EP1212579A1 - Electronic time-fuse for a projectile - Google Patents
Electronic time-fuse for a projectileInfo
- Publication number
- EP1212579A1 EP1212579A1 EP00956486A EP00956486A EP1212579A1 EP 1212579 A1 EP1212579 A1 EP 1212579A1 EP 00956486 A EP00956486 A EP 00956486A EP 00956486 A EP00956486 A EP 00956486A EP 1212579 A1 EP1212579 A1 EP 1212579A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- input
- electronic
- programming
- projectile
- time
- 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.)
- Granted
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
- F42C11/00—Electric fuzes
- F42C11/06—Electric fuzes with time delay by electric circuitry
- F42C11/065—Programmable electronic delay initiators in projectiles
Definitions
- the present invention relates to an electronic projectile time fuse according to the preamble of claim 1.
- a fuse can e.g. can be taken from DE 42 40 263 Cl.
- modern electronic detonators preferably use batteries for energy supply, which are only mechanically and chemically activated by the high accelerations that occur when a projectile is fired.
- This has the advantage that igniters equipped in this way do not require any maintenance with regard to replacement, e.g. an otherwise used battery primary cell because these batteries are completely passive during storage and therefore allow long storage times.
- the projectile detonators equipped with them are therefore cheaper in terms of the detonator structure, the running time costs and the logistics than comparable detonators, e.g. are equipped with primary cells.
- Timers of this type which generally have no impact function for reasons of overflight safety, are used to initiate the dismantling of a cargo projectile that emits submunition. Since, especially in the case of use in artillery, such troops are also to be used to overshoot their own troops, the requirements with regard to security against premature disassembly (overflight security) are generally very high. Known numbers for the maximum permitted probability of premature disassembly are between 10 "5 and 10 " 6 . In order to be able to achieve such values, several measures are usually taken in the igniter electronics.
- the possibly incorrect (too early) time of dismantling a projectile does not only depend on potential influences during the flight, but can also result from an incorrect fire command, incorrect programming of the igniter runtime and incorrect start of the igniter runtime in the igniter.
- the first two cases cannot be corrected by measures in the detonator and should not be considered further here.
- the latter case of the faulty (too early) start of the igniter runtime is the starting point for the proposed improvement with regard to overflight safety.
- the activatable batteries used must be designed so that they reliably activate in the entire temperature range even with the smallest propellant charge when fired. On the other hand, they must be subjected to mechanical loads
- the detonator starts with the execution of the mission program, ie the start of the runtime, loading of the ignition circuits and ignition, with the usual electronic design.
- the projectile Before firing, in the pipe and at a defined distance in front of the pipe (security of the pipe), the projectile is generally prevented from igniting by a mechanical (or electronic) safety device.
- This safety device is designed so that unintentional (mechanical-pyrotechnic) unlocking processes can only occur with a very low probability (10 7 and less).
- the ignition means are in the ignition position and contacted. If an ignition now takes place, the bullet is disassembled. If the run time is correctly started by the shot, the disassembly takes place in the intended target area.
- the unintentional earlier start of the runtime function can occur, especially in the case of a defective battery, as a result of the acceleration processes when the projectile is being charged (attached). It can be assumed that an activation of the battery during the charging process cannot be excluded with a probability of 10 "5 to 10 " 6 .
- the described safety problems caused by web breakers may be due to the relatively long times between attaching the bullet (possibility of faulty battery activation) and firing due to the inhibiting effect the safety device has been reduced. If the time between the attachment of the projectile and the firing of the projectile is longer than the programmed flight time, the electrical ignition means ignites in the tube and further ignition is then prevented by the securing device being secured. However, new guns introduced today are automatically loaded and fired. Here, the time processes are shorter, ie the times between the automatic application of the projectile and the firing are shorter or comparable to the set ignition times. On guns of this type, the probability of web breakers is therefore increased for electronic time detonators (with an activatable battery) with the prior art.
- a voltage regulator 2 is connected to an acceleration-activated battery 1 via a decoupling diode 13 and supplies the igniter electronics and especially a microprocessor 3 with the operating voltage Uv.
- the flight program programmed into the EEPROM 16 via an inductively operating interface 12, 15 is processed in the microprocessor by software and the ignition is initiated at the appropriate time via the remaining igniter electronics 4.
- the operating voltage Uv required for the programming process is derived from the energy of the inductive programming via the diode 14 and the voltage regulator 2.
- the two operating modes, programming / flight, are detected via the resistor 11 with the voltage level at the microprocessor port U. If there is no voltage, the battery is not yet activated (the programming voltage is kept away from the port U by the decoupling diode 13) and the microprocessor is recognized when Uv occurs on programming and processes the corresponding programming sequences at port up. However, if the battery is activated, it is due to port Ü High level on and the microprocessor 3 processes its programmed flight program.
- the input voltage of the voltage regulator 2 is sent to the input port Us via a switch 5 and the RC combination 6, 7 and 8 of the microprocessor 3 passed.
- the switch 5 is actuated by a suitable mechanical actuating device 10 by the mechanical securing device 9. In the case under consideration, it is open when the safety device is in the safeguard and it is closed in the arming mode.
- the microprocessor 3 also queries the port Us. If the switch is open, i.e. If the safety device is in the safe position, there is no voltage at Us and the programming can be carried out as intended. However, if the switch 5 is closed during the programming process, i.e. If the safety device is in the armed position, the input voltage of the voltage regulator is given to the port Us of the microprocessor via the resistor 8. In this case there is a high level and the programming is suppressed. Since the programming is generally bidirectional, this dangerous state of the safety device can also be reported back to the programming device and thus to the operator in this case and thus provide information for further handling of the detonator.
- the second advantage (main advantage) of the method improves the safety of the detonator or the projectile.
- the battery 1 is activated during the tube passage phase. This supplies the igniter electronics with energy and the Microprocessor 3 begins with the stabilization of the operating voltage Uv
- This voltage state depends on the mechanical closing of the switch 5 by the safety device.
- the safety device closes the switch 5 via the device 10 when it is fired. On the other hand, it reliably prevents closing in the case of briefly acting environmental forces which result from environmental pollution. However, if the environmental forces of a regular shot are present, the switch 5 closes, at least briefly. Even if the switch 5 then opens again due to accelerations when the projectile emerges from the pipe mouth, the switch 6, which was in the pipe, is temporarily stored by the capacitor 6 (because the capacitor 6 is charged by the battery activating in the pipe during the pipe passage phase) to the microprocessor 3 switches on after stabilizing its operating voltage Uv (this is the case approx. 20-100 m after leaving the pipe mouth).
- Uv this is the case approx. 20-100 m after leaving the pipe mouth.
- Resistor 8 ensures the adaptation of the higher voltage level of the activatable battery 1 to the voltage level of the microprocessor.
- the DC path for the CMOS input port of the microprocessor 3 is closed via the resistor 7 in the event that the switch 5 is open when the port is queried (a small input DC current must always be able to flow).
- the flight program is processed regularly, with an ignition of the explosives ends.
- the software concludes that the battery has been activated unintentionally and prevents the flight program from being processed further. In this case, the detonator and thus the projectile remain blind. This ensures that the ammunition is safe to fly over.
- this event of the unintentional activation of the battery can be stored in a non-volatile manner in the EEPROM 16.
- you can query it Information can then be determined whether the battery is in the course of storage,
- Transport or handling phases had already been activated (unintentionally) and is therefore no longer available for the planned mission. This provides an additional means for further quality control of the “One Sho” component that can be activated.
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Air Bags (AREA)
- Ignition Installations For Internal Combustion Engines (AREA)
- Luminescent Compositions (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Fuses (AREA)
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
- Floor Finish (AREA)
- Fittings On The Vehicle Exterior For Carrying Loads, And Devices For Holding Or Mounting Articles (AREA)
- Bidet-Like Cleaning Device And Other Flush Toilet Accessories (AREA)
Abstract
Description
Claims
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19941301A DE19941301C1 (en) | 1999-08-31 | 1999-08-31 | Electronic timed shell detonator has timing program for electronic control unit initiated only after closure of switch via mechanical safety device |
DE19941301 | 1999-08-31 | ||
PCT/EP2000/008321 WO2001016551A1 (en) | 1999-08-31 | 2000-08-26 | Electronic time-fuse for a projectile |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1212579A1 true EP1212579A1 (en) | 2002-06-12 |
EP1212579B1 EP1212579B1 (en) | 2003-06-04 |
Family
ID=7920211
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP00956486A Expired - Lifetime EP1212579B1 (en) | 1999-08-31 | 2000-08-26 | Electronic time-fuse for a projectile |
Country Status (7)
Country | Link |
---|---|
US (1) | US6598533B1 (en) |
EP (1) | EP1212579B1 (en) |
AT (1) | ATE242472T1 (en) |
DE (2) | DE19941301C1 (en) |
IL (2) | IL148141A0 (en) |
NO (1) | NO321418B1 (en) |
WO (1) | WO2001016551A1 (en) |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7124689B2 (en) * | 2004-11-22 | 2006-10-24 | Alliant Techsystems Inc. | Method and apparatus for autonomous detonation delay in munitions |
US8113118B2 (en) * | 2004-11-22 | 2012-02-14 | Alliant Techsystems Inc. | Spin sensor for low spin munitions |
US8559575B2 (en) * | 2007-12-19 | 2013-10-15 | Apple Inc. | Microcontroller clock calibration using data transmission from an accurate third party |
DE102010006529B4 (en) | 2010-02-01 | 2013-12-12 | Rheinmetall Air Defence Ag | Method and device for transmitting energy to a projectile |
DE102010006530B4 (en) | 2010-02-01 | 2013-12-19 | Rheinmetall Air Defence Ag | Programmable ammunition |
RU2767827C2 (en) * | 2019-12-19 | 2022-03-22 | Акционерное общество "ПКК МИЛАНДР" | Universal electronic fuse for small-caliber ammunition |
Family Cites Families (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
NL125215C (en) * | 1959-11-06 | |||
DE6921163U (en) * | 1969-05-24 | 1976-07-01 | Siemens Ag | PNEUMATIC SUCTION DEVICE. |
US4320704A (en) * | 1972-06-09 | 1982-03-23 | Dynamit Nobel Ag | Electronic projectile fuse |
US4454815A (en) * | 1981-09-21 | 1984-06-19 | The United States Of America As Represented By The Secretary Of The Army | Reprogrammable electronic fuze |
US4480550A (en) * | 1982-07-26 | 1984-11-06 | Motorola, Inc. | Relative velocity sensor for void sensing fuzes and the like |
US4799429A (en) * | 1984-03-30 | 1989-01-24 | Isc Technologies, Inc. | Programming circuit for individual bomblets in a cluster bomb |
EP0174115B1 (en) * | 1984-09-04 | 1989-07-26 | Imperial Chemical Industries Plc | Method and apparatus for safer remotely controlled firing of ignition elements |
DE3607372A1 (en) * | 1986-03-06 | 1987-09-17 | Honeywell Gmbh | FLOOR TIP WITH A TIMER |
DE3821912A1 (en) * | 1988-06-29 | 1990-01-11 | Honeywell Regelsysteme Gmbh | MISSILE |
DE3926585C1 (en) * | 1989-08-11 | 1991-03-07 | Honeywell Regelsysteme Gmbh, 6050 Offenbach, De | |
US5293153A (en) | 1991-04-09 | 1994-03-08 | Trw, Inc. | Method and apparatus for testing an airbag restraint system with parallel sensors |
US5343795A (en) * | 1991-11-07 | 1994-09-06 | General Electric Co. | Settable electronic fuzing system for cannon ammunition |
DE4240263C1 (en) * | 1992-12-01 | 1993-12-23 | Honeywell Ag | Programmable igniter for projectile - is programmable and provided with voltage during programming phase by rectifying inductively transmitted programme information |
US5335598A (en) * | 1993-05-07 | 1994-08-09 | Universal Propulsion Company, Inc. | Timing and firing circuitry |
US5497704A (en) * | 1993-12-30 | 1996-03-12 | Alliant Techsystems Inc. | Multifunctional magnetic fuze |
US5705766A (en) * | 1995-10-30 | 1998-01-06 | Motorola, Inc. | Electronic turns-counting fuze and method therefor |
-
1999
- 1999-08-31 DE DE19941301A patent/DE19941301C1/en not_active Expired - Fee Related
-
2000
- 2000-08-26 WO PCT/EP2000/008321 patent/WO2001016551A1/en active IP Right Grant
- 2000-08-26 IL IL14814100A patent/IL148141A0/en active IP Right Grant
- 2000-08-26 AT AT00956486T patent/ATE242472T1/en not_active IP Right Cessation
- 2000-08-26 DE DE50002475T patent/DE50002475D1/en not_active Expired - Lifetime
- 2000-08-26 US US10/069,591 patent/US6598533B1/en not_active Expired - Lifetime
- 2000-08-26 EP EP00956486A patent/EP1212579B1/en not_active Expired - Lifetime
-
2002
- 2002-02-13 IL IL148141A patent/IL148141A/en not_active IP Right Cessation
- 2002-02-27 NO NO20020946A patent/NO321418B1/en not_active IP Right Cessation
Non-Patent Citations (1)
Title |
---|
See references of WO0116551A1 * |
Also Published As
Publication number | Publication date |
---|---|
ATE242472T1 (en) | 2003-06-15 |
EP1212579B1 (en) | 2003-06-04 |
US6598533B1 (en) | 2003-07-29 |
NO20020946D0 (en) | 2002-02-27 |
NO321418B1 (en) | 2006-05-08 |
DE50002475D1 (en) | 2003-07-10 |
IL148141A (en) | 2006-07-05 |
WO2001016551A1 (en) | 2001-03-08 |
IL148141A0 (en) | 2002-09-12 |
NO20020946L (en) | 2002-02-27 |
DE19941301C1 (en) | 2000-12-07 |
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