CA1119886A - Fuse for a rocket projectile - Google Patents
Fuse for a rocket projectileInfo
- Publication number
- CA1119886A CA1119886A CA000331485A CA331485A CA1119886A CA 1119886 A CA1119886 A CA 1119886A CA 000331485 A CA000331485 A CA 000331485A CA 331485 A CA331485 A CA 331485A CA 1119886 A CA1119886 A CA 1119886A
- Authority
- CA
- Canada
- Prior art keywords
- fuse
- projectile
- detonator
- retarding mechanism
- safety
- 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
Links
- 230000000979 retarding effect Effects 0.000 claims abstract description 15
- 238000006073 displacement reaction Methods 0.000 claims abstract description 7
- 230000000903 blocking effect Effects 0.000 claims description 24
- 238000012546 transfer Methods 0.000 claims description 9
- 230000001133 acceleration Effects 0.000 claims description 5
- 239000003380 propellant Substances 0.000 abstract description 5
- 239000007789 gas Substances 0.000 abstract description 3
- 239000002360 explosive Substances 0.000 abstract description 2
- 238000010304 firing Methods 0.000 abstract description 2
- 238000009527 percussion Methods 0.000 description 3
- 230000035939 shock Effects 0.000 description 2
- 208000008103 Amniotic Band Syndrome Diseases 0.000 description 1
- 230000004913 activation Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
Classifications
-
- 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
- F42C15/18—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a carrier for an element of the pyrotechnic or explosive train is moved
- F42C15/184—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a carrier for an element of the pyrotechnic or explosive train is moved using a slidable carrier
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Air Bags (AREA)
Abstract
ABSTRACT
"FUSE FOR A ROCKET PROJECTILE"
Hitherto, an additional explosive charge or the pressure of the rocket propellant gases has been necessary for fuses in rocket projectiles in order to displace a detonator from its safety position into its armed position.
In the fuse according to the invention, an inertial body is present which, on firing of the rocket projectile, drives a retarding mechanism by its inertia. As soon as the retarding mechanism has run down, the detonator can be displaced from its safety position into the armed position and can be secured there against further displacement.
"FUSE FOR A ROCKET PROJECTILE"
Hitherto, an additional explosive charge or the pressure of the rocket propellant gases has been necessary for fuses in rocket projectiles in order to displace a detonator from its safety position into its armed position.
In the fuse according to the invention, an inertial body is present which, on firing of the rocket projectile, drives a retarding mechanism by its inertia. As soon as the retarding mechanism has run down, the detonator can be displaced from its safety position into the armed position and can be secured there against further displacement.
Description
lli98~
" FUSE FOR A ROCKET PROJECT ILE "
The invention relates to a fuse for a rocket project-lle, having a detonator which is fixed on a slider and is dlsplaceable in the axial direction of the projectile from a safety position into an armed position in which the detonator is located next to a transfer charge, and having blocking members and a displaceable safety element for holding the slider in the safety position and for releasing the slider for its displacement into the armed position.
In a known fuse of this type, disclosed in Swiss Patent Specification No. 294,729, an additional explosive charge, or the pressure of the gases from the rocket pro-pellant charge, is required for displacing the safety element. The fuse of the projectile is thus dependent on the rocket propulsion unit which is located immediately behind the projectile. This dependence is a disadvantage, ln particular if lt is not possible to arrange the rocket propulsion unit lmmediately behind the projectile. The known fuse also has the disadvantage that the activation of the slider takes place when the rocket propellant charge begins to burn off, that is to say at the start of the trajectory. Admittedly, the slider re~ains in the safety position under the action of the inertial force which is effective up to the end of burning of the propellant charge, but in the case of malfunctioning of the propulsion unit, for example if the propulsion unit becomes extinguished within the safety zone in the forefield, the slider wlll pass into the armed position immediately after acceleration ceases.
The object of the present invention is the provision o~ a fuse which does not re~uire any gas pressure from the rocket motor to displace the detonator into its armed pos~tion and ln which the slider does not pass into the armed position when the acceleration of the projectile ceases within the safety zone in the forefield.
To achieve this object, in the fuse according to the invention the safety element comprises an inertial body ~988~;
which, on acceleration of the projectile, is displaceable against the force of a spring in order to drive a retarding mechanlsm and release the blocking members after the retard~ng mechanism has run down, and, in the safety pos-ition thereof, the detonator is located in front of thetransfer charge.
An illustrative embodiment of the fuse according to the invention is described in detail in the following text by reference to the attached drawing in which:
Figure 1 shows a longitudinal section through a hollow-charge project1le having a rocket drive;
Figure 2 shows a longitudinal section through the rear fuse of the hollow-charge projectile in its safe transport positlon, on an enlarged ~cale;
lS Figure 3 shows a cross-section along line III-III in Figure 2;
Figure 4 shows a cross-section along line IV-IV ln Flgure 2;
Figure S shows the same as Figure 2, but simplified and immedlately before armlng;
Figure 6 shows the same as Flgure 5, but already armed;
and Figure 7 shows the same as Figure 5, but armed and blocked.
As shown in Figure 1, the projectile in which the fuse 1 according to the invention is located, has a case 2 on which a cartridge-like attachment 3 is fixed, to receive the fuse 1. A hollow charge 4 is located in the interlor of the case 2. A percussion fuse la is fitted on the tip of the projectile. This percussion fuse la is presumed to be known and ls therefore not described in greater detail.
The fuse 1 located in the attachment 3 partly protrudes into the interior of the hollow charge 4. The projectile has a rocket drive which is visible in Figure 1 but which is not described in more detail since it does not form part of the 11~9886 subject of the invention.
As shown in Figure 2, the fuse 1 has a casing which ls formed by a cartridge 5, a cartridge base 6 and a guide piece 7. The casing 5, 6 and 7 is sub-divided into two S chambers by a disc 8. A transfer charge 10 is present in the front chamber. The disc 8 and $he transfer charge 10 are supported on a drilled shoulder 9 of.~he cartrldge 5, which has orlfices 12 through which the chamber and the transfer charge 10 are connected to the interior of the case
" FUSE FOR A ROCKET PROJECT ILE "
The invention relates to a fuse for a rocket project-lle, having a detonator which is fixed on a slider and is dlsplaceable in the axial direction of the projectile from a safety position into an armed position in which the detonator is located next to a transfer charge, and having blocking members and a displaceable safety element for holding the slider in the safety position and for releasing the slider for its displacement into the armed position.
In a known fuse of this type, disclosed in Swiss Patent Specification No. 294,729, an additional explosive charge, or the pressure of the gases from the rocket pro-pellant charge, is required for displacing the safety element. The fuse of the projectile is thus dependent on the rocket propulsion unit which is located immediately behind the projectile. This dependence is a disadvantage, ln particular if lt is not possible to arrange the rocket propulsion unit lmmediately behind the projectile. The known fuse also has the disadvantage that the activation of the slider takes place when the rocket propellant charge begins to burn off, that is to say at the start of the trajectory. Admittedly, the slider re~ains in the safety position under the action of the inertial force which is effective up to the end of burning of the propellant charge, but in the case of malfunctioning of the propulsion unit, for example if the propulsion unit becomes extinguished within the safety zone in the forefield, the slider wlll pass into the armed position immediately after acceleration ceases.
The object of the present invention is the provision o~ a fuse which does not re~uire any gas pressure from the rocket motor to displace the detonator into its armed pos~tion and ln which the slider does not pass into the armed position when the acceleration of the projectile ceases within the safety zone in the forefield.
To achieve this object, in the fuse according to the invention the safety element comprises an inertial body ~988~;
which, on acceleration of the projectile, is displaceable against the force of a spring in order to drive a retarding mechanlsm and release the blocking members after the retard~ng mechanism has run down, and, in the safety pos-ition thereof, the detonator is located in front of thetransfer charge.
An illustrative embodiment of the fuse according to the invention is described in detail in the following text by reference to the attached drawing in which:
Figure 1 shows a longitudinal section through a hollow-charge project1le having a rocket drive;
Figure 2 shows a longitudinal section through the rear fuse of the hollow-charge projectile in its safe transport positlon, on an enlarged ~cale;
lS Figure 3 shows a cross-section along line III-III in Figure 2;
Figure 4 shows a cross-section along line IV-IV ln Flgure 2;
Figure S shows the same as Figure 2, but simplified and immedlately before armlng;
Figure 6 shows the same as Flgure 5, but already armed;
and Figure 7 shows the same as Figure 5, but armed and blocked.
As shown in Figure 1, the projectile in which the fuse 1 according to the invention is located, has a case 2 on which a cartridge-like attachment 3 is fixed, to receive the fuse 1. A hollow charge 4 is located in the interlor of the case 2. A percussion fuse la is fitted on the tip of the projectile. This percussion fuse la is presumed to be known and ls therefore not described in greater detail.
The fuse 1 located in the attachment 3 partly protrudes into the interior of the hollow charge 4. The projectile has a rocket drive which is visible in Figure 1 but which is not described in more detail since it does not form part of the 11~9886 subject of the invention.
As shown in Figure 2, the fuse 1 has a casing which ls formed by a cartridge 5, a cartridge base 6 and a guide piece 7. The casing 5, 6 and 7 is sub-divided into two S chambers by a disc 8. A transfer charge 10 is present in the front chamber. The disc 8 and $he transfer charge 10 are supported on a drilled shoulder 9 of.~he cartrldge 5, which has orlfices 12 through which the chamber and the transfer charge 10 are connected to the interior of the case
2 in which the hollow charge 4 is located. The rear cha~ber of the casing 5, 6 and 7 contains a displaceable inertial body 13 and a bolt 14, which is arranged parallel to the axis of the cartridge and which, according to Figures 2 and 4, protrudes through a bore 16 of the inertial body 13.
The front part of the bolt 14 has a smaller diameter than the rear part which has the form of a rack 15. A spring 17 which surrounds the front part of the bolt 14 is backed up on one side on a should'er 19 of the bolt 14 and on the other side on a wall 18 of the inertial body 13. This spring 17 tends to push the inertial body 13 against the disc 8 and to push the bolt 14 against the cartridge base 6.
As shown in Figure 4, the inertial body 13 has a longitudinal groove 20 which ls parallel to the axis of the cartridge 5 and ln which a retarding mechanism 1~ located.
This retarding mechanism comprises a rotatably mounted, toothed flutter body 21 (Figure 2) which can be driven by a pinlon 22 (Figure 4) vla a form-ground gear 23 and a number of gears (Figure 2) not marked ln more detall. The pinion 22 engages with the rack 15 of the bolt 14 S9 that the flutter body 21 i5 driven via the pinion 22 and the gears mentloned when the lnertial body 13 is displaced relative to the bolt 14. The complete retardlng mechanism ls mounted within the inertial body, A cap carrler 24 (Figure 2) r which is composed of a flange 25 and a cylindrical part 26, protrudes into a central bore 11 of the guide body 7. In the position shown, the flange 25 makes contact on one side with the rear side of the disc 8 and on the other side with the front face of the inertial body 13.
At its rear end, the cap carrier 24 has a central bore 27, the longitudinal axis of which coincides with the long-ltudinal axis of the cartridge 5. A control bolt 28 which protrudes into the said central bore 27 of the cap carrier 24 is fixed to the inertial body 13. The control bolt 28 consists of a front part 28b of a smaller diameter than that of the rear part 28a. The two parts 28a and 28b are joined to one another by a part 29 in the shape of a truncated cone.
At the front end of the cylindrical part 26 of the cap carrier 24, there is a detonator cap 32 - with an open front - ln a thin-walled cartridge 33 which protrudes into the conlcal shape of the hollow charge 4 (Figure 1). In the transport po~ition'shown, the detonator cap 32 is in the interior of the guide piece in front of the transfer charge 10.
As wlll be seen ln Figure 3, the flange 25 of the cap carrier has three radially pointing bores 30, the three angles between these three bores30 being equal. In each of these bores 30, there is one blocking bolt 31, the outer ends of these blocking bolts each having a head 31a in the shape of a truncated cone. These blocking bolts 31 are dlsplaceable and are supported on the said control bolt 28.
The flange 25 also has abore 34 which is parallel to the axis of the casing and into which the front end of the said bolt 14 protrudes.
Behind the disc 8, the inner wall of the cartrldge 5 has an annular grooye 36 which i~ delimited at the bottom by a conical surface 35. Below this conical surface 35, there are three bore sectlons 37, 39 and 38, of which the upper bore section 37 has a smaller diameter than the central bore section 39 and the central bore section 39 has a smaller diameter than the lower bore séction 38 This lower bore section is delimited by two conical surfaces 38a and 38b, and the central bore section 39 is delimited at the top by a conical surface 39a.
As shown in Figure 2, the heads 31a of the blocking bolts 31 protrude into the annular groove 36 and the inner end of the blocking bolts 31 is supported on the thicker part 28a of the control bolt 28. In Figure 6, the heads 31a of the blocking bolts 31 are in the lower bore section 38 and the inner end of the blocking bolts 31 can likewise be supported on the thicker part 28a of the control bolt 28. However, lf the heads 31a of the bolts 31 are in the central bore section 39, the blocking bolts 31 can only be lS supported on the thinner part;28b of the control bolt;
and if the heads 31a of the bolts 31 are ln the upper bore section 37, the blocking bolts 31 cannot then be supported on either of the two p~rts 28a and 28b of the control bolt 28.
The mode of action of the fuse described is as follows:
In the transport positio~ of the fuse before the projectile ig fired, the spr1ng 17 tends to push the inert- ¦
ial body 13 and the cap carrier 24 into their frontmost position ~hown in Figure 2. ~he heads of the blocking bodies - 25 31 protrude into the annular groov~ 36 and are held ln this position by the thicker part ~8a of the control bolt. The pinion 22 of the retarding mechanism engages with the upper end of the rack 15.
In the case of shocks during transport of the project-ile, the inertial body 13 can be displaced by small amounts.
The retarding mechanism, however, prevents larger displace-- ments of the inertial body due to its resistance. It is therefore not possible for the blocking bodies 31 to come out of the annular groove 36 since, during transport, they are contin~ously ln contact with the thlcker end ~8a of the 1119~8~
control bolt 28. In the case of a possible displacement due to transport shocks, the spring 17 will lmmediately return the inertlal body 13 back into its starting position.
Even if the blocking bolts 31 are supported on the thinner part 28b of the control bolt 28, the heads 31a of the blocking bolts cannot come out of the annular groove 36 and the cap carrier 24 is thus held in its frontmost pos-ition. The detonator cap 32 is therefore in its safety position and not in the zone of the transfer charge 10.
On firing the projectile and during its acceleration after the rocket propellant charge has been ignited, an inertlal force acts on the inertial body 13, and this force tends to push the inertial body to the rear against the force of the spring 17 and against the braking action of the retarding mechanism. This displacement is, however, strongly slowed down by the retarding mechanism.
The control bolt 28 has such a length that the block-ing bolts 31 are released only when the retarding mechanism has fully run down, that ls to say when the pinion 22 is at the lower end of the rack 15, as shown in Figure 5. As soon as the pinion 22 has reached the lower end of the rack 15, the braking action of the retarding mechanism ceases and the inertial body 13 suddenly passes into its rearmost position shown in Figure 6. In this rearmost position of the inertial body 13, the blocking bolts 31 are no longer underplnned ~y the control bolt 28 and are thus pushed radlally lnwards by the conical surface 35 in the bores 30 o~ the flange 25. The cap carrier 24 can, under the action of the said inertial force, likewise be displaced lnto the position shown in Figure 6. ~he blocking bolts 31 are then again in contact with the thicker part 28a of the control bolt 28 and the heads 31a of the blocking bolts 31 thus protrude into the bore section 38, as a result of which the cap carrier 24 is secured in its armed position and can no longer be d1splaced forward, Th1s 1s prevented by the 1119~386 spring 17 which presses the inertial body 13 against the flange 25 of the cap carrier 24. At the same time, the thicker part 28a of the control bolt 28 remains in the zone of the blocking bolts 31 (Flgure 7).
~hen the projectile hits a target, the percussion fuse la is ignited causing the detonator cap 32 of the rear fuse 1 to respond. The detonator cap in turn ignites the trans-fer charge 10 and the latter ignites the hollow charge 4.
The truncated conical part 29 of the control bolt 28 has the effect that, on displacement of the cap carrier 24 from its safety position into i~s armed position according to Figure 6, the heads 31a of the blocking bolts 31 pass behind the conical surface 38b and the cap carrier 24 is thus secured ln its armed position.
.
The front part of the bolt 14 has a smaller diameter than the rear part which has the form of a rack 15. A spring 17 which surrounds the front part of the bolt 14 is backed up on one side on a should'er 19 of the bolt 14 and on the other side on a wall 18 of the inertial body 13. This spring 17 tends to push the inertial body 13 against the disc 8 and to push the bolt 14 against the cartridge base 6.
As shown in Figure 4, the inertial body 13 has a longitudinal groove 20 which ls parallel to the axis of the cartridge 5 and ln which a retarding mechanism 1~ located.
This retarding mechanism comprises a rotatably mounted, toothed flutter body 21 (Figure 2) which can be driven by a pinlon 22 (Figure 4) vla a form-ground gear 23 and a number of gears (Figure 2) not marked ln more detall. The pinion 22 engages with the rack 15 of the bolt 14 S9 that the flutter body 21 i5 driven via the pinion 22 and the gears mentloned when the lnertial body 13 is displaced relative to the bolt 14. The complete retardlng mechanism ls mounted within the inertial body, A cap carrler 24 (Figure 2) r which is composed of a flange 25 and a cylindrical part 26, protrudes into a central bore 11 of the guide body 7. In the position shown, the flange 25 makes contact on one side with the rear side of the disc 8 and on the other side with the front face of the inertial body 13.
At its rear end, the cap carrier 24 has a central bore 27, the longitudinal axis of which coincides with the long-ltudinal axis of the cartridge 5. A control bolt 28 which protrudes into the said central bore 27 of the cap carrier 24 is fixed to the inertial body 13. The control bolt 28 consists of a front part 28b of a smaller diameter than that of the rear part 28a. The two parts 28a and 28b are joined to one another by a part 29 in the shape of a truncated cone.
At the front end of the cylindrical part 26 of the cap carrier 24, there is a detonator cap 32 - with an open front - ln a thin-walled cartridge 33 which protrudes into the conlcal shape of the hollow charge 4 (Figure 1). In the transport po~ition'shown, the detonator cap 32 is in the interior of the guide piece in front of the transfer charge 10.
As wlll be seen ln Figure 3, the flange 25 of the cap carrier has three radially pointing bores 30, the three angles between these three bores30 being equal. In each of these bores 30, there is one blocking bolt 31, the outer ends of these blocking bolts each having a head 31a in the shape of a truncated cone. These blocking bolts 31 are dlsplaceable and are supported on the said control bolt 28.
The flange 25 also has abore 34 which is parallel to the axis of the casing and into which the front end of the said bolt 14 protrudes.
Behind the disc 8, the inner wall of the cartrldge 5 has an annular grooye 36 which i~ delimited at the bottom by a conical surface 35. Below this conical surface 35, there are three bore sectlons 37, 39 and 38, of which the upper bore section 37 has a smaller diameter than the central bore section 39 and the central bore section 39 has a smaller diameter than the lower bore séction 38 This lower bore section is delimited by two conical surfaces 38a and 38b, and the central bore section 39 is delimited at the top by a conical surface 39a.
As shown in Figure 2, the heads 31a of the blocking bolts 31 protrude into the annular groove 36 and the inner end of the blocking bolts 31 is supported on the thicker part 28a of the control bolt 28. In Figure 6, the heads 31a of the blocking bolts 31 are in the lower bore section 38 and the inner end of the blocking bolts 31 can likewise be supported on the thicker part 28a of the control bolt 28. However, lf the heads 31a of the bolts 31 are in the central bore section 39, the blocking bolts 31 can only be lS supported on the thinner part;28b of the control bolt;
and if the heads 31a of the bolts 31 are ln the upper bore section 37, the blocking bolts 31 cannot then be supported on either of the two p~rts 28a and 28b of the control bolt 28.
The mode of action of the fuse described is as follows:
In the transport positio~ of the fuse before the projectile ig fired, the spr1ng 17 tends to push the inert- ¦
ial body 13 and the cap carrier 24 into their frontmost position ~hown in Figure 2. ~he heads of the blocking bodies - 25 31 protrude into the annular groov~ 36 and are held ln this position by the thicker part ~8a of the control bolt. The pinion 22 of the retarding mechanism engages with the upper end of the rack 15.
In the case of shocks during transport of the project-ile, the inertial body 13 can be displaced by small amounts.
The retarding mechanism, however, prevents larger displace-- ments of the inertial body due to its resistance. It is therefore not possible for the blocking bodies 31 to come out of the annular groove 36 since, during transport, they are contin~ously ln contact with the thlcker end ~8a of the 1119~8~
control bolt 28. In the case of a possible displacement due to transport shocks, the spring 17 will lmmediately return the inertlal body 13 back into its starting position.
Even if the blocking bolts 31 are supported on the thinner part 28b of the control bolt 28, the heads 31a of the blocking bolts cannot come out of the annular groove 36 and the cap carrier 24 is thus held in its frontmost pos-ition. The detonator cap 32 is therefore in its safety position and not in the zone of the transfer charge 10.
On firing the projectile and during its acceleration after the rocket propellant charge has been ignited, an inertlal force acts on the inertial body 13, and this force tends to push the inertial body to the rear against the force of the spring 17 and against the braking action of the retarding mechanism. This displacement is, however, strongly slowed down by the retarding mechanism.
The control bolt 28 has such a length that the block-ing bolts 31 are released only when the retarding mechanism has fully run down, that ls to say when the pinion 22 is at the lower end of the rack 15, as shown in Figure 5. As soon as the pinion 22 has reached the lower end of the rack 15, the braking action of the retarding mechanism ceases and the inertial body 13 suddenly passes into its rearmost position shown in Figure 6. In this rearmost position of the inertial body 13, the blocking bolts 31 are no longer underplnned ~y the control bolt 28 and are thus pushed radlally lnwards by the conical surface 35 in the bores 30 o~ the flange 25. The cap carrier 24 can, under the action of the said inertial force, likewise be displaced lnto the position shown in Figure 6. ~he blocking bolts 31 are then again in contact with the thicker part 28a of the control bolt 28 and the heads 31a of the blocking bolts 31 thus protrude into the bore section 38, as a result of which the cap carrier 24 is secured in its armed position and can no longer be d1splaced forward, Th1s 1s prevented by the 1119~386 spring 17 which presses the inertial body 13 against the flange 25 of the cap carrier 24. At the same time, the thicker part 28a of the control bolt 28 remains in the zone of the blocking bolts 31 (Flgure 7).
~hen the projectile hits a target, the percussion fuse la is ignited causing the detonator cap 32 of the rear fuse 1 to respond. The detonator cap in turn ignites the trans-fer charge 10 and the latter ignites the hollow charge 4.
The truncated conical part 29 of the control bolt 28 has the effect that, on displacement of the cap carrier 24 from its safety position into i~s armed position according to Figure 6, the heads 31a of the blocking bolts 31 pass behind the conical surface 38b and the cap carrier 24 is thus secured ln its armed position.
.
Claims (4)
PROPERTY OR PRIVILEGE IS CLAIMED ARE DEFINED AS FOLLOWS:
1. A fuse for a rocket projectile, having a detonator which is fixed on a slider and is displaceable in the axial direction of the projectile from a safety position into an armed position in which the detonator is located next to a transfer charge, and having blocking members and a displaceable safety element for holding the slider in the safety position and for releasing the slider for its displacement into the armed position, wherein the safety element comprises an inertial body which, on acceleration of the projectile, is displaceable against the force of a spring in order to drive a retarding mechanism and to release the blocking members after the retarding mechanism has run down, and wherein, in the safety position thereof, the detonator is located in front of the transfer charge.
2. A fuse according to Claim 1, wherein the inertial body has a stepped bolt which consists of a thick part and a thin part, and the blocking members are held by both parts of the bolt when in the safety position, and only by the thick part when in the armed position.
3. A fuse according to Claim 1 or 2, wherein the retarding mechanism comprises a flutter body and a toothed gearing and can be driven via a displaceable rack.
4. A fuse according to Claim 1 or 2, wherein the retarding mechanism comprises a flutter body and a toothed gearing and can be driven via a rack which is held in the fuse casing and the inertial body contains the toothed gearing and the flutter body.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CH8113/78-2 | 1978-07-28 | ||
| CH811378A CH633367A5 (en) | 1978-07-28 | 1978-07-28 | IGNITION DEVICE FOR A ROCKET BULLET. |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1119886A true CA1119886A (en) | 1982-03-16 |
Family
ID=4335374
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000331485A Expired CA1119886A (en) | 1978-07-28 | 1979-07-10 | Fuse for a rocket projectile |
Country Status (5)
| Country | Link |
|---|---|
| JP (1) | JPS5520395A (en) |
| CA (1) | CA1119886A (en) |
| CH (1) | CH633367A5 (en) |
| GB (1) | GB2026654B (en) |
| IT (1) | IT1122629B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3441385A1 (en) * | 1984-11-13 | 1986-05-22 | Gebrüder Junghans GmbH, 7230 Schramberg | IGNITION SYSTEM FOR STEERING UNITS AND ROCKET BULLETS |
-
1978
- 1978-07-28 CH CH811378A patent/CH633367A5/en not_active IP Right Cessation
-
1979
- 1979-07-10 CA CA000331485A patent/CA1119886A/en not_active Expired
- 1979-07-12 GB GB7924293A patent/GB2026654B/en not_active Expired
- 1979-07-19 IT IT24480/79A patent/IT1122629B/en active
- 1979-07-26 JP JP9433479A patent/JPS5520395A/en active Pending
Also Published As
| Publication number | Publication date |
|---|---|
| GB2026654A (en) | 1980-02-06 |
| JPS5520395A (en) | 1980-02-13 |
| GB2026654B (en) | 1983-01-12 |
| IT7924480A0 (en) | 1979-07-19 |
| CH633367A5 (en) | 1982-11-30 |
| IT1122629B (en) | 1986-04-23 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MKEX | Expiry |