US2440723A - Apparatus for launching rockets from airplanes - Google Patents

Description

y 1948- l... s. MACDONALD APPARATUS FOR LAUNCHING ROCKETS FROM AIRPLANES Filed June 6, 1945 7 Sheets-Sheet 1 lnvenfor Leszer lfcwdonalo APPARATUS FOR LAUNCHIlfIG ROCKETS 'Fnou AIRPLANES D L A N O D C A M s L Filed June 6, 1945 7 Sheets-Sheet 2' In ven for 7 Lester J. ffacdonajd I By hbAo May 4, 1948. L. s. MACDONALD APPARATUS FOR LAUNCBING ROCKETS FROM AIRPLANES '7 Shets-Sheet :5

Filed June 6, 1945 nven ar eszer Mac'donald May 4, 1948. L. s. MACDONALD APPARATU FOR LAUNCHING ROCKETS FROM AIRPLANES Filed June 6, 1945 7 Sheets-Sheet 4 [mmmm?" Lester J/Vacdonald a? 3, i948. L. s. MACDONALD v 294401723 AfRfiRATUS FOR LAUNCHING ROCKETS FROM AIRPLANES Filed June 6, 1945 TSheets-Sheet 5 [wwwahf v 1 L. s. MACDONALD 4Q APPARATUS FOR LAUNCHING ROCKETS FROH AIRPLANES Filed June 6, 1945 7 Sheets-Sheet e j I .1 j I i' v L. 5 MAQDQNALD APPARATUS FOR LAUNCHING ROCKETS FROM Mum-Arms Filed June 6, 19% 7 511ee'ts=-Shest T maven izwr Macdonczld Lesfer Patented May 4, 1948 APPARATUS FOR LAUNCHING ROCKETS FROM AIRPLANES Lester S. Macdonald, Beverly, Mass assignor to United Shoe Machinery Corporation, Flemingw ton, N. 3., a corporation of New Jersey Application June 6, 1945, Serial No. 597,921

1 18 Claims. This invention relates to apparatus for launching projectiles and is illustrated herein as embodied in a rocket launching apparatus adapted for use in combat airplanes. It is to be understood, however, that, in some of its aspects, the invention is not limited to rocket launching apparatus and that, with certain modifications, the apparatus may be adapted for use on carriers other than airplanes. I

The increasing use, in recent years, of rockets vide a rocket launching apparatus by the use of which a plurality of rockets may be indexed and firedat a rapid rate, and in which the indexing launched from combat airplanes has necessitated the development of launching devices for carrying and firing the rockets. One type of device heretofore used for launching rockets from airplanes consisted of a plurality of rocket carrying tubes mounted under the wings of an airplane, the tubes being arranged to be dropped from the airplane after the completion of a mission. Each tube was provided with a pair of electric contacts placed against the tail rings on the rocket, in position to set oil an electric igniter in the rocket, which in turn ignites the propelling charge, upon operation by the pilot of a firing trigger located on the joy stick of the airpl ne. The number of rockets that can be launc ed from any one airplane in this manner is necessarily limited, since any appreciable increase in the weight of the launchers would increase the air resistance, with a resultant decrease in the speed of the airplane. Moreover, the rocket carrying tubes being mounted outside the airplane, the length of each tube must similarly be limited,

and this has an important effect on the accuracy with which the rockets can be directed at a target, since the longer the tube through which a rocket is fired, the more the rocket is likely to maintain a true course in its flight.

It is an object of the present invention to provide a rocket launching apparatus by the use of which a larger number of rockets may be launched from airplanes than has heretofore been possible, and which can be readily installed in an airplane without necessitating substantial alterations in the airplane structure and removed therefrom when it is desired to utilize the airplane for launching other types of projectiles, or for other purposes.

It is another object of the invention to provide a rocket launching apparatus adapted to move a pluralit of rockets one at a time from within the airplane into a launching position outside the airplane, to fire each rocket after the same has been moved .into launching position, and to dispose of defective or misfired rockets.

It is a further object of the invention to proand firing of the rockets, as well as the release of undischarged rockets, are remotely controlled by the airplane pilot.

With these and other objects in view, the illustrated rocket launching apparatus comprises, in accordance with a feature of the invention, a magazine adapted to hold a plurality of rockets, the magazine being mounted in the bomb bay of an airplane in such manner that a portion of the magazine projects through an opening in the airplane and is connected to a long projection tube that is supported on the underside of the fuselage and through which the rockets carried by the magazine are launched successively. In

accordance with another feature of the inven-f tion, means is provided whereby the magazine and the projection tube may be adjusted as a unit to obtain the desired angle of elevation for the launching of the rockets.

The rockets are carried in the magazine by a plurality of tubes that are connected by links to form an endless chain and moved intermittently by an indexing mechanism constructed and ar ranged to move one rocket carrying tube at a time into launching position in register with the previously mentioned projection tube. Preferably, the indexing mechanism is operated by remotely controlled power means, auxiliary means being also. provided for manual operation of the indexing mechanism in the event of failure of the power means. The operation of the indexing mechanism is controlled by a clutch and brake mechanism and, in accordance with a feature of the invention, clutch control means is provided which is operative at predetermined times in the power or manual operation of the indexin; mechanism automatically to disengage the clutch and apply the brake after the indexing mechanism has moved the rocket carrying tube chain a distance substantially equal to the spacing between the centers of 'two adjacent tubes.

Each rocket in a rocket carrying tube which has been moved into rocket launching position is held in that position until fired and, in ac-- cordance with a further feature of the invention, means is provided for preventing the indexing of the rocket carrying tube chain while a rocket is in launching position. As herein illustrated, the rocket is held in its launching position by a retaining lever arranged to engage the flange on the rear end of the rocket. This retaining lever is connected, by means including a spring, to a microswitch that is connected in the electrical circuit controlling the indexing mechanism. The spring normally maintains the microswltch closed and holds-the previously mentioned retaining lever in position to be engaged by the flange of a rocket contained in a tube which has been moved into rocket launching position by the indexing mechanism. Engagement of the rocket flange with the retaining lever causes the lever to swing in a direction to open the microswitch, thereby preventing initiation of the power operation of the indexing mechanism until the rocket has been launched, whereupon the spring acts and to move the retaining lever into position to engage the flange of the next succeeding rocket.

Another feature of the invention relates to a firing mechanism under the control of the airplane pilot and adapted to fire the rockets successively at the end of' each indexing operation. In the illustrated apparatus, the firing mechanism includes a pair of insulated and individually yieldable contact fingers adapted to engage the contact members on the rear end of the rocket to set off an igniter in the rocket, which in turn ignites the propelling charge.

To insure that the firing mechanism will not be rendered operative to fire a rocket unless the rocket is correctly positioned in alinement with the projection tube, there is provided, in accordance with a further feature of the invention. means associated with the firing mechanism and with the indexing mechanism and operative to prevent the operation of the firing mechanism until the indexing mechanism has completed its operation to move a rocket carrying tube into rocket launching position. In the illustrated construction, the means just mentioned comprises a microswitch mounted on the magazine and connected in the electrical circuit controlling the firing mechanism. Upon initiation of the power operation of the indexing mechanism, the microswitch, which is normally closed, is opened by engagement thereof with the periphery of a cam carried by the ,indexing mechanism and remains open until the indexing mechanism has completed its indexing movement. The firing mechanism is further provided with manual locking means for rendering the firing mechanism inoperative at all times when the apparatus. is not in operation, to prevent accidental firing of a rocket.

For releasing any misfired or defective rocket so that it may be ejected from the magazine, there'is provided, in accordance with another feature of the invention, a release mechanism controlled by a switch on the instrument panel. As herein illustrated, the release mechanism comprises a solenoid operatively connected to the previously mentioned rocket retaining lever, the

arrangement being such that, when the pilot opcrates the release switch to release an undischarged rocket, the solenoid is energized and actuates the retaining lever to release the rocket,

which is then free to be ejected through the rear end of the magazine by a blast of' air passing through the projection tube.

These and other features of the invention will now be described in detail with reference to the accompanying drawings, and pointed out in the claims.

In the drawings,

Fig. 1 is a view in side elevation of the forward end of an airplane, illustrating the apparatus embodying the invention mounted part y to again close the microswitch in the bomb bay of the airplane and partly outa side the airplane;

Fig. 2 is a vertical section along'the line 11-11 of Fig. 1, illustrating the manner in which the forward portion o1 a projection tube, shown in that figure, is attached to the airplane;

Fig. 3 is a vertical section along the line III- III of Fig. 1, illustrating the manner in which the intermediate portion of the projection tube is attached to the airplane;

Fig. 4 is a vertical section along the line IV--IV of Fig. 1, illustrating the manner in which the rear portion of the projection tube is attached to the airplane;

Fig. 5 is a view in rear elevation of the apparatus shown in Fig. 1, this view illustrating means for successively indexing and firing a plurality of rockets and for releasing defective or misfired rockets, and means for mounting the apparatus within the bomb bay of the airplane;

Fig. 6 is a view in side elevation, partly in section and on an enlarged scale, taken in the direction of the arrow in Fig. 5, of the upper portion of the apparatus shown in Fig. 1, this view illustrating the indexing mechanism and means for adjusting the heightwise position -of the apparatus in the bomb bay;

"Fig. '7 is a detail view in rear elevation, taken at right angles to Fig. 6, of means shown in that figure for supporting the apparatus within the bomb bay;

Fig. 8 is a transverse section along the line VIII of Fig. 6, showing parts of a clutch and brake mechanism for controlling the indexing'mechanism shown in F18. 5;

Fig. 9 is a perspective view of the indexing mechanism;

Fig. 10 is a detail view, taken along the line X--X of Fig. 6, of the upper portion of one of the end plates of the apparatus, this view showing a plurality of rocket carrying tubes connected together to form an endless chain and means for guiding the tubes during the indexing thereof Fig. 11 is a detail sectional view taken along the line IHXI- of Fig. 10;

Fig. 12 is a view in side elevation and on an enlarged scale, taken in the direction of the arrow in Fig. 5, of the firing mechanism in inoperative position and of retaining means located at the launching end of the apparatus for locking each rocket in its launching position;

Fig. 13 is a view substantially similar to Fig. 12 but illustrating the firing mechanism in operative position;

Fig. 14 is a bottom view, on a reduced scale. of the firing mechanism taken in the direction of the arrow in Fig. 12;

Fig. 15 is a sectional View of a portion of the firing mechanism taken along the line XV-XV of Fi 13;

Fig. 16 is a detail view of locking means for rendering the firing mechanism inoperative;

Fig. 17 is avertical section, on an enlarged scale, taken along the line XVIL-XVII of Fig. 12;

Fig. 18 is a transverse section along the line XVIIIXVIII of Fig. 17, this view showing more particularly the means for locking each rocket in launching position; and

Fig. 19 is mainly a wiring diagram.

The illustrated apparatus is a rocket launching apparatus adapted to be used in combat airplanes. In the embodiment shown herein by way of example, the apparatusis mountairplane A (Fig. 1), with the upper portion of the apparatus supported in the bomb bay and the lower portion projecting through an opening in the airplane. The apparatus may be installed in the bomb bay of an airplane from which the bombs have been temporarily removed, without altering the airplane structure, and easily and quickly removed therefrom in order to reconvert the airplane to its normal use. It is to be understood. however, that. with certain slight modifications, the apparatus may be adapted for use in craft other than airplanes.

The apparatus consists principally of a magazine M (Fig. 1) adapted to hold a plurality of rocket carrying tubes; an indexing mechanism I for moving the tubes successively into rocket launching position; a firing mechanism F for firing the rockets successively; and a release mechanism for causing defective or unfired rockets to be ejected from the airplane. The indexing, firing and release mechanisms are all controlled by the airplane pilot by means of switches located on the instrument panel.

The magazine Referring to Figs. 1 and 6, the magazine M comprises a frame consisting of two endplates 20, 22 joined by rods 24. The magazine is removably'mounted in the bomb bay of the airplane A and is attached thereto at its upper end by means of a hanger comprising a laterally extending hollow shaft 26 formed with flanged bosses 28 riveted to angle brackets 30, which are bolted to the upper end portions of the end plates 20, 22, and two inclined rods 32 pivotally conected at their lower ends to the bosses 28 and at their upper ends to a connecting member 34. The connecting member is provided with a socket 36 for the reception of a downwardly extending threaded rod 38 pivotally connected at its upper end to a lug 40 depending from a crosshead 42 that is secured to brackets 44 provided in the bomb bay. Mounted on the lower end of the rod 38 is a hand wheel 46 by means of which the apparatus may be raised or lowered in the bomb bay, the hand wheel being provided with an internally threaded hub 41 and a thrust bearing 48 which engages the connecting member 34. Intermediate its upper and lower ends the magazine is provided with brackets 50 (Fig. 5) which extend between the opposite end plates at the front and rear of the magazine and by means of which the magazine may be mounted on bomb rails 52 in the bomb bay in any desired angular position relative to the longitudinal axis of the airplane. The brackets 50 are provided with bolts 54 extending through inclined slots 56 provided in plates 58 which are suspended on hooks 60 on the bomb rails 52 and secured thereto by bolts 6|. a

The magazine M is designed to hold aplurality. of rocket carrying tubes 62 which are connected together in an endless chain by links 84 mounted on the opposite ends of the tubes. The magazine of the illustrated apparatus is adapted-to carry sixteen tubes, although this number may be increased to the maximum permitted.by considerations of weight and of the space in which the magazine is to be mounted. The tubes 62 are moved in a closed, non-circular path in.guide-.

ways formed by angleirons 66 (Figs. 10, 11 and 17), and guide plates 68 secured to the inner surfaces of the end plates 20 and 22. The guide plates 68 are preferably made in two sections, as shown in Fig. 17, the lower portions of the plates being secured to the end plates 20 22 by bolts 10 engaging in elongated slots 12, by means of which the lower portions of the guide plates may be adjusted heightwlse relatively to the upper portions thereof to compensate for any slack which may be present in the chain of rocket carrying tubes. Between the guide plates 88 on the opposite end plates extend flanged reinforcing tubes "I4 bolted to the guide plates.

The lower end portion of the rear end plate 20 is provided with a circular opening having an internal diameter substantially equal to the internal diameter of a rocket carrying-tube 62, and has-secured thereto a flanged collar I8 (Fig. 1) through which the rockets are inserted into the rocket carrying tubes during the loading of the such as to afford the maximum opportunity for' the rockets to maintain a true course in flight. The projection tube 80 issurrounded by straps 82 to which are riveted brackets 84, 86 and 88 (Figs. 2, 3 and 4). Pivotally connected to the brackets 84 and 88 are rods 90, which are also pivotally connected at 9| to a bracket 92 depending from the airplane fuselage. The forward portion of the tube 80 is supported by a. bracket 94 depending from the airplane fuselage and connected by a pivot pin 96 to the bracket 84.

The intermediate portion of the tube 80 is con-' nected to the airplane by turnbuckles 98 (Fig, 3) pivotally connected by the pin 9| to the bracket 92 and by a pin I00 to the bracket 86. The rear portion of the tube 80 is connected to the airplane by turnbuckles I02 the lower ends of which are pivoted at I04 to the bracket 88 (Fig. 4) and the upper ends of which are pivoted at I06 to a bracket I08 depending from the airplane fuselage. The apparatus and the projection tube may be adjusted as a unit heightwlse of the airplane to obtain the desired angle of elevation of the projection tube for the launching of the rockets.

The indexing mechanism The indexing mechanism I is mounted on the upper end of the rear end plate 20 of the magazine (Figs. 1, 5 and 6) and is arranged to move the rocket carrying tubes 62 successively into rocket launching position in registerwith the projection tube 80. The tubes 62 are supported and moved one at a time by sprockets H0 (Figs. 6 and 9) mounted on the opposite ends of a shaft II2 mounted in bearings H4 in the upper end portions of theend plates 20, 22. is driven from a primary source of power through a reduction gearing, comprising a gear II6 mounted on the shaft II2 and meshing with a pinion Il8 keyed to one end of a shaft I20 the other end of which is journaled in a bearing in a shaft I2'2 mounted in a bearing I24 in.a hous- 'ing I26 mounted on the upper end of the rear end plate 20. The shaft I22 operates a varying speed drive mechanism substantially similar to The shaft II2- that described in United States Letters Patent No. 2,309,595, granted on January 26, 1943, upon an application of Lester E. James, to drive the spi'ocket shaft II2 ata low velocity at the beginning and end of each indexing cycle and at a high velocity in the intermediate portion of the cycle so that the rocket carrying tube chain will be rotated smoothly. This varying speed drive mechanism includes a sun gear I28 (Fig. 9) mounted on the outer end of the previously mentioned shaft I28 and meshing with planetary gears I38, which also mesh with the internal teeth I32 of a I ring gear I34 mounted on the inner end of the.

of the ring gear I34. The outer end of the shaft 7 I22 carries a worm gear I48 which meshes with a worm I58 (Figs. 5 and 9) fast on a sleeve I5I rotatably mounted on a vertical drive shaft I52 journaled in the housing I26. The upper end of the shaft I52 carries a worm gear I54 which meshes with a worm I56 fast on a shaft I58 connected to the shaft of an electric motor I68 secured to a housing I62 mounted on top of the housing I26. -The drive shaft I52, rotates continuously while the motor is runningand the worm sleeve I5I is brought into .driving engagement with the drive shaft to operate the indexing mechanism by engagement of a multiple disk friction clutch I64 of the type described in United States Letters Patent No. 2,201,676, granted on May 21, 1940, upon an application of Allen R. Coe. The clutch, which is interposed between the lower end portion of the sleeve I5I and the shaft I52, is actuated by a forked clutch shifting lever I66 fulcrumed at I68 on the housing I26. The upper ends of the arms of the lever I66 carry blocks I18 which engage in anannular groove I1I provided in a clutch sleeve I12 slidably mounted on the lower end of the shaft I52. The upper end of the clutch shifting lever I'66 carries an eyebolt I14 (Fig. 5) to which is anchored one end of a spring I16, the other end of which is secured to a cover plate I18 on the housing I26. Mounted on the lower end of the sleeve I5I is a brake disk I88 with which cooperates a brake shoe I82 mounted on an eccentric shaft I84 (Fig. 8) journaled in ears I86 on the housing I26. A lever I88 clampedon the shaft I84 is connected by a pin I98 to a link I92 pivotally connected to a pin I94 integral with the clutch shifting lever I66.

For actuating the lever I66 to release the brake I82 and engage the clutch I64 there is provided means including a. clutch tripping bell-crank lever I96 (Fig. 5) fulcrumed at I98 on the housing I26. The horizontal arm 288 of the bell crank I96 is connected to the plunger 282 of a solenoid 284 that is secured by a clamp 286 to a bracket 288 mounted on the outer surface of the rear end plate 28. The bell cram; I96 has an upwardly extending arm 2l8, to the upper end of which is pivotally connected a forked latch lever 2I2 arranged to engage the hooked tail 2I4 of a latch 2I6 pivotally connected at 2I8 to the lever I66.

The lever 2I2 is biased by a spring 228 connected at one end to the lever 2I2 and at its opposite end to an eye in the arm 2I8. The latch 2I6 is biased by a spring 222 attached .at one end to the latch and at its opposite end to a lug 224 on the lever I66.'

Referring to Fig. 5, in which the parts are shown in inoperative position, the indexing mechanism operates as follows to move a rocket carrying tube '62 into rocketlaunching position in register with the projection tube 88. The power being turned on to start the motor and the solenoid switch being closed. when the indexing switch is operated a circuit is established through a lower relay coil 225 (Fig. 19) to energize the solenoid 284, thus: From the positive side of the source of power to the closed solenoid switch, and through this switch to the closed indexing switch, thence to a normally closed microswitch 268, the purpose of which will be explained hereinafter, thence to the relay coil 225, and from the relay coil to ground. Current passing through the relay coil causes the relay contacts to be closed, establishing acircuit from the positive side of the source of power through the closed solenoid switch to the relay, thence to the solenoid 284, and thence to ground, whereupon the solenoid 284 is energized and the solenoid plunger 282 moved downward, causing the clutch tripping lever I96 to swing in a counterclockwise direction and the latch lever! to engage the hooked tail 2 ll of the latch 2 I6. During the continued counterclockwise movement of the lever I96, the latch lever 2I2 pulls the latch 2I6 toward the left of Fig. 5, against the tension of the spring 228, and causes the clutch shifting lever I66 to swing in acounterclockwise direction against the tension of the spring I16. As a result of this swinging movement of the lever I66.

' to engage the clutch I64 and bring the worm sleeve I5l into driving engagement with the drive shaft I52 to operate the indexing shaft I22. The shaft I22 rotates in the direction of the arrow in Fig. 5 and, through the gear train illustrated in Figs. 6 and 9, operates the sprocket shaft II2 to move one rocket carrying tube into rocket launch.- ing position. 1

To insure that the clutch I64 will be held firmly engaged during an indexing cycle and also that the clutch will be disengaged and the brake applied upon completion of the indexing cycle, there is provided a clutch control mechanism comprising a pair of cam disks 228, 228 (Figs. 5 and 6) mounted on the outer end of the shaft I22 and bolted together for rotation in unison therewith. The cam disk 226 is provided with three notches 238, within which a roller 232 carried by the clutch shifting lever I 66 is arranged to engage successively upon completion of each indexing cycle. Upon initiation of an indexing cycle by operation of the indexing switch, as previously explained, the clutch shifting lever I66. swings in a counterclockwise direction, as seen .in Fig. 5, and'the roller 232 is withdrawn from engagement with a notch 238 in the cam disk 226. Durin rotation of the shaft I22, the roller rides on the periphery of the cam disk between two notches and holds the clutch firmly engaged until the roller engages in the next notch 238, whereupon the spring I16 causes the lever to swing in'a clockwise direction to disengage the clutch and apply the brake I 82. The notches 238 in the cam disk 226 are spaced equal distances from one another, the arrangement being such that the clutch will be disengaged and the,brake applied to bring the indexing shaft I22 to rest after rotating through a distance corresponding to the spacing between the centers of two adjacent tubes 62 of the rocket carrying tube chain, that is, through a distance sufiicient to move one tube into rocket launching position in register with the projection tube 80.

. The cam disk 228 is provided on its periphery with three depressions which are spaced equal distances from one another and with which the latch 2I6 successively engages at the end of each indexing cycle. Shortly after the initiation of the rotation of the indexing shaft I22, that is to say, after the latch lever 2I2 has acted to pull the latch 2I6 toward the left of Fig. 5 to cause the clutch shifting lever I66 to swing in a counterclockwise direction'to engage the clutch, the latch is caused, by engagement with the part of the periphery of the cam 228 between two depressions, to swing in a clockwise direction against the tension of the spring 222. movement of the latch, itshooked tail 2I4 is moved out of engagement with the latch lever 2 I 2 and is held disengaged by continued engagement of the latch with the above-mentioned part of the periphery of the cam 228 until the end of an indexing cycle, so that the clutch shifting lever I66 will thereafter be free, upon engagement of the roller 232 with a notch 230 in the cam 226, to swing in a clockwise direction to disengage the 'clutch and apply the brake. Upon stopping of the rotation of the shaft I22, the

latch 2I6 engages the next depression of the cam lever I96 for actuating the lever to cause release of the brake and engagement of the clutch. After engagement of the clutch, rotation of the shaft I52 by means of the hand crank. 234 will operate the indexing mechanism in the same manner as when the mechanism is power operated, and the previously described clutch control mechanism will be efiective to control the rotation of the shaft I22 to cause it to come to rest atthe end of an indexing cycle- The manual means just described may also be As a result of this,

tube will be moved down into position to receivea rocket. This procedure is repeated until all the tubes have been filled. The same procedure is employed to load the magazine manually, when the electric motor cannot be used, the hand crank 234 being secured to the shaft I52 and used to rotate the shaft after each successive engagement of the clutch by a pull on the cable 236.

' the slot 246.

Each rocket R in the tube 62 which has been moved into rocket launching position in register with the projection tube 86 is held, until fired by mechanism to be described hereinafter, by a retaining lever 240 (Figs. 5, 12, 17, 1'8 and 19) pivoted at 242 on a bracket 244 mounted on the lower end of the rear end plate 20. The upper end of the lever 240 extends through a slot in the collar 16 and is provided with a slot 246 (Fig. 18) which is engaged by the flange 248 on the rear end of the rocket. As shown in Fig. 18, each rocket carrying tube 62 is cut away at 258 to provide clearance for the lever 240. The upper end of the lever 240 is bifurcated and has pivotally connected thereto at 252 an arm 254 having a cam portion 255 adapted to bear against the collar 16. When a rocket is fired, the blast of the propelling charge causes the arm 254 to swing in a clockwise direction, as seen in Fig. 18, and the cam 255 to act against the collar I6, so as to cause the lever 240 to swing in a direction to release the rocket flange from engagement with Upon emergence of the rocket from the projection tube 80, the rocket fins 238 open to stabilize the rocket in flight.

Mechanism is provided, in accordance with the invention, for preventing initiation .of the power operation of the indexing mechanism while a rocket is in launching position. As shown in Figs. 5 and 19, the retaining lever 248 is provided with an upwardly extending arm 256 which is connected by a rod 258 to a bell crank 260 pivotally connected to a. downwardly extending lug 262 of a housing 264 supported by a bracket 266 secured to the bracket 244. The bell crank 260 is adapted to operate the previously mentioned microswitch 268 in'the housing 264, this microswitch, as already stated, being included in circuit with the coil of the relay 225 which controls used, in the absence of power, for indexing the rocket carrying tube chain during the loading of the magazine, which takes place before the apparatus is installed in the airplane. The loading operation may be effected either by means of the power-operated indexing mechanism or by means of the hand crank 234. Regardless; however, of

the means by which the operation is effected, the cable 236 is used in place of the indexing switch, which is located in the cockpit of the airplane, to actuate the clutch tripping lever I96 to cause engagement of the clutch. If the loading is done by power, the motor switch is closed and the solenoid switch (see Fig. 19) left open, With the motor running, a rocket R (Fig. 18) is inserted through the collar 16 (Fig. 1) into the lowermost tube 62 in the magazine, the rocket being inserted with the nose forward and the fins 238 (Fig. 18) folded- The cable 236 (Fig. 5) is next pulled downward to actuate the clutch tripping lever I96 to release the brake I82 and engage the clutch I64. The indexing mechanism will thereupon'be operated to index the tube chain so that the filled tube will be moved up and an empty the indexing solenoid 284 (see wiring diagram, Fig. 19). The rod 258 carries a spring 269 comfined between a shoulder provided on the righthand end of the rod 258 and the bracket 266 through which the rod extends. The spring 269 normally maintains the microswitch 268 closed and holds the retaining lever 240 in position to be engaged by the rocket flange 248. When the flange of a rocket R engages in the slot 246 in the retaining lever 248, the lever is caused to swing in a clockwise direction, as seen in Fig. 5, thus causing the rod 258 to be moved to the right to open the microswitch 268 and to compress, the spring 269. With the microswitch open, operation of the indexing mechanism will be prevented until the rocket has been discharged, whereupon the spring 269 under compression will expand, thereby closing the microswitch and returning the lever 240 to its rocket engagingposition.

The firing mechanism The firing mechanism F (Figs. 1 and 5) is mounted on the lower end portion of the rear end plate 26 directly above the collar I6, and is actuated by a solenoid 210 (Figs. 5, 12, 13 and 19) energized by operation of a firing switch located on the control panel in the cockpit of the airplane. The solenoid is secured by means of a clamp collar 212 to a casting 214 mounted on theend plate 28. The plunger 218 oi! the solenoid 218 is connected by a clevis 218 to a link 288 pivotally connected at 282 to a two-arm lever 284 fulcrumed at 288 to the casting 214. 284 has a bifurcated portion 288 to which is pivotally connected at 289 a downwardly extending latch 298 biased by a spring 292 attached at one end to the upper end of the latch and at itsopposite end to the link 288. The lower hooked The lever end 294 of the latch 298 is arranged to engage a shoulder 298 on a rack slide 298 mounted for vertical reciprocating movement in the casting 214. The slide 298 moves upward against the resistance of a compression spring 388 mounted in a bore in the slide and confined between the slide and a stationary abutment 382 on the casting 214. The teeth 384 of the rack slide mesh with a gear segment 388 iormed integral with a block 388 of non-conducting material mounted on a shaft 318 rotatably mounted in the casting 214. The block 388 is provided with grooves for the reception of a pair of contact fingers 3l2 mounted on studs 314 carried by the block 388, the fingers being arranged, upon operation of the firing switch, to swing in a clockwise direction, as seen cuit from the closed solenoid switch through the relay and the firing solenoid 218 to ground, as a result of which the solenoid 218 is energized and causes the lever 284 to swing in a clockwise direction as seen in Fig. 13. Clockwise movement .of the lever 284 causes the heel portion 334 of the detent 338 to depress the upper end of the latch 322, against the resistance of the spring 332, thereby moving. the crossbar 328 of the latch out of the path of the fingers 3i2, which are there after free to be moved into operative position, the detent 338 continuing to swing in a clockwise direction until stopped by engagement with a stop pin 342 on the casting 214. Upon being depressed by the (detent 338, the upper end 'of the latch 322 is moved out of engaflement with the notch in the heel portion 334 of the detent, and thereafter moves along the lower edge lace of the heel portion, pushing this'portion of the detent upward against the tension of the spring 348, into the position shown in Fig. 13. When the firing solenoid 218 is deenergized and the lever 284 swings in a counterclockwise direction, the detent swings in the same direction, under the action of the spring 348, to return to its normal position, shown in Fig. 12, in which the upper end of the latch ls again engaged in the notch in the heel portion of the detent. In this position the latch 322 locks the contact fingers against clockwise movement until released by the detent upon a succeeding energization of the firing solenoid. Clockwise movement of the lever 284 simultaneously causes the latch 288 to move upward until its hooked portion 294 engages the shoulder 296 on the rocket, the fingers are caused to swing reversely, to return to inoperative position, and are held in that position until the next actuation of the firing switch by the pilot, thereby insuring against possible damage to the fingers resulting from blast produced by a discharged rocket. For this purpose the fingers 3l2 are provided with notches 3I8 which, upon return of the fingers to their inoperative positions, are arranged to be engaged by a crossbar 328 of a substantially T- shaped latch 322 to lock the fingers against clockwise movement until actuated by operation of the firing switch. The latch 322 is pivotally mounted on a pin 323 mounted in lugs 324 on a plate 326 fixed by screws 323 to the casting 214 and insulated therefrom by a plurality of layers 338 of material such as leather which lessen the shock when the fingers 8|2 strike against the plate 328 upon their return to inoperative position. The latch 322is actuated against the'resistance of a spring 332 that surrounds the pin 323 and bears against the inner face of the latch. In the inoperative position of the firing mechanism the upper end of the latch 322 is engaged in a notch formed in the heel portion 334 of a detent 338 pivotally connected at 338 to the lever 284, the detent having connected thereto one end of a spring 348 the other end of which is connected to the lever 284.

Fig. 12 shows the firing mechanism in inoperative position. When the pilot operates the firing switch to fire a rocket which has been moved into launching position, a circuit is established through the closed solenoid switch (see wiring diagram, Fig. 19), the indexing switch. a release switch, a normally closed microswitch 318, and the coil of a relay 3, causing the relay contacts to be closed to establish an energizing ciron the rack slide 298, and pulls the slide upward, compressing the spring 388, the extent of upward movement of the slide being variably determined by the engagement of a lug 344 on the latch 288 with an adjustable stop screw 348 mounted on the casting 214. Upward movement of the rack slide 298 causes the block' 388, which is integral with the gear segment 388, to be rotated in a clockwise direction, as seen in Fig. 13, to move the fingers 312 into engagement with the contact members348 and 388 on the tail of the rocket R (see Fig. 5). The engagement of the fingers 3l2 with the contact members 348 and 358 on the rocket is timed to coincide substantially with the engagement of the lug 344 of the latch 298 with the stop screw 348. Engagement of the lug 344 with the screw 348 causes the latch 298 to swing, against the action 01 the spring 292, in a direction to cause the hooked end 294 of the latch to be disengaged from the shoulder 298 of the slide 298, which is thereupon moved downward by the spring 388 under compression, so that the gear segment 388 and the block 388 will be rotated in a counterclockwise direction, as seen in Fig. 13, to return the fingers 3l2 to their inoperative positions. As previously explained, the fingers, upon their return to inoperative position, are locked in that position by engagement of the crossbar 328 of the latch 322 with the notches 3 I 8 oi. the fingers, thereby insuring against movement of the fingers until actuated by the next operation of the firing switch.

for energizing the fingers 3I2 is supplied from a suitable source of power through wires 362 attached to the screws 356.

For preventing accidental firing of a rocket at all times when the apparatus is not in use, there is provided a manually controlled firing mechanism locking means. Referring to Figs. 5, 14 and 16, the locking means comprises a sprin pressed plunger 364 provided with a knurled knob 366 and mounted in a socket 368 formed integral with the casting 214. The plunger 364 is provided with two diametrically opposed fins 318 which are arranged to engage in either of two pairs of diametrically opposed notches 312, 314 provided in the socket 368, the notches 312 bein of greater depth than the notches 314. When the fins 318 on the plunger 364 engage in the notches 312, the inner end of the plunger projects beyond the end of the socket 368 into the path of movement. of the detent 336, thereby preventing the detent from being moved suflicientl'y to release the latch 322, and hence preventing the operation of the firing mechanism.

For preventing operation of the firing mechanism until a rocketis in correct launching position in register with the projection tube 88, there is provided the previously mentioned microswitch 316 (Fig. 5) mounted on the cover plate I18 of the housing I26 and included in circuit with the relay 34I which controls the firing solenoid 218 (see wiring diagram, Fig. 19). The microswitch 316 is normally closed while the indexing mechanism is in inoperative position, being in register with a notch 238 in the cam disk 226. However, while the indexing mechanism is operated, engagement of the periphery of the cam disk 226 with the microswitch 316 opens the switch and prevents actuation of the firing mechanism by operation of the firing switch.

The release mechanism For releasing an undischarged or defective rocket so that it may be ejected from the magazine in a direction away from the projection tube 88, there is provided a release mechanism including a rod 318 (Figs. 5 and 19) connected at its lower end to the lower end of the retaining lever The upper end of the rod 318 is connected by a link 388 to the plunger 38I of a solenoid 382 secured by a clamp 384 to the lower end portion of the rear end plate 28. When it is desired to eject an undischarged or defective rocket from its carrying tube which has been moved into -rocket launching position, the pilot operates a release switch located on the control panel in the cockpit of the airplane This establishes a circuit from the positive side of the source of current, through the closed solenoid switch (Fig. 19), the indexing switch, and the coil of a relay 383 to ground, causing the relay contacts to be closed to establish an energizing circuit for the solenoid 382, from the closed solenoid switch through the relay 383 and the release solenoid 382 to ground. Thereupon the solenoid 382 is energized, causing the rod 318 to be moved upward and the retaining lever 248 to swing in a counterclockwise direction, as seen in Figs. 5 and 19, to release the rocket flange 248 from engagement with the slot 246 in the retaining lever. As the lever 248 thus swings in a counterclockwise direction, the action of the can. portion 255 (Figs. 12 and 18) of the arm 254 against the collar 16 permits the arm 254 to swing in a clockwise direction out of the path of the rocket, which is than free to be ejected from the magazine through the collar 16 and along a' pair 14 of parallel rails 386 fixed to the collar, by a. blast of air passing through the projection tube 88.

Operation 6 The manner in which the several mechanisms operate has already been fully explained. It will sufiice, therefore, to summarize briefly the operation of the apparatus.

It will be assumed that the magazine, fully loaded with rockets, has been installed in the bomb bay of an airplane and adjusted in the desired angular position in the manner explained above. Referring to Fig. 5, which shows the parts in their inoperative positions, the cam roller 232 15 carried by the clutch shifting lever IE6 is in engagement with a notch 238 in the cam 226, the latch 2I6 is in engagement with a depression in the cam 228, the brake shoe I82 is in engagement with the brake disk I88, and the clutch I64 is disengaged. To operate the apparatus the pilot first closes the motor switch and the solenoid switch. The pilot next closes the indexing switch, whereupon the indexing solenoid 284 is energized and, through the clutch tripping lever I96, latch lever 2I2 and latch 2 l6, actuates the clutch shifting lever I66 to swing in a counterclockwise direction to release the brake I82 from en agement with the brake disk I88 and to engage the clutch so as to bring the worm sleeve I5I into driving engagement with the drive shaft I52 to rotate the indexing shaft I22. counterclockwise swinging movement of the lever I 66 causes the cam roller 232 to be disengaged from the notch 238 in the cam 226, the roll thereafter riding in engagement with the periphery of the cam between two notches until it engages in the next notch in the cam, whereupon the lever I66 swings in the reverse direction to cause the clutch to be disengaged and the brake to be applied after the 4 chain of rocket carrying tubes has been moved 1 tact fingers 3| 2 and, through the latch 298, to move the rack slide 298 upward, thereby causing the block 388 to rotate in a clockwise direction to 5 bring the fingers 3I2 into engagement with the contact members on the rear end of the rocket to set off the igniter in the rocket, which in turn ignites the propelling charge. Should the firing switch be operated before a rocket is in correct firing position, that is, before the indexing mechanism has come to a complete stop, the firing mechanism will be prevented from being operated by the engagement of the periphery of the cam 226 (Fig. 5) with the microswitch 316 which, as previously explained, is connected in the circuit controlling the firing mechanism. y In other words, the firing mechanism cannot be operated unless this microswitch is inregister with a notch 238 in the cam 226. At the same time, while a rocket is in launching position, engagement of the rocket flange with theretaining lever 248.

will open the microswitch 268 which is connected I in the. circuit controlling the indexing mechanism, so that the indexing mechanism will be 7 prevented from being operated by operation of I the indexing switch until the rocket has either been launched through the projection tube 80 or, in the case of a misfired rocket, has been ejected through the collar I6. In the event oi a which said rockets are to be launched, .a magazine connected at one end thereof to said projection tube and adapted to hold a plurality of rockets, remotely controlled indexing means on said magazine for moving the rockets successively into a launching position in register with said projection tube, and remotely controlled firing means located on said magazine and operated independently of said indexing means to fire the rockets successively at the will of the operator.

2. An apparatus for launching rockets, having, in combination with a projection tube through which said rockets are to be launched, a magazine connected at one end thereof to said ineffective to operate the firing means before the completion of an indexing cycle.

5. An apparatus for launching rockets, having in combination with a projection tube through which said rockets are to be launched, a magazine connected at one end thereof to said projection tube and adapted to hold a plurality of rockets, remotely controlled indexing means on said magazine for moving the rockets successively into a launching position in register with said projection tube, remotely controlled means on said magazine for firing each rocket after the same has been moved into said launching position, and

means normally actuated by the successive rock- 'in combination with a projection tube through projection tube and adapted to hold a plurality of rockets, remotely controlled indexing means on said magazine for moving the rockets successively into a launching position in register with said projection tube, remotely controlled means on said magazine for firing each rocket after the same has been moved into said launching position, and manual locking means for rendering the firing means inoperative at will.

3. An apparatus for launching rockets, having, in combination with a projection tube through which said rockets are to be launched, a magazine connected at one end thereof to said projection tube and adapted to hold a plurality of rockets, remotely controlled indexing means on said magazine for moving the rockets successively into a launching position in register with said projection tube, remotely controlled means on said magazine for firing each rocket after the same has been moved into said launching position, retaining means located on said magazine and adapted to engage the rear end of a rocket in the launching position and to retain the rocket until fired by said firing means, and means associated with said retaining means and actuated by the blast of the fired rocket to cause said retaining means to release the rocket.

4. An apparatus for launching rockets, having, in combination with a projection tube through which said rockets are to be launched, a magazine connected at one end thereof to said projection tube and adapted to hold a plurality of rockets, remotely controlled indexing means on said magazine for moving the rockets successively into a launching position in register with said projection tube, remotely controlled means located on said magazine and actuated independently of said indexing means to fire the rockets successively, an electrical circuit controlling said firing means, switch means'for closing said cirets in the launching position to prevent operation of said indexing. means while a rocket is in said launching position.

6. An apparatus for launching rockets, having in combination with a projection tube through which said rockets are to be launched, a magazine connected at one end thereof to said projection tube and adapted to hold a plurality of rockets. remotely controlled indexing means on said magazine for moving the rockets successively into a launching position in register with said projection tube, remotely controlled means on said magazine for firing each rocket after the same has been moved into said launching position, retaining means located on said magazine and adapted to engage a rocket which has been moved into launching position and to retain it until fired by said firing means, means associated with saidretaining means and actuated upon the firing of the rocket to causesaid retaining means to release the rocket to permit it to be launched through said projection tube, and remotely controlled means for causing said retaining means to release an undischarged rocket to permit the same to be ejected from said magazine in a direction away from said projection tube by a blast of air passing therethrough.

'7. An apparatus for launching rockets, having, in combination with a projection tube through which said rockets are to be launched, a magazine connected at one end thereof to said projection tube and adapted to hold a plurality of rockets, remotely controlledindexing means on said magazine for moving the rockets successively into a launching position in register with said projection tube, remotely controlled means on said magazine for firing each rocket after the same has been moved into said launching position, means associated with said indexing means and acting automatically to prevent actuation of said firing means during operation of said indexing means, and means normally actuated by the successive rocketsin the launching position to prevent operation of said indexing means while a rocket is in said launching position.

8. An apparatus for launching rockets, having, in combination with a projection tube through which said rockets are to be launched, a magazine connected at one end thereof to said projection tube and adapted to hold a plurality of rockets, remotely controlled indexing means on said magazine for moving the rockets successively into a launching position in register with said projection tube, remotely controlled means on said magazine for firing each rocket after the same has been moved into said launching position, manually operated means for locking the firing means to prevent operation thereof when the apparatus is not in use, retaining means lo cated on said magazine in position to engage a rocket which has, been moved into launching position and to retain 3 means, means actuated upon the firing of the rocket to cause said-retaining means to release 17 it until fired by said firing operation of said indexing means while a rocket is in said launching position, and remotely controlled means for causing said retaining means to release an undischarged rocket to permit the same to be ejected from said magazine by a blast ,of air passing through said projection tube.

9. The combination of an airplane and an apprising a projection tube mounted outside the airplane, a magazine for holding a plurality of rockets, said magazine being mounted within the airplane but projecting therethrough and being connected to said projection tube, remotely controlled indexing means on said magazine for mov ing said rockets successively into launching position in register with said projection tube, and remotely controlled firing means on said magazine actuated independently of said indexing means to fire said rockets successively through said projection tube at will after the rockets have been moved into said launching position.

10. The combination of an airplane and an apparatus for launching rockets therefrom, comprising a projection tube mounted outside the airplane, a magazine mounted within the airplane but projecting therethrough and connected to said projection tube, a plurality of rocket carrying tubes in said magazine connected together,

to form an endless chain, indexing means on said magazine controlled by the airplane pilot for rotating said rocket carrying tube chain to move said tubes successively into rocket launching osition in register with said projection tube, and means on said magazine under the control of the pilot for successively firing said rockets at will after the same have been moved into said launching position.

11., The combination of an airplane and an apparatus for launching rockets therefrom, comprising a projection tube mounted 'outside the airplane, a magazine mounted within the airplane but projecting therethrough and connected to said projection tube, a plurality of rocket carrying tubes in said magazine connected together to form an endless chain, means in said magazi ne for guiding said rocket carrying tube chain in a closed, non-circular path, indexing means on said magazine controlled by the airplane pilot controlled power-operated means mounted on paratus for launching rockets therefrom, 'comsaid magazine for driving said shaft to cause said rocket carrying tube chain to be rotated, starting and stopping means associated with said driving means and acting automatically to stop rotation of said shaft after said rocket carrying tube chain has been rotated a distance sufficient to move onerocket carryingtube into rocket launching position, and means under the control of the-pilot for firing a rocket at will after the tsame has been moved into said launching posiion.

paratus for launching rockets therefrom comprising aeprojection tube mounted outside the airplane, a magazine mounted within the airplane but projecting therethrough and connected to said projection tube, a plurality of rocket carrying tubes in said magazine connected together i porting and moving successive rocket carrying tubes into said rocket launching position, remotely controlled power-operated means mounted on said magazine for driving said shaft to cause said rocket carrying tube chain to be rofor rotating said rocket carrying tube chain to move said tubes successively into rocket launching position in register with said projection tube, and means on said magazine under the control of the pilot for successively firing said rockets at will after the same have been moved into said launching position.

12. The combination of an airplane and an apparatus for launching rockets therefrom, comprising a projection tube mounted outside the airplane, a magazine mounted within the airplane but projecting therethrough and connected to said projection tube,- a plurality of rocket carrying tubes in said magazine connected together of form an endless chain, means in said magazine for guiding said rocket carrying tube chain tated, auxiliary manual means for driving said shaft, starting and stopping means associated with said driving means and acting at predetermined times in the power or manual operation of said driving meansautomatically to stop rotation of said shaft after said rocket carrying tube chain has been rotated a distance sufiicient to move one rocket carrying tube into rocket launching position, and means under the control of the pilot for firing a rocket 'at will after the same has beenmoved into said launching position.

14. The combination of an airplane and an apparatus for launching rockets therefrom, comprising a projection tube pivotally mounted outside the airplane, a magazine removably mounted within the airplane but projecting therethrough and connected to said tube, means for adjusting said magazine and tube as a unit relatively to the airplane, means on said magazine for moving said rockets successively into a launching position in register with said projection tube, and means for firing each rocket after the same has been moved into said launching position.

15. An apparatus for launching rockets, having, in combination, a magazine for a plurality of rockets, power-operated indexing means for feed-- 1 ment of said rockets, remotely controlled firing.

means actuated independently of said indexing means to fire the rockets successively at the will of the operator and means actuated by said cam to prevent actuation of said firing means during operation of said indexing means to feed a rocket to said firing position.

16. An apparatus for launching rockets, having, in combination with a projection tube through which said rockets are to be launched, a magazine connected at one end thereof to said projection tube and adapted to hold a plurality of rockets, remotely controlled indexing means on said magazine for moving the rockets successively 13. The combination of an airplane and an apinto a launching, position in register with said projection tube, remotely controlled means on said magazine actuated at will and independently of said indexing means to fire a rocket after the same has been moved into said launching position, said firing means comprising a pair of contact members arranged to engage each rocket. resilient means associated with said contact members for permitting said members to yield independently of each other upon engagement with a rocket, and means arranged to energize said members Just before their engagement with a rocket to cause them to ignite the charge in the rocket.

17. An apparatus for launching rockets, having, in combination with a projection tube through which said rockets are to be launched, a magazine connected atone end thereof to said projection tube and adapted to hold a plurality of rockets, remotely controlled indexing means on said magazine for moving the rockets successively into a launching position in register with saidprojection tube, remotely controlled means on said magazine for firing each rocket after the same has been moved into said launching position, said firing means comprising a pair of contact members yieldableindependently of each other, a spring-actuated latch normally holding said contact members in inoperative position, and means for actuating said latch to cause it to release said contact members upon actuation of in combination with a projection tube 20 a magazine connected at one end thereof to said projection tube and adapted to hold'a plurality of rockets; remotely controlled indexing means on said magazine for moving the rockets successively into a launching position in register with said projection tube, and operator controlled contact members arranged to engage a rocket in launching position and to fire the same, a spring actuated latch normally holding said contactmembers in inoperative position, means for actuating said latch to cause it to release said contact members, and a locking plunger which in one position thereof is. arranged to prevent said latch actuating means from operating to release said latch.

LESTER S. MACDONALD.

REFERENCES CITED The following references are of record in the file of this patent:

UNITED STATES PATENTS Number Name Date 319,898 Frost June 1, 1885 332,071 Gavitt Dec.. 8, 1885 488,409 White Dec. 20, 1892 1,273,078 McManus July 16, 1918 1,786,207 Hudson Dec. 23, 1930 2,088,503 Broussard July 27, 1937 2,340,991 Severance Feb. 8, 1944 2,356,304 Da Costa Aug. 22, 1944 2,364,510 Bertram et al Dec. 5, 1944 2,371,324 Trotter Mar. 13, 1945 2,380,024 Chandler July 10, 1945 2,380,455 Lippert et al July 31, 1945 FOREIGN PATENTS Number Country Date 12,113 Great Britain 1888 747,080 France Mar. 21, 1933

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