US3788229A - Fuse for non-gyratory missiles - Google Patents

Fuse for non-gyratory missiles Download PDF

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Publication number
US3788229A
US3788229A US00285123A US3788229DA US3788229A US 3788229 A US3788229 A US 3788229A US 00285123 A US00285123 A US 00285123A US 3788229D A US3788229D A US 3788229DA US 3788229 A US3788229 A US 3788229A
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US
United States
Prior art keywords
auxiliary
striker
detonator
missile
main
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US00285123A
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English (en)
Inventor
R Simmen
O Chabloz
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mefina SA
Original Assignee
Mefina SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Mefina SA filed Critical Mefina SA
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Publication of US3788229A publication Critical patent/US3788229A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C14/00—Mechanical fuzes characterised by the ammunition class or type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C1/00—Impact fuzes, i.e. fuzes actuated only by ammunition impact
    • F42C1/02—Impact fuzes, i.e. fuzes actuated only by ammunition impact with firing-pin structurally combined with fuze
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/24—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein the safety or arming action is effected by inertia means

Definitions

  • ABSTRACT A fuse provided with two striker-and-detonator systems, one of which operates upon impact against a target and may be manually locked against operation and the other operates only with a predetermined lag after impact.
  • the first system is adapted to be brought in all cases into a ready-for-operation condition at the moment of the firing of the missile, in which condition the member carrying the detonator of the first system is brought within reach of the corresponding striker while it simultaneously releases a safety interceptor extending between the striker and detonator of the system operating with a lag.
  • Fuses for non-gyratory missiles are already known, which include a striker operating upon hitting of the target, a detonator adapted to move from a position for which it is beyond reach of the striker into a position for which it lies across the path of the striker, and a system providing delayed ignition.
  • the delayed ignition system is intended to allow the missile to enter to a more or less considerable extent into the target and possibly into the ground before exploding.
  • the delay is obtained by means of a load of powder inserted between the detonator and the primer and the combustion of which serves for igniting the primer.
  • the delay provided by such arrangements is not uniform and varies in particular with their ageing.
  • the present invention has for its object a fuse the delayed ignition of which is independent of the ageing of the fuse and of the storing conditions provided for said fuse.
  • the improved fuse for non-gyratory missiles is provided in its delayed-ignition system with an auxiliary striker adapted to act with a lag on a second detonator while locking means are adapted to prevent operation of the main striker operating immediately upon impact on the target, if it is desired to delay the explosion of the missile.
  • FIG. I is a longitudinal cross-section of the fuse.
  • FIG. 2 is a fragmentary cross-section through line II-II of FIG. 1.
  • FIG. 3 is a cross-section of a detail through line III- III of FIG. 1.
  • the fuse illustrated includes a casing l the front section of which carries a longitudinally sliding head 2 covered by a readily deformable cap 3 made for instance of plastics.
  • the head 2 is subjected to the action of a spring 4 which urges it against two guiding studs 5 which serve as abutments for the rear ends of the guiding grooves 6 formed in the sliding head 2.
  • a main striker 7 adapted to produce instantaneously ignition of the main detonator up to hitting of the missile against the target,
  • a locking mechanism constituted by a hand-operable rotary member 8 housed inside a bore extending radially through the wall of the casing 1.
  • the outer end of said member 8 is in the shape of a screw head while its inner end forms an arcuate projection 9 which enters, according to the angular position given to the rotary locking member 8, a position either crossing the path of the striker 7 or else a position free of said path.
  • the locking and releasing positions of the locking member 8 are defined by two studs 10 and 11 (FIG. 3) forming abutments for the corresponding ends of the arcuate projection 9.
  • the main striker 7 serves for igniting the missile through action on the detonator ll2 fitted inside a tubular member 13 slidingly carried inside a longitudinal bore 14 formed inside a support 15 fitted in the casing 1.
  • the tubular member 13 is provided with an axial bore 16 leading the flame from the burning detonator towards a safety device 17 the detail of which is not illustrated since it is well known per se.
  • Said safety device is provided with at least one channel connecting, when the missile is cocked, the end of the bore 16 with a primer 18 adapted to ignite the missile.
  • a primer may in fact be fitted inside such a channel in the safety device 17.
  • the sliding tubular member 13 is subjected to the pressure of the spring 19 which urges it forwardly, so as to bring the detonator 12 into the vicinity of the main striker 7, so that it may be hit by the latter immediately the missile impinges on the target.
  • the sliding of the tubular member 13 is prevented by a further locking mechanism constituted by an annulus 20 carrying elastic longitudinally directed tongues 21, the rear free ends of which engage on one side a peripheral groove in the tubular member 13 and, on the other side, a groove in the inner periphery of a sliding sleeve 22 located to the rear of the annulus 20 round the tubular member 113.
  • Said sliding sleeve 22 is normally held with reference to the member 13 in the position illustrated in FIG. 1 by a spring 23.
  • the axial acceleration of the missile causes the sleeve 22 to move rearwardly by reason of its inertia with reference to the body of the missile against the pressure of the spring 23.
  • the sleeve 22 impinges thus against a shoulder 24 formed on the rear end of the tubular member 13, whereby the tongues 21 are released and are shifted downwardly together with the annulus 20 while expanding outwardly, so to move past the peripheral bead 25 at the lower end of the groove in the tubular member 13.
  • the tongues 21 are held in their shifted position to the rear of said peripheral bead 25 by the sleeve 22.
  • tubular member 13 is no longer locked in the position illustrated and can move forwardly inside the missile together with the annulus 20 and the sleeve 22 under the action of the spring 19.
  • the detonator 12 is then within operative reach for the striker 7, provided the arcuate projection 9 is set in the position for which it allows the striker to move.
  • the fuse includes, on the other hand, a delayed ignition system of a mechanical type, which system is housed inside a longitudinal bore 26 parallel with the bore M.
  • This mechanical delayed ignition system forms a structure very similar to the safety mechanism associated with the detonator 12. It includes an auxiliary striker 27 carried by a support 28 subjected to the action of a spring 29 which is normally in a non-tensioned condition. Said support 29 is held in the forward position illustrated by a sleeve 30 and. an annulus 31 provided with elastic longitudinal tongues 32 clamped between the sleeve 30 and the support 28 in a manner similar to that disclosed for the tongues 21 of the safety mechanism illustrated on the right hand side of FIG. 1; the sleeve 30 is subjected similarly to the pressure of a spring 33.
  • the spring 29 acting on the support 28 engages the bottom ofa recess formed in a cylindrical block 34 sliding inside the casing l and provided with a peripheral groove housing an elastic ring 35. Said sliding cylindrical block is urged rearwardly through inertia upon firing of a shot, whereby the spring 29 is stressed. When the cylindrical block has thus receded, the ring 35 expands elastically and moves past the shoulder 36 defining the recess housing the block 34', which latter is thus locked in a position for which the spring 29 remains stressed.
  • the auxiliary striker 27 is adapted to cooperate with an auxiliary detonator 37 the combustion of which produces a flame which starts the ignition of the primer 18 through a second channel in the safety device 17.
  • auxiliary striker 27 When the fuse is at rest, it is impossible for the auxiliary striker 27 to reach the auxiliary detonator 37 since it is held against rearward motion by an interceptor constituted by a pivoting flap 38 clearly shown in FIG. 2. Said flap is subjected to the action ofa spring 39, but it is prevented from moving by a transverse pin 40 slidingly carried in a radial bore formed in the support 15.
  • the locking member 8 is set in the position illustrated, so as to cause the striker, when the missile impinges against the target, to abut against said locking member and to prevent it from reaching the detonator 12.
  • the tubular member 13 carrying the main detonator 12 is released and urged forwardly by the spring 19. During this movement, it releases a stud 4l locking the safety device 17, whereby the channels in the latter are brought into a position for which the primer l8 communicates both with the bore 16 leading to the main detonator l2 and with the auxiliary d etonator 37.
  • the fuse described hereinabove is wholly reliable since it can be cocked only after the shot has been fired and only then can the axial acceleration be sufficiently high and last a sufficiently long time for it to provide for the release of the sliding tubular member 13. As long as the latter has not been shifted, the delayed ignition system cannot operate; in fact, even if the front end of the missile impinges against a hindrance with an energy sufficient for it to release the support 28 of the auxiliary striker 27, the latter cannot reach the auxiliary detonator by reason of the presence of the flap 38, while furthermore the spring 29 is not tensioned.
  • a fuse for a non-gyratory missile the combination of a main striker, a main detonator, means for bringing the detonator into a position within reach of the main striker at the moment of the firing of the missile, said means including'a longitudinally slidable carrier for the main detonator, a spring urging said carrier member towards the main striker, at least one longitudinally shiftable locking member holding said carrier member in an inoperative position and adapted upon firing of the missile to be shifted into a position releasing said carrier member, means causing the main detonator to be struck by the main striker upon impact of the missile against a target, hand operable means insertable between the main striker and the main detonator to thereby prevent said striker from operatively striking said detonator, an auxiliary striker, an auxiliary detonator, means causing said auxiliary striker to strike the auxiliary detonator with a perdetermined time lag after said impact, missile-igniting means actuatable by either
  • a fuse as claimed in claim 1 including an interceptor inserted between the auxiliary striker and the auxiliary detonator, means whereby the slidable carrier member locks said interceptor in its operative position and means controlled by said carrier member when released whereby said interceptor is shifted out of its operative position to allow operation of the means causing the striking of the auxiliary detonator by the auxiliary striker.
  • a fuse as claimed in claim 1 including a pivoting flap extending between the auxiliary striker and the auxiliary detonator, a spring urging said flap into an inoperative position allowing the auxiliary striker to strike the auxiliary detonator, a pin slidable transversely of the fuse and holding the flap in position against the tension of said spring, said means for bringing the detonator within the reach of the main striker including means operable upon firing of the missile to shift the carrier member into a position whereby detonator is within reach of the striker and said carrier member releases the slidable pin to allow operation of the auxiliary striker.
  • said means causing said auxiliary striker to strike the auxiliary detonator includes at least one member adapted to lock the auxiliary striker against movement towards the auxiliary detonator and to be shifted through inertia at the moment of the impact into a position releasing the auxiliary striker and elastic means urging the auxiliary S U'llSQIL V VJI C H released towards the auxiliary detonator.
  • said means causing said auxiliary striker to strike the auxiliary detonator includes at least one member adapted to lock the auxiliary striker against movement towards the auxiliary detonator and to be shifted through inertia at the moment of the impact into a position releasing the auxiliary striker, elastic means urging the auxiliary striker when released towards the auxiliary detonator and a longitudinally slidable block against which said elastic means bear and which is shifted rearwardly at the moment of the firing of the missile to thereby stress said elastic means and provide it with the energy required for the striking of the auxiliary detonator by the auxiliary striker.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Air Bags (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Refuge Islands, Traffic Blockers, Or Guard Fence (AREA)
  • Portable Nailing Machines And Staplers (AREA)
US00285123A 1971-09-10 1972-08-31 Fuse for non-gyratory missiles Expired - Lifetime US3788229A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH1328971A CH539835A (fr) 1971-09-10 1971-09-10 Fusée pour projectile à mouvement non giratoire

Publications (1)

Publication Number Publication Date
US3788229A true US3788229A (en) 1974-01-29

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Family Applications (1)

Application Number Title Priority Date Filing Date
US00285123A Expired - Lifetime US3788229A (en) 1971-09-10 1972-08-31 Fuse for non-gyratory missiles

Country Status (17)

Country Link
US (1) US3788229A (pt)
JP (1) JPS5230800B2 (pt)
AR (1) AR196882A1 (pt)
AT (1) AT324174B (pt)
AU (1) AU473077B2 (pt)
BE (1) BE788201A (pt)
BR (1) BR7205912D0 (pt)
CA (1) CA983313A (pt)
CH (1) CH539835A (pt)
DE (1) DE2242956A1 (pt)
ES (1) ES406525A1 (pt)
FR (1) FR2152028A5 (pt)
GB (1) GB1346703A (pt)
IT (1) IT965169B (pt)
NL (1) NL7212233A (pt)
NO (1) NO133002C (pt)
SE (1) SE396655B (pt)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4230042A (en) * 1978-07-26 1980-10-28 Dragolyoub Popovitch Point-detonating impact fuze
EP2659220A1 (en) * 2010-12-29 2013-11-06 Life Time Engineering Aktiebolag Fuzing system for a submarine signal flare
CN114111470A (zh) * 2021-11-23 2022-03-01 南京理工大学 一种能预防弹道炸的中大口径旋转炮弹弹头机械触发引信

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH664010A5 (fr) * 1985-07-12 1988-01-29 Mefina Sa Fusee pour projectile.
JPS62268816A (ja) * 1986-05-14 1987-11-21 Asahi Chem Ind Co Ltd 吸湿性ポリアミド繊維およびその製造方法

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1863888A (en) * 1929-01-30 1932-06-21 Varaud Andre Fuse for artillery projectiles
US2173620A (en) * 1937-10-19 1939-09-19 Harold M Brayton Combination projectile fuse
US2999461A (en) * 1958-03-28 1961-09-12 Mach Tool Works Oerlikon Impact fuze
US3715987A (en) * 1970-05-14 1973-02-13 Mefina Sa Fuze for a nongyratory projectile

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1863888A (en) * 1929-01-30 1932-06-21 Varaud Andre Fuse for artillery projectiles
US2173620A (en) * 1937-10-19 1939-09-19 Harold M Brayton Combination projectile fuse
US2999461A (en) * 1958-03-28 1961-09-12 Mach Tool Works Oerlikon Impact fuze
US3715987A (en) * 1970-05-14 1973-02-13 Mefina Sa Fuze for a nongyratory projectile

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4230042A (en) * 1978-07-26 1980-10-28 Dragolyoub Popovitch Point-detonating impact fuze
EP2659220A1 (en) * 2010-12-29 2013-11-06 Life Time Engineering Aktiebolag Fuzing system for a submarine signal flare
EP2659220A4 (en) * 2010-12-29 2014-07-09 Life Time Engineering Aktiebolag FIRE SYSTEM FOR UNDERWATER SIGNALING FUSE
CN114111470A (zh) * 2021-11-23 2022-03-01 南京理工大学 一种能预防弹道炸的中大口径旋转炮弹弹头机械触发引信
CN114111470B (zh) * 2021-11-23 2023-04-07 南京理工大学 一种能预防弹道炸的中大口径旋转炮弹弹头机械触发引信

Also Published As

Publication number Publication date
DE2242956A1 (de) 1973-03-15
AT324174B (de) 1975-08-25
JPS4837999A (pt) 1973-06-04
NL7212233A (pt) 1973-03-13
CA983313A (en) 1976-02-10
AR196882A1 (es) 1974-02-28
AU473077B2 (en) 1976-06-10
IT965169B (it) 1974-01-31
BR7205912D0 (pt) 1973-07-26
GB1346703A (en) 1974-02-13
CH539835A (fr) 1973-07-31
SE396655B (sv) 1977-09-26
JPS5230800B2 (pt) 1977-08-10
NO133002B (pt) 1975-11-10
FR2152028A5 (pt) 1973-04-20
AU4630072A (en) 1974-03-14
ES406525A1 (es) 1975-09-01
NO133002C (pt) 1976-02-18
BE788201A (fr) 1972-12-18

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