EP1212579B1 - Elektronischer geschoss-zeitzünder - Google Patents
Elektronischer geschoss-zeitzünder Download PDFInfo
- Publication number
- EP1212579B1 EP1212579B1 EP00956486A EP00956486A EP1212579B1 EP 1212579 B1 EP1212579 B1 EP 1212579B1 EP 00956486 A EP00956486 A EP 00956486A EP 00956486 A EP00956486 A EP 00956486A EP 1212579 B1 EP1212579 B1 EP 1212579B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- fuse
- input
- time
- programming
- electronic
- 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
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Images
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 timer the generic term of claim 1.
- a detonator can e.g. the DE 42 40 263 C1 can be taken.
- Further state of the art is on US 4,454,815, DE 39 26 585 C1, DE 38 21 912 A1 and DE 692 11 638 T2.
- the sequence becomes the previous one programmed ignition time by activating the battery, i.e. through the Startup of the battery voltage during the mechanical - chemical activation by the Launch accelerations started.
- This type of runtime start also has the Another advantage is that there is a separate sensor for detecting the firing in the igniter superfluous, which leads to a further simplification of the igniter structure.
- 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 shoot over their own troops, the requirements with regard to security against premature disassembly (overflight security) are generally very high. Known numbers for the maximum permissible likelihood of premature disassembly are between 10 -5 and 10 -6 .
- igniter electronics are usually used taken several measures. These constructive measures range from use redundant acceleration-resistant oscillators, which allow the speed of the Prevent the igniter runtime of a single malfunctioning oscillator by Only very late loading of the ignition circuits with ignition energy shortly before the time of disassembly.
- the possibly incorrect (too early) time of dismantling a storey depends not only depending on potential influences during the flight, but can also be caused by a faulty fire command, faulty programming of the igniter runtime and faulty start of the igniter running time in the igniter.
- the first two cases cannot be corrected by measures in the detonator should not be considered further here.
- the latter case of the faulty (to early) starts of the igniter runtime is the starting point for the proposed improvement in terms of overflight safety.
- the activatable batteries used must be designed so that they are in the entire temperature range even with the smallest propellant charge during firing activate reliably. On the other hand, they have to be subjected to mechanical loads Environmental tests (e.g. 1.5 m drop on steel plate) and the accelerations during the loading process survive without activation. This means that the design-related ones are inevitable Safety margins between activation and non-activation small. Also can still Individual errors in the battery, that of poor battery production or material defects originate, further reduce this safety reserve.
- the projectile Before firing, in the pipe and at a defined distance in front of the pipe (security against the pipe), the projectile is generally prevented from igniting by a mechanical (or electronic) safety device.
- This safety device is designed in such a way that unintentional (mechanical - pyrotechnic) unlocking processes can only occur with a very low probability (1O -7 and smaller).
- the ignition means in ignition position and contacted. If an ignition now takes place, this leads to a disassembly of the floor. If the runtime is started correctly by the launch, the dismantling takes place in the intended target area.
- the unintentional earlier start of the runtime function can already occur as a result of the acceleration processes when the projectile is loaded (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 cutters may be due to the relatively long times between attaching the projectile (possibility of faulty battery activation) and Firing has been reduced by the inhibiting effect of the safety device. Namely, is the time between the application of the projectile and the firing of the If the projectile is longer than the programmed flight time, the electrical ignition device ignites already in the pipe and a further ignition is then ensured by the Safety device prevented.
- An acceleration-activated battery 1 is connected via a decoupling diode 13 Voltage regulator 2 connected to the igniter electronics and specifically there Microprocessor 3 supplied with the operating voltage Uv.
- Microprocessor 3 supplied with the operating voltage Uv.
- the microprocessor it will programmed into the EEPROM 16 via an inductively operating interface 12, 15 Flight program processed by software and the ignition at the appropriate time the remaining igniter electronics 4 initiated.
- the operating voltage Uv required for the programming process is via the diode 14 and the voltage regulator 2 is derived from the energy of the inductive programming.
- the two operating modes programming / flight are recognized by the Resistor 11 with the voltage level at the microprocessor port Ub. There is none Voltage, the battery is not yet activated (the programming voltage is from the decoupling diode 13 kept away from the port Ub) and the microprocessor recognizes when Uv occurs on programming and processes the corresponding ones Programming sequences on port up. However, if the battery is activated, the port is Ub High level on and the microprocessor 3 works its programmed flight program from.
- the microprocessor 3 When programming, the microprocessor 3 also the port us queried. If the switch is open, i.e. is the safety device in Make sure there is no voltage at Us and the programming can be done as intended be performed. However, switch 5 is during the programming process closed, i.e. if the security device is in focus, the Input voltage of the voltage regulator via the resistor 8 to the port Us of the Given microprocessor. In this case there is a high level and the Programming is suppressed. Since programming is generally bidirectional in this case, this dangerous condition of the safety device can also occur the programming device and thus be reported back to the operator and thus Give instructions for further handling of the igniter.
- the second advantage (main advantage) of the procedure improves the overfly safety of the Detonator or the projectile.
- the shot is during the pipe passage phase Battery 1 activated.
- Battery 1 activated.
- This supplies the igniter electronics with energy and the Microprocessor 3 begins with the stabilization of the operating voltage Uv Execution of the programmed flight program.
- the program flow made dependent on the voltage state of the port Us.
- This voltage state depends on the mechanical closing of the switch 5 by the Belay device.
- the safety device closes switch 5 when the shot is fired via the device 10. On the other hand, it reliably prevents closing short-term environmental forces resulting from environmental pollution. If however, the environmental forces of a regular shot are present, the switch 5 closes, at least for a short time. Even if the switch 5 is then accelerated at Exit of the bullet from the pipe opening opens again, through the condenser 6 the switch state that prevailed in the pipe is temporarily stored (because the capacitor 6 is during the pipe passage phase by the battery activating in the pipe charged) until the microprocessor 3 after stabilizing its operating voltage Uv switches on (this is the case approx. 20 - 100 m after leaving the pipe mouth).
- the Resistor 8 ensures the adaptation of the higher voltage level of the activatable Battery 1 to the voltage level of the microprocessor. Via the resistor 7 DC path for the CMOS input port of the microprocessor 3 for the case concluded that switch 5 is open when querying the port (it must always be on small input DC current can flow).
- the software will select unintended Activation of the battery closed and further processing of the flight program prevented. In this case, the detonator and thus the projectile remain blind. This is the Ammunition overfly guaranteed.
- this event can Accidental activation of the battery is stored permanently in EEPROM 16 become.
- 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 therefore is no longer available for the planned mission.
- You get an additional one Means for further quality control of the "One Shot" component can be activated Battery.
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)
- Bidet-Like Cleaning Device And Other Flush Toilet Accessories (AREA)
- Floor Finish (AREA)
- Fittings On The Vehicle Exterior For Carrying Loads, And Devices For Holding Or Mounting Articles (AREA)
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Description
Wurde er hingegen vorher programmiert, so beginnt bei der bisher üblichen Elektronikauslegung der Zünder mit der Abarbeitung des Missionsprogramms, d.h. Start der Laufzeit, Laden der Zündkreise und Zündung.
Claims (13)
- Elektronischer Geschoß-Zeitzünder mit einer elektronischen Steuereinheit (3), die mit einem ersten Eingang (Up) an eine Programmierschnittstelle (12, 15) für die Eingabe eines Zeitprogrammes angeschlossen ist, mit einem Spannungsregler (2), der die elektronische Steuereinheit (3) aus der Programmierinformation oder über eine beschleunigungsaktivierte Batterie (1) an einem zweiten Eingang (Uv) mit Spannung versorgt, und mit einer mechanischen Sicherungseinrichtung (9, 10), die bei ihrer Aktivierung eine Zündstrecke freigibt, dadurch gekennzeichnet, daß ein durch die mechanische Sicherungseinrichtung (9, 10) betätigter Schalter (5) angeordnet ist, der den Eingang des Spannungsreglers (2) mit einem dritten Eingang (Us) der elektronischen Steuereinheit (3) verbindet, wobei die Abarbeitung des Zeitprogrammes nur bei betätigtem Schalter (5) ermöglicht wird.
- Elektronischer Geschoß-Zeitzünder nach Anspruch 1 mit induktiver Programmierung mittels einer Induktionsspule (12), dadurch g e kennzeichne t , daß die Induktionsspule (12) und die beschleunigungsaktivierte Batterie (1) jeweils über Entkopplungsdioden (14, 13) an den Eingang des Spannungsreglers (2) angeschlossen sind.
- Elektronischer Geschoß-Zeitzünder nach Anspruch 2, dadurch gekennzeichnet, daß der Eingang des Spannungsreglers (2) über den Schalter (5) und ein RC-Speicherglied (6, 7, 8) an den dritten Eingang (Us) der elektronischen Steuereinheit (3) angeschlossen ist.
- Elektronischer Geschoß-Zeitzünder nach Anspruch 3, dadurch gekennzeichnet, daß die beschleunigungsaktivierte Batterie (1) über einen Widerstand (11) an einen vierten Eingang (Ub) der elektronischen Steuereinheit (3) angeschlossen ist, wobei ein hohes Potential an diesem vierten Eingang für die Abarbeitung des Zeitprogrammes erforderlich ist.
- Elektronischer Geschoß-Zeitzünder nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, daß die elektronische Steuereinheit (3) eine Programmierung der Zündzeit nur dann gestattet, wenn Programmierimpulse an dem ersten Eingang (Ub) vorliegen und der zweite Eingang (Uv) den hohen Pegel aufweist.
- Elektronischer Geschoß-Zeitzünder nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, daß die elektronische Steuereinheit (3) die Abarbeitung des Zeitprogrammes nur ermöglicht, wenn der dritte Eingang (Us) und der vierte Eingang (Ub) hohes Potential aufweisen.
- Elektronischer Geschoß-Zeitzünder nach Anspruch 3, dadurch gekennzeichnet, daß der dritte Eingang (Us) bei der Abarbeitung des Flugprogramms abgefragt wird und die Zündfünktion sperrt, wenn der Schalter nicht die korrekte Schalterposition aufweist.
- Elektronischer Geschoß-Zeitzünder nach Anspruch 3, dadurch gekennzeichnet, daß der dritte Eingang auch während der Programmierung des Zünders abgefragt wird und die Programmierfunktion deaktiviert, wenn der Schalter nicht die korrekte Schalterposition aufweist.
- Elektronischer Geschoß-Zeitzünder nach Anspruch 3, dadurch gekennzeichnet, daß die nicht korrekte Schalterposition über einen Rückmeldekanal der Programmierfunktion einem Bediener angezeigt wird.
- Elektronischer Geschoß-Zeitzünder nach Anspruch 3, dadurch gekennzeichnet, daß die nicht korrekte Schalterposition während der Abarbeitung des Flugprogramms abgespeichert wird und aufgrund dieser Information eine nachfolgende Programmierung deaktiviert wird.
- Elektronischer Geschoß-Zeitzünder nach Anspruch 10, dadurch gekennzeichnet, daß die nichtflüchtig abgespeicherte Information über eine frühere Batterieaktivierung über einen Rückmeldekanal der Programmierfunktion dem Bediener angezeigt wird.
- Elektronischer Geschoß-Zeitzünder nach einem der Ansprüche 1 bis 11, gekenn zeichnet durch einen Mikroprozessor (3) als elektronische Steuereinheit.
- Elektronischer Geschoß-Zeitzünder nach Anspruch 12, dadurch gekennzeichnet, daß ein nicht-flüchtiger Speicher (EEPROM 16) an den Mikroprozessor (3) angeschlossen ist, in welchem die programmierte Zünderzeit abgelegt ist.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19941301 | 1999-08-31 | ||
DE19941301A DE19941301C1 (de) | 1999-08-31 | 1999-08-31 | Elektronischer Geschoß-Zeitzünder |
PCT/EP2000/008321 WO2001016551A1 (de) | 1999-08-31 | 2000-08-26 | Elektronischer geschoss-zeitzünder |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1212579A1 EP1212579A1 (de) | 2002-06-12 |
EP1212579B1 true EP1212579B1 (de) | 2003-06-04 |
Family
ID=7920211
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP00956486A Expired - Lifetime EP1212579B1 (de) | 1999-08-31 | 2000-08-26 | Elektronischer geschoss-zeitzünder |
Country Status (7)
Country | Link |
---|---|
US (1) | US6598533B1 (de) |
EP (1) | EP1212579B1 (de) |
AT (1) | ATE242472T1 (de) |
DE (2) | DE19941301C1 (de) |
IL (2) | IL148141A0 (de) |
NO (1) | NO321418B1 (de) |
WO (1) | WO2001016551A1 (de) |
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 |
DE102010006530B4 (de) | 2010-02-01 | 2013-12-19 | Rheinmetall Air Defence Ag | Programmierbare Munition |
DE102010006529B4 (de) | 2010-02-01 | 2013-12-12 | Rheinmetall Air Defence Ag | Verfahren und Vorrichtung zur Übertragung von Energie auf ein Projektil |
RU2767827C2 (ru) * | 2019-12-19 | 2022-03-22 | Акционерное общество "ПКК МИЛАНДР" | Универсальный электронный взрыватель для мелкокалиберных боеприпасов |
Family Cites Families (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
NL125215C (de) * | 1959-11-06 | |||
DE6921163U (de) * | 1969-05-24 | 1976-07-01 | Siemens Ag | Pneumatisches sauggeraet. |
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 |
GB2164730B (en) * | 1984-09-04 | 1988-03-16 | Ici Plc | Remotely controlled firing of ignition elements |
DE3607372A1 (de) * | 1986-03-06 | 1987-09-17 | Honeywell Gmbh | Geschossspitze mit einem zeitzuender |
DE3821912A1 (de) * | 1988-06-29 | 1990-01-11 | Honeywell Regelsysteme Gmbh | Flugkoerper |
DE3926585C1 (de) * | 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 (de) * | 1992-12-01 | 1993-12-23 | Honeywell Ag | Zünder für ein Geschoß |
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/de not_active Expired - Fee Related
-
2000
- 2000-08-26 EP EP00956486A patent/EP1212579B1/de not_active Expired - Lifetime
- 2000-08-26 US US10/069,591 patent/US6598533B1/en not_active Expired - Lifetime
- 2000-08-26 AT AT00956486T patent/ATE242472T1/de not_active IP Right Cessation
- 2000-08-26 IL IL14814100A patent/IL148141A0/xx active IP Right Grant
- 2000-08-26 DE DE50002475T patent/DE50002475D1/de not_active Expired - Lifetime
- 2000-08-26 WO PCT/EP2000/008321 patent/WO2001016551A1/de active IP Right Grant
-
2002
- 2002-02-13 IL IL148141A patent/IL148141A/en not_active IP Right Cessation
- 2002-02-27 NO NO20020946A patent/NO321418B1/no not_active IP Right Cessation
Also Published As
Publication number | Publication date |
---|---|
WO2001016551A1 (de) | 2001-03-08 |
IL148141A (en) | 2006-07-05 |
DE19941301C1 (de) | 2000-12-07 |
US6598533B1 (en) | 2003-07-29 |
NO20020946D0 (no) | 2002-02-27 |
ATE242472T1 (de) | 2003-06-15 |
NO20020946L (no) | 2002-02-27 |
DE50002475D1 (de) | 2003-07-10 |
EP1212579A1 (de) | 2002-06-12 |
IL148141A0 (en) | 2002-09-12 |
NO321418B1 (no) | 2006-05-08 |
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