EP1166036B1 - Electronic fuse for a projectile - Google Patents

Electronic fuse for a projectile Download PDF

Info

Publication number
EP1166036B1
EP1166036B1 EP01911473A EP01911473A EP1166036B1 EP 1166036 B1 EP1166036 B1 EP 1166036B1 EP 01911473 A EP01911473 A EP 01911473A EP 01911473 A EP01911473 A EP 01911473A EP 1166036 B1 EP1166036 B1 EP 1166036B1
Authority
EP
European Patent Office
Prior art keywords
programming
capacitor
switch
voltage
projectile
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
EP01911473A
Other languages
German (de)
French (fr)
Other versions
EP1166036A1 (en
Inventor
Bertram KÖLBLI
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.)
Honeywell GmbH
Original Assignee
Honeywell GmbH
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 Honeywell GmbH filed Critical Honeywell GmbH
Publication of EP1166036A1 publication Critical patent/EP1166036A1/en
Application granted granted Critical
Publication of EP1166036B1 publication Critical patent/EP1166036B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C11/00—Electric fuzes
    • F42C11/008—Power generation in electric fuzes
    • 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
    • F42C15/40—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein the safety or arming action is effected electrically
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C17/00—Fuze-setting apparatus
    • F42C17/04—Fuze-setting apparatus for electric fuzes

Definitions

  • the present invention relates to an electronic projectile fuze after Generic term of claim 1.
  • Today's electronic detonators either use energy to power Primary cells or preferably batteries, which only by the large accelerations, the during the firing of a projectile-occurring, mechanically-chemically activated. This has the advantage that such equipped igniter no maintenance in terms of Exchanges e.g. need an otherwise used battery primary cell, since these Batteries are completely passive during storage and therefore long storage times allow.
  • the sequence of the before programmed igniter function by activating the battery i. through the Ramp - up of the battery voltage during the mechanical - chemical activation by the Launch accelerations started.
  • the activatable batteries used must therefore be constructively designed that they in the entire temperature range even with the smallest propellant charge during firing Reliable activate. On the other hand, they have mechanical stress through Environmental tests (e.g., 1.5 m fall on steel plate) and accelerations during charging survive without activation. This will inevitably be the constructive Safety margins between activation and non-activation small. In addition, still can Single fault in the battery caused by poor battery or material defects to further reduce this safety margin.
  • FR 2 545 207 A1 describes a projectile fuse with a capacitor, which is charged during a programming phase and immediately ignites, after the programming has taken place.
  • the capacitor is a pure one Filter capacitor and forms one together with the resistor and the diode simple circuit for demodulating an amplitude modulated oscillation.
  • the flight phase is then preferably initiated by a switch 5 which is designed to be very high-impedance (for the blocking phase during programming and the time before the shot) and which connects the inverting switching voltage regulator 17 to the capacitor 1.
  • the switch 5 is actuated by the generally specially designed, environmentally-protected safety device 9 very safe when the typical environment for a shot environmental forces by an actuator 10, so that an inadvertent closing of the switch 5 before the actual shot practically only with the at Mechanical security devices may experience common tiny probabilities of 10 -7 to 10 -8 . If the detonator is not programmed, it is even completely energy-free, which makes it even safer compared to detonators with built-in batteries.
  • the switching voltage regulator 17 must be high in order to avoid unnecessary energy losses Have efficiency and a very large input voltage range. He will therefore preferably designed especially for this or similar applications and because of the smaller and therefore power-saving structures integrated into an ASIC.
  • the storage capacitors 1 and 19 must also for reasons of small losses preferably foil or ceramic capacitors with the smallest possible leakage current, as their charge remains unchanged even after 10 to 20 minutes after the Programming in the flight phase must be available.
  • the supply capacitor 19 for the ignition stage 16 is, as already mentioned, in parallel charged to the supply capacitor 1 during the programming phase.
  • the capacitor 19 Shortly before the ignition of the ignition stage 16 by the ignition trigger signal at the output T of Igniter electronics 3, via the signal S of the detonator electronics 3 and a suitable electronic switch 24, the capacitor 19 is connected to the ignition stage 16 and this energized only at this late date. This will despite early Charging the capacitor 19 in the programming phase, a high overflight safety of the Igniter reached.
  • Fig. 1 has a further advantage.
  • the input F is also polled by the detonator electronics 3 in addition to the programming input Up. If the switch is open, ie if the safety device is in safe condition, there is no voltage at F and the programming can be carried out as intended. However, if the switch 5 is closed during the programming operation, ie if the safety device is in the armed position, the voltage of the charging capacitor 1 during the programming, converted by the voltage regulator 17, is applied to the input F of the detonator electronics. If this voltage is detected in conjunction with a programming sequence on U P , the programming function is suppressed. Since the programming is generally bidirectional, in this case, this dangerous state of the safety device can also be reported back to the programmer and thus to the operator and thus give clues for further handling of the igniter.

Description

Die vorliegende Erfindung bezieht sich auf einen elektronischen Geschoßzünder nach dem Gattungsbegriff des Patentanspruches 1.The present invention relates to an electronic projectile fuze after Generic term of claim 1.

Moderne elektronische Zünder verwenden heutzutage zur Energieversorgung entweder Primärzellen oder vorzugsweise Batterien, die erst durch die großen Beschleunigungen, die bei der Abfeuerung eines Geschosses-auftreten, mechanisch - chemisch aktiviert werden. Dies hat den Vorteil, daß derartig ausgerüstete Zünder keine Wartung hinsichtlich des Austausches z.B. einer sonst verwendeten Batterie-Primärzelle benötigen, da diese Batterien während ihrer Lagerung vollständig passiv sind und darum lange Lagerzeiten zulassen.Today's electronic detonators either use energy to power Primary cells or preferably batteries, which only by the large accelerations, the during the firing of a projectile-occurring, mechanically-chemically activated. This has the advantage that such equipped igniter no maintenance in terms of Exchanges e.g. need an otherwise used battery primary cell, since these Batteries are completely passive during storage and therefore long storage times allow.

Im allgemeinen wird bei derartig ausgestatteten Zündern der Ablauf der vorher einprogrammierten Zünderfunktion durch das Aktivieren der Batterie, d.h. durch den Hochlauf der Batteriespannung bei der mechanisch - chemischen Aktivierung durch die Abschußbeschleunigungen gestartet.In general, in such equipped igniters, the sequence of the before programmed igniter function by activating the battery, i. through the Ramp - up of the battery voltage during the mechanical - chemical activation by the Launch accelerations started.

Die verwendeten aktivierbaren Batterien müssen deswegen konstruktiv so ausgelegt sein, daß sie im gesamten Temperaturbereich auch bei kleinster Treibladung bei der Abfeuerung zuverlässig aktivieren. Andererseits müssen sie mechanische Belastungen durch Umwelttests (z.B. 1,5 m Fall auf Stahlplatte) und die Beschleunigungen beim Ladevorgang ohne Aktivierung überstehen. Damit werden notgedrungen die konstruktiv bedingten Sicherheitsmargen zwischen Aktivierung und Nichtaktivierung klein. Zudem können noch Einzelfehler in der Batterie, die von mangelhafter Batteriefertigung oder Materialfehlern herrühren, diese Sicherheitsreserve weiter vermindern. The activatable batteries used must therefore be constructively designed that they in the entire temperature range even with the smallest propellant charge during firing Reliable activate. On the other hand, they have mechanical stress through Environmental tests (e.g., 1.5 m fall on steel plate) and accelerations during charging survive without activation. This will inevitably be the constructive Safety margins between activation and non-activation small. In addition, still can Single fault in the battery caused by poor battery or material defects to further reduce this safety margin.

Es kann also nach dem oben Gesagten nicht ausgeschlossen werden, daß derartige Batterien schon vor dem Schuß aktivieren. Dies kann je nach Funktions- und Sicherheitsauslegung des Zünders ggf. zu gefährlichen Zünderzuständen während der Überflugphase führen.It can not be ruled out from the above that such batteries activate before the shot. This may vary depending on functional and safety design If necessary, the detonator may cause dangerous detonator conditions during the overflight phase.

Speziell im Falle des Einsatzes bei der Artillerie, werden auch eigene Truppen überschossen. Deswegen sind die Forderungen hinsichtlich der Sicherheit gegen eine zu frühe Geschoßzerlegung (Überflugsicherheit) hier im allgemeinen sehr hoch. Bekannte Zahlen für die maximale zugelassene Wahrscheinlichkeit einer zu frühen Zerlegung liegen zwischen 10-5 und 10-6.Especially in the case of use in the artillery, own troops are overshadowed. Therefore, the security requirements against too early projectile breakdown (overflight safety) are generally very high here. Known numbers for the maximum allowed probability of too early decomposition are between 10 -5 and 10 -6 .

Andererseits sind durch die oben erwähnten, notwendigen kleinen konstruktiven Abstände zwischen Funktion und Nichtfunktion einer beschleunigungsaktivierbaren Batterie (1,5 m Fall: nein, kleinste Ladung: ja) auch Funktionsprobleme bei kleinen Ladungen zu erwarten und werden in der Praxis auch beobachtet.On the other hand, by the above-mentioned, necessary small constructive distances between function and non-functioning of an acceleration-activatable battery (1.5 m case: no, smallest charge: yes) also functional problems with small loads too expect and are also observed in practice.

Zudem hat sich die Herstellung derartiger Spezialbatterien infolge der heutzutage zunehmenden Industriezusammenschlüsse auf immer weniger Firmen konzentriert, so daß die Versorgungslage, nicht zuletzt auch durch Exportrestriktionen einiger Länder für derartige Produkte, immer schwieriger wird. Wenn jedoch Batterien verfügbar sind, dann im allgemeinen zu Preisen, die oft mit dem "Low Cost - Produkt" Zünder inkompatibel sind.In addition, the production of such special batteries as a result of today Increasing industrial concentrations concentrated on fewer and fewer companies, so that the supply situation, not least due to export restrictions in some countries Such products are becoming increasingly difficult. However, if batteries are available, then in Generally at prices that are often incompatible with the "low cost product" detonator.

Andere bekannte Methoden der Energieerzeugung während des Geschoßfluges sind Generatoren, die entweder über Piezoeffekt oder elektrodynamisch über Geschoßbeschleunigung, Drallaufbau oder Windanströmung elektrische Energie für die in den Zünder eingebaute Elektronik erzeugen. Derartige Lösungen sind jedoch z.B. für einen Artilleriezünder entweder wegen der kleinen Energieausbeute (Piezo) nicht geeignet oder sind noch teurer und unzuverlässiger als eine eingebaute Batterie und zudem entweder Spezialanfertigungen als Produkt einer langen und teuren Entwicklungsphase oder zumindest ähnlich schwierig zu beschaffen wie eine beschleunigungsaktivierbare Batterie. Other known methods of energy production during the projectile flight are Generators, either via piezo effect or electrodynamically over Projectile acceleration, swirl construction or wind flow electrical energy for the in generate the igniter built-in electronics. However, such solutions are e.g. for one Artilleriezünder either because of the small energy yield (Piezo) not suitable or are even more expensive and unreliable than a built-in battery and either Special productions as a product of a long and expensive development phase or at least as difficult to obtain as an accelerator-activated battery.

Die US 5,343,795 gemäß dem Oberbegriff des Anspruchs 1 offenbart eine Vorrichtung zur elektrischen Energieversorgung von Geschoßzündern ohne Batterie, wobei zum Betrieb des Geschoßzünders in der Flugphase ein während einer induktiven Programmierphase aufgeladener Versorgungskondensator hinter einem Halbleiterschalter angeordnet ist, der in einem Empfangszustand positive Halbwellen eines eingekoppelten Signals durch parallel geschaltete Dioden durchlässt, um eine Spannungsversorgung aufzuladen und die Fluginformationen einem Demodulator zur Programmierung des Geschoßzünders zuzuleiten.US 5,343,795 according to the preamble of claim 1 discloses a device for electrical power supply of projectile detonators without battery, wherein the operation of the projectile fuze in the flight phase one charged during an inductive programming phase Supply capacitor is arranged behind a semiconductor switch, the positive half-waves of a coupled-in signal in a receiving state through diodes connected in parallel to a power supply to charge and the flight information to a demodulator for programming of the projectile fuze.

Die FR 2 545 207 A1 beschreibt einen Geschoßzünder mit einem Kondensator, der während einer Programmierphase aufgeladen wird und unmittelbar zündet, nachdem die Programmierung stattgefunden hat. Der Kondensator ist ein reiner Filterkondensator und bildet zusammen mit dem Widerstand und der Diode eine einfache Schaltung zur Demodulation einer amplitudenmodulierten Schwingung.FR 2 545 207 A1 describes a projectile fuse with a capacitor, which is charged during a programming phase and immediately ignites, after the programming has taken place. The capacitor is a pure one Filter capacitor and forms one together with the resistor and the diode simple circuit for demodulating an amplitude modulated oscillation.

Bei dem Geschoßzünder gemäß US 4,644,864 wird zu Beginn der Programmierung ein erster Puls verwendet, um einen Energieversorgungskondensator mit geringer Leckage aufzuladen. Erst mit den nachfolgend gesendeten Pulsen wird die Programmierung durchgeführt.In the projectile fuze according to US 4,644,864 is at the beginning of programming a first pulse used to power a power supply capacitor low leakage. Only with the subsequently transmitted pulses the programming was done.

Ausgehend von diesem Stand der Technik ist es die Aufgabe der vorliegenden Erfindung, einen neuen Geschosszünder, speziell einen Artillerie-Geschoßzünder anzugeben, der ohne Batterie oder zusätzliche Energieerzeugung im Geschossflug auskommt.Based on this prior art, it is the object of the present Invention, a new projectile fuse, especially an artillery projectile fuse indicate that without battery or additional power generation gets by in the projectile flight.

Die Lösung dieser Aufgabe gelingt gemäß den kennzeichnenden Merkmalen des Patentanspruches 1. Vorteilhafte Ausgestaltungen des erfindungsgemäßen Geschosszünders können den abhängigen Ansprüchen entnommen werden. Im folgenden sei anhand der beigefügten Fig. 1 der erfindungsgemäße Geschosszünder kurz erläutert. The solution to this problem succeeds according to the characterizing features of claim 1. Advantageous embodiments of the invention Projectile fuze can be found in the dependent claims. in the The following is based on the attached Fig. 1 of the projectile fuse according to the invention briefly explained.

Es wird vorgeschlagen, zum Betrieb des Geschoßzünders in der Flugphase einen während der Programmierphase aufgeladenen Kondensator zu verwenden, der einen sehr geringen Leckstrom aufweist, um eine Zeit im Minutenbereich zwischen der Programmierung und dem Beginn der Flugphase ohne wesentlichen Energieverlust überbrücken zu können.It is proposed to operate the projectile fuze in the flight phase to use a capacitor charged during the programming phase, which has a very low leakage current to a time in the minute range between the programming and the beginning of the flight phase without significant To be able to bridge energy loss.

Es ist bekannt, während der induktiven Programmierphase über die zünderinterne Programmierspule 12 durch die Sendespule 22 eines zünderexternen Programmiergerätes 23 über die magnetische Kopplung der beiden Spulen und ein moduliertes magnetisches Wechselfeld Energie und Programmierinformation zu übertragen. Ferner ist bekannt, die im Programmiervorgang übertragene Energie zur Versorgung des Zünders während des Programmiervorgangs heranzuziehen und, da nach dem Programmiervorgang die Energieübertragung durch das Programmiergerät 23 unterbrochen wird, die während des Programmiervorgangs übertragene Information nichtflüchtig, z.B. in einem EEPROM in der Zünderelektronik abzuspeichern.It is known during the inductive programming phase via the igniter internal Programming coil 12 through the transmitting coil 22 of an igniter external Programmer 23 via the magnetic coupling of the two coils and a modulated alternating magnetic field energy and programming information transferred to. It is also known that transmitted in the programming process Energy to supply the igniter during the programming process and, since after the programming process the energy transfer is interrupted by the programmer 23 during the programming process transmitted information non-volatile, e.g. in an EEPROM in store the detonator electronics.

Um die Idee der Erfindung verstehen zu können, wird zunächst auf den oben erwähnten Programmiervorgang etwas näher eingegangen.
In der NATO STANAG 4369 mit der zugehörigen AOP22 sind Schaltvorschläge für die Beschaltung der induktiven Programmierschnittstelle vorgeschlagen, die so oder in ähnlicher Form in jedem Zünder, der die Kompatibilitätsforderung erfüllen muß, realisiert sind. Diese Beschaltung ist grob auch in Fig. 1 durch die Elemente 22, 12, 14, 4, 15 und 2 angedeutet. Es fällt bei der näheren Betrachtung nur dieser wenigen Elemente auf, daß die in die Spule 12 durch die Programmierspule 22 induzierte Wechselspannung über die Diode 14 einweggleichgerichtet und durch das Programmierinterface 15, den Spannungsregler 2 mit angeschlossener Last belastet wird. Zusätzlich wird diese Spannung durch eine Zenerdiode 4 in der Höhe begrenzt, um die Bauelemente der Elemente 2 und 15 vor Überspannung zu schützen. Durch die Einweggleichrichtung durch die Diode 14 wird jedoch nur die positive Halbwelle der am Verbindungspunkt der Bauelemente 12, 14, 13 und 18 anstehenden Wechselspannung belastet, so daß die positive Halbwelle an diesem Punkt praktisch nie über die Zenerspannung der Zenerdiode 4 plus der Flußspannung der Diode 14 hinausgeht.In order to understand the idea of the invention, first of all, the above-mentioned programming process will be discussed in more detail.
In the NATO STANAG 4369 with the associated AOP22 suggested switching suggestions for the wiring of the inductive programming interface are proposed, which are realized in a similar or similar way in each igniter, which must meet the compatibility requirement. This wiring is roughly indicated in Fig. 1 by the elements 22, 12, 14, 4, 15 and 2. It is obvious from the closer consideration of only a few elements that the induced in the coil 12 by the programming coil 22 AC voltage through the diode 14 is rectified rectified and loaded by the programming interface 15, the voltage regulator 2 with connected load. In addition, this voltage is limited by a zener diode 4 in height to protect the components of the elements 2 and 15 from overvoltage. Due to the one-way rectification by the diode 14, however, only the positive half wave of the connection point of the components 12, 14, 13 and 18 pending AC voltage is charged, so that the positive half wave at this point practically never beyond the Zener voltage of the zener diode 4 plus the forward voltage of the diode 14 goes out.

Betrachtet man zunächst die Dioden 13 und 18 der Fig. 1 als nicht vorhanden, können am Ausgang der Spule 12 die negative Halbwellen eine Spannungsamplitude von 50 bis 60 V annehmen. Die Energie, die in diesen Halbwellen steckt, wird bisher nicht genutzt. Setzt man nun in die Schaltung der Fig. 1 die hochsperrenden Dioden 13 und 18 wieder ein, so werden durch die Einweggleichrichtung der negativen Halbwellen des Ausgangs der Spule 12 der Versorgungskondensator 1 für die Zünderelektronik und der Versorgungskondensator 19 für die Zündstufe aufgeladen. Die den Kondensatoren parallelgeschalteten sehr hochohmigen Widerstände 6 und 20 dienen der definierten Entladung der Kondensatoren im Falle eines nicht erfolgten Verschusses des Zünders und belasten den Aufladevorgang praktisch nicht. Dies bedeutet, daß beide Kondensatoren auf eine Gleichspannung bis zu einer Höhe zwischen -50 und -60V aufgeladen werden.Considering first the diodes 13 and 18 of Fig. 1 as not available, can on Output of the coil 12, the negative half-waves a voltage amplitude of 50 to 60 V. accept. The energy that is in these half waves is not used yet. Puts Now in the circuit of Fig. 1, the high-blocking diodes 13 and 18 again, so be through the half - wave rectification of the negative half waves of the output of Coil 12 of the supply capacitor 1 for the detonator electronics and the Supply capacitor 19 charged for the ignition stage. The the capacitors parallel-connected very high-impedance resistors 6 and 20 serve the defined Discharge of the capacitors in case of failure of firing the igniter and load the charging process practically not. This means that both capacitors on a DC voltage can be charged up to a height between -50 and -60V.

Definiert man als C1 und U1 die Kapazität und die Spannung des Kondensators 1 und als C19 bzw. U19 als die entsprechenden Größen des Kondensators 19, so steht nach der Programmierung zur Versorgung des Spannungsreglers 17 und der Zünderelektronik 3 die Energie 0,5 C1 U1 2 und zur Versorgung der Zündstufe die Energie 0,5 C19 U19 2 zur Verfügung.Defining the capacitance and the voltage of the capacitor 1 as C 1 and U 1 and as the corresponding magnitudes of the capacitor 19 as C 19 and U 19, the power is 0 after the programming for the supply of the voltage regulator 17 and the detonator electronics 3 5 C 1 U 1 2 and to supply the ignition stage the energy 0.5 C 19 U 19 2 available.

Da die Spannung quadratisch in die Höhe der während des Programmiervorgangs in die Kondensatoren gespeicherten Energie eingeht, die Baugröße und der Preis der Kondensatoren aber nur proportional zum Produkt C U steigt, läßt sich durch Ausnutzung der hohen negativen Halbwellen des Programmiervorgangs im Zünder auf kleinem Raum preiswert Energie speichern. Since the voltage in the square of the height during the programming process in the Capacitors stored energy, the size and price of the received Capacitors but only proportional to the product C U increases, can be exploited high negative half-waves of programming in the igniter in a small space inexpensive to save energy.

Die Flugphase wird dann vorzugsweise durch einen (für die Sperrphase während der Programmierung und die Zeit vor dem Schuß) sehr einfach hochohmig auszulegenden Schalter 5 eingeleitet, der den invertierenden Schaltspannungsregler 17 mit dem Kondensator 1 verbindet. Der Schalter 5 wird durch die im allgemeinen speziell entwickelte, gegen Umwelteinflüsse gehärtete Sicherungseinrichtung 9 sehr sicher beim Auftreten der für einen Schuß typischen Umweltkräfte durch ein Betätigungselement 10 betätigt, so daß ein unbeabsichtigtes Schließen des Schalters 5 vor dem eigentlichen Schuß praktisch nur mit den bei den mechanischen Sicherungseinrichtungen üblichen winzigen Wahrscheinlichkeiten von 10-7 bis 10-8 vorkommen kann. Ist der Zünder nicht programmiert, so ist er sogar vollkommen energielos, was ihn gegenüber Zündern mit eingebauten Batterien noch sicherer macht.The flight phase is then preferably initiated by a switch 5 which is designed to be very high-impedance (for the blocking phase during programming and the time before the shot) and which connects the inverting switching voltage regulator 17 to the capacitor 1. The switch 5 is actuated by the generally specially designed, environmentally-protected safety device 9 very safe when the typical environment for a shot environmental forces by an actuator 10, so that an inadvertent closing of the switch 5 before the actual shot practically only with the at Mechanical security devices may experience common tiny probabilities of 10 -7 to 10 -8 . If the detonator is not programmed, it is even completely energy-free, which makes it even safer compared to detonators with built-in batteries.

Ist der Schalter 5 konstruktiv so ausgelegt, daß er nach Auftreten der typischen Geschoßbeschleunigungen schließt und z.B. durch mechanische Verriegelung auch während der gesamten Flugphase geschlossen bleibt, erübrigt sich die, gestrichelt in Fig. 1 eingezeichnete, elektronische Selbsthaltung 11. Kann dies nicht gewährleistet werden, so sorgt die Selbsthaltung 11 dafür, daß beim Auftreten einer Spannung am Punkt Z der Eingang X mit dem Ausgang Y leitend verbunden wird und, solange der Spannungsregler 17 arbeitet, auch verbunden bleibt.Is the switch 5 constructively designed so that after the occurrence of the typical Gap accelerations include and e.g. by mechanical locking even while the entire phase of flight remains closed, is unnecessary, dashed lines in Fig. 1 drawn, electronic self-holding 11. If this can not be guaranteed, then the latch 11 ensures that when a voltage occurs at the point Z of Input X is conductively connected to the output Y and, as long as the voltage regulator 17 works, remains connected.

Die Erkennung der beiden Betriebsarten Programmierung / Flug erfolgt über die beiden Eingänge Up und F der Zünderelektronik. Liegt an UP Spannung an und an F nicht, so ist der Schalter 5 noch offen und die Elektronik erkennt beim Auftreten von Uv auf Programmierung und verarbeitet dabei die entsprechenden Programmiersequenzen an Port Up Ist jedoch Schalter 5 geschlossen, so liegt am Eingang F Spannung an (und am Eingang UP keine Programmiersequenz) und die Elektronik arbeitet ihr einprogrammiertes Flugprogramm ab.Recognition of the two operating modes programming / flight takes place via the two inputs Up and F of the detonator electronics. If voltage is present at U P and not at F, then switch 5 is still open and the electronics recognizes programming when Uv is present and processes the corresponding programming sequences at Port Up. However, if switch 5 is closed, voltage is present at input F. (and at the input U P no programming sequence) and the electronics work off their programmed flight program.

Der Schaltspannungsregler 17 muß zur Vermeidung unnötiger Energieverluste einen hohen Wirkungsgrad sowie einen sehr großen Eingangsspannungsbereich besitzen. Er wird deshalb vorzugsweise speziell für diese oder ähnliche Anwendungen entwickelt und wegen der kleineren und deshalb stromsparenden Strukturen in ein ASIC integriert. The switching voltage regulator 17 must be high in order to avoid unnecessary energy losses Have efficiency and a very large input voltage range. He will therefore preferably designed especially for this or similar applications and because of the smaller and therefore power-saving structures integrated into an ASIC.

Die Speicherkondensatoren 1 und 19 müssen ebenfalls aus Gründen kleiner Verluste vorzugsweise Folien- oder Keramikkondensatoren mit möglichst kleinem Leckstrom sein, da ihre Aufladung möglichst unverändert auch nach 10 bis 20 Minuten nach der Programmierung in der Flugphase zur Verfügung stehen muß.The storage capacitors 1 and 19 must also for reasons of small losses preferably foil or ceramic capacitors with the smallest possible leakage current, as their charge remains unchanged even after 10 to 20 minutes after the Programming in the flight phase must be available.

Der Versorgungskondensator 19 für die Zündstufe 16 wird, wie schon erwähnt, parallel zum Versorgungskondensator 1 während der Programmierphase aufgeladen. Diese Anordnung ist notwendig, weil der Kondensator 1 während der Versorgung der Zünderelektronik 3 entladen wird und deswegen eine ausreichende Zündspannungshöhe bei einer möglichen Mitversorgung der Zündstufe 16 aus Kondensator 1 nicht garantiert werden könnte.The supply capacitor 19 for the ignition stage 16 is, as already mentioned, in parallel charged to the supply capacitor 1 during the programming phase. These Arrangement is necessary because the capacitor 1 during the supply of Igniter electronics 3 is discharged and therefore at a sufficient Zündspannungshöhe a possible supply of the ignition stage 16 from capacitor 1 is not guaranteed could be.

Kurz vor der Zündung der Zündstufe 16 durch das Zündtriggersignal am Ausgang T der Zünderelektronik 3, wird über das Signal S der Zünderelektronik 3 und einen geeigneten elektronischen Schalter 24 der Kondensator 19 mit der Zündstufe 16 verbunden und diese erst zu diesem späten Zeitpunkt mit Energie versorgt. Dadurch wird trotz frühzeitiger Aufladung des Kondensators 19 in der Programmierphase eine hohe Überflugsicherheit des Zünders erreicht.Shortly before the ignition of the ignition stage 16 by the ignition trigger signal at the output T of Igniter electronics 3, via the signal S of the detonator electronics 3 and a suitable electronic switch 24, the capacitor 19 is connected to the ignition stage 16 and this energized only at this late date. This will despite early Charging the capacitor 19 in the programming phase, a high overflight safety of the Igniter reached.

Die Anordnung nach Fig. 1 besitzt einen weiteren Vorteil. Bei der Programmierung wird durch die Zünderelektronik 3 neben dem Programmiereingang Up auch der Eingang F abgefragt. Ist der Schalter offen, d.h. ist die Sicherungseinrichtung in Sicherstellung, liegt an F keine Spannung und die Programmierung kann wie vorgesehen durchgeführt werden. Ist jedoch während des Programmiervorganges der Schalter 5 geschlossen, d.h. befindet sich die Sicherungseinrichtung in Scharfstellung, so wird die Spannung des sich während der Programmierung aufladenden Kondensators 1, gewandelt durch den Spannungsregler 17, an den Eingang F der Zünderelektronik gegeben. Bei gleichzeitiger Erkennung dieser Spannung in Verbindung mit einer Programmiersequenz an UP wird die Programmierfunktion unterdrückt. Da die Programmierung im allgemeinen bidirektional erfolgt, kann in diesem Falle dieser gefährliche Zustand der Sicherungseinrichtung auch an das Programmiergerät und somit an den Bediener zurückgemeldet werden und damit Hinweise für eine weitere Handhabung des Zünders geben. The arrangement of Fig. 1 has a further advantage. During programming, the input F is also polled by the detonator electronics 3 in addition to the programming input Up. If the switch is open, ie if the safety device is in safe condition, there is no voltage at F and the programming can be carried out as intended. However, if the switch 5 is closed during the programming operation, ie if the safety device is in the armed position, the voltage of the charging capacitor 1 during the programming, converted by the voltage regulator 17, is applied to the input F of the detonator electronics. If this voltage is detected in conjunction with a programming sequence on U P , the programming function is suppressed. Since the programming is generally bidirectional, in this case, this dangerous state of the safety device can also be reported back to the programmer and thus to the operator and thus give clues for further handling of the igniter.

Dadurch läßt sich auch die Forderung 4.6.6 des Zünder-Sicherheitsstandards MIL-STD 1316 D elegant erfüllen, der eine externe Kontrollmöglichkeit des Sicherheitszustandes der Sicherungseinrichtung vor Einbau des Zünders in die Munition vorschreibt. Diese Kontrolle kann dadurch über eine schon vorhandene Schnittstelle, die Programmierschnittstelle, vorgenommen werden und erfordert so keine zusätzlichen aufwendigen Maßnahmen wie Sichtfenster oder Durchbrüche am Zündergehäuse.As a result, also the requirement 4.6.6 of the igniter safety standard MIL-STD 1316 D elegantly fulfilling an external control of the Safety state of the safety device before installation of the igniter in the ammunition prescribes. This control can be achieved through an already existing interface, the Programming interface, be made and thus requires no additional elaborate measures such as viewing windows or openings on the igniter housing.

Claims (10)

  1. Device for supplying electrical power to projectile detonators without a battery or additional power generation during the flight of the projectile, a supply capacitor (1) charged during an inductive programming phase being arranged in the device in order to operate the projectile detonator in the flight phase, said supply capacitor having a very low leakage current in order to bridge over a time in minutes between the programming phase and the start of the flight phase without a significant loss of power, said device being characterized in that the AC programming voltage is switched across a diode (14) poled in a first direction to a programming interface (15) and a programming voltage regulator (2), and in that the supply capacitor (1) is charged from the AC programming voltage across a diode (13) poled in the opposite direction, wherein, in order to charge the supply capacitor (1), use is made of the half-waves of the AC programming voltage which are unused and unloaded during the programming phase.
  2. Device according to Claim 1, characterized by a switch (5) actuated by a mechanical fuse device (9), which switch supplies the charge of the supply capacitor (1) to a voltage regulator (17) having a large input voltage range and high efficiency.
  3. Device according to Claim 2, characterized in that the voltage regulator (17) inverts its input voltage.
  4. Device according to Claims 1 to 3, characterized in that the switch (5) actuated by the fuse device (9) is bridged by a self-locking switch (11).
  5. Device according to one of Claims 1 to 4, characterized in that a detonation capacitor (19) for controlling a detonation stage (16) is arranged in parallel with the supply capacitor (1).
  6. Device according to Claim 5, characterized in that the charge of the detonation capacitor (19) is placed on the detonation stage (16) via an electronic switch (24) actuated by the detonator electronics (3).
  7. Device according to one of Claims 2 to 6, characterized in that the output of the voltage regulator (17) for the flight phase is interrogated at a terminal (F) by the detonator electronics (3) even during the programming of the detonator, and the programming function is deactivated if the switch (5) at the input of this voltage regulator (17) does not have the correct switch position.
  8. Device according to Claim 7, characterized in that the incorrect switch position is indicated to the operator via a reporting channel of the programming function.
  9. Device according to Claim 5 or one of the subsequent claims, characterized in that the detonation capacitor (19) is charged from the AC programming voltage across a diode (18) poled in the opposite direction to the diode (14) poled in the first direction.
  10. Device according to Claim 9, characterized in that high-value resistors (6, 20) are connected in parallel with the supply capacitor (1) and the detonation capacitor (19).
EP01911473A 2000-02-02 2001-01-11 Electronic fuse for a projectile Expired - Lifetime EP1166036B1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE10004582 2000-02-02
DE10004582A DE10004582C1 (en) 2000-02-02 2000-02-02 Electronic projectile detonator
PCT/EP2001/000264 WO2001057468A1 (en) 2000-02-02 2001-01-11 Electronic fuse for a projectile

Publications (2)

Publication Number Publication Date
EP1166036A1 EP1166036A1 (en) 2002-01-02
EP1166036B1 true EP1166036B1 (en) 2005-07-27

Family

ID=7629606

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01911473A Expired - Lifetime EP1166036B1 (en) 2000-02-02 2001-01-11 Electronic fuse for a projectile

Country Status (6)

Country Link
US (1) US6675715B1 (en)
EP (1) EP1166036B1 (en)
JP (1) JP2003521668A (en)
DE (2) DE10004582C1 (en)
WO (1) WO2001057468A1 (en)
ZA (1) ZA200107412B (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2836991B1 (en) * 2002-03-08 2006-05-19 Alkan Sa ELECTRO-PYROTECHNIC SAFETY DEVICE FOR MUNITION AND ITS CONTROL METHOD
US7077045B2 (en) * 2003-09-24 2006-07-18 Raytheon Company Projectile inductive interface for the concurrent transfer of data and power
WO2008112012A2 (en) * 2006-10-04 2008-09-18 Raytheon Company Supercapacitor power supply
US10615695B1 (en) * 2017-12-13 2020-04-07 The United States Of America As Represented By The Secretary Of The Army High voltage generation for ESAD munition fuzing circuitry
CN115586366B (en) * 2022-11-17 2023-03-10 中国工程物理研究院电子工程研究所 Method for calculating steady-state work average peak current in fuse high-voltage charging process

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL257675A (en) * 1959-11-06
FR2545207B1 (en) * 1974-06-25 1986-11-21 France Etat Armement ENERGY PROGRAMMING AND TRANSFER DEVICE FOR WEAPON SYSTEMS AND PROJECTILE FOR WEAPON SYSTEMS PROVIDED WITH SUCH A DEVICE
GB2153495B (en) * 1984-01-25 1987-10-21 Plessey Co Plc Improvements relating to variable timing and power storage arrangements
US4586437A (en) * 1984-04-18 1986-05-06 Asahi Kasei Kogyo Kabushiki Kaisha Electronic delay detonator
DE3571873D1 (en) * 1984-09-04 1989-08-31 Ici Plc Method and apparatus for safer remotely controlled firing of ignition elements
US4928570A (en) * 1986-07-08 1990-05-29 Thomson Brandt Armements Method and system for transmitting a command to start up a device on board a missile
US5117756A (en) * 1989-02-03 1992-06-02 Atlas Powder Company Method and apparatus for a calibrated electronic timing circuit
JP3312740B2 (en) * 1991-10-11 2002-08-12 旭化成株式会社 Electric detonator continuity checker
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
US5363765A (en) * 1993-03-12 1994-11-15 Asahi Kasei Kogyo Kabushiki Kaisha Electronic delay circuit for firing ignition element
US5497704A (en) * 1993-12-30 1996-03-12 Alliant Techsystems Inc. Multifunctional magnetic fuze
WO1996003614A1 (en) * 1994-07-28 1996-02-08 Asahi Kasei Kogyo Kabushiki Kaisha Electronic delay igniter and electric detonator
DE59608912D1 (en) 1995-09-28 2002-04-25 Contraves Pyrotec Ag Method and device for programming projectile timers
US5705766A (en) * 1995-10-30 1998-01-06 Motorola, Inc. Electronic turns-counting fuze and method therefor

Also Published As

Publication number Publication date
DE50106864D1 (en) 2005-09-01
EP1166036A1 (en) 2002-01-02
WO2001057468A1 (en) 2001-08-09
US6675715B1 (en) 2004-01-13
DE10004582C1 (en) 2001-08-30
ZA200107412B (en) 2002-03-14
JP2003521668A (en) 2003-07-15

Similar Documents

Publication Publication Date Title
DE2945122C2 (en)
DE2143119C3 (en) Electric projectile fuse
JPH049600A (en) Modular electronic safety device release device
DE10020037C1 (en) Electronic self-destruct device has capacitors connected to comparator so varying operating voltage and output of variable voltage amplitudes by piezoelement do not affect timing
DE3202612C2 (en) Electric power generator
EP1166036B1 (en) Electronic fuse for a projectile
DE2653452C3 (en) Electronic ignition circuit
EP1125094B1 (en) Detonation system for detonators which can be tripped by radio, and a method for tripping these detonators
CN109489507B (en) Self-destruction device based on in-line fuze
US3541393A (en) High energy solid state blasting machine
DE19941301C1 (en) Electronic timed shell detonator has timing program for electronic control unit initiated only after closure of switch via mechanical safety device
DE4330195C1 (en) Detonation instant fuze
CH696892A5 (en) Projectile fuze.
DE2539541C2 (en) Circuit for an electric projectile fuse
DE19945790A1 (en) Ignition device for igniters which can be triggered by radio and method for triggering these igniters
DE10133832B4 (en) Safety device for igniter
EP0281088A2 (en) Submissile with an ignition device
DE2259378C3 (en) Protection circuit for electric tinder
DE1291260B (en) Emergency firing for guns
DE2750972B2 (en) Circuit for controlling low-resistance loads, especially detonators
AT220523B (en) Electric projectile ignition device
DE2035056C3 (en) Electric tinder with pre-pipe safety
DE1925866C3 (en) Electrical circuit arrangement for the delayed ignition of an electric igniter
DE1948382C (en) Electrical pulse generation arrangement
DE1948382B2 (en) ELECTRIC PULSE GENERATION ARRANGEMENT

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20010926

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE TR

AX Request for extension of the european patent

Free format text: AL;LT;LV;MK;RO;SI

17Q First examination report despatched

Effective date: 20040204

RBV Designated contracting states (corrected)

Designated state(s): CH DE FR GB LI SE

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): CH DE FR GB LI SE

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REF Corresponds to:

Ref document number: 50106864

Country of ref document: DE

Date of ref document: 20050901

Kind code of ref document: P

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20051027

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20051020

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20060131

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20060131

ET Fr: translation filed
PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20060428

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20090130

Year of fee payment: 9

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20081211

Year of fee payment: 9

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20090106

Year of fee payment: 9

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20100111

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20100930

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20100201

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20100803

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20100111

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230525