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Publication numberUS3102479 A
Publication typeGrant
Publication dateSep 3, 1963
Filing dateMar 18, 1955
Priority dateMar 18, 1955
Publication numberUS 3102479 A, US 3102479A, US-A-3102479, US3102479 A, US3102479A
InventorsSeverance Ralph H
Original AssigneeMagnavox Co
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Fuze mechanism
US 3102479 A
Abstract  available in
Images(2)
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Claims  available in
Description  (OCR text may contain errors)

United States Patent Oflice WZAYQ Patented Sept.. 3, 1963 3,102,479 FUZE MECHANISM Ralph H. Severance, Fort Wayne, 1nd., assigner to; The Magnavox Company, lEort Wayne, 1nd a corporation Filed Mar. 1S, 1955, Ser. No. 495,279 9 Claims. (V3i. 10E-71) `This invention relates |generally to fuzes for projectiles or rockets, and more particularly to such tuzes wherein there are provided means for `arming .a fuze Within a predetermined distance .after the projectile `or rocket has been launched, and wherein further means are provided for self-destruction of the projectile or rocket within a predetermined distance after the projectile or rocket has passed its tar-get.

In accordance with conventional practice, projectiles or rocket fuzes include .arming mechanisms having a timing clock adapted to arm a tuze within a predetermined time after the projectile `or rocket has been launched. Clock mechanisms are relatively expensive and also relatively delicate, whereby it is extremely costly to manufacture delayed arming fuzes, and a tuze may not be armed after launching of the projectile tor rocket because of a damaged timing mechanism.

ln connection with rockets, it is especially important to provide a timing mechanism adapted to destroy the rocket within -a certain time after it has missed an intended target. in case of aircraft launched rockets, it is particularly important to prevent explosion of spent rockets in friendly territory.

Accordingly, the principal object of this invention is to provide a fuze for projectiles or rockets having simple and 'inexpensive timing means tor arming a projectile or rocket and for destroying the projectile or rocket in the event that the intended target is missed.

Another object of this invention is to provide a fuze arming and self-destroying mechanism which includes safety features adapted to prevent premature 'arming or self-destruction.

ln accordance with this invention there is provided a fuze tor projectiles or rockets comprising a means movable in response to the eiiects of acceleration for positioning a detonator in operative association with a tiring mechanism, a timing mechanism normally effective to prevent movement ofsaid means and responsive to the effects of acceleration for permitting movement of said means, tiring means operatively Iassociated with said detonator, and a timing i Lechanism normally locking said firing means and responsive to the eiects of deceleration for unlocking said tiring means.

The full nature of the invention will be understood from the accompanying drawings and the lfollowing description yand claims:

FIG. l is la side elevation ot a fuze embodying the invention.

FIG. 2 is :a cross section taken on line 2 2 of FIG. 1.

FlG. 3 is a cross section taken on line 3 3 tof FIG. 2.

PEG. 4 is `a cross section taken on line 4 4 of FIG. 2 showing, in addition, the housing members in which the fuze of FIG. l is mounted.

Referring to the drawings, .a fuze embodyingthis invention comprises a housing member 1t) having a threaded portion 11 adapted to receive .the warhead 12 of a rocket or projectile 'and having a second threaded portion 14 adapted to receive a casing member 15 which may be the propellant containing casing of a projectile or rocket. Within housing .11i there is provided a block member 16 within which is rotatably supported a substantially cylindrical detonator member 17 mounted for rotation on an axle 18. Axle 18 may be supported .in removable insert 19. Within the detonator member 17 there is provided a detonating charge 2G which is normally retained in a non-detonating position, as indicated in FIG. 1.

The detonator member 17 is provided with :a solid portion 22, the weight tof which yoverbalances the diametrically opposite portion 23. Consequently, in response to acceleration of the projectile or rocket, the unbalanced member tends to rotate in a -counterc-lockwise direction (FIG. 4). For preventing such rotation until after the projectile or rocket is launched, there is provided a timing and arming mechanism consisting of a slideably mounted cylinder 25 which normally engages iiattened side 26 of Idetonatcr member 17.` So long as cylinder 25 engages surface 26, the detonator cannot move .out of .its disarmed position. Cylinder 25 slides on a shaft 27 and is normally held in the illustrated position by means of an anti-creep spring 28, one end ot which enga-ges `cylinder Z5, and the other end of which engages a cover member Sil suitably fastened to the block 16. Cylinder ZS is -lled with small beads 31, preferably formed of glass .and having a diameter on the order of .0055 to .0065 inch. Shaft 27 has mounted thereon a node `or plunger 21 having a diameter slightly snraller than the internal diameter of cylinder 25, and having suiiicient clearance with respect to the cylinder wall to permit flow of beads past the .outer edge thereof. Normal shocks to ywhich a projectile or rocket may be subjected are insufficient to overcome the action of the anti-creep spring 28. Therefore, anti-creep spring 28 holds cylinder 25 in the position illustrated in FIG. 4, which is a forward position with respect to direction of iiight of the projectile or rocket. Thus, forces resulting from acceleration tend to move the cylinder 25 and the beads contained therein to a rearward position where cylinder 25 .is out of contact with the detonator member 17, leaving it free to rotate. In order .to permit the detona-tor member 17 to rotate only in a counterclockwis-e direction (FIGS. 3, 4), there is provided a stop .member 33 normally engaging a tongue 34 tonmed on a portion of the detonator member. This insures that this member will rotate only in a counterclockwise direction in response to acceleration :forces The rotor is also provided with a stop surface 35 whereby rotation of the rotor in response to lacceleration positions the rotor with stop surfaces-5 in contact with stop 33, thereby to present the proper end 36 -of detonator charge Ztl into the path of a stab type :of ring pin 37. The pin 37 is an integral part of a liring spring 38 mounted ion a post 39, the ends of which are embedded in the walls of a spring receiving recess 4@ in lblock 16.

For holding firing pin 37 and the spring 38 in cocked position, there is provided a trigger 42 pivotally mounted on a pin 43 embedded in the block member 16 as illustrated. Trigger 42 includes a tiring pin receiving notch 4d for normally holding a firing pin 37 in la cocked position. Trigger d2 in turn is held in a cocked position by means of a second delay mechanism comprising a cylinder 45 slideably mounted within block 16 in a bore 46. Cylinder 45 is mounted to the rear of the block 16 `as contrasted with cylinder 25 which is mounted in a `forward position thereof, whereby cylinder 45 responds to decelerative `forces. As in the case of cylinder 25, the cylinder 45 is mounted for sliding movement onV a stationary shaft 41 positioned by means of a pair of discs 47 and 48 suitably fixed to block 16. Shaft 41 includes node or plunger `419, the outside diameter of which is slightly less than the inside diameter of cylinder 45. Beads 50 ll the rear end of cylinder 45, whereby accelerative `forces tend to `cause the beads and the cylinder to move in a forward direction in response to decelerative forces. Such forward motion normally is prevented by the depending portion 52 of detonator member 17 which 3. extends into the path |of movement of cylinder 45. When the projectile or rocket is launched and becomes armed, this portion 52 of detonator member 17 moves out of the way of cylinder 45, whereby subsequent decelerative forcescan cause movement lof cylinder 45 out of the way of trigger 42, thereby to release firing pin 37.

In operation it may be assumed that detonator member 17 is in the position illustrated in FIGS. 3 and 4 where the detonating charge 20 is held in a safe position in which the fuze is disarmed. When the rocket or projectile is launched, the accelerative iforces cause cylinder 25 and beads held therein to move rearwardly against the action of anti-creep spring 28; and since the beads flow past the node 311 at a rate determined by the rate of acceleration, there is a certain time interval between the time of launching and the time of operation of detonator member 17. The rate of llow of the beads is calculated with respect to probable rates of acceleration to arm the projectile or rocket when it will have travelled approximately three hundred lfeet along its trajectory. At this point cylinder 25 will free .the detonator member 17, allowing it to rotate in a counterclockwise direction through an angle of ninety degrees, whereby the detonating charge 20 is in alignment with the path of movement of ring pin 37 land :also in alignment with the explosive charge within the warhead.

It will be noted that the fuze embodying this invention is not illustrated in the idrawing as including a tiring mechanism adapted to vrespond to impact with a target. The ring mechanism Yforms no part of this invention, but it will be obvious to those skilled'in the art that conventional tiring mechanisms may be adapted to release a firing pin or to initiate detonation electrically.

Ifl the projectile or rocket misses its target, and espe- -cially in thecalse of a rocket, deceleration will commence when the propellant charge has burned out. In response to such deceleration, cylinder 45 will move in a forward direction to release trigger 42 and firing pin 37, whereby the projectile or rocket `destroys itself before falling into friendly territory. respond to such decelerative 4forces within la period of approximately one second.

From the lforegoing description it will be apparent that this invention provides la simplified delay mechanism adapted to arm fuzes in projectiles or rockets. This mechanism is positive in its action and cannot respond to normal shock conditions created during shipment and storage, whereby there is adequate safety hntil the projeetile or rocket has actually been launched `along its trajectory.

The invention claimed is:

l. A fuze mechanism for projectiles and rockets comprising a block member adapted to be assembled in a projectile or rocket adjacent to the warhead thereof, a detonator movably mounted in said block member and normally positioned in inoperative relation to said warhead, 'whereby said projectile or rocket is disarmed and i-n a safe condition, means responsive to accelerative forces for moving said detonator into operative relation with said warhead, an arming delay device including a member normally positioned in said block in the way of movement of said detonator and movable in response to accelerative forces out of the way of said detonator to permit rotation of said detonator into said operative relationship with said warhead, a firing pin mounted -in said block in alignment with said detonator when said detonator is in an operative position with respect to said warhead, Ia spring member connected to said block `and said ring pin for moving said tiring pin into firing engagement with said detonator, a trigger mounted in said block in the way of movement of said firing pin and normally holding said iring pin in la cocked position, and a selfdestruction timing device including a member lnormally positioned in said block in the way of movement of said trigger and movable in response to longitudinal decelera- It is preferable that the cylinder 45 venting movement thereof untilV said detonator has been moved into operative relation with said warhead.

2. A fuze mechanism for projectiles and rockets comv prising a block member adapted to be assembled in a projectile or rocket adjacent to the warhead thereof, a detonator movably mounted in said block member and normally positioned in inoperative relation to said warhead, Awhereby said projectile or rocket is disarmed and in a safe condition, said detonator having means responsive to -accelerative forces for moving said detonator into operative relation with said warhead, a tiring pin mounted in said block in alignment with said detonator when said detonator is in an operative position with respect to said warhead, a spring member connected to said block and said firing pin for moving said firing pin into firing engagement with said detonator, a trigger mounted in said block in the way of movement of said tiring pin and normally holding said -iiring pin in a cocked position, and a selfdestruction timing device including a member normally positioned in said block in the way of movement of said trigger Aand movable in response to longitudinal decelerative forces for releasing said trigger, said detonator including :a stop member normally positioned in the way of movement of said self-destruction timing device for preventing movement thereof until -said detonator has been moved into operative relation with said warhead.

3. A fuze mechanism for projectiles and rockets comprising a block member adapted to be assembledY in a projectile or rocket adjacent to the warhead thereof, a detonator rotatably mounted in said block member and normally positioned in inoperative relation to said warhead, whereby said projectile or rocket is disarmed and in a safe condition, said detonator having an off center weight responsive to accelerative forces for rotating said detonator into operative relation with said warhead, an arming delay device including a cylindrical member normally positioned in said block in the way of movement of said detonator and movable in response to accelerative (forces out of the way of said detonator to permit rotation thereof into said operative relationship with said warhead, a plunger in said cylindrical member, and beads contained in said cylindrical member 'and movable past said plunger for regulating the rate of movement of said cylindrical member in response to accelerative forces.

4. A fuze mechanism for projectiles and rockets comprising a block member adapted to be assembled in a projectile 0r rocket adjacent to the warhead thereof, a detonator movably mounted in said block member and normally positioned in inoperative relation to said warhead, whereby said projectile or rocket is disarmed and in a safe condition, said detonator having means responsive to accelerative forces for moving said detonator into operative relation with said warhead, an arming deilay device including a container normally positioned in said block in the way of movement of said detonator and movable in response to accelerative forces out of the way of said detonator to permit rotation thereof into said operative relationship with said warhead, and means within said container for controlling the rate of movement of said container in response to accelerative forces.

5. A fuze mechanism for project-iles and rockets comprising a block member having a detonator adapted to be assembled in a projectile or rocket adjacent to the warhead thereof, a tiring pin mounted in said block member for movement into ring engagement with said detonator, a trigger mounted in said block in the way of movement of said tiring pin and normally holding said firing pin in a cocked position, and a timing Idevice including a cylindrical member normally positioned in said block in the way of movement of said trigger and movable in response to decelerative forces for releasing said trigger, a plunger in said cylindrical member, and a plurality of beads in said cylindrical member for regulating the rate of movement of said cylindrical member.

6. A fuze mechanism for projectiles and rockets comprising a block member having a detonator adapted to be assembled in la projectile vor rocket adjacent to the warhead thereof, a tiring pin mounted in said block member for movement into yfiring engagement with said detonator, a trigger mounted in said block in the way of movement of said tiring pin and normally holding said firing pin in a cocked position, and 1a timing device including a container normally positioned in said block in the Way of movement of said trigger and movable in response tto longitudinal decelerative forces for releasing said trigger, and means within said container for controlling the rate of movement of said container in response to longitudinal decelerative forces.

7. A fuze mechanism for projectiles and rockets comprising a block member adapted to be assembled in a projectile or rocket adjacent to the warhead thereof, a detonator movably mounted in said block member and normally positioned in inoperative relation to said warhead, whereby said projectile or rocket is disa-rined and in a safe condition, said detonator including means responsive to longitudinal accelerative forces for rotating said detonator into operative relation with said warhead, an arming device mounted within said block member for longitudinal movement and positioned in the way of movement of said detonator for movement longitudinally of `said block member by longitudinal accelerative forces out of the Way of said detonator to permit movement of said detonator into operative relationship with said warhead, means in the way of movement `of said device for impeding its movement and movable longitudinally out of the Way of said device at a controlled irate by and proportional to longitudinal accelerative forces, a firing means mounted in said block in alignment with said detonator when said detonator is in an operative position with respect to said warhead, a release member normally positioned in said block in the Way of movement of said tiring means and mounted for movement longitudinally of said block member, and means in the way of movement of said release member for impeding its movement and movable longitudinally out of the way of said release member at a controlled rate by and proportional to longitudinal decelerative forces occurring before said projectile or rocket impacts a target for releasing Said firing means for self-destruction of the projectile or rocket.

8. A lfuze mechanism for projectiles and rockets comprising a block member adapted to be assembled in a projectile or rocket adjacent to the warhead thereof, a detonator movably mounted in said block member and normally positioned in inoperative relation to said warhead, whereby said projectile or rocket is disarmed and in a safe conditi-on, said detonator including means responsive to longitudinal accelerative tierces for rotating said detonator into operative relation with said warhead, an arming device mounted within said block member for longitudinal movement and positioned in the way of movement or said detonator for movement longitudinally of said block member by longitudinal accelerative tor-ces out of the way of said Kdetonator to permit movement of said detonator into operative relationship with said warhead, a ring means mounted in said block in alignment with said detonator when said detonator is in ran operative position with respect to said warhead, a release member normally positioned in said block in the way of movement of said firing means and mounted for movement longitudinally of said block member, an-d means in the -way of movement of said release member for impeding its movement and movable longitudinally out of the vway of said release member at a controlled rate by and proportional to longitudinal decelerative tonces Ioccurring before said projectile or rocket impacts a target for releasing said iiring means for self-destruction of the projectile or rocket.

9. A uze mechanism yfor projectiles and rockets comprising a block member adapted to be assembled in a project-ile =or rocket adjacent to the -warhead thereof, a detonator movably mounted in said block member and normally positioned in inoperative relation to said Warhead, whereby said projectile or rocket is disarmed and in a safe condition, said detonator including means responsive to longitudinal accelerative forces lfor rotating said detonator into operative relation with said warhead, an arming device including a member mounted Within said block member for longitudinal movement and positioned in the way Ioi movement of said detonator for movement longitudinally of said block member by longitudinal accelerative forces out of the way of said detonator to permit movement of said ldetonator into operative relationship with said warhead, a ring means mu-nted in said block in alignment with said detonator when said detonator is in an operative position with respect to said warhead, a release member normally positioned in said lblock in the way of movement of said ring means and mounted for movement longitudinally of said block member, and means in the Way of movement `of said release member for impeding its movement and movable longitudinally out of the -way of said release member at a controlled rate by and proportional to longitudinal decelerative forces occurring before said projectile or rocket impacts a target for releasing said firing means for self-destruction of the projectile or rocket, said detonator including a4 stop member normally positioned in the path of movement of said release member yfor preventing movement or" said release member and movable with said detonator out of the Way of said release member when said detonator moves into operative relation with said warhead.

References Cited in the file of this patent UNITED STATES PATENTS 896,135 Meigs et al. Aug. 18, 1908 977,440 Dolby Dec. 6, 1910 1,311,104 Watson July 22, 1919 1,333,667 McCabe Mar. 16, 1920 2,014,393 Mathisen Sept. 17, 1935 2,167,197 Brandt July 25, 1939 2,331,633 Spooner Oct. l2, 1943 3,486,362 OBrien Oct. 25, 1949 2,700,934 Thompson Feb. 1, 1955 FOREIGN PATENTS 83,957 Sweden July 23, 1935

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US896135 *Dec 19, 1904Aug 18, 1908Bethlehem Steel CorpMechanical time-fuse.
US977440 *Dec 17, 1909Dec 6, 1910Jesse H DolbyTiming attachment for cameras.
US1311104 *Jul 27, 1915Jul 22, 1919 Detonator por ordnance-projectiles
US1333667 *Jun 4, 1917Mar 16, 1920Mccabe Thomas W RTime-fuse mechanism
US2014393 *Jun 4, 1934Sep 17, 1935Mathsen Marvin LFuse for projectiles
US2167197 *Nov 2, 1937Jul 25, 1939Sageb SaFuse for rotative projectiles
US2331633 *Jun 20, 1939Oct 12, 1943Spooner Henry WFuse for projectiles
US2700934 *Aug 29, 1945Feb 1, 1955Marion L J LambertCentrifugal fuze unlatched by setback
US3486362 *Mar 4, 1968Dec 30, 1969Filson John RichardCrimping device
SE83957A * Title not available
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US5898213 *Jul 7, 1997Apr 27, 1999Motorola, Inc.Semiconductor package bond post configuration
Classifications
U.S. Classification102/250, 102/266
International ClassificationF42C15/00, F42C15/285
Cooperative ClassificationF42C15/285
European ClassificationF42C15/285