodiment of the tripper mechanism 177 is shown. Where appropriate, the same reference numerals used in FIGS. 19, 20 and 21 have been applied. FIG. 23 shows in front elevation the tripper housing 258 with one end broken away to show the springs for the latch, sear, and tripper, and the cover for the springs and their associated parts. These springs and associated parts are shown in side elevation, with the cover removed, in FIG. 22, and in top plan in FIG. 24. Referring specifically to FIG. 22, the latch spring is shown at 277. It has its aft end mounted rigidly in a clip 278 which is secured to the outer wall of the tripper housing 258 and its forward end bearing against the pin 279 of a crank 280, the crank having a stub shaft 281 that extends into the housing and is pinned to its associated latch 264. As will be apparent, the latch spring urges the latch tongue 266 into engagement with the keeper in the latch plate 179.

A sear spring 282 is mounted on the tripper housing wall beneath the latch spring 277 and bears against a crank 283, similar to the crank 280, which is attached to the sear 270, and normally retains said sear in engagement with the detent 267 of the latch 264. Also mounted on the tripper housing wall, beneath the sear spring 282 and with its aft end in a clip 284, is a tripper spring 285, the forward end of which engages a pin 286 on a tripper lever 287. The tripper lever has an arm 288 with relief pins 289 thereon which engage the springs 277 and 282 when the tripper 271 is engaged by the forward missile shoe 189 for relieving pressure on the latch 264 and the sear 270, as shown in FIG. 22b. The tripper lever also has an extension 289' which engages the movable arm 290 of a switch 291 that is connected in an interlock circuit. As in the cases of the latch spring 277 and the sear spring 282 as to the latch and sear, respectively, the tripper spring 285 normally retains the tripper 271 with its stop 274 (FIGS. 19, 20 and 21) in engagement in the aft notch 276 of the sear 270. A cover 292, shown best in FIGS. 23 and 24, encloses the springs 277, 282 and 285 and their associated parts, and a projection 293 on the tripper housing 258 is engageable with the latch plate assembly 178 for limiting upward movement of the forward rail section 174.

By referring to FIGS. 22a through 22d, the operation of the tripper mechanism may be followed from immediately before engagement of the forward shoe 189 with the buffer spring 275 of the tripper 271 (condition 1-FIG. 22a) until said shoe has cleared the tripper and the forward rail section 174 has been elevated, for the purpose stated hereinabove (condition 4-FIG. 22d).

The actuator 263 per se is shown in FIG. 25. The cylinder is indicated at 294 and receives the piston rod 262 therein. As will be seen, the piston rod extends throughout the length of the cylinder and beyond the forward and aft ends thereof. As its forward end the piston rod 262 carried a clevis 295 which is suitably secured to said rod.

The cylinder 294 is provided with an enlarged forward end portion which defines a shoulder 296. A forward bearing 297 surrounds the piston rod 262 within the enlarged forward end portion and bears against the shoulder 296, the forward bearing having packing rings 298 and being held in place by a forward end plug 299 which is screwed into said forward end portion.

The cylinder 294 is enlarged throughout the aft one-half of its length, the enlarged aft section defining an internal shoulder 300 and the aft end portion of said section being slightly further enlarged and internally threaded to receive an aft end plug 301.

Mounted in the cylinder 294 and surrounding the piston rod 262 is a separator ring 302. The separator ring has a flange 303, which bears against the shoulder 300, and suitable packing and seals to prevent leakage along the piston rod or between said ring 302 and the inner wall of the cylinder. A stop ring 304 retains the separator ring 302 in place.

Secured in the aft end portion of the cylinder 294, and retained in place by the aft end plug 301, is an elongated aft bearing 305, and disposed between the forward end of said aft bearing and the stop ring 304, and in engagement with the inner wall of the cylinder is a spacer sleeve 306. The spacer sleeve is provided with an opening 307 which is located beneath a filler plug 308.

It will be seen from the foregoing that the separator ring 302 divides the interior of the cylinder 294 into fore and aft chambers, hereinafter called an air chamber 309 and a buffer chamber 310. High pressure air is introduced to one end or the other of the air chamber 309 by pipes 311 and 312. The buffer chamber 310 is filled with a liquid of appropriate viscosity and sealed. An actuator piston 313 is fitted on the piston rod 262, as by snap rings 314, within the air chamber 309, and a buffer piston 315 is secured to said rod 262 within the buffer chamber 310. As will be seen in FIG. 25, the buffer piston is of smaller diameter than the spacer sleeve 306, thus to define a liquid passage between said piston and said sleeve, the piston, the sleeve and the liquid in the buffer chamber 310 defining a buffer 316.

At the forward end of the actuator 263 a mounting flange 317 is provided, to permit mounting of said actuator on the forward frame section 12 of the frame 10.

When a missile is made ready for launching, air is admitted to the forward end of the air chamber 309 and acts on the actuator piston 313 for stressing the piston rod 262 toward the aft end of the cylinder 294. The piston rod will be held in constraint, however, since, as previously described, the tongues of the latches 264 will be retained in engagement with their keepers by the sears and the trippers. The forward rail section will thus be retained in lowered, normal, position until the missile is fired. When the missile is fired the forward missile shoe 189 will engage the trippers 271 and release the latches 264, as shown in FIGS. 22a through 22d, when the piston rod 262 will be urged aft in the cylinder. Aft movement of the piston rod will be transmitted through the crank 261 to the clevis 260. Since the clevis 260 has its upper end attached to the upper wall or frame section of the launcher, the rail section will be elevated. Release of the latches 264 will take place suddenly, with the result that were it not for the buffer 316, damage to the forward end of the rail section 174 or to the launcher frame, or to the tripper mechanism itself, could take place. As will be clear from the foregoing, movement of the piston rod 262 by the actuator piston 313 will of course move the buffer piston 315. Movement of the buffer piston and the rod 272 will be retarded by the action of the liquid as it flows in the buffer chamber 310 from one side of said buffer piston to the other side thereof.

Return of the rail section 174 to its lowered, pre-launch position will be effected by movement of the piston rod 262 in the opposite direction, in response to high pressure air acting on the aft face of the actuator piston 313. Again, the buffer 316 will act to cushion the movement of the rod 262 to protect the rail section, launcher frame and tripper mechanism from damage due to shock.

As shown in FIG. 41, the missile 171 is provided at its aft end with self-erecting foldable fins 318. The fins 318 are held in folded positions by clips 319 prior to loading the missile into the launcher. As the missile is rammed into the launcher, however, the clips are automatically removed, by engagement thereof with the launcher body, for allowing the fins 318 to come into spring-loaded contact with guide rails 320. During a missile launch the fins 318 follow the guide rails 320 throughout the length of the body. As the aft end of the missile leaves the launcher, the fins will snap to erect position. The guide rails are shown schematically in FIGS. 13 through 16 and as in actual use in FIGS. 3, 6, 7 and 18.

By referring to FIG. 18 it will be seen that the guide rails 320 are mounted in opposition in the frame at each side thereof and medially of its height. The guide rails, as stated, extend throughout the length of the launcher and, as shown in FIG. 13, have their forward, intermediate and aft end portions secured to the forward, intermediate and aft frame sections 12, 14 and 16, respectively. Also as shown in FIG. 13, the opposed walls of the rails 320 are tapered inwardly, i.e., toward each other, substantially three-eights of an inch, from the aft frame 16 toward the intermediate frame 14, and are tapered outwardly substantially 2 inches, from said intermediate frame toward the forward frame. During a missile launch the inward taper of the aft sections of the guide rails forces the panels of the fins 318 to rock within a small angle about their erection hinge centerlines, thus eliminating any sticking of the fins that might have developed as a result of missile stowage in the launcher. The outward taper of the forward sections of the guide rails permits the fins to start their opening cycle and also provides clearance for missile side shift that may occur after drop-off while the missile is in free flight and partially in the launcher.

Prior to launching the missile 171 electric power and command signals must be transmitted thereto from the launcher. The connector 170 employed for the purpose is shown in FIGS. 9, 10, and 11, FIG. 10 being an exploded perspective. The connector includes a missile socket 322 on the aft end of the missile, an adapter 323, an expendable wiring harness 324, and a frame socket 325 on the aft end of the launcher. A base 326 mounts the frame socket and a tubular, generally reversed L-shape housing 327 supports the harness 324. As shown in FIG. 10, the wiring harness 324 has a spring-loaded plug 328 which mates with the adapter 323 and maintains a slip fit engagement and is so mounted in the housing 327 as to permit freedom of motion to compensate for any linear or angular misalignment. When the missile 171 is launched, its forward motion will pull the adapter 323 free of the plug 328 of the harness 324. Following a missile launch the harness 324 is discarded and a new one used for the next missile to be fired.

An aft closure for the launcher is shown at 330 in FIG. 11. The aft closure 330 seals the aft opening of the launcher but is displaced or ruptured by internal pressures of the order of 5 to 7 psi during a missile launch, but is able to withstand external green sea loads of 1,000 lbs. per square foot. Ideally the aft closure is made of lightweight material of the rupture-diaphragm.

Referring to FIG. 41, there is shown a loading apparatus which may be used under certain conditions to facilitate the loading of a missile into the launcher. The loading apparatus is indicated at 331 and includes a supporting frame 332 and a missile loading beam 333, the forward end of which beam is attached to the yokes 186 at the aft end of the launcher after removal of the aft closure 330. As will be obvious, a missile to be loaded into the launcher is placed on the beam 333 and moved therealong and into the launcher body A.

To show the feasibility of a multiple cell launcher according to the invention, the arrangement of FIG. 40 is provided. In this view, which is a perspective partially broken away, eighteen launcher cells are arranged in batteries of nine for movement in azimuth and elevation at each side of a suitable mount. The mount is shown at 335 and the batteries of launcher cells at 336 and 337.

The control system for the launcher is shown in FIGS. 35, 36, 38, 39 and 39a. It should be understood, however, that in actual practice the launcher control system would be modified to suit the conditions under which it would operate. It is believed, furthermore, that an adequate understanding of the operation of the invention can be obtained from a study of the wiring circuits and pneumatic system utilizing as reference numerals the letter-number combinations shown, together with the legends applied. Accordingly, only those additional reference numerals thought necessary have been used.

The control console is shown at 338 and the launcher A on a mount 339. On the panel of the console are indicator lights 340, bearing the legends shown, for showing air pressure, rail position, forward door position, etc. Switches 341 on the panel are used for controlling the various circuits. The pneumatic system shown in FIG. 38 and the electric circuits shown in FIGS. 39 and 39a work together, i.e., the valves in the pneumatic system are controlled by solenoids in the electric circuits. For example, in FIG. 38 the actuator 263 for the forward rail section 174 is controlled by a valve 342 (FIG. 38) which is operated by a solenoid V-3 (FIG. 39a) under the control of a relay R-3 (FIG. 39), the relay R-3 also including firing and arming interlock switches and switches for controlling the appropriate indicator lamps on the panel of the console 338. A flow control valve 343 and a muffler 344, both of conventional design, are connected to the valve 343. Similarly, air flow to the pneumatic jack 221 of the arming mechanism 220 is controlled by a valve 345 (FIG. 38) which is operated by a solenoid V-2 (FIG. 39a) under the control of a relay R-4 (FIG. 39). A muffler 346 is connected to the valve 345 and a pair of flow control valves 347 and 348 are connected between said valve and the jack 221.

The door actuator 68 is controlled by a valve 349 which has a muffler 350 connected thereto. The valve 349 is operated by solenoids V1-O and V1-D (FIG. 39a) under the control of a relay R-1 (FIG. 39). Flow control valves 351 and 352 are connected between the valve 349 and the actuator 68, and a quick exhaust valve 353 is interposed in the line between said flow control valve 351 and said actuator.

The master air valve, shown at 354 in FIG. 38, is operated by solenoid V-4. The valve 354 is connected to the air storage containers 52 via a drain 355 and a pressure regulator 356. A pressure indicator is shown at 357, a manual shut-off valve at 358 and a filler pipe at 359, the filler pipe being adapted for connection to an air supply source 360 through a flexible line 361 and a quick disconnect 362.

The electrical circuits also include a cancelling relay R-2, which is connected to a cancelling switch S-16, the firing transformers 166 having secondary terminals connected to the contact buttons 250, and a firing switch S-17 connected to a firing relay R-5. The circuits further include means for disarming the missile, for effecting emergency opening of the forward door 60, and for controlling air pressure in the pneumatic system. For remote operation cancellation, arming and firing switches S-30, S-18 and S-20, respectively, are mounted in a remote control box 364.

In FIG. 37 is shown a time sequence chart. From a scrutiny of this chart it will be seen that the total time consumed for launching a missile is one and one-half seconds.

In its initial condition the launcher has its forward rail section latched down, its forward door closed, and is disarmed.

When the power switch S-9 (FIG. 39) is closed, those indicator lights 340 on the panel of the console 338 which show power On, air Off, door CLOSED, rail DOWN and arming SAFE are energized, and relay R-3 closes the arming circuit. The air control switch S-10 (FIG. 39) is then closed, when the air ON light will be energized and the air OFF light will be extinguished, and the master air valve 354 (FIG. 38), controlled by the solenoid V-4 (FIG. 39a), will be opened. At the same time air is supplied to the DOWN side of the rail actuator 263, to the CLOSED side of the door actuator 68, and to the SAFE side of the arming actuator. Air pressure in the system is sensed by a pressure switch 365 (FIG. 38), which is connected to the master air valve 354, and indicated by appropriate lights 340 on the console 338. The switch 365 is set to operate from 150 lbs. to 275 lbs.

When the DOOR-OPEN switch S-11 (FIG. 39) is closed the relay R-1 is energized for operating the solenoid V1-O (FIG. 39a) and opening the valve 349. Energization of the relay R-1 also closes the arming and firing circuits. When the valve 349 is opened, the actuator 68 will be operated for opening the forward door 60. When the door 60 is open, a DOOR-OPEN microswitch S-7 (FIG. 39a) completes a circuit to a DOOR-OPEN indicator light on the console panel and interrupts a DOOR-CLOSED light thereon. When the door 60 is fully open a RAIL-UP microswitch S-3 (FIG. 39a) closes to energize the solenoid V3 to apply air to the UP side of the rail actuator 263, said rail, however, being held down by the latches 264 of the tripper mechanism 177.

Operation of an arming switch S-14 (FIG. 39) energizes the solenoid V-2 (FIG. 39a) for operating the valve 345 and thus the jack 221 of the arming and firing mechanism 220. Also, arming microswitches S-4 and S-5 (FIG. 39) are actuated to illuminate the ARMED indicator light on the console panel and open the circuit to the SAFE light on said panel.

To fire a missile from the launcher a FIRE switch S-17 (or switch S-20 in the remote control box 364) (FIG. 39) is closed for operating the relay R-5 and energizing the primaries of the firing transformers 166 for firing squibs in the missile.

It should be understood that the arming and firing functions are interlocked with the door opening and rail positioning functions. Thus, it is necessary that the forward door 60 be open, the forward rail section latched down, and the missile armed before firing can take place.

At any time up to the point of closing the FIRE switch S-17, the firing sequence may be cancelled and the launcher returned to its initial condition. To effect cancellation a switch S-16 (FIG. 39) is closed, when the relay R-2 (FIG. 39) will be energized for operating the DOOR CLOSE solenoid V1-C (FIG. 39a) for closing the door. At the same time the DOOR-OPEN and the arming and firing circuits are interrupted, the forward rail is reset to the DOWN position, and the indicator lights on the console panel are returned to CLOSED, as to the door 60, DOWN, as to the rail, and SAFE, as to the arming circuits.

The forward door 60 may be closed and the arming and firing circuits interrupted by operating the DOOR CLOSE switch S-12 (FIG. 39). Operation of this switch S-12 opens the holding circuit to the coil of the relay R-1, opens the circuit to the solenoid V1-O (FIG. 39a) and completes the circuit to the solenoid V1-C (FIG. 39a). If arming had been effected previously, the breaking of the circuit to the relay R-1 would interrupt the circuit to the solenoid V-2 (FIG. 39a) with the result that the actuator 220 would assume the DISARM position.

If it is only desired to disarm the missile, a pushbutton DISARM switch S-15 (FIG. 39) is depressed, when the circuit to the coil of the relay R-4 will be broken and the solenoid V-2 de-energized, for permitting the arming mechanism to return to SAFE. Opening of the circuit to the coil of the relay R-4 also results in interruption of the circuit to the firing relay R-5.

It is believed that the construction and operation of the present invention will be understood from the foregoing description.