Fuze including safety element (30) includes an acceleration detector (31) that acts on a timer (32) coacting with a primer housing rotor (14). Rotation of the rotor can be halted by a second safety device (35) responsive to the dynamic pressure generated by the speed of the projectile (11) in flight
Fuze including safety element (30) includes an acceleration detector (31) that acts on a timer (32) coacting with a primer housing rotor (14). Rotation of the rotor can be halted by a second safety device (35) responsive to the dynamic pressure generated by the speed of the projectile (11) in flight. For this purpose, the device includes a diaphragm (36) engaging a flexible blade (51) to space apart the end (55) of the blade and the rotor when the dynamic pressure has a predetermined value, whereby a primer (18) can be moved into line in the explosive train. When the dynamic pressure is too low, the end (55) stops the rotor (14) from rotating and the firing procedure is also blocked in a notch in the rotor (14). The resulting fuze thus has highly reliable dual safety element responsive to two separate physical phenomena and having a simple construction.
대표청구항▼
The invention claimed is: 1. A missile fuse, comprising: an ignition device (12); and a security means (30), intended to enable ignition of a missile only under predetermined conditions, including a detection device (35) configured i) to be sensitive to a dynamic air pressure arising at the missile
The invention claimed is: 1. A missile fuse, comprising: an ignition device (12); and a security means (30), intended to enable ignition of a missile only under predetermined conditions, including a detection device (35) configured i) to be sensitive to a dynamic air pressure arising at the missile (11) in flight, and ii) to enable the ignition of the missile when the dynamic pressure attains a predetermined value of dynamic pressure corresponding to a given speed of the missile, and further configured to prevent the ignition of the missile when the dynamic pressure does not attain the predetermined pressure value, wherein the detection device comprises a detector element (36) configured to be, under the influence of the dynamic air pressure, any of displaced and deformed, so as to enable the ignition of the missile if the dynamic pressure attains the predetermined value, and to prevent the ignition of the missile if the dynamic pressure does not attain the predetermined pressure value, wherein the detector element (36, 50) cooperates with a mobile mechanical element (14), the mobile mechanical element (14) configured to be displaceable from an initial position to an ignition position after launch of the missile, the detector element (36, 50) being configured i) to prevent the mobile mechanical element (14) from being displaced to the ignition position when the value of dynamic pressure is not attained, and ii) to move away from the mobile mechanical element, and thereby not prevent the mobile mechanical element (14) from being displaced to the ignition position, when the value of dynamic pressure is attained, wherein the mobile mechanical element consists of a detonator rotor (14), a periphery of the detonator rotor (14) being configured to cooperate with a section (55) of a flexible blade (51), and wherein the periphery of the detonator rotor (14) comprises i) a first retaining element (62) preventing rotation of the rotor to the ignition position when the section (55) is not lifted from the periphery, and ii) a second retaining element (63, 64) configured to prevent the flexible blade (51) from moving away from the periphery when the rotation of rotor (14) has been prevented by the flexible blade (51). 2. The fuse according to claim 1, wherein the detector element (36, 50) is configured to occupy either of a rest position and the ignition-enabling position, wherein the security means (30) are configured to definitively prevent the detector element (36, 50) from occupying the ignition-enable position when the value of dynamic pressure is not attained after a predetermined period of time counted from missile launch. 3. The fuse according to claim 1, wherein the detector element (36) is housed in a chamber (37) of the fuse and linked by a channel (40) to a hole (41) situated in a front section (42) of the fuse, and wherein the detector element comprises a transmission element (50) configured i) to enable the ignition and ii) to interrupt an ignition process. 4. The fuse according to claim 3, wherein the detector element further comprises an elastic membrane (36, 50) having borders, the borders of the elastic membrane being retained in said chamber (37), and wherein the elastic membrane is configured to curve in under the dynamic pressure and to act on said transmission element (50) so as to deform and/or displace a flexible blade (51) of the transmission element to enable the ignition. 5. The fuse according to claim 1, further comprising: an acceleration detector (31) configured to block the ignition device (12) when an acceleration of the missile is less than a predetermined acceleration value, and to release the ignition device and initiate an ignition procedure when the acceleration is equal or greater than the predetermined acceleration value. 6. The fuse according to claim 5, further comprising: a delay element (32), wherein the acceleration detector (31) is configured to cooperate with the delay element (32), and the delay element is configured to control the ignition procedure and the rotation of the detonator rotor (14). 7. The fuse according to claim 3, further comprising: a plug (47) in a first section (45) of said channel (40), wherein the plug, in a first mode, is in a first section (45) of said channel (40), closing off said channel (40), and wherein the plug is displaceable by the dynamic pressure to be in a second section (46) of the channel in a second mode, said channel not closed off by the plug in the second mode. 8. A missile fuse, comprising: an ignition device (12); and a security means (30), intended to enable ignition of a missile only under predetermined conditions, including a detection device (35) configured i) to be sensitive to a dynamic air pressure arising at the missile (11) in flight, and ii) to enable ignition of the missile when the dynamic pressure attains a predetermined value of dynamic pressure corresponding to a given speed of the missile, and further configured to prevent ignition of the missile when the dynamic pressure does not attain the predetermined pressure value, wherein the detection device comprises a detector element (36) configured to be, under the influence of the dynamic air pressure, any of displaced and deformed, so as to enable ignition if the dynamic pressure attains the predetermined value, and to prevent ignition if the dynamic pressure does not attain the predetermined pressure value, wherein the detector element (36, 50) is configured to occupy either of a rest position and an ignition-enabling position, wherein the security means (30) are configured to definitively prevent the detector element (36, 50) from occupying the ignition-enabling position when the value of dynamic pressure is not attained after a predetermined period of time counted from missile launch, and wherein the detector element (36, 50) cooperates with a mobile mechanical element (14), the mobile mechanical element (14) configured to be displaceable from an initial position to an ignition position after launch of the missile, the detector element (36, 50) being configured i) to prevent the mobile mechanical element (14) from being displaced to the ignition position when the value of dynamic pressure is not attained, and ii) to move away from the mobile mechanical element, and thereby not prevent the mobile mechanical element (14) from being displaced to the ignition position, when the value of dynamic pressure is attained. 9. The fuse according to claim 8, wherein the detector element (36) is housed in a chamber (37) of the fuse and linked by a channel (40) to a hole (41) situated in a front section (42) of the fuse, and wherein the detector element comprises a transmission element (50) configured i) to enable the ignition and ii) to interrupt an ignition process. 10. The fuse according to claim 9, wherein the detector element further comprises an elastic membrane (36, 50) having borders, the borders of the elastic membrane being retained in said chamber (37), and wherein the elastic membrane is configured to curve in under the dynamic pressure and to act on said transmission element (50) so as to deform and/or displace a flexible blade (51) of the transmission element to enable the ignition. 11. The fuse according to claim 9, further comprising: a plug (47) in a first section (45) of said channel (40), wherein the plug, in a first mode, is in a first section (45) of said channel (40), closing off said channel (40), and wherein the plug is displaceable by the dynamic pressure to be in a second section (46) of the channel in a second mode, said channel not closed off by the plug in the second mode. 12. The fuse according to claim 8, further comprising: an acceleration detector (31) configured to block the ignition device (12) when an acceleration of the missile is less than a predetermined acceleration value, and to release the ignition device and initiate an ignition procedure when the acceleration is equal or greater than the predetermined acceleration value. 13. The fuse according to claim 12, further comprising: a delay element (32), wherein the acceleration detector (31) is configured to cooperate with the delay element (32), and the delay element is configured to control the ignition procedure and the rotation of the detonator rotor (14). 14. A missile fuse, comprising: an ignition device (12); and a security means (30) , intended to enable ignition of a missile only under predetermined conditions, including a detection device (35) configured i) to be sensitive to a dynamic air pressure arising at the missile (11) in flight, and ii) to enable ignition of the missile when the dynamic pressure attains a predetermined value of dynamic pressure corresponding to a given speed of the missile, and further configured to prevent ignition of the missile when the dynamic pressure does not attain the predetermined pressure value, wherein the detection device comprises a detector element (36) configured to be, under the influence of the dynamic air pressure, any of displaced and deformed, so as to enable ignition if the dynamic pressure attains the predetermined value, and to prevent ignition if the dynamic pressure does not attain the predetermined pressure value, and wherein the detector element (36) is housed in a chamber (37) of the fuse and linked by a channel (40) to a hole (41) situated in a front section (42) of the fuse, wherein the detector element comprises a transmission element (50) configured i) to enable ignition and ii) to interrupt an ignition process, and wherein the detector element (36, 50) cooperates with a mobile mechanical element (14), the mobile mechanical element (14) configured to be displaceable from an initial position to an ignition-enabling position after launch of the missile, the detector element (36, 50) being configured i) to prevent the mobile mechanical element (14) from being displaced to the ignition position when the value of dynamic pressure is not attained, and ii) to move away from the mobile mechanical element, and thereby not prevent the mobile mechanical element (14) from being displaced to the ignition position, when the value of dynamic pressure is attained. 15. The fuse according to claim 14, wherein the detector element further comprises an elastic membrane (36, 50) having borders, the borders of the elastic membrane being retained in said chamber (37), and wherein the elastic membrane is configured to curve in under the dynamic pressure and to act on said transmission element (50) so as to deform and/or displace a flexible blade (51) of the transmission element to enable the ignition. 16. The fuse according to claim 14, further comprising; a plug (47) in a first section (45) of said channel (40), wherein the plug, in a first mode, is lit a first section (45) of said channel (40), closing off said channel (40), and wherein the plug is displaceable by the dynamic pressure to be in a second section (46) of the channel in a second mode, said channel not closed off by the plug in the second mode. 17. The fuse according to claim 14, further comprising: an acceleration detector (31) configured to block the ignition device (12) when an acceleration of the missile is less than a predetermined acceleration value, and to release the ignition device and initiate an ignition procedure when the acceleration is equal or greater than the predetermined acceleration value. 18. The fuse according to claim 17, further comprising: a delay element (32), wherein the acceleration detector (31) is configured to cooperate with the delay element (32), and the delay element is configured to control the ignition procedure and the rotation of the detonator rotor (14).
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이 특허에 인용된 특허 (6)
O\Steen James K. (Olney MD), Air driven energy storing fuze safing and arming mechanism.
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