US3641868A

US3641868A - Firing mechanism for a multishot rocket launcher

Info

Publication number: US3641868A
Application number: US54722A
Authority: US
Inventors: Frederick P Reed
Original assignee: US Department of Army
Current assignee: US Department of Army
Priority date: 1970-07-14
Filing date: 1970-07-14
Publication date: 1972-02-15
Anticipated expiration: 1989-02-15

Abstract

A trigger-actuated firing mechanism for a multishot rocket launcher comprises in association with each rocket a firing pin with a roller arranged for cam engagement by a trigger-rotated cam rotor to retract and release for rocket primer impact the related firing pin, and disposed in cooperation with the cam rotor is an antihang-up device including a spring-biased driving member actuatable against a driven member connected to the cam rotor to effect counterrotation thereof, and thereby return the firing pin engaged by the cam rotor back to its normal position, if trigger pressure is released before the retraction and release of the firing pin is completed. Means are provided for mounting the cam rotor for limited free rotation on the supporting shaft whereby the cam rotor is accelerated in the direction of rotation sufficiently, by the camming engagement of the cam lobe peak with the circumference of the roller when the cam lobe peak is moved past the center of the engaged roller, to release the roller and assure immediate impact of the related firing pin against the associated rocket primer.

Description

Uiiiififl gt Reed ts tet 5] Feh.15,1972

[54] FIRING MECHANISM FOR A MULTISHOT ROCKET LAUNCHER [72] Inventor: Frederick P. Reed, Davenport, Iowa [73] Assignee: The United States of America as represented by the Secretary of the Army 22 Filed: July 14, 1970 211 Appl.No.: 54,722

[52] US. Cl. ..89/1.8l3, 42/1 R, 89/1 L, 89/27 R [51] Int. Cl ..F41f 3/04 [58] Field of Search ..89/9, 12, 160, l L, 27 R, 27 C, 89/126; 42/1 R [56] References Cited UNITED STATES PATENTS 3,535,979 10/1970 Ashley ..89/l2 X Primary Examiner-Samuel W. Engle Attomey-Harry M. Saragovitz, Edward J. Kelly, Herbert Berl and Albert E. Arnold, Jr.

[57] ABSTRACT A trigger-actuated firing mechanism for a multishot rocket launcher comprises in association with each rocket a firing pin with a roller arranged for cam engagement by a trigger-rotated cam rotor to retract and release for rocket primer impact the related firing pin, and disposed in cooperation with the cam rotor is an antihang-up device including a spring-biased driving member actuatable against a driven member connected to the cam rotor to effect counterrotation thereof, and thereby return the firing pin engaged by the cam rotor back to its normal position, if trigger pressure is released before the retraction and release of the firing pin is completed. Means are provided for mounting the cam rotor for limited free rotation on the supporting shaft whereby the cam rotor is accelerated in the direction of rotation sufficiently, by the camming engagement of the cam lobe peak with the circumference of the roller when the cam lobe peak is moved past the center of the engaged roller, to release the roller and assure immediate impact of the related firing pin against the associated rocket primer.

7 Claims, 11 Drawing Figures PATENTEBFEBIS I972 3.641.868

SHEET 3 [IF 5 'INVENTOR FIEHEII'Ek PREEEL ATTORNEYS PATENTEBFEB 1 5 I972 3.641.868

sum u [1F 5 INVENTOR Frederick PREELEL W 2* ATTO NEY;

PNENTEBFEB 15 I972 3.641 .868

SHEET 5 or 5 FrederinkEEeeil BY W T OR EYS FIRING MECHANISM FOR A MULTISHOT ROCKET LAUNCHER The invention described herein may be manufactured, used, and licensed by or for the Government for governmental purposes without the payment to me of any royalty thereon.

BACKGROUND OF THE INVENTION This invention relates to multishot rocket launchers and pertains more particularly to a firing mechanism therefor comprising a trigger-actuated cam rotor which has camming engagement with successive ones of the firing pins, for retraction and release thereof.

In such a firing mechanism for a particular rocket launcher trouble has been experienced when trigger pressure is released before the cam rotor is rotated sufficiently to release the firing pin roller which is engaged thereby to convert rotational displacement of the cam rotor to translational displacement to the related firing pin whereby, the engaged roller is hung up along the cam lobe ramp of the cam rotor as there is not sufficient force in the firing pin spring to counterrotate the cam rotor back to its normal position. Or, the roller is hung up on the cam lobe peak whereby the associated rocket may be accidentally launched by a sufficient jar on the rocket launcher to displace the roller on the peak, making for a hazardous condition.

SUMMARY OF THE INVENTION It is a principal object of this invention to provide for such a firing mechanism an antihang-up device which will return the firing pin back to its forward safe position if trigger pressure is released while one of the rollers is located along the cam lobe ramp or will continue the rotation of the cam rotor for release of the engaged roller, and consequential impact of the related firing pin against the associated rocket primer, when the peak of the cam lobe is located past the center of the engaged roller.

To achieve this object there is provided in cooperation with the cam rotor an antihang-up device comprising a driving member disposed for translational displacement by a driven member through the camming contact of apex terminated posts thereon with cam lobes on the driving member, responsive to rotation of the cam lobe, to load a cooperating spring backing up the driving member. If rotation of the cam rotor is interrupted while the firing pin roller is on the cam lobe ramp the pressure of the driving member spring applied to the driven member effects counterrotation of the cam rotor so as to return the engaged firing pin back to its forward safe position. Means are also provided for mounting the cam rotor for limited free rotation on its mounting shaft so that when the peak of the cam lobe moves past the center of the roller the cam rotor is accelerated in the direction of rotation a distance assuring release of the roller from the cam lobe and consequential impact of the associated firing pin against the primer of the respective rocket to initiate the launching thereof.

Further objects and advantages of the invention will be apparent from the following specification and the accompanying drawings which are for the purpose of illustration only.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a longitudinally cross-sectioned view of the section of a multishot rocket launcher which includes the firing mechanism and shows all the members of the firing mechanism in their normal positions;

FIG. 2 is a cross-sectional view taken along line 2-2 of FIG. 1;

FIG. 3 is a cross-sectional view taken along line 3--3 of FIG. 1;

FIG. 4 is a cross-sectional view taken along line 4-4 of FIG. 1;

FIG. 5 is a view of the antihang-up device similar to that shown in FIG. 1 but shows the relationship of the members when trigger pull on the lanyard is initiated;

FIG. 6 is a view similar to FIG. 5 but shows the relationship of the members when the lanyard is pulled sufficiently to locate the peak of the cam lobe on the cam rotor in alignment with the center of the roller;

FIG. 7 is a displacement diagram showing the cam profile through 360 of operation and relationship of the firing pin rollers therewith;

FIG. 8 is an enlarged fragmentary view showing the cooperation of the safety member with the cam rotor;

FIG. 9 is a view taken along line 9-9 of FIG. 8;

FIG. 10 is a view taken along line 10-10 of FIG. 8; and

FIG. 11 is an exploded view of the driven, cam rotor and safety members.

DESCRIPTION OF A PREFERRED EMBODIMENT Shown in the figures is a multishot rocket launcher 12 comprising a receiver 14 and a cylindrical housing 16 mounted to the front end thereof. Housing 16 is adapted to receive for launching a cluster of four rockets which are secured together in rectangular relationship by a clip so that the longitudinal axes of the rockets, and therefore the primer elements therein, are equally spaced relative to each other and to the central axis of the housing. Neither the clip nor the rockets are shown as they are not part of this invention.

Shown in FIG. 1 are two of the four recesses 18 which are formed in the rear end of housing 16 to respectively receive the primers related to the four rockets. Each of the rockets is launched by an associated firing pin 20 which includes a body member 22 and a striker assembly 24. Such striker assembly 24 comprises a sleeve 25 and a striker pin 26 slidingly received thereby, and body-member 22 includes a large diameter portion 28 and a coaxial stem portion 30 of smaller diameter extending rearwardly therefrom.

Extending rearwardly in housing 16, from each of the recesses 18 and in coaxial alignment therewith is a bore 32 which is counterbored at 34 from the rear face of the housing to a shoulder 36 for slidingly receiving the front end of striker assembly 24 so that striker pin 26 may make impact with the associated primer to initiate the launching of the respective rocket. Each body member 22 is received by a cooperating hole 38 longitudinally formed in receiver 14 for coaxial alignment with the respective bore 32. Hole 38 includes a forward section 40 which extends rearwardly from the front end of receiver 14 to a shoulder 42 and is adapted for slidingly receiving large diameter portion 28 of body member 22, and a rearward section 44 which extends coaxially from such shoulder to the rear face of the receiver and is adapted for slidingly receiving stem portion 30. Stem portion 30 forms with large diameter portion 28 a rearwardly facing shoulder 46 and a compression spring 48 is operationally disposed between

shoulders

42 and 46 for biasing body member 22 forwardly in receiver 14.

Firing pins 20 are of the inertia type. That is, they are positioned, normally, away from contact with the primers of the associated rockets but, through inertia, make impact with the associated ones thereof after being released from a retracted spring-pressed position. Provided in each of the body members 22 is an axial well 50 which extends rearwardly from the front end thereof and such well slidingly receives the rear portion of striker assembly 24. Striker pin 26 is fixed by pin 52 to a body member 22 so as to be propelled forwardly therewith for impact against the primer of the rocket in the associated recess 18. The front end of sleeve 25 is received by counterbore 34 so as to contact shoulder 36 and a compression spring 54 is disposed between the rear end of well 50 and the rear end of sleeve 25 to bias body member 22 rearwardly against the opposition of spring 48. Spring 54 is designed to oppose spring 48 sufficiently so that when the forces of the springs are in balance striker pin 26 is withdrawn from the associated recess 18. A post 56 extends radially from body member 22 and rotatingly mounted thereon is a roller 58 which provides means assisting in the retraction and release of firing pin 20, as hereinafter described.

Striker pins 26 are successively retracted and released for impact against the primers of the rockets in the associated recesses 18 by an actuator mechanism 60 which is mounted within a stepped chamber 62 longitudinally disposed in receiver 14. Actuator mechanism 60 includes a shaft 64 which extends along the length of chamber 62 into housing 16 and which is journaled for rotation at 66 in receiver 14 and at 68 in housing 16. Journal 68 comprises a bushing with an annular flange 69 which is located outside the rear end of housing 16, as shown in FIG. 8. Mounted for free rotation on shaft 64 within the rear section of chamber 62 is a pulley 70 having a circumferential channel 72 which receives a trigger pulled lanyard 74 anchored at one end to the pulley within such channel. As shown in FIG. 2, pulley 70 is engageable with shaft 64, for transferring full trigger displacement of lanyard 74 to the shaft for at least 90 rotation thereof each time the lanyard is pulled, through the cooperation of a pawl 76 mounted within the pulley with four equally spaced teeth 78 formed around the shaft. A torsion spring 80 is operationally disposed so as to be loaded by pulley 70, when lanyard 74 is pulled, for returning the pulley to its nonnal position. Rear end 82 of spring 80 is used, as shown in FIGS. 1 and 2, to bias pawl 76 against shaft 64 for successive engagement with teeth 78. Mounted for limited free displacement on shaft 64 within the front section of chamber 62, and so as to have engageable cooperation with rollers 58 which extend thereinto, is a cam rotor 84 provided with, as shown in FIGS. 7, a pair of diametrically opposed slots 86 which are elongated in a transverse 'plane respective to shaft 64 a distance at least equal to the radius of rollers 58. Slots 86 receive ends 88 ofa pin 90 which extends diametrically through shaft 64 thereby to provide limited rotation of cam rotor 84, relative to shaft 64, equal to the radius of rollers 58 and, referring to FIG. 6, each of the slots includes one end 91 against which ends 88 of pin 90 bear to transfer counterclockwise rotation of the shaft to cam rotor 84. Pin 90 extends through shaft 64 by means of a longitudinally elongated slot 92 therein which permits limited longitudinal displacement of cam rotor 84 relative to the shaft for a purpose hereinafter described. Cam rotor 84 is provided around the rear end thereof with a planar surface 94 which is coincident with a plane disposed normal to the longitudinal axis of the cam rotor and which is disposed forwardly of rollers 58 so as to be contactable thereby. When rollers 58 have contact with surface 94, the associated firing pins are maintained slightly retracted from their normal, unloaded positions, to safe positions, thereby preventing accidental impact with the related rockets in housing 16, and the cam rotor is displaced forwardly through the biased contact of rollers 58 therewith, as far as permitted by the engagement of pin 90 with slot 92. Surface 94 is interrupted by a cam lobe 96 comprising a ramp 98 which inclines rearwardly and in a clockwise direction, or from right to left referring to FIG. 7, for approximately 90 to form peak 100 with a side 102 disposed normal to surface 94. Side 102 extends forwardly beyond the plane of surface 94 to form one side of a firing depression 104 which provides a clearance for rollers 58, when snapping off peak 100, so that the related firing pins 20 are free to be propelled into impact with the associated primers. A sloping surface 106 leads from firing depression 104 to surface 94 to direct roller 58 in the firing depression back to surface 94 the next time shaft 64 is rotated by trigger pull on lanyard 74.

Actuator mechanism 60 also includes an antihang-up device 107 for preventing hang up of a roller 58 on ramp 98 or peak 100, as explained hereinafter, which device comprises a driving member 108 and a driven member 110. Driving member 108 is mounted on shaft 64 for free sliding movement therealong but is held against rational displacement relative thereto through the cooperation of tongue 112 thereon with a longitudinal slot 113 in the wall of chamber 62. A compression spring 114 presses driving member 108 forwardly into resilient engagement with driven member 110. Driven member 110 is secured to shaft 64 forwardly of driving member 108 by pin 90 which extends through mating holes therein, as shown in FIG. 4. Driven member 110 includes a bearing portion 118 which mounts cam rotor 84 for free rotational movement thereon, and four posts 120 which extend rearwardly from the bearing portion and are equally spaced therearound. Each of the posts is terminated by a pair of angular surfaces comprising a forward surface 122 and a rearward surface 123, respective to the counterclockwise direction of rotation of cam rotor 84, and such surfaces form an apex 124.

Driving member 108 includes a pair of diametrically spaced cam lobes 126 which extend forwardly therefrom for engageable cooperation with successive pairs of posts 120 responsive to rotation of driven member 110 relative to the driving member. Each of the cam lobes 126 is provided with a helical surface 128 which inclines forwardly and in a counterclockwise direction, as shown in FIGS. 5 and 6, to form with a straight side 132, longitudinally disposed relative to the axis of shaft 64, a peak 130. Thus, each time trigger pull is made on lanyard 74 and shaft 64 is rotated thereby at least through the engagement of pawl 76 with successive ones of the teeth 78, apexes 124 on the pair of posts 120 engaged with cam lobes 126 move along helical surfaces 128 thereof to move driving member 108 rearwardly. At the same time, the rotation of shaft 64 is transferred to cam rotor 84 through the engagement of ends 88 of pin 90 with ends 91 of slots 86 so that ramp 98 of the cam rotor moves relative to one of the rollers 58 to retract the associated firing pin 20 against the bias of its cooperating spring 48. Before the trigger displacement of lanyard 74 is completed, roller 58 snaps off peak with cam rotor 84 being rotated by camming contact of such peak with the roller to where ends 88 contact the opposite ends of slots 86, thereby permitting entry of the roller into firing depression 104 and impact of the respective firing pin 20 against the primer of the related rocket to initiate the launching thereof. At the same time, apexes 124 of the pair of posts engaged by cam lobes 126 are moved past peaks thereof and along rearward surfaces 123 to free driving member 108 for return to its normal position by spring 114 and to position the next pair of the posts for engagement with cam lobes 126.

Referring to FIG. 6, it is seen that when ends 88 of pin 90 are in contact with ends 91 of slots 86, peak 100 of cam lobe 96 and peak 130 of one of the cam lobes 126 are both on centerline x-x and that centerline yy of the one of the pair of apexes 124 engaged with cam lobes 126 is spaced below centerline xx, whereby antihang-up device 106 functions to prevent hangup of a roller 58 along ramp 98 or on peak 100 as hereinafter explained.

If trigger pull on lanyard 74 is released while one of the rollers 58 is on ramp 98, and a pair of the apexes 124 are therefore engaged with helical surfaces 128, the pressure of spring 114 against driving member 108 is cammingly applied to shaft 64 through driven member 110 to rotate cam rotor 84 backwards thereby permitting the return of the related firing pin 20 to its forward safe position, where the roller is in contact with surface 94, through the bias of related spring 48. If the trigger pull on lanyard 74 should be released when one of the rollers 58 is located on peak 100, so that its center is located on centerline xx, as shown in FIG. 6, the roller is prevented from being hung up on the peak as the pair of apexes 124 are still in camming engagement with helical surface 128 and thereby the pressure of spring 114 is applied to shaft 64 which is counterrotated thereby to permit the roller to back down ramp 98 to surface 94 and return the associated firing pin 20 to its forward safe position. However, if the trigger pull on lanyard 74 should be released when the center of one of the rollers 58 is located past the centerline x-x the pressure of spring 48, which is loaded by the retraction of the related firing pin 20, is cammingly applied by the respective roller through peak 110 to cam rotor 84 to continue the rotation of the cam rotor free of shaft 64 a distance equal to the radius of rollers 58, as permitted by the cooperation of ends 88 in slots 86, to where the engaged roller is free to snap forwardly into firing depression 104 and permit impact of the related firing pin 20 with the primer of the associated rocket.

When cam rotor 84 is in its normal position with no trigger pull being made upon lanyard 74, three of the rollers 58 are in contact with surface 94 to block forward displacement of the related firing pins 20 while the fourth roller is located in firing depression 104, as shown in FIG. 7. Consequently, when a clip of four live rockets is installed to housing 16, the rocket indexed with the firing pin 20 having roller 58 thereof located in firing depression 104, might accidentally be discharged by a sudden jar upon the launcher if sufficient to propel the firing pin into impact with the associated primer. To prevent this mishap, there is provided a safety member 134 of ring configuration which is rotatably mounted on flange 69 of journal 68 and is also displaceable rearwardly against cam rotor 84. Provided on safety member 134, as shown in FIGS. and 11, are four equally spaced radial detents 136 which protrude from the front face thereof and such detents are simultaneously received by four mating grooves 138 in the rear end of housing 16 when indexed therewith. The pressure of springs 48 applied to cam rotor 84 through rollers 58 having contact therewith is in turn applied to safety member 134 to resiliently hold detents 136 in grooves 138 when indexed therewith. A handle 140 provides means for manually rotating safety member 134 between SAFE and FIRE positions.

Thus, when safety member 134 is in the FIRE position with detents 136 received by grooves 138, cam rotor 84 is located in its forward normal position whereby three of the four firing pins 20 are held, through the contact of the respective rollers 58 with surface 94, in their safe positions while the roller of the fourth firing pin is located unblocked in firing depression 104. When safety member 134 is rotated to the SAFE position, detents 136 are moved out of grooves 138 to displace the safety member rearwardly against cam rotor 84 which is rearwardly displaced accordingly so that the inside surface of firing depression 104, noted at 143 in FIG. 7, contacts roller 58 therein to block forward displacement of the related firing pin 20 into accidental impact with the associated primer.

OPERATION With housing 16 loaded with rockets, the firing mechanism of this invention is ready to launch one of such rockets when safety member 134 is indexed in the FIRE position. The firing mechanism acts responsive to trigger pull on lanyard 74 whereby shaft 64 is rotated 90. As shaft 64 rotates, ramp 98 on cam rotor 84 moves against one of the rollers 58 to cammingly retract the associated firing pin 20. At the same time apexes.l24 of a pair of the posts 120 on driven member 110 move along helical surfaces 128 of driving member 108 which, thereby, is retracted to load its cooperating spring 114. Immediately before the 90 rotation of shaft 64 is completed peak 100 moves past the engaged roller 58 and the camming engagement therebetween accelerates cam rotor 84 forwardly in the direction of rotation a distance equal to the radius of the roller, as determined by the displacement of ends 88 in slots 86, whereby the engaged roller is free to be propelled by the force of the compressed spring 48 into firing depression 104 for impact of the related firing pin 20 with the associated primer.

When peak 100 moves sufficiently past the center of roller 58, so that the roller can not hang up thereon and the need for antihang-up device 107 is no longer required, apexes 124 on driven member 110 move past peaks 130 of cam lobes 126 of driving member 108 thereby permitting the driving member, which is no longer required, to be returned to its normal position. Release of the trigger pull on lanyard 74 permits pulley 70 to be rotated to its normal position and so in position to engage pawl 76 therein with the next one of the teeth 78 for a further 90 rotation of shaft 64 and the launching of another one of the rockets the next time trigger pull is made on the lanyard.

I wish it to be understood that I do not desire to be limited to the exact details of construction shown and described, for obvious modifications will occur to a person skilled in the art.

lclaim:

1. In a mutlishot rocket launcher comprising a housing for receiving a plurality of rockets for launching, and a firing mechanism including a firing pin associated with each of said rockets to initiate the launching thereof, a roller rotatingly mounted to each of said firing pins, a cam rotor, means for sequentially rotating said cam rotor in segments of rotational equal to the number of firing pins, and a cam lobe on said rotor engageable during each segment of rotation with a successive one of firing rollers for retraction and release of the respective one of said firing pins, the improvement comprising antihang-up means disposed in cooperation with said cam rotor for preventing hand up of one of said rollers on said cam lobe when rotation of said cam rotor is stopped before retraction and release of the respective one of said firing pins is completed, said antihang-up means including a driven member arranged for displacement by said means sequentially rotating said cam rotor, a driving member actuatable by said driven member responsive to displacement thereof, energy storing means disposed in operational cooperation with said driving member, and means for transferring energy from said driven member through said driving member to said energy storing means responsive to displacement of said driven member by said means sequentially rotating said cam rotor and from said energy storing means through said driving member back to said driven member to effect counterrotation of said cam rotor when a segmental rotation of said cam rotor is not completed.

2. The invention as defined in claim 1 wherein said cam lobe is provided with an inclined ramp engageable with successive ones of said rollers responsive to sequential rotation of said cam rotor for retracting the respective ones of said firing pins against the bias of related springs and an apex terminating said ramp to release the one of said rollers engaged thereby when the respective one of the said firing pins is retracted and permit displacement thereof to launch the associated one of said rockets, and including means for mounting said cam rotor on a supporting drive shaft of said means sequentially rotating said cam rotor to effect limited free rotation of said cam rotor relative to said shaft and acceleration of said cam rotor relative thereto in the direction of rotation when said apex is located past the center of said roller engaged by said ramp.

3. The invention as defined in claim 2 wherein said means for mounting said cam rotor on said drive shaft comprises a pin extending diametrically through said shaft to form a pair of ends extending therefrom, and a pair of slots provided in said cam rotor for receiving said ends so as to transfer rotation of said shaft to said cam rotor, said slots being elongated in a transverse plane relative to said shaft to permit limited free rotation of said cam rotor relative to said shaft.

4. The invention as defined in claim 3 wherein said energy storing means comprises a spring mounted on said drive shaft, and including means for mounting said driving member on said shaft for translational, nonrotating displacement relative thereto so as to be displaceable against said spring for compression thereof, means for mounting said driven member on said drive shaft for rotation therewith, and cooperating cam means on said driving and driven members for converting rotational displacement of said driven member by said drive shaft to translational displacement of said driving member against said spring and for converting translation of said driving member by said spring to counterrotation of said driven member and said drive shaft.

5. The invention as defined in claim 4 wherein said cooperating cam means on said driving and driven members are disposed in operational engagement when one of said rollers is located on said ramp and said apex, and including means for disengaging said cam means when said apex is located past the center of the one of said rollers engaged with said ramp.

6. The invention as defined in claim 5 wherein said cam rotor comprises a planar annular surface around one end ar ranged for contact by all of said rollers except one thereof to block displacement of the respective ones of said firing pins to launch the associated ones of said rockets, said surface leading to said ramp for directing said rollers from said surface to said peak responsive to segmental rotation of said cam rotor, a side disposed normal to said planar surface to form said peak with said ramp, and a firing depression located at the base of said side for receiving said rollers when released from said peak to permit displacement of the associated firing pins to launch the associated ones of said rockets.

7. The invention as defined in claim 6 wherein said cam rotor is mounted for limited longitudinal displacement relative to said shaft and through the contact of said rollers with said surface is pressed forwardly to the forward extent of its limited longitudinal displacement by said firing pin biasing springs, and including an inside section of said firing depression, and a safety member disposed between said cam rotor and the adjacent face of said housing for manual rotation between a fire and a safe position, said safety member comprising detent means extending from the end thereof facing said receiver for contact with said face thereof when said safety member is in the safe position to position said cam rotor away from said face and position said inside section so that when one of said rollers is in contact therewith the associated one of said firing pins is blocked against impact displacement to launch the associated one of said rockets, and mating recesses in said face for receiving said detents when said safety member is in the fire position permitting displacement of said cam rotor by the bias of said firing pins springs towards said housing to where said inside section is positioned so as not to block displacement of said firing pins to launch the associated ones of said rockets when the related ones of said rollers are released from said peak into said firing depression.

Claims

6. The invention as defined in claim 5 wherein said cam rotor comprises a planar annular surface around one end arranged for contact by all of said rollers except one thereof to block displacement of the respective ones of said firing pins to launch the associated ones of said rockets, said surface leading to said ramp for directing said rollers from said surface to said peak responsive to segmental rotation of said cam rotor, a side disposed normal to said planar surface to form said peak with said ramp, and a firing depression located at the base of said side for receiving said rollers when released from said peak to permit displacement of the associated firing pins to launch the associated ones of said rockets.