US2754759A - Time delay fuze for a rocket - Google Patents

Description

July 17, 1956 K. L.. BAKER ETAI- TIME DELAY FUZE FOR A ROCKET 4 Sheets-Sheet. 1

Filed Aug. 29, 1947 n NN July 17, 1956 K. L.BAK|:R ET A1- 2,754,759

TIME DELAY FUZE FOR A ROCKET Filed Aug. 29 1947 4 Sheets-Sheet 2 KLLBLZ er A.AXeZs0l July 17, 1956 K. L. BAKER ET Al- TIME DELAY FUZE FOR A ROCKET Filed Aug. 29, 1947 y .limuV/ Il? S/IOS |108 illl'll'l'll 4 Sheets-Slime?l 3 Siwa/VMM KZ/.Baker CAAAxeZSon July 17, 1956 K. l.. BAKER ET AL TIME DELAY FUZE FOR A ROCKET 4 Sheets-Sham, 4

Filed Aug. 29, 1947 United States Patent TIME DELAY FUZE Fon A ROCKET Kennethl L. Bakerand Carl Axelson, Washington, ll). C;

Application August 29, 1947,- Serial No. 771,288 7 Claims. (Cl. 102;'71)

(Granted under Titia 35, Ui S. Code (1952), sec. 266) This` invention relates' generally to a time delay fuze for use with an armor piercing rocket and more particularly to a time delay fuze in which means controlled by a predetermined amount of gas pressure produced as the propellant charge of the rocket motor burns is adapted to arm the fuze as' the rocket is propelled along the traject-'or' toward the target, the firing of the fnze being controlled by firing rineans rotatably and slideably arranged within the fuze casing and adapted to be rotated to an armed position and thereafter moved longitudinally to a tiring position rin response to the sudden impact of 'the rocket with the target, at which time the tiring means are locked in the firing position, whereupon the bursting charge within the rocket shell is detonated in predetermined time delayed relation with respect to the aforesaid impact of the rocket with the target', such time' delay period being controlled by a delay charge arranged within the' firing plunger slideably arranged within the ftize casing. Furthermore, on impact of the rocket with the target, the rocket is adapted to pierce the outer plates of a target such, for example',v as a naval vessel, aircraft, or thelike and to exp-lode the interior thereof whereby the force of the explosion is concentrated on the vital interior structural arrangement of the' target.

More specifically the invention relates to' a fuze for a rocket in which the tiring means are maintained in a safe position during handling and transportation and in which arm-ing thereof will not occur until after the rocket has been propelled from the launching rack and traveled a predetermined distance therefrom, the arming of the tuz'e' occurring during the free iiight of the rocket toward the target.

One of the objects of the present invention is the provision of a' new and improved time dela-y fuze for a rocket inl which the tiring means of the fuze is locked in a safe position until the rocrcet is launched from a launching r'a'ck or tube', as the case may be, whereupon the tiring means is released from an initial locked safe position and rotated to an armed position.

Anothery object of the present invention is the provision of a new and i'rriproved` time delay fuze for arocket in which a pressure controlled arming member is adapted to arm the fuze as the rocket is propelled toward the target.

Another object of the present invention is the provision of anew and improved fuze for a rocket inwhich arming means controlled by the pressure of combustion' of the propellant is releasably and rotatably supported within the fuze' casing.` and adapted to rotate the firing means from' a safe position tio an armed position when the arming means have been released by the pressure controlled means.

A further object of the invention is the provision of a new and improved fuze for a rocket having a rotatable armi-ng member arranged therein adaptedy to be released and rotated to an armed position during the free ght of the rocket toward the target, and' in which the-tiring means is sli'deabiy arranged therein and adapted to be locked in 2,754,759 Patented July 17, 1956 the firing position upon impact of the rocket with the target.

Still another object of the present invention is the provision of a new' and improved time delay fuze for a rocket in which the tiring means thereof is adapted to be rotated from a safe position to an armed position, and thereafter to be moved longitudinally to' a firing position and det# nate the bursting charge within the rocket shell in pre# determined time delay relation with respect t the aforesaid impact.

Still other objects, advantages and improvements will be apparent from the following description, taken in connection with the accompanying drawings,- of which:

Fig; l is an elevational view of a rocket partially broken away and showing the fuz'e' of th present invention scured thereto;

Fig.` 2 is an enlarged longitudinal sectional view of the fuze of Fig. 1 and Showing the fuze in a safe or unarmed condition;

Fig. 3 is a transverse sectional view of the fuie taken on the line 3"-'3 of Fig. 2;

Fig'. 4 is a transverse sectional view of the fiiz taken on the line' 4-4 of Fig. 2;

Fig. 5 is a transverse sectional v'iew' of the fuze taken on the line' 5=5 of Fig'. 2, and showing the means for preventing further movement of the arming member after the member has been rotated to an riiied position;

Fig'. 6 is a fragmentary elevational view of the ue partially broken away and in section and showing the' shear pin for' maintaining the rotatable arming member in an' initial locked or safe position;

Fig. 7 is a View partially in longitudinal section and partially broken away showing the fuze in an armed con dition;

Figi. 8 is a transverse sectional view of the fuze taken on the line 8-S of Fig. 7;

Fig. 9' is atransverse sectional View of the fuzev taken on the line 9--9 of Fig. 7;

Fig. 10 is afrag'mentary longitudinal sectional view of the fuZe showing the firing plunger in a iiing position;

Fig. l1 isa transverse sectional View ofthe fue taken 01'1 the line` 11`11of Fig. l0 and showing, the arming meinberotated to the armed position and a stop pin for preventing the further rotation thereof; and

Figl 12 is a transverse sectional View of they uz'e taken "ice l on the line IZ-12 of Figl. l() and showing a pair of detents for locking t-le 'ringV plunger in the firing position.

Referring now to the drawings for a more complete understanding of the invention and more particularly to Fig'. I thereof, there is shown thereon a rocket indicated generally by the reference character l0 comprising a motor tube 11 having theusual rocket motor generally indicated by the numeral 12 arranged' therein. Secured to' one end ofthe motor tube 11 in any suitable manner, preferably by thrfeadingthe parts together, is a rocket head I3 comprisinga shell 14y having arranged therein a bursting charge 155. Disposed in one end of the headand' attached thereto as by an adapter 16 is the fuze of the present invention generally indicated by the referencei character 17.

rfhe rocket, Fig. 1, is a conventional type rocket and the motor thereof comprises the usual component parts` such, for" eXample, as a propellant 18, grid 19 for supporting the propellant within the tube 11, nozzle 21 adapted' t'o direct' the gas jet in the desired direction as thev propellant burns and to provide for expansion ofthe gases in`- the eXit cone ofthe nozzle, igniter 2v2, squib 23 arranged' in operativerelation with respect to the ignit'er, andl conductors- 24 attached tothe squib and adapted to supply an electrical impulse thereto'Y as" the rocket is` launchedthereby to" fire' the" sq'uib and ignite theA igniter' which, in turn, ignites the propellant.

The motor tube 11 has secured to the other end thereof the usual stabilizing assembly generally indicated by the reference character 25 comprising a plurality of ns 26, the ns being attached -to the -tube in any suitable mannei and extending radially therefrom and having a shroud 27 'secured to the outer portions thereof. As lthe operation and structure of the aforesaid rocket is wellknown to those skilled in the art, further detailed description of the operation and structural arrangement thereof is deemed unnecessary as the aforesaid rocket is disclosed for the purpose of more clearly illustrating the manner in which the fuze is armed in response to a predetermined amount of pressure created by the propellant 18 as the propellant burns.

The adapter 16 is threaded into the open end of 'the head 13, Figs. l, 2 and 3, and has a centrally disposed threaded bore 28 formed therein for threaded engagement with the fuze 17, thus the fuze is secured to the adapter and extends a predetermined distance into the bursting charge 15.

The fuze of the present invention comprises a casing I29 composed of any material suitable for the purpose such, for example, as steel or the like and is provided with a centrally disposed 'bore 31, in which is -arranged a plunger generally indicated by the numeral 32. The .plunger comprises a body 33 having trunnions 34 and 135 respectively formed on the ends thereof which extend -outwardly therefrom and slidably and rotatably support the plunger within the fuze casing 29. Arranged with-in a plurality of grooves 36 formed in the body 33 of the plunger are a plurality of anti-friction balls `37 adapted tto engage the wall delining the bore 31, thereby to permit the plunger to move slidably and rotatably within 'the bore with no appreciable amount of friction between lthe wall delning the bore and the plunger when the plunger is released. The balls are maintained within the grooves 36 by a washer 38 and a collar 39 surrounding the trunnion 35 and secured to the body 33 of the plunger .in any suitable manner such, for example, as by a pin 41.

As shown on Figs. 2, 7 and 10 the plunger has formed `therein a bore or well 42 having arranged therein a delay element generally indicated by the numeral 43 and comprising a casing 44 within which is disposed a delay charge 45. One end portion of the delay charge is in proximate space relation with respect -to one end of a detonator 46 arranged in a reduced bore 47 and in communication with the bore 42 in the plunger, the other end of the detonator being in substantial abuttingengagement with a 'lead-out charge 48 arranged in a transverse bore 49 disposed within the body 33 of the plunger. The lother end of the delay charge -is arranged in spaced 'relation with respect to a primer indicated by the reference character 50 and adapted to re the del-ay charge by way of bore 51 and passages 52 disposed within the ycasing 44.

The primer 50 is disposed within a well 53 formed in la nipple 54 and having threaded engagement with the threaded portion of bore 42, the primer being clamped between the member 44 and nipple 54, Fig. 2. Threaded into the nipple 54 is a casing 55 having an explosive cap '56 arranged -therein and adapted to be 'red as the rocket strikes the target. Arranged within a bore 57 formed in the nipple 54 is an annular member 5'8 having a centrally disposed opening extending therethrough. Disposed in the opening and secured to the annular member '58 by a shear pin 60 is a firing piston 59 comprising a head `61 and a striker 62, the striker being adapted to strike the primer 50 with suflicient force to cause tiring thereof when the cap 56 has been red upon impact of the rocket wi-th the target. It will be understood, however, that when the cap 56 is tired, the force of the explosion therefrom will be sulhcient to sever the shear pin and drive the piston to'ward the primer 50 and the striker 62 'thereon will strike the primer '50 with Sll- 4 cient force to cause explosion thereof thus igniting the delay charge and tiring the detonator.

An anti-creep device 63 comprising a skirt 64 is arranged about a portion of the trunnion 35 and about an enlarged head 65 formed on the nipple 5'4, the anti-creep device being maintained on the trunnion and head by a iange 66 formed thereon and clamped between the head 6'5 and a anged portion 67 formed on the casing 55. -As best shown on Fig. 2 the skirt 64 seals a pair of diametrically arranged ports 68 formed in the head 65, the ports being in communication with lthe bore 57, the purpose of which will be more fully described hereinafter. Premature longitudinal movement of the plunger 32 after rotation thereof is prevented by a plurality of 5ta-bs 80 formed on the skirt 64 and extending outwardly therefrom and adapted to engage a disc 69. lUpon irnpact these 'tabs are bent inwardly sufficiently to release the plunger for longitudinal movement.

The disc 69 has a centrally disposed opening 70 therein and is arranged within an enlarged portion 71 of bore 31, the disc being maintained within the aforesaid enlarged portion by a plug 72 having threaded engagement therewith. It will be understood, however, that when Ithe plunger has been released and moved to a tiring position, Fig. 10, upon impact of the rocket with a target, lthe plunger is forced toward a tiring pin 73. The ring pin is secured to the plug 72 in any suitable manner such, for example, as being pinned thereto and having a striker 74 formed thereon adapted to extend into a recess T5 arranged in plug 72 in such a manner as to have tiring engagement with the explosive cap 56 when the plunger has been moved a predetermined amount in response to Ithe aforesaid impact of the rocket with a target. As the plunger is moved to the fir-ing position the anti-creep device attached thereto is moved through opening 70 formed in disc 69 a predetermined amount and upon ring of the cap 56 in the aforesaid manner the skirt 64 of the anti-creep device is distorted or bulged as at 76 lat two points opposite ports 68, Fig. 10, -in response to the force of the explosion partially directed thereagainst by way of the aforesaid bore 57 and ports 68, it being understood, that the explosive force is also directed against the head 61 of the tiring piston 59, the divided force of the aforesaid explosion being controlled by a dellector 77 arranged in the bore 57. Thus the force of the explosion is suicient not only to cause the skirt 64 to be bulged in the aforesaid manner but also to drive the piston 59 rearwardly with sucient force to cause the shear pin to be severed whereupon the striker 62 formed thereon will be driven into firing engagement with the primer 50.

When the plunger has been moved longitudinally to the tiring position in response to the set-forward force as the rocket strikes the target, the skirt 64 will be bulged as heretofore described, the bulged portions thereof being adapted to engage the disc 69 and prevent reverse movement of the plunger from the forward position thereof before it is locked by the detent locking mechanism,

Fig. l0. When this occurs, a pair of diametrically disposed spring controlled locking detents 78 slideably arranged within bores formed in the casing are brought into axial alignment with their respective slots 79 formed in the plunger 32, the detents being urged therein by a pair of springs 81 respectively arranged within Vthe aforesaid Figs. 7 and 9,. the plunger 32 has been released and rofatedA from the safe position to an armed position. With particular reference to Fig. 9 the detents 78 remain` in engagement with the outer periphery of the plunger after the plunger has been rotated from the safe position to anr armed position, a movement of substantially 90, the slots 79 therein are thus brought into longitudinal spaced alignment with respect to the detents 78 and upon impact of the rocket with the target the plunger is driven longitudinally forwardly to the tiring position, Fig. l0, ard locked in the firing position by the aforesaid detents 7 As shown on Figs. 2, 3, and 5 a pair of diametrically disposed pins 82 are secured to the casing 2'9 in any suitable manner and extend into the bore 31 a predetermined amount, the respective ends thereof having abutting engagement with the forward endrofV the plunger thus preventing longitudinal movement of the plunger within the bore 31 until the plunger has been rotated substantially 90 by an arming memberY as will be hereafter more fully described. It will be understood, however, that when the plunger has been rotated substantially a quarter of a turn, the ends of the pins are brought into spaced longitudinal alignment with a pair of complementary longitudinall arranged slots 83 formed in the plunger thereby to permit free passage of the plunger with respect to the pins as the plunger is moved longitudinally within the bore 31 to the aforesaid tiring position. It will be further understood, that when the plunger 32 is rotated substantially 90 the detents 78 are brought into spaced longitudinal alignment with a pair of slots 79, such rotative movement also being adapted to bring the slots 83 into spaced' longitudinal alignment with pins 82 thereby to permit longitudinal movement of the plunger to the ring position and also providing means for locking the plunger in the tiring position upon impact of the 'rocket with the target.`

As shown most clearly on Figs. 2 and 7 of the drawings there is arranged within the casing 29 an arming device generally indicated by the numeral 84 and comprising a bearing member 85 disposed within an enlarged recess 86' formed in one end of the casing 29, the bearing member being maintained therein by an annular nut 87 having abutting engagement with a shoulder S8 formed on the bearing member 85 and adapted to be threaded into the recess 86. Disposed within the bearing member 85 and rotatably supported with respect thereto is a normally locked spring actuated rotor 89 adapted to rotate the plunger 32 to an armed position when released. The rotor is maintained within the bearing member by an annular disc 91 secured to the member in any suitable manner such, for example, as by crimping one end portion of the member about the annular disc Figs. 2, 6, 7 and 10.

The rotor 89 is rotatably supported by the disc 91 and a'. sleeve 92, releasably and slideably arranged within a bore 93 disposed in the rotor 89 and an opening 94 in the member 85, the sleeve 92 being releasably supported by a shear pin 95 extending through openings 96 in the sleeve 92 and complementary openings 97 arranged in the bearing member.

A drive pin 98 extends through a slot 99 formed in trunnion 34A and into corresponding openings 101 `arranged in the rotor 89, the pin also extending through a pair of slots 102 in sleeve 92. By this arrangement, a driving connection is provided between the plunger 32, arming member 89 and sleeve 92 by pin 98 and rotative movement will be imparted to these component parts when the shear pin 95 is severed, such rotation being imparted. thereto by a spring 103 surrounding the rotor 89 and having one end thereof anchored therein and the other end anchored in the bearing 85. it will be understood', that when the shear pin 95 has been severed the rotor', plunger, and sleeve will be rotated a predetermined amount such, for example, as approximately 90", the

rotation thereby being controlled by a stop pin 104 secured to the casing 291m any suitable manner and extending through a recess 105 in the bearing 8'5 and into a slot 106 formed in the rotor 89 Figs. 2, 5, and l1. A shoulder 107, Figs. 5 and ll, on the rotor and formed by the wall defining the slot 106 thereof is adapted to engage the pin 104 and prevent further rotation of the aforesaid' rotatable elements when the elements have been released and rotated substantially in response to the action of spring 103.

When the plunger 32 has been rotated substantially 90 in the aforesaid manner the lead-out charge 48 therein is brought into spaced longitudinal alignment with respect to a pair of diametrically disposed booster charges 108 arranged Within complementary recesses 109 formed in casing 29 as clearly shown on Fig. 7. A pair of additional diametrically disposed boostercharges 111 are re` e' spectively arranged Within recesses 112 formed in the` casing 29 in proximate spaced relation with respect to the charges 108 and adapted to be r'ed thereby. The aforesaid charges 108 and 111 are maintained within their respective recesses by a retaining cup 113 enclosing the charges and having threaded engagement with the casing 29.

As shown on Fig. l0 the plunger 32 has been moved to a firing position in response to the impact of the rocket with a target and locked therein by the aforesaid detents 78. When this occurs a. continuous tiring train is provided from the cap 56 to the booster charges 108 by way of cap 56, primer 50, delay charge 45, detonator 46, lead-out charge 48 and booster charges 108 and 111 which are adapted to tire the bursting charge 15. arranged within the shell 14 of the rocket head 13. It will be understood, however, that the bursting charge 15 will not be red by the aforesaid booster charges until a predetermined period of time has elapsed after the rocket strikes the target, the time delay period being controlled by the delay charge 45 thus permitting' the rocket to pierce the outer structure or plates of the target and enter the interior thereof before the bursting charge 15 is fired.

A plug generally indicated by the reference numeral 114 is threaded into a well 115 formed in one end of the casingV 29 and comprises an end wall 116 having a centrally disposed opening 117 arranged therein and an annular flange 118 formed thereon. Secured within the opening 117 as by threaded engagement therewith is a valve 119 comprising a` casing 121 having a centrally disposed bore 122 extending partially therethrough in which is arranged a. ball valve 123 adapted to normally seal a restricted bore 124, the bore being in communication with the bore 122. The ball valve 123 is urged in sealing engagement with respect to bore 124 by a spring 125, one end thereof being in abutting engagement with the ball valve, and the other end in engagement with a plug 126 secured in the casing 121 as by threaded engagement therewith.

A pair of diametrically disposed exhaust ports 127 are arranged within the casing 121 and in communication with the bore 122, the ports also being in communication with a chamber 128 provided between the end wall 116 on plug 114 and an end wall 129 formed on a cup-shaped member 131 arranged within the well 115 and maintained therein by the aforesaid plug 114. Extending transversely through the casing 121 and in communication with bore 124 is an inlet port 132,- thus providing means whereby the gas pressure created by the propellant 18 as the propellant burns is admitted therethrough and into chamber 12S when the pressure within the motor tube 12 has increased sufficiently to overcome the tension of the spring and unseat the valve 123.4

Clamped between a shoulder 133 formed within the well 115 and the member 131 by the plug 114 is a flexible diaphragm 134 having a substantial portion thereof reinforced by a disc 135 secured thereto in any suitable manner preferably as by soldering the parts together. It will be understood, however, that the diaphragm is adapted to be expanded in response to a predetermined amount of pressure exerted thereon, such pressure being created in the aforesaid manner and entering into a chamber 136 provided between the wall 129 and the diaphragm by way of an orifice 137 formed in the wall 129 and in communication with the aforesaid chambers 128 and 136. It will be further understood, that when a suicient amount of pressure has entered into chamber 136 by Way of orifice 137, the diaphragm will be forced into engagement with sleeve 92 by the aforesaid pressure, whereupon the sleeve 92 is driven inwardly by the expansion of the diaphragm suliiciently to cause the shear pin 95 to be severed due to the frangibility thereof and the shearing action exerted thereon as the sleeve 92 is moved inwardly with respect thereto in the aforesaid manner, the inward movement of the sleeve being permitted by the slots 83 formed there- Clamped between an enlarged head 138 formed on the valve casing 121 and the end wall 116 of plug 114 is a screen or filter member 139 adapted to permit the aforesaid gas pressure to enter into the chamber 128 by way of valve 119 but to exclude foreign matter therefrom such, for example, as the particles of combustion produced as the propellant 18 burns. The head 138 is also adapted to clamp a grip member 141 to the plug 114.

The aforesaid arming of the fuze will occur as the rocket is propelled along the trajectory by the functioning of the motor 17 as is well known to thoseskilled in the art, it being understood, however, that the propellant charge of the rocket motor is ignited in the usual manner as the rocket is launched from the launching rack or tube (not shown), as the case may be. As the rocket is propelled along the trajectory by the rocket motor a suiiicient amount of gas pressure enters into the chamber 128 by way of valve 119 as the propellant charge burns and causes expansion of the diaphragm 134, such expansion being sui'iicient to drive the sleeve 92 inwardly with sufficient force to cause the shear pin 95 to be severed.

When the shear pin has been severed, the arming member 89 is released and rotated substantially 90 to an armed position, Fig. 7, by the action of spring 103, further rotation thereof being prevented by stop pin 104. It will be understood, however, that as the arming member is rotated, rotation of the plunger 32 is effected by the drive pin 98 secured to the arming member and extending through slot 99 formed in trunnion 34 of the plunger. When this occurs, the lead-out charge 48 is brought into spaced longitudinal alignment with the booster charges 108, Fig. 7, and the slots 83 are brought into spaced longitudinal alignment with pins 82 thus permitting free longitudinal movement of the plunger to a tiring position upon impact of the rocket with the target, the pins 82 preventing longitudinal movement of the plunger until the plunger has been moved to an armed position in the aforesaid manner. As the rocket strikes the target the plunger ismoved to the tiring position in response to the set-forward force applied thereto, whereupon the explosive cap 56 is fired by the tiring pin 73, the force of the explosion being suiicient to cause the skirt 64 to be bulged as at 76 and hold the plunger momentarily, thereby to permit the locking detents 78 to be urged into their respective slots 79, thus locking the plunger in the firing position. As the cap 56 is tired by the firing pin 73, the force of the explosion is suicient not only to bulge the skirt 64 but also to sever the shear pin 60 and drive the piston toward primer 50, whereupon the striker 62 thereon will strike theY primer with sufficient force to cause explosion thereof, the fiash therefrom igniting the delay charge 45 thereby exploding the detonator 46 when a predetermined period of time has elapsed. The detonator fires the leadout charge 48 andthe booster charges 108 are red thereby ,whichinitiates firing of the auxiliary booster charges 111 and concurrently therewith the burstingvcharge 15 is tired and fragmentation of the shell occurs.

Briefly stated in summary, the -present invention cornprises the provision of a new and improved Vtime delay fuze for an armor piercing rocket in which -means are provided for tiring an explosive charge arranged within the rocket shell in predetermined time delayed relation with respect to impact of the rocket with the target, and in which the arming means is controlled by gas pressure formed by combustion of the rocket propellant and adapted to release a rotor within the fuze as the rocket is propelled along the trajectory thereby to rotate a firing plunger from an initial safe position to an armed position, the plunger thereafter being adapted to be moved longitudinally to a firing position and locked therein as the,

rocket strikes the target, and in which means are provided for detonating the bursting charge arranged within the rocket shell when a predetermined period of time has elapsed after impact of the rocket with the target.

While the invention has been described with reference to a preferred Vexample Vthereof which gives satisfactory results, it will be obvious to those skilled in the art to which the invention pertains, after understanding the in-` vention, that various changes and modifications may be made Without departing from the spirit and scope of the invention, and it is intended therefore, in the appended claims, to cover all such changes and modifications.

The invention herein described and claimed may be manufactured and used by or for the Government of the United States of America for governmental purposes without payment of any royalties thereon or therefor.

What is claimed as new and desired to be secured by Letters Patent of the United States is:

l. A time delay fuze for a rocket comprising a casing, a pair of booster charges arranged within said casing, an arming member releasably and rotatably supported within said casing in a safe position and adapted to be ro-l tated to an armed position when released, means including a device slideably arranged within said arming member and releasably secured to the casing for maintaining the arming member in said safe position, means secured to the casing and the arming member for rotating the arming member a predetermined amount to said armed position when the arming member is released, flexible means sealed to the casing and normally spaced from said device for moving said device suiciently to release the device from the casing as the flexible means is moved into engagement with the device in response to the pressure applied to the flexible means as the rocket travels along a trajectory, a firing plunger rotatably supported within the casing and adapted to be rotated to an armed position and moved longitudinally to a firing position upon impact of the rocket with a target, a bifurcated portion on said plunger, driving means on said arming member and slideably disposed within said bifurcated portion for rotating the plunger to said armed position thereof when the arming member is rotated said predetermined amount, explosure means including a time delay element arranged within said plunger for tiring said booster charges when a predetermined period of time has elapsed after said irnpact, and means on the casing for firing said explosive means upon forcible engagement therewith as the plunger moves to said tiring position in response to said impact.

2. A time delay fuze for a rocket comprising a casing having a pair of diametrically disposed recesses formed therein, a pair of booster charges respectively arranged within said recesses, an arming member releasably and rotatably supported within said casing in an initial safe position and adapted to be rotated to an armed position when released, means including a shearable member secured to said casing and operatively connected to said arming member for maintaining the arming member in said initial safe position and adapted to release the arming member when severed in response to a predetermined pressure applied thereto, pressure controlled means sealed to the casing and movable into engagement with said arming member by pressure applied thereto from the combustion of thel rocket propellant as the rocket travels along a trajectory for applying said pressure tothe shearable member, spring means secured to the casing and arming member for rotating the arming member to said armed position as said shearable member is severed, spring urged valve means on the casing in communication with said propellant and said pressure controlled means for applying said pressure to the pressure controlled means when the pressure from said propellant has reached a predetermined value, a tiring plunger rotatably supported within the casing and adapted to be rotated to an armed position by said arming member and moved longitudinally to a tiring position upon impact of the rocket with a target, a bifurcated portion on said plunger, drive means on the arming member and disposed within said bifurcated portion for rotating the plunger to said armed position as the arming member is released, explosive means including a time delay element arranged within said plunger for ring said booster charges when a predetermined period of time has elapsed after said impact, means on the casing for tiring said explosive means when thel plunger is moved to said armed. position and the explosive charge is driven into tiring engagement therewith in response to said impact, a plurality of yieldable tabs carried by said plunger and extending outwardly therefrom, and means on said casing in the path of travel of said tabs for preventing said longitudinal movement of the plunger until said impact.

3. A time delay fuze for a rocket comprising a casing, a pair of booster charges arranged within said casing, an arming member releasably and rotatably supported within said casing in an initial safe position, a sleeve disposed within said arming member and slideably arranged within said casing for supporting the arming member Within the casing, shearable locking means secured to the casing and sleeve for releasing the arming member for rotation to said armed position when the locking means is severed in response to a predetermined amount of movement of said sleeve, spring means secured to the casing and arming member for rotating the arming member to said armed position as the arming member is released, a firing plunger rotatably supported within the casing and adapted to be rotated to an armed position by said arming member and moved longitudinally to a firing position upon impact of the rocket with a target, said plunger having a slot formed therein, a drive pin secured to the arming member and slideably disposed within said slot formed in said plunger for rotating the plunger to said armed position in response to rotation of the arming member, explosive means carried by said plunger and including a time delay element for ring said booster charge when a predetermined period of time has elapsed after the explosive means is tired, means on the casing for ring said explosive means upon forcible engagement therewith when the plunger is moved to said firing position, a plurality of yieldable elements carried by and extending outwardly from the plunger, and means on said casing in the path of travel of said elements for preventing said longitudinal movement of the plunger to said firing position until said impact.

4. A time delay fuze for a rocket comprising a casing, a pair of booster charges arranged within said casing, a normally locked tiring plunger releasably and rotatably arranged within the casing and adapted to be rotated from an initial safe position to an armed position when released and to be moved to a tiring position in response to said impact, said plunger having a slot formed therein, a shear pin secured to said casing and disposed Within said slot for locking the plunger against rotation to said armed position until said pin is severed in response to a predetermined amount of pressure applied thereto, an arming member rotatably supported within the casing and locked against rotation by said shear pin and adapted to be rotated a predetermined amount when said shear pin is severed, sleeve means releasably supported within the arming member by said shear pin for severing the pin in response to said pressure thereon as the sleeve is moved a predetermined amount, a exible diaphragm sealed to the casing andy movable into engagement with said sleeve by the gas pressure of combustion of the rocket propellant for moving the sleeve said predetermined amount,- means on said arming member and secured to the casing for rotating the arming member said predetermined amount, means secured to the arming member and traversing said slot for rotating the plunger from said initial safe position to said armed position when the arming member is released and rotated said predetermined amount, means including a time delay element arranged Within the plunger for tiring said booster charge in time delayed relation with respect to said impact, and means on the casing for firing said last named means upon forcible engagement therewith as the plunger is moved to said tiring position in response to said impact.

5. A fuze for a rocket comprising a casing, a normally locked firing plunger releasably and rotatably arranged' within the casing and adapted to be rotated from an initial safe position to an armed position when released and to be moved to a tiring position upon impact of the rocket with a target, a bifurcatedportion on said plunger, shearable locking means secured to saidV casing and traversing said bifurcated portion for locking the plunger against rotationl to said armed position until the. shearable means is` severed in response to a predetermined amount of pressure applied thereto, sleeve means releasably supported within. the casing by said shearable locking means for applying said pressure thereto, means sealed to the casing and movable into engagement with said sleeve means by gas pressure from combustion of the rocket propellant for applying said pressure to the sleeve means, arming means rotatably supported within the casing and connected for rotation with the plunger and adapted to be rotated a predetermined amount when said locking means is severed, means on said arming means and secured to the casing for rotating the arming means said predetermined amount, means secured to the arming means and traversing said bifurcated portion for rotating the plunger from said initial safe position to said armed position when the plunger is released and the arming means is rotated said predetermined amount, explosive means carried by said plunger, and means on the casing and normally spaced from said plunger for tiring said explosive means upon forcible engagement therewith when the plunger is moved to said firing position in response to said impact.

6. A time delay fuze for a rocket comprising a casing, a pair of booster charges arranged Within said casing, rotor means releasably supported within said casing and adapted to be rotated a predetermined amount when the rotor means is released, spring means on said rotor means and secured to the casing for rotating the rotor means said predetermined amount as the rotor means is released, a shear pin secured to the casing and operatively connected to said rotor means for releasably supporting the rotor means within the casing and adapted to prevent rotation thereof until said shear pin is severed, means including a flexible diaphragm sealed within the casing and movable by gas pressure of combustion of the rocket propellant for causing the shear pin to be severed as said diaphragm is forcibly driven into engagement with the rotor means in response to an increase in said pressure, a plunger operatively connected to the rotor means for rotation from an initial safe position to an armed position as the rotor means is rotated said predetermined amount, said plunger being adapted to be moved longitudinally to a tiring position upon impact of the rocket with a target, a bifurcated portion on said plunger, means on the rotor means and disposed within said bifurcated portion for rotating the plunger from said initial safe position to said armed position as the rotor means is released and rotated said predetermined amount, yieldable means on the plunger in engagement with the casing for releasably locking the plunger in said armed position until said impact, explosive means including a time delay element arranged with the plunger for tiring said booster chargesin timedelayed relation with respect to said impact, and means on said casing for ring said explosive means upon forcible en-v gagement therewith when ythe plunger is lreleased and driven into said tiring position in response to said impact-` 7.l A time delay fuze for a rocket comprising a casing, a pair of booster charges arranged within said casing, a plunger rotatably and slideably supported within the cas-v ing in an initial safe position and adapted to be rotated to an armed position as the rocket travels along a trajectory, said plunger being adapted to be moved slideably from said armed position to a firing position in response to impact of the rocket with a target, a pair of stop pins secured to said casing, complementary means on the plunger in engagement with said stop pins for preventing said sliding movement of the plunger until the plunger has been rotated to said armed positon, rotatable arming means releasably secured to said casing and rotatively connected to the plunger and adapted to be rotated a predetermined amount when released, a bifurcated portion on said plunger, a shear pin secured to the casing and disposed within said bifurcated portion for releasing the arming means and plunger when the pin is severed in response to a predetermined pressure applied thereto, a

flexible diaphragm sealed within the casing and movable 25 into engagement with said arming means by gas pressure of combustion of the rocket propellant thereon for apply ing said pressure to the shear pin, drive means on said l2 arming means and rotatable therewith and disposed' slide-f ably within said bifurcatedV portion for rotating said plunger fromY said initial safe position to said armed position when the arming means is released and rotated said predetermined amount, explosive means including a time delay element carried by the plunger for firing said booster charges in predetermined time delayed relation with respect to said impact, means on said casing and forcibly engageable with said explosive means to cause tiring thereof as the plunger is driven to said ring position, means' on said plunger and effective by the force of the explosion as the explosive means is red for momentarily maintaining the plunger in said tiring position, a pair of detents on the casing, and complementary means on the l plunger and adapted to coact with said detents for locking the plunger in said firing position.

References Cited in the le oi' this patent UNITED STATES PATENTS Y Woodberry May 3, 1921 2,145,507 Denoix Jan. 31, 1939 2,397,781 Fischer Apr. 2, 1946 2,409,205 Graumann Oct. 15, 1946 2,441,897 Nichols May 18, 1948 FOREIGN PATENTS 257,335 Great Britain Aug` 27, 1926 wad.; 't i

Images