US3618453A

US3618453A - Open breech high rate automatic rocket launcher

Info

Publication number: US3618453A
Application number: US873418A
Authority: US
Inventors: Corbet M Cornelison
Original assignee: US Department of Army
Current assignee: US Department of Army
Priority date: 1969-11-03
Filing date: 1969-11-03
Publication date: 1971-11-09
Anticipated expiration: 1988-11-09
Also published as: CA923741A

Abstract

AN OPEN BREECH, HIGH RATE, AUTOMATIC, ROCKET LAUNCHER PROVIDED WITH A PAIR OF LAUNCHING TUBES AND A FOUR CHAMBER REVOLVING AND RECIPROCATING REVOLVER. THE REVOLUTION OF THE REVOLVER ALLOWS TWO CHAMBERS TO BE ALIGNED WITH THE LAUNCHING TUBES WHILE THE OTHER TWO CHAMBERS ARE BEING LOADED. THE RECIPROCATING MOTION OF THE REVOLVER ALLOWS IT TO MOVE FOREWARD TO SEAL AND ALIGN THE FIRING CHAMBERS WITH THE LAUNCHING TUBES, THEN TO MOVE BACK TO CLEAR THE SEALS AND THE LATCH THE ROUNDS BEING LOADED INTO THE LOADING CHAMBERS. THE REVOLVER IS THEN FREE TO ROTATE 90* TO REPEAT THE CYCLE. THE MOTIONS ARE ACCOMPLISHED USING LINEAR HYDRAULIC ACTUATORS WITH VARIABLE ORIFICE END SNUBBERS TO CONTROL THE ACCELERATION AND DECELERATION AT EACH END OF THE STROKES TO PREVENT EXCEEDING THE STRUCTURAL LIMITATIONS OF THE ROCKETS, TO MAINTAIN CONTROL OF ROCKET POSITION AND TO LIMIT EXCITING VIBRATIONS WHICH WOULD DEGRADE THE ACCURACY OF THE LAUNCH. THE ROTATION CYLINDER CONTROLS THE ANGULAR POSITION OF THE REVOLVER BY MEANS OF A MODIFIED 90* HALF SINE WAVE CAM TRACK (PEAK OF THE SINE WAVE) MOUNTED ON THE REVOLVER ASSEMBLY. THE LINEAR STROKE OF THE HYDRAULIC CYLINDER IS THUS CONVERTED TO A 90* OF ROTATING MOTION OF THE REVOLVER. THE SAME 90* ARC BEING USED CLOCKWISE THEN COUNTER-CLOCKWISE FOR EACH SUCCEEDING CYCLE OF THE LAUNCHER''S OPERATION. A RAM-RETRACT CYLINDER LOCTED ON THE CENTER LINE OF THE REVOLVER CONTROLS THE LOADING OF THE NEW ROUNDS, MOVING THE REVOLVER FORWARD TO SEAL WITH THE LAUNCH TUBES AT THE BEGINNING OF THE RAM STOKE AND RELEASING THE REVOLVER TO SPRING BACK FROM THE SEALS AT THE END OF THE STROKE, AND DEPRESSING A PLURALITY OF FIRING SWITCHES IN SEQUENCE TO OBTAIN THE MAXIMUM FIRING INTERVAL POSSIBLE WHILE THE CHAMBERS ARE SEALED TO THE LAUNCHING TUBES. THE RETURN OR RETRACT STROKE IS RAPIDLY ACCOMPLISHED TO PROVIDE TIME FOR THE LOADER ASSEMBLY LOCATED ON ITS EXTREME REAR TO PROPERLY ENGAGE THE NEW ROUNDS FOR THE NEXT CYCLE AND TO PREVENT JAMMING OF THE MECHANISM. THE ROCKETS FIRED FROM THE LAUNCHER MAY BE THE TYPE WHICH INCLUDES A PROPULSION SYSTEM HAVING A BOOST PHASE AND AN AFTER-BOOST SUSTAIN PHASE. THE ROCKET BOOST PHASE OCCURS WHOLLY WITHIN THE LAUNCHER TUBE AT ALL TEMPERATURES. THE IGNITION SYSTEM OF THE BOOST AND SUSTAIN PHASES IS INCORPORATED IN THE SYSTEM IN A MANNER WHICH INSURES THAT NO DEBRIS (WIRES, METAL PARTS, ETC.) IS EJECTED FROM THE REAR OF THE LAUNCHER TUBE ON FIRING. BOOSTER THRUST TERMINATION AND IGNITION OF THE SUSTAINER MOTOR OCCURS WITHIN THE LAUNCHER TUBE AND THE TUBE SERVES AS THE COMBUSTION CHAMBER FOR THE MOTORS.

Description

Nov. 9, 1971 c. M. CORNELISON 3,618,453

OPEN BREECH HIGH RATE AUTOMATIC ROCKET LAUNCHER Filed NOV. 5, 1969 ll Sheets-Sheet 1 Corbet M. Cornelison,

INVj'NTUR. M.

nY E V 4 Wimp Maw/w 9, 1971 c. M. CORNELISON 3,618,453

OPEN BREECH HIGH RATE AUTOMATIC ROCKET LAUNCHER Filed Nov. 3, 1969 ll Sheets-Sheet 8 m g a N o I o o o /N FIG. 2

n I H I i l g I f I I Corbe'r M. Cornelison,

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m Mg I Wu/ OPEN BREECH HIGH RATE AUTOMATIC ROCKET LAUNCHER Filed NOV. 5, 1959 C. M. CORNELISON Nov. 9, 1971 ll Sheets-Sheet 5 FIG. 4

Corbet M.Cornelison, INV NTOR.

Z w; BY I A-LZZJ 514/ #Mfk fli/fa OPEN BREECH HIGH RATE AUTOMATIC ROCKET LAUNCHER Filed Nov. 5, 1969 Nov. 9, 1971 c. M. CORNELISON ll Sheets-Sheet 4.

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1971 c. M. CORNELISON 3,618,453 OPEN BREECH HIGH RATE AUTOMATIC ROCKET LAUNCHER ll Sheets-Sheet 6 Filed Nov. 5, 1969 IN IENTOR "Z i j M W J #W/ w A M/W Nov. 9, 1971 c. M. CORNELISON 3,618,453

OPEN BREE-CH HIGH RATE AUTOMATIC ROCKET LAUNCHER Filed Nov. 5, 1969 r 11 Sheets-Sheet 7 FIG. l2

I ROCKET FIRING FIRING M PULSING SOURCE DETENT A BAND CONTACT SWITCH SWITCH FIRING FIRING ROCKET SWITCH CONTACT BAND DETENT FIG. l4

Corbef M.Cornelison,

IN ENTOR. w

2 M MILL/6w Nov. 9, 1971 3,618,453

OPEN BREECH HIGH RATE AUTOMATIC ROCKET LAUNCHER Filed Nov. 3. 1969 C. M. CORNELISON l1 SheetsSheet 9 Nov. 9, 1971 c. M. CORNELISON 3,618,453

OPEN BREECH HIGH RATE AUTOMATIC ROCKET LAUNCHER Filed NOV. 3, 1969 ll Sheets-Sheet 1O Corbet M. Cornelison,

1 VENTOR. M W 3 BY 04? 111% was) 1 c. M. CORNELISON 3,618,453

OPEN BREECH HIGH RATE AUTOMATIC ROCKET LAUNCHER Filed Nov. :5, 1969 11 Sheets-Sheet 11 FIG. l8

Corbet M. Cornelison, V '"NTOR.

BY MM 2w f #MMJQJ. Mm.

United Smtes Patent Ofice US. Cl. 89-1.804 7 Claims ABSTRACT OF THE DISCLOSURE An open breech, high rate, automatic, rocket launcher provided with a pair of launching tubes and a four chamber revolving and reciprocating revolver. The revolution of the revolver allows two chambers to be aligned with the launching tubes while the other two chambers are being loaded. The reciprocating. motion of the revolver allows it to move forward to seal and align the firing chambers with the launching tubes, then to move back to clear the seals and latch the rounds being loaded into the loading chambers. The revolver is then free'to rotate 90 to repeat the cycle.

The motions are accomplished using linear hydraulic actuators with variable orifice end snubbers to control the acceleration and deceleration at each end of the strokes to prevent exceeding the structural limitations of the rockets, to maintain control of rocket position and to limit exciting vibrations which would degrade the accuracy of the launch. The rotation cylinder controls the angular position of the revolver by means of a modified 90 half sine wave cam track (peak of the sine wave) mounted on the revolver assembly. The linear stroke of the hydraulic cylinder is thus converted to a 90 of rotating motion of the revolver. The same 90 are being used clockwise then counter-clockwise for each succeeding cycle of the launchers operation.

A ram-retract cylinder located on the center line of the revolver controls the loading of the new rounds, moving the revolver forward to seal with the launch tubes at the beginning of the ram stroke and releasing the revolver to spring back from the seals at the end of the stroke, and depressing a plurality of firing switches in sequence to ob tain the maximum firing interval possible while the chambers are sealed to the launching tubes.

The return or retract stroke is rapidly accomplished to provide time for the loader assembly located on its extreme rear to properly engage the new rounds for the next cycle and to prevent jamming of the mechanism.

The rockets fired from the launcher may be the type which includes a propulsion system having a boost phase and an after-boost sustain phase. The rocket boost phase occurs wholly within the launcher tube at all temperatures. The ignition system of the boost and sustain phases is incorporated in the system in a manner which insures that no debris (wires, metal parts, etc.) is ejected from the rear of the launcher tube on firing. Booster thrust termination and ignition of the sustainer motor occurs within the launcher tube and the tube senves as the combustion chamber for the motors.

SUMMARY OF THE INVENTION This invention relates to a rocket launching system and particularly to an open breech, high rate, automatic rocket launcher wherein a plurality of rockets are rapidly fed into a pair of launch tubes while, simultaneously, a second pair of rockets are being fired.

It is, therefore, an object of the present invention to provide an open breech high rate automatic rocket launcher.

3,618,453 Patented Nov. 9, 1971 It is a further object of the present invention to provide a launcher in which a plurality of rockets are loaded in launching position simultaneously with the firing of another plurality of rockets.

It is another object of the present invention to provide such a launcher in which dud rounds are automatically ejected without interruption of the firing cycle.

It is a further object of the present invention to provide such a launcher having minimum dimensions and weight so as to permit the launcher to be mounted on and fired from helicopters or other light weight mounts while permitting the helicopter to maintain its stability characteristics.

It is yet a further object of the present invention to provide such a rocket launcher which will minimize the effects of vibration, blast, noise, and noxious gas on personnel in the aircraft.

Other objects and advantages will be apparent after a study of the following detailed description taken in conjunction with the dravw'ngs wherein:

FIG. 1 is a perspective view, partially cut-away, of the launcher ha ving missiles loaded therein.

FIG. 2 is an elevational side view of the launcher of the present invention.

FIG. 3 is an elevational view, partially in section, of the rear of the launcher.

FIG. 4 is a view along line 44 of FIG. 3 and illustrates the spring assembly of the loading chutes.

FIG. 5 is a sectional view along line 55 of FIG. 3.

FIG. 6 is a sectional view taken along line 66 of FIG. 3.

FIG. 7 is an elevational view, partially in section, of the revolver section and loader assembly.

FIG. 8 is a view along line 88 of FIG. 7.

FIG. 9 is a fragmentary elevational view, partially in section, showing the revolver in aft position with one revolver chamber having a rocket therein in firing orientation, the detents for retaining the rocket in the chamber, and a second revolver chamber in loading position.

FIG. 10 is an elevational view of the loader members and support therefor.

FIG. 11 is an elevational view of the loader and detent member therefor.

FIG. 12 is a plan view, partially in section of the cam dog assembly secured to the revolver support shaft.

FIG. 13 is a diagrammatic view of the launcher of the present invention illustrating the electro-hydraulic scheme.

FIG. 14 is a diagrammatic view of the firing circuit of the launcher.

FIG. 15 is an elevational sectional view of the ram cylinder assembly.

FIG. 16 is an elevational sectional view of the revolver rotation cylinder assembly.

FIG. 17 is a partially cut-away pictorial view of the type of missile as utilized by the launcher of the present invention.

FIG. 18 is a view of the present launcher carried by a helicopter.

DESCRIPTION OF THE PREFERRED EMBODIMENT As shown in FIG. 1, a rocket launcher 10 includes a suppont frame 11, a loader mechanism 12, a rotatable reciprocal revolver section 14, a pair of launch tubes 16 (one removed for clarity) and a hydraulic actuating assembly 17 for reciprocating movement of revolver 14.

Revolver assembly The revolver section includes four chambers 18 (only 2 shown in FIG. 1) supported by a pair of

yokes

19 and 21 concentrically about hydraulic actuating assembly 17. Two of the chambers are disposed for vertical alignment with the launch tubes to fire rockets therefrom while the other two chambers are horizontally disposed while being loaded with another pair of rockets.

The two to one ratio of revolver cylinders to launch tubes permits balanced heat loads in both the revolver chambers and tubes. That is, since the rockets accelerate in the revolver chambers more heat is generated in the revolver chambers than in the launch tubes, thus the two to one ratio permits the heat to be dissipated in the pair of chambers not being fired.

Rocket storage and loading chutes The loader mechanism (FIGS. 1 and 3) is provided with a pair of loading chutes 22 and a pair of trays 24 communicating with the respective chutes. Each chute and tray is separated by a starwheel mechanism 26. The movement of the round is downward while in a horizontal position within the loading chute. Movement is effected by the combined force of gravity plus a leaf spring assembly 28 (FIG. 4) carried in a cap 30 disposed at the top of the chutes. A plunger 31 is disposed at the base of the spring assembly for engagement with the upper rocket in the chutes. The leaf spring design provides that the spring rate and loaded height apply a 3g load on the rounds in the chutes. As the rounds are moved out of the trays to the revolver, the spring load decreases so as to always maintain a 3g load on the rounds in the chute. The motion is intermittent, all rounds moving simultaneously after the bottom round is rammed forward into the revolver loading chamber. The bottom round is separated from the stack above by starwheels 26 which support the stack in a horizontal fashion to prevent jamming during the loading stage. The starwheel includes four spokes 27 and is made of nylon and engages the rocket along the whole cylindrical body longitudinally. As the starwheel turns, the next spoke of the starwheel positions between the round in the tray and the bottom round in the chute. This allows a low friction surface on which the round to be loaded can slide without being in contact with the next round to come down. A form sprag clutch 29 permits only one direction of rotation of the starwheel, holds the round in the loader tray and aligns it with the revolver cylinder into which it is loaded. The two rounds are handled jointly during each ram stroke. A detent 25 is provided in the bottom of each loading tray to engage an obturating ring of the rocket to prevent forward motion of the round until the rocket is rammed forward as is discussed hereinbelow.

Loading mechanism To move the rounds into the four barrel revolver section for subsequent movement into the launch tubes there is provided a loading mechanism 32 (FIGS. 1, 3, 6, 7 and 13) powered by a hydraulic piston 34 for forward and rearward movement of mechanism 32. Mechanism 32 includes a loader arm 33 connected to piston 34 for movement therewith and having a loader support member 38 secured at one end thereof. The piston and arm are mounted along the axis about which each revolver chamber 18 is concentrically disposed.

Loader support member 38 includes a pair of downwardly extending elements 37 (FIGS. 3, 7, 8, 10 and 11) each having a loading member 40 (FIGS. 1, 7, 8, l0 and 11) at the ends thereof. A spring loaded detent 42 is provided at the forward end 44 of member 40 to rest in a detent ring 45 of the rocket (FIGS. 1 and 17) when member 40 engages the rocket for loading thereof, to maintain positive control over the round during the loading operation. Movement of piston 34 carries the loader assembly forward and positions the rounds in the revolver chamber.

After the loader arm reaches the end of its stroke, the revolver chamber is unlatched in a manner described hereinbelow, and caused to move to the rear to permit an angular surface 46 (FIG. 8) on the revolver chamber to engage detent 42 causing it to slide down and disengage from rocket detent 45. The face 48 (FIG. 7) of loading member 40 remains in position and holds the missile forward until the revolver reaches its rearmost position and locks into the round by a separate set of detents 92 (FIGS. 1 and 9) mounted in the revolver cylinders, for retention of the round in the revolver cylinder. A revolver rotating hydraulic piston assembly 39 then rotates revolver 14 90 to align the two empty chambers with the loading trays and the loaded chambers with the launch tubes in a manner to be discussed below.

To permit the loader assembly 32 to return to pick up another round for loading thereof, piston 34 is moved rearward carrying the loading mechanism with it. As shown in FIGS.,7 and 11 loading members 40 are pivotally mounted to support member 38 at 50 and spring loaded by spring 52 in the support member to retain their initial positions for the loading action. As the loader retracts responsive to rearward movement of piston 34, members 40 are forced to pivot down and ride the body of the next rocket to be loaded, located in the loading trays. When the loader reaches its rearmost position, loading member 40 is biased upward by spring 52, back up behind the round and detents 42 of members 40 engage rocket detent ring 45 for forward movement of the next pair of rockets.

Obturating mechanism With a pair of rockets in the chambers aligned with the launcher tubes, piston 34 and arm 33 move forward to carry with them the next pair of rockets to the other two chambers of the revolver. With the second pair of rockets in the revolver chambers, piston 34 and arm 33 move slightly forward and carries with it a pair of cam dogs 54 (FIGS. 1, 6, and 12) which engage the revolver causing it to obturate for sealing of the two vertical cylinders of the revolver with the two launch tubes.

To accomplish this, cam dogs 54 (FIGS. 1, 6, and 12) are secured in a cam dog housing 58 which is secured to a revolver support shaft 57 carried about arm 34. A revolver chamber support tube 63 (FIG. 6) is slidably mounted about support shaft 57 and is secured to

yokes

19 and 21 which slidably support the revolver section. Cam dogs 54 engage a plate 60 secured at the end of tube 63 to force the revolver forward against the force of a spring 62 carried about the cylinder of piston 34 and seated between the revolver support shaft and frame 11. The forward movement of the revolver forces the revolver chambers in sealed relation with the launch tubes.

To permit engagement of cam dogs 54 with the revolver section, loader arm 33 is provided on opposite sides thereof with a longitudinal cam 66 (FIGS. 1 and 6) having a pair of forward recesses 68 and rearward recesses 70 at opposite ends thereof. When piston 34 and arm 33 move forward the cam dogs rise out of forward recess 68 to ride along longitudinal earns 66 for engagement with pressure plate 60 of the revolver section, moving the revolver section forward into obturation position with the launch tubes and at the same time a switch 71 is closed firing the top tube (FIGS. 1 and 13). The ram piston 34 continues to a second position (while revolver and tubes are obturated) until a second switch 72 is tripped closed and the rocket in the bottom tube is fired. When the piston has reached its forward position of the stroke, the cam dogs fall into the rear recesses 70 of the cam and allows the revolver to be pushed back under force of spring 62. As the ram stroke retracts, a spring 63 (FIG. 12) rotates cam dogs 54 in an opposite direction and allows the cam dogs to slide back along the cam track until they drop back into recesses 68. During deobturation, a pulsing switch 48 (FIGS. 1 and 13) is depressed sending a signal to a pair of solenoid valves 78 and 80 (FIG. 13) whichv retracts piston 34 and initiates the next cycle by energizing the second ram assembl 39 to rotate the revolver.

Revolver rotating mechanism To rotate the revolver after a pair of rockets have fired, the second ram assembly 39 includes a piston 84 (FIGS. 7, 13, and 16) provided with a rod 86 which extends out of piston cylinder 88. Rod 86 is provided with a cam follower 89 at the end thereof which rides in a sinusoidal cam track assembly 90 disposed about the periphery of the revolver section. As more clearly shown in FIG. 13, after the first pair of rockets have been fired, solenoid valve 80 is actuated to permit hydraulic fluid to move piston 84 of assembly 39 to rotate the revolver section to align the second pair of chambers with the launcher tubes. The same 90 arc is used clockwise and then counter-clockwise for each succeeding cycle of the launchers operation.

The operating cycle requires that the revolver must rotate while the rocket loader is traveling from full forward to full aft and must be held stationary while the rocket loader is traveling from full aft to full forward (i.e., the cycle ratio of the rocket loader valve 7 8 to the revolver valve 80 is 2:1). When the rocket loader begins forward travel from full aft, the revolver will forward obturate 0.25 inch and when the rocket loader reaches full forward position, the revolver will rear obturate 0.25 inch. The obturating motion of the revolver will operate pulsing control switch 48 which will provide electrical pulses to control the rocket loader. Only the pulse from revolver rear obturate can be used to control the rotation of the revolver.

Using basically a two stage flip flop circuit the desired control can be obtained. The pulses for control are obtained from control switch 48 which is closed as the revolver completes rotation, opens as the revolver forward obturates, closes as the revolver rear obturates and opens as the revolver begins rotation. Positive pulses from the switch are inverted by an electrical signal inverter (not shown) and used to trigger the rocket loader at first stage of the flip flop. The loader solenoid valve 78 is connected in one leg of the flip flop and one pulse will energize and the next pulse de-energizes it, etc. The solenoid valve 78 may be connected in either leg of the flip flop, having the rocket loader travel forward when the valve is energized, or in the other leg, forward when de-energized. Triggering pulse for the revolver solenoid :80, or second stage flip flop are taken from the first stage through an inverter stage. The electrical control system is more fully set forth in an application filed Feb. -4, 1966, Ser. No. 525,808, by Frank H. Case, Jr., Edgar Losberg, and Corbet M. Cornelison for Electrical Control System.

The hydraulic actuating valves are two position, two stage solenoid operated, i.e., when the solenoid is energized the hydraulic fluid flows in one direction and when the solenoid is de-energized the fluid flows in the opposite direction.

The rate of fire is 400 to 450 rounds per minute, firing two rounds 50 milliseconds apart on each half cycle, at present sizing and acceleration limit of the rocket. This would vary with different rockets.

The firing of the rockets is schematically shown in FIGS. 13 and 14 and is accomplished by closing the two

firing switches

71 and 72, as discussed above. After the rocket loader begins forward travel, the first switch 71 is closed completing the electrical circuit to the top rocket chamber, and as the loader approaches the end of forward travel the second switch 72 is closed, completing the electrical circuit to the bottom rocket chamber.

To insure that the electrical circuit to the rocket is not completed until the revolver forward obturates and to insure that only the two rockets which are aligned with the launcher tubes will be fired, detent pins 92', carried in the revolver chambers in contact with the rocket firing circuit, are electrically connected to switches 71 and '72. respectively, through a pair of firing springs 96 and 98 mounted externally of the revolver section. When the revolver rotates to its 90 degree rest position (in alignment with the launcher tubes) and forward obturates, the firing springs engage the detents of the chambers in alignment with the launch tubes. The detent pins are moved inwardly under spring force to engage a contact band 45 (FIG. 17) on the rocket. At this point in the cycle, the ground contact and firing circuit contacts are closed, leaving only switches 71 and 72 open. The firing switches are closed responsive to revolver movement as described, supra, and as shown in FIGS. 13 and 14, to launch the rockets in sequence Which permits the maximum time interval between the pair of rockets which is consistent with the ignition delays, thrust build up and gas evaculation times predicated by the rocket characteristics interrelated with the launcher.

As shown in FIG. 17, rocket 20 is generally shown to have booster and sustainer motors and 102, respectively. An obturating ring 104 is located just aft of head 106. This ring prevents booster motor gas blow-by and can act as the ground leg of the firing circuit. The ring is made of brass and is slotted at 107 to reduce the friction load created by the fit of the ring in the tube. Silicone rubber is potted in the groove to seal the slots.

A single nozzle assembly 108 serves both the booster and the sustainer motors.

Four fins 109 are secured to the aft periphery of the rocket. The fins are spring loaded by springs 110. When the rocket is in the launcher, the fins are held down by a nylon cord which burns during the boost phase and frees the fins so they can be extended outwardly by spring 110.

The ignition and retention ring or detent 45 is secured to the nozzle assembly. The ignition ring includes a contact band 114 electrically isolated from the metal parts of the missile and electrically connected to squibs (not shown) in the booster and sustainer motors. The launcher detent pin fits into the contact ring and holds the rocket in position during loading and cycling operations.

As shown in FIG. 18, launcher 10 is mounted on a helicopter. One launcher is mounted on each side of the aircraft. When installed, the weapon has the capability of firing from 15 degrees elevation to 20 degrees depression. The limiting factor is the rotor blade. Hydraulic power for the system is available from the hydraulic system of the helicopter.

I claim:

1. An open breech, high rate, automatic rocket launcher comprising:

(a) storage means having a plurality of rockets therein, said storage means including a pair of trays each having a single rocket therein;

(b) support means having a pair of launch tubes secured thereto;

(0) a revolver section having a plurality of chambers therein; said revolver section disposed for rotary movement for alignment of a first pair of said plurality of chambers with said launch tubes and for reciprocating movement between said storage means and said launch tubes;

(d) firing circuit means disposed for ignition of the motors of said rockets in said first pair of chambers;

(e) loader means including a pair of arms respectively slidably carried in said trays for engagement with said rockets therein for moving said rockets from said trays to a second pair of said plurality of chambers of said revolver section, said means including motion transmitting means disposed for moving said arms from a first position of enagement with said rockets in said trays to a second position of disengagement from said rockets in said second pair of chambers, said loader means disposed for displacement to a third position for energization of said firing circuit for ignition of the motors of said rockets in said first pair of revolver chambers which are in alignment with said launch tubes while simultaneously loading rockets in said second pair of chambers which are not in alignment with said launch tubes.

2. A rocket launcher as set forth in claim 1 wherein said storage means includes a pair of loading chutes having said plurality of rockets therein and said pair of trays being disposed beneath said chutes to receive rockets therefrom, said loader means disposed for engaging said rockets in said trays for movement thereof to said revolver chambers.

3. A rocket launcher as set forth in claim 2 including means for connecting said motion transmitting means to said revolver section for reciprocating movement thereof from a first position of engagement with said storage means to a second position of engagement with said launch tubes for sealing engagement between said first chambers and said launch tubes.

4. A rocket launcher as set forth in claim 3 including second motion transmitting means disposed for rotating said revolver section for alignment of said second pair of chambers responsive to firing said rockets from said second pair of chambers.

5. Apparatus as in claim 4 wherein said first transmission means includes a hydraulic cylinder having a piston slidably secured therein and connected to said loader arms for movement thereof.

6. A rocket launcher as set forth in claim 5 wherein 8 said second motion transmission means includes a second hydraulic cylinder having a piston slidably secured therein; and

means connected to said piston for transferring linear movement of said piston to rotary movement of said revolver section responsive to firing said rockets from said first pair of cylinders.

7. A rocket launcher as set forth in claim 6 including air transport means for transporting said launcher to a target.

References Cited UNITED STATES PATENTS 1,709,399 4/1929 Herlach et a1. 89-33 B 2,453,830 11/1948 Chadwick et al 8933 B 2,594,199 4/1952 Motley 89-33 B 2,972,286 2/1961 Marquardt 89-155 X 3,331,284 7/1967 Case, Jr. et a1 89l35 X SAMUEL W. ENGLE, Primary Examiner U.S. Cl. X.R.