US2485715A

US2485715A - Rocket launching apparatus

Info

Publication number: US2485715A
Application number: US783716A
Authority: US
Inventors: Fred C Eastman
Original assignee: United Shoe Machinery Corp
Current assignee: United Shoe Machinery Corp
Priority date: 1947-11-03
Filing date: 1947-11-03
Publication date: 1949-10-25
Anticipated expiration: 1966-10-25

Description

Oct. 25, 1949. F.c. EAsTMAN I ROCKET LAUNCHING APPARATUS rr sheets-sheet 1 Filed Nov. 5, 1947 Inventor Fre CEaman Oct. 25, 1949. F, C', EASTMAN I 2,485,75

ROCKET LANCHING APPARATUS Filed Nov. 3, 1947 7 Sheets-Sheet 2 Inventor (kt. 25, 1949, F.c. EASTMAN I 2,485,715

ROCKET LAUNCHING APPARATUS Filed Nov.' s, 1947 V7 sheets-snee; s

Inventor Fred Gatman l o@ 25, 1949-. v F. c. EAsTMAN Y 2,485,715 z ROCKET LUNCHING APPARATUS Filed Nov. 5, 1947' 7 Sheets-Sheet 4 Inventor F'r'ed C'Eaatman Oct. 25, 1949. n F. c. EASTMAN 2,485,715

ROCKET LAUNCHING APPARATUS Filed Nov. s. 1947- 7 sheets-sheet 5 I- Inventor Fred GEastman '7 Sheets-Sheet 6 Filed Nov. 3, 1947 Oct. 25, 1949. F. c. l-:AsTMAN ROCKET LAUNCHING APPARATUS '7 shets-sheet 7 Filed Nov. 3, 1947 m/enor Fred C Eastman Patented Oct. 25, 1949 2,485,715 Y n ROCKET LAUNCHING APPARATUS Fred C. Eastman, Marblehead, Mass., assignor to United Shoe Machinery Corporation, Flemington, N. J., a corporation of New Jersey Application November 3, 1947, Serial N o. 783,716

(Cl. Sil-1.7)

9 Claims.

This invention relates to a rocket launching apparatus particularly adapted for use in airplanes.

The invention has as its objective to facilitate the automatic indexing and firing of successive rockets from the apparatus as well as to improve the structure oi the apparatus generally.

In accordance with one feature of the invention, therefore, the illustrated rocket launching apparatus, comprising a magazine with a firing tube and an exhaust tube at opposite ends thereof, means for indexing rocket carrying tubes into firing position in alinement with the iiring tube, and means for firing the rocket, is provided with means for automatically initiating another indexing and ring cycle upon iiring of each successive rocket.

In accordance with another feature of the invention, removal of defective or unred rockets is facilitated by providing an ejecting or jettisoning station, which consists of an opening in the magazine normally closed by gates forming a continuous path for the rocket tubes in the magazine, and providing means for instituting a jettisoning cycle, diiring which the gates are released and the defective rocket moved from the firing station into position above the gates which open under the weight of the rocket so that it may drop through the opening.

These and other features of the invention will appear more fully from the following description when read in connection with the accompanying drawings and will be pointed out in the appended claims.

In the drawings,

Fig. 1 is a side view of the rocket launching apparatus;

Fig. 2 is a longitudinal sectional view through a rocket carrying tube showing a rocket mounted therein;

Fig. 3 is a front side, partly in section, of a portion of a rocket indexing mechanism and a driving mechanism therefor;

Fig. 4 is a sectional View of a clutch and brake associated with the driving mechanism;

Fig. 5 is an end view of a control mechanism for the clutch shown in its clutch-disengaging position;

Fig. 6 is a detail view of a portion of the clutch control mechanism;

Fig. 7 is an end view showing the structure of a lever and link assembly forming a portion of the control mechanism;

Figs. 8 and 9 are end views of the control mechanism in the positions assumed thereby during engagement of the clutch;

Fig. 10 is a side view, partly in section, of a mechanism for automatically initiating an indexing cycle, showing the parts in inoperative position;

Fig. 11 is an end View, partly in section, of the parts shown in Fig. 10.

Fig. l2 is a side view corresponding to Fig. 10, showing the parts in operative position;

Fig. 13 is a Wiring diagram;

Fig. 14 is an angular View of a jettisoning mechanism; and

Fig. 15 is a view in end elevation of the rocket launching apparatus shown in Fig. 1, illustrating the rockets in the apparatus with a rocket and its tube in firing position and a rocket and its tube in loading position.

General The illustrated rocket launching apparatus holds a plurality of rocket containing tubes which are successively brought into a firing position in the apparatus and red therefrom. It is designed for use in airplanes and may conveniently be located either on the outside of the airplane below the bomb bay or within the bomb bay, in which latter case the lower portion of the apparatus projects through an opening in the airplane.

The apparatus consists of a magazine I9 (Fig. l) provided with a firing tube I2 and an exhaust tube I 4. The magazine comprises end walls or brackets I6, I8 and a body portion or sides 20 and has a noncireular, elongated shape. It is closed as well as sealed at all parts through which flame leakage might occur to prevent the ignition of fumes within the airplane. An opening is provided at the top of the magazine through which access may be had to the interior of the magazine for the purpose of loading it with rockets. The opening is normally closed by means of a cover 22 pivoted to the brackets I6, I8. The cover may be locked in its closed position by latches 24 which engage pins 26 secured in the brackets I6, i8.

3 Illustrated in Fig. 2- is a tube 28 in which is contained a rocket 38. While the illustrated magazine is designed to hold six tubes, it can readily be expanded to hold a greater number of tubes by elongatng the mid-section thereof heightwise.

Indexing The tubes 28 with the rockets 3Q are moved or indexed in the magazine in the following manner. Shafts 32, 34 (Figs. l and 3) are mounted to rotate in the brackets |8, |8. These shafts carry near their

ends star wheels

38, 38 which engage successive rocket tubes 23 and feed them around the curved top and bottom portions of the magazine. The tubes are oonveyed from the Vstar wheels 36 to the star wheels 38 by guide rolls 38 carried by shafts "l2 (only one shown in Fig. 1) which move with a portion of the drive mechanism, as Ywill be described.. The indexing of the tubes 28 is further facilitated by rolls lil rotatably mounted in the ends of the

star wheels

38, 38, the rolls lill tending to roll the tubes 28 along the inner face of the magazine body 28.

The shafts 32, 34 are rotated by a motor 43 (Fig. 3) through a clutch and a variable tspeed mechanism. The motor 48 is secured to a housing 43 which contains the variable speed drive 'parts land is attached to the bracket 3. A motor gear` 58 (Fig. 3), rotated by the motor, meshes with a gear 52 (Figs. 3 and 4) forming the driving part of a multiple disk clutch 54 of conventional type. The vclutch disks are mounted on a shaft 53. The clutch is engaged and a multiple disk n,

brake 60 of conventional type is disengaged by a spring 58 (Fig. 4) which moves a clutch controlling operating screw 82 and a shaft 81| connected to the screw lengthwise (to the right of Fig. l4). Reverse movement of the screw 82 and the shaft |53 disengages the clutch and engages the brake.

When the clutch 5t is engaged to rotate the shaft 53, a pinion (S6 secured to the shaft 56 rotates an intermediate reduction gear 6B mounted in bearings 'lll in the housing 48. A pinion l2 integral with the said gear 83 meshes with a gear lvl on a shaft 16 which is also mounted to rotate in the housing 48 and may be designated as the input shaft into a variable speed drive 78. The vari-able speed drive le is a combination of a continuous motion with a dierential and produces a harmonic or intermittent movement. Thus the input shaft f6 of the variable speed drive is rotated at substantially constant velocity, but an output shaft 88 of said drive 'E8 will move at varying velocity so that at the beginning and the end of each cycle the velocity of the shaft 88 is zero and its acceleration is zero or substantially zero. The velocity of the shaft 88 accordingly is gradually increased at the beginning of each cycle and gradually decreased at the end of each cycle, making a smooth operation of the indexing mechanism at high speeds possible. Such variable speed drives are well known and are described, for example, in United States Letters Patent No. 2,309,595, granted January 26, 1943, upon application of Lester E.. James.

The output shaft 38 of the variable speed drive, which shaft is also a sprocket shaft, carries a sprocket 82. Rotation of the sprocket 82 is transmitted to a sprocket 86| on a shaft 88, mounted to rotate in the bracket I8, by means of a chain 88. Pinions 38, 92 likewise -secured to the

shafts

88, 88 mesh with gears 94, 86 on shafts 98, '|33 rotatably mounted in the bracket I8. Pinions |82, |83 on the shafts 88, |08 mesh with pinions '4 |83, |08 on the aforementioned shafts 32, 34. Only the series of gears and pinions at the right side of the magazine ||l is illustrated in Fig. 3. A corresponding series of drive parts comprising pinions, gears, sprockets, and a chain is provided at the left side of the magazine, rotation being imparted to the drive parts at the left side by the shaft 88 through the drive parts at the right side of the magazine and through the shafts 32, 34. The chains 88 carry the aforementioned shafts l2 so that the rolls d!! move with the chains.

Indexing control As previously mentioned, engagement and disengagement of the clutch 52 and the brake 8U are effected upon lengthwise Vmovement of the screw |52-, Movement of the screw 62 is controlled by an adjustable screw Hil (Figs. 3, 4, 5, and 6) mounted in a lever ||2 and held in adjusted position by a nut H4 (Fig. 6). The lever 2 is secured to a shaft ||6 which rotates in bearings in a bracket H8 secured to the aforementioned housing 38. Likewise joined to the shaft i6 is a lever |28 to which is pivotally connected a rod |22.

y, in alinement the levers |24, |28 have the effect of a straightened toggle, locking the screw |||l in its clutch disengaging position.

Operation of indexing control When the solenoid |68 is energized, the pawl |54 is swung counterclockwise (Fig. 5) about its connection with the lever |58 until the abutment |66 engages the screw |64 (Fig. 8). This movement of the pawl |54 swings the latch |42 clockwise (Fig. 5) about its fulcrum pin |44, against the action of the spring |56. Clockwise move- Y ment of the latch |42 shifts the links |46 horizontally. Since the pivot pin |36 at this time is iixed by engagement of the high face of a earn |16 with a roll |14 carried by the right-hand end of the lever |38, the links |46 move the pivot pins |30, |34 in a clockwise path about the roll |52, whereby the pivot pins |30, |34 are moved out of alinement with the pins |28, |36, as shown in Fig. 8, and the levers |24, |26 are displaced, disturbing their toggle or locking effect, as may be determined by comparison of Figs. 5 and 8. 'Ihis displacement of the pivot pins |34, |30 and the corresponding movement of the levers |24, |26 permit the spring 58 (Fig. 4) to move the screws 62, l0 outward, the lever |2 moving outward about the shaft ||6 with the screw ||0 and the rod |22 moving upward (Fig. 8). The spring 58 in thus shifting the screw 62 to the right of Fig. 4 engages the clutch 54 and disengages the brake 60, whereupon the motor 46 rotates the shaft 56 and, through the gears and pinions 66, 68, 12, 14, 90, 82, |02, |04, rotates the shafts 32, 34, thus effecting an indexing cycle and moving a tube 28 into firing position in the magazine l0.

The parts are restored to their original positions as follows. When the solenoid is deenergized, the lever |58 and the pawl |54 move downward and the spring |62 swings the pawl back into locking engagement with the latch |42. As the shaft 16 completes its rotary movement, the high face of the cam |16 again engages the roll |14 swinging the lever |38 counterclockwise (Fig. 9) about the pin |40. This effects adownward movementor the left end of the lever |38, moving the lever assembly |24, |26 downward as a unit and returning the links |32 to their normal vertical positions. This downward movement of the levers |24, |26 swings the screw ||0 inward or to the ft of Fig. 4 through the rod |22 and the lever ||2. Inward movement of the screw ||0 shifts the .screw 62 to the left of Fig. 4, against the pressure of the spring 58, disengaging the clutch and engaging the brake. The clutch now is locked in disengaged position again by the levers Automatic firing control As has been stated before, it is the purpose of the present invention to be able continuously to fire successive rockets as they are automatically indexed into firing position. Before describing the electrical system which makes this possible, a switch control instrumental in eifecting the desired purpose will be, described.

Secured to the ring tube I2 outside of the magazine |8 is a casing |18 (Figs. 10, 11, and 12) containing two gas-tight chambers |80, |82 (Fig. il) separated from each other by an inner wall |84. Mounted to rotate in the wall |84 and extending into both chambers is a shaft |86. The shaft end extending into the chamber carries a lever |88 (Fig. 10), the end of which extends downward through a hole |90 in the ring tube and is positioned in the path of the rocket as it passes through the iiring tube.

Secured to the shaft |86 within the chamber 82 is a cam |92. A spring |94 tends to hold the cam |62 in its inoperative position and the end of the lever |88 in its downward position, extending into the firing tube. One end of the spring is joined to the cam |92 and the other' end is joined to a bifurcated member comprising a bolt |96 and a clamp |98, each provided with a prong, said member maintaining the spring under preliminary tension. As the ired rocket passes through the tube I2, the force of the rocket swings the lever |88 upward into the position shown in dotted lines in Fig. 12, in which position the lever |88 engages a stop 200. Upward movement of the lever |88 rotates the shaft |86 and the cam |92 simultaneously, further tensioning the spring |194. In rotating, the high face of the cam |92 is brought into engagement with a switch 202 which, as will be described below, closes the circuit of the indexing solenoid |68 (Fig. 5). The spring |94 returns the cam |92 and the lever |88 to their initial positions after the rocket has passed the hole |90.

Indez'ng and firing systems In describing an automatic rocket ring cycle, it will be assumed that a rocket has been indeXed to firing position in the magazine l0 (Fig. 1) in which position a ground contact ring 204 (Fig. 2) on the rocket tube 28 is in engagement with a grounded plunger 286 in the magazine |0 A positive contact ring 208 on the tube 28 engages a terminal 2I0 in the magazine. As likewise shown in Fig. 2, wires 2|2, 2|4 leading from the rocket are attached to ground and positive terminals 2|6, 2|8 on the inner face of the tube 28 which terminals are connected, respectively, to the contact rings 204, 208. The power is turned on to start the motor 46 (Fig. 13) by closing a motor switch 228 on a switchboard B. This establishes a circuit from the positive side of the source of power through a motor relay 228 to ground, causing the armature of the relay to be 75 drawn up to connect the positive side of the source of power to a wire 229 which is also permanently connected to the armatures of four other relays, to be referred to hereinafter, and to one terminal of the motor 46, the other terminal of which is grounded. A switch 222, which may be termed a timing switch, in the firing circuit is held closed by the lever |38 when the roll |14 is upon the high face of the cam |16 (Fig. 5)

Closing of an automatic firing switch 224 (Fig. 13) to fire the rocket located in firing position establishes a circuit through a relay coil 226, namely: from the positive side of the source of power through the motor switch 228, the automatic firing switch 224, and the relay 226 to ground, drawing up its armature. Thus a circuit is established from the positive wire 229 through the armature of the relay 226, a line 23D, the switch 222, the terminal 2|, the squib of the rocket, and the plunger 266 to ground.

Firing of the rocket by closing of the ring circuit, as described in the preceding paragraph, causes the switch 262 to be closed by upward movement of the lever |88 (Fig. 12) and rotation of the cam E92 and an indexing circuit is then completed as follows: from the positive side of the source of power through the armature of the relay 228, the line 229, the armature of the relay 226, a line 232, the switch 202, a line 234, and the solenoid |68 to ground. During the indexing, the timing switch will be opened but upon completion of the indexing cycle, the timing switch 222 will again be closed by the cam |16 and the next firing cycle will automatically be initiated, the ring circuit being completed in the manner aforedescribed, as long as the switch 224 is held closed.

If desired, each rocket, as has heretofore been customary, may be lired individually, at any time desired, in the following manner. With the motor circuit closed, a single ring switch 236 is closed. This establishes the following circuits to rire a rocket, namely: (a) from the positive side of the source of power to the motor switch 220, the single firing switch 236, a relay 238, whereby the armature of the relay 238 is drawn up, to ground, and (Zr) from the positive side of the source of power, to the armature of the relay 228, the armature of the relay 238, the line 230, the switch 222, the terminal 2|0, the squib of the rocket, and the plunger 286 to ground.

After firing the rocket in this manner, it is then necessary to bring about an indexing cycle to move another rocket into firing position. To do so, an indexing switch 246 is closed, establishing the following circuits: (a) from the positive side of the source of power to the motor switch 228, the indexing switch 24E), a relay 242, and ground, whereby the armature of said relay is drawn up, and (b) from the positive side of the source of power to the armature of the relay 228, the armature of the relay 242, a line 244, and the solenoid |68 to ground.

When the magazine is to be loaded, the cover 22 (Fig. 1) is opened and the motor circuit is closed by a switch 246 (Fig. 13) located more conveniently relatively to the magazine than is the switchboard containing the automatic rng, single firing, and other switches previously mentioned. With the motor circuit closed, closing a loading switch 248 establishes the following circuits: (a) from the positive side of the source of power, through the switch 246, the switch 248, and the relay 242 to ground, and (b) from the positive side of the source of power to the armature of the relay 228, the armature of the relay 242, the line 244, and the solenoid |68 to ground, thus initiating an indexing cycle.

J ettisom'ng At times a dud or misiire is encountered and it is necessary to remove the defective rocket from the magazine before ring can be continued. Such a rocket is removed by jettisoning in the following manner. Immediately beyond the firing position (in the direction of indexing) the magazine is provided with an opening the width and length of which correspond to that of a tube 28. The guideway or path of the rocket across this opening during normal indexing of the rocket is formed by a pair of gates 250 (of which only one is shown in Fig. 14). Since the gates and their release mechanism are identical at both ends of the opening, only one has been illustrated in Fig. 14 and only one will be described. Each gate 266 is pivoted at 252 to the magazine and the gates are swung together into an indexing path-forming position in engagement with stop faces 254 on the magazine by torsion springs 256, of which only one is shown. The springs 256 are mounted on the pivots 252, one end of each spring engaging a pin 258 secured to the corresponding gate 258. The gates are locked in closed position by a latch 268 which engages the adjacent gate faces, as illustrated. The latch 26!)v is pivotally mounted at 262 in lugs on the magazine I6 and is also pivoted to a link 264. The link 264 in turn is pivotally joined to a twoarmed lever 266. The lever 266 is mounted between lts ends to swing about a pin 268 mounted in lugs in the magazine i0. A connection 210 joins the lever 266 to a jettison solenoid 212.

When the solenoid is energized, as will be described below, the lever 266 is swung clockwise about the pin 268 (Fig. lll), shifting the link 264 to the left and moving the latch 26) out of engagement with the gates 250. As the rocket and its tube are then moved beyond the ring station and into position over the gates 250 by closing the indexing circuit, said gates will be opened by the weight of the rocket and permit the rocket and its tube to drop out of the magazine. If the magazine is located Within the bomb bay, the opening in the magazine will be positioned directly above a corresponding opening in the bomb bay. A pin 214 moved inward into the magazine, by clockwise movement of the lever 266 about the pin 268, prevents the rocket from accidentally rolling beyond the magazine opening and into the magazine. When the rocket has dropped out of the magazine, the springs 256 return the gates to their closed position. Deenergizing the solenoid causes the gate release parts to return to their initial position, the latch 260 again locking the gates 258.

In order that the rocket may be jettisoned by movement beyond the firing position and over the opening in the magazine, an indexing cycle must be initiated as indicated above. The jettison solenoid 212, is arranged in the circuit of the indexing solenoid |68 so that closing of a jettison switch 216 (Fig. 13) will simultaneously effect an indexing cycle or the rockets and an energizing of the solenoid 212. Assuming that the motor circuit is closed, closing the jettison switch 216 establishes a circuit through a relai7 coil 218 and the jettisoning-indexing circuit is completed as follows: from the positive side of the source of power, through the armature of the relay 228, the armature of the relay 218, and the jettison solenoid 212 to ground; and simultaneously from..

h thev positive side of the sourceof power, through the armature of the relay 228, the armature of the relay 218, the line 244, and the solenoid |68 to ground. Upon completion of the indexing cycle initiated by closing the jettison switch 216, another rocket has been moved into firing position and the regular nring cycles, either single or automatic, can then be resumed.

Operation The launching apparatus is operated in the following manner. It is assumed that the magazine is loaded and that a rocket is stationed in the firing position. The ring switch is closed VVand the rocket is red. If the single firing switch 236 (Fig. 13) is used, the indexing switch 240 must then be pressed to initiate the indexing cycle and move the next rocket into ring position. If the automatic ring switch 224 has been closed, ring of the rocket will have swung the lever |88 upward so that the cam |92 has closed the switch 202. In either case, the solenoid |68 (Fig. 5) is energized to swing the pawl |54, thus rotating the latch |42. The latch |42 displaces the levers |24, |26 through the links |46,

permitting the spring 58 (Fig. 4) thereupon to move the screws 62, outward and to engage the clutch 54 and disengage the brake 60. Engagement of the clutch 54 permits the motor 46 to rotate the shaft 5B and, through the gears 68, 12, 14, the variable speed drive 18 (Fig. 3), and the pinions and gears 90, 92, 94, 96, |92, |04, |06, |08, to rotate the shafts 32, 34. Rotation of said shafts causes the

star wheels

36, 38 to index the rockets, moving another rocket into the firing position. Substantially at the end of the indexing movement, the cam |16, which is rotated with the variable speed drive 18, swings the lever |38 (Fig. 5) and thereby (a) returns the screw |I0 to its inward position through the levers |24, |26 and the rod |22, and (b) closes the timing switch 222 in the firing circuit. Inward movement of the screw ||0 shifts the screw 62 to the left of Fig. 4, engaging the brake 60 and disengaging the clutch 54. Since the levers |24, |26 and the links |46 have been returned to their initial positions, the screw 0 is held locked in its clutch disengaging position. If the automatic nring switch is closed, the next ring cycle will automatically be instituted by the closing of the switch 4222. If the single firing switch is used, closing the switch 236 will effect iiring of the next rocket. After each rocket is fired its tube is moved out of ring position during the succeeding indexing operation. The empty tubes are indexed in the magazine until they are removed for reloading.

Whenever a dud or misre is encountered, the jettison switch 216 is closed, effecting an indexing cycle and releasing the gates 250 (Fig. 14). The defective rocket, in moving out of firing position and into position over the gates 250, causes the gates to open under the weight of the rocket and the rocket will then fall through the opening. The springs 256 immediately return the gates to their closed positions and the jettisoning solenoid is deenergized, permitting the latches 260 to return to gate-locking position. Firing may then be resumed by closing either of the firing switches.

Having thus described my invention, what I claim as new and desire to secure by Letters Patent of the United States is:

1. In a rocket launching apparatus including a firing tube and a magazine for a plurality of rocket carrying tubes, the combination with means for indexing the rocket carrying tubes in the magazine from a loading position to a firing position in register with the ring tube, and means for ring a rocket from the ring position, of means rendered operative by the rocket passing through the firing tube upon ring to effect automatic indexing and firing of a succeeding rocket.

2. In a rocket launching apparatus including a firing tube and a magazine for a plurality of rocket carrying tubes, means for indexing the rocket carrying tubes in the magazine from a loading position to a firing position in register with the iiring tube, means including an electric firing circuit for firing a rocket located in firing position, means rendered operative by the fired rocket passing through the iiring tube automatically to actuatethe indexing means to move another rocket into firing position, and means in said ring circuit rendered operative by the indexing mechanism at the conclusion of the indexing cycle automatically1 to nre the rocket moved into ring position.

3. In a rocket launching apparatus having a magazine for a plurality of rocket carrying tubes and a iring tube, the combination with operatorcontrolled means for indexing the rocket carrying tubes successively `irom a loading position to a firing position in register with the ring tube and ring means for firing the rockets one at a time, of means rendered operative after the firing of the first rocket to effect automatic and continuous indexing and ring of the remaining rockets by the passage of each rocket through the firing tube, said last-named means comprising an automatic firing switch that is closed to re the first rocket, a housing secured to the nring tube, a lever secured to a shaft in the housing and projecting into the path of travel of a rocket through the firing tube, a cam on the lever shaft, and an indexing switch in the housing, said switch being closed by the cam to initiate an indexing cycle each time the lever is actuated by the rockets passing successively through the ring tube.

4. In a rocket launching apparatus including a ring tube and a magazine for a plurality of rocket carrying tubes, means for indexing the rocket carrying tubes in the magazine from a loading position to a firing position in register with the firing tube, an electric circuit associated with the indexing means, an electric circuit for controlling the firing of a rocket from the ring position, both electric circuits being supplied from a common source of power, a firing switch, and interlocking switches cooperating with the ring switch to eiect continuous indexing and nring of successive rounds from the apparatus.

5. In a rocket launching apparatus including a firing tube and a magazine for a plurality of rocket carrying tubes, means for indexing the rocket carrying tubes in the magazine from a loading position to a firing position in register with the firing tube, a motor for actuating the indexing means, a clutch for transmitting the output of the motor to the indexing means, means including a ring circuit for firing the rocket from the firing position, an electric indexing circuit, a solenoid in the indexing circuit, means rendered operative by the fired rocket passing through the ring tube to energize the solenoid, clutch controlling means moved by the solenoid from a position in which said clutch is held disengaged to a position in which the clutch becomes engaged, means activated by the indexing means at the end of the indexing cycle to shift said clutch .nre the round moved into ring position by the indexing means.

6. In a rocket launching apparatus including a firing tube and a magazine for a plurality of rocket carrying tubes, means for indexing the rocket carrying tubes in the magazine from a loading position to a firing position in register with the ring tube, a clutch associated with the indexing means, means including an electric ring circuit for ring a rocket indexed into iiring position, an electric indexing circuit, a solenoid arranged in the indexing circuit, a rotatable lever extending into the ring tube and swung by the nred rocket passing through the ring tube, a solenoid controlling cam movable lwith said lever, a switch in the indexing circuit closed by the movement of the solenoid controlling cam to energize said solenoid, a lever mechanism for controlling said clutch and operated upon energizing of the solenoid to elect engagement of the clutch, a ring controlling cam. rotated by the indexing mechanism, a rotatable lever moved by said firing controlling cam upon conclusion of the indexing cycle to operate said lever mechanism to disengage the aforementioned clutch, and a switch in the firing circuit closed by the firing controlling cam to initiate another ring cycle.

'7. In a rocket launching apparatus including a firing tube and a magazine for a plurality of rocket carrying tubes, the combination with means for indexing the rocket carrying tubes in the magazine from a loading position to a ring position in register with the firing tube, an electric circuit associated with the indexing means, an electric circuit for controlling the ring of a rocket, a firing switch for closing the firing circuit to eiect firing of the rocket, and an indexing switch for closing the indexing circuit to eiect an indexing cycle, of another firing switch and interlocking switches cooperating therewith to eect continuous indexing and ring of successive rounds.

8. In a rocket launching apparatus including a firing tube and a magazine in which a plurality of rocket carrying tubes are moved along an indexing path to index successive rockets into ring position in register with the firing tube, means for firing a rocket located in the firing position, movable gates normally held in locked position to provide a guideway for the rockets during indexing across an opening in the magazine adjacent to the ring position, and means for releasing the gates and instituting an indexing cycle when the rocket located in firing position is undischarged, whereby the undischarged rocket is moved over said released gates to drop from the magazine and another rocket is moved into iiring position.

9. In a rocket vlaunching apparatus including a ring tube and a magazine in which a plurality of rocket carrying tubes are moved along an indexing path to index successive rockets into ring position in register with the ring tube, movable gates normally held in closed position to provide a guideway for the rockets during indexing across an opening in the magazine adjacent to the firing position, movable latches for locking the gates in closed position, rotatable levers for moving the latches, solenoids for rotating the levers, when energized, to move the latches out of gate-locking position, means for energizing the solenoids and for instituting an indexing cycle when the rocket located in ring position is undischarged, whereby the undischarged rocket is moved over the released gates to drop through the opening in the magazine, means moved into operative position by said rotatable levers upon energizing of the solenoids to prevent the rocket from moving.

The following references are of record in the file of this partent:

UNITED STATES PATENTS Name Date Macdonald May 4, 1948 Number