EP1909056A1 - Fuse for a projectile - Google Patents

Fuse for a projectile Download PDF

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Publication number
EP1909056A1
EP1909056A1 EP07019217A EP07019217A EP1909056A1 EP 1909056 A1 EP1909056 A1 EP 1909056A1 EP 07019217 A EP07019217 A EP 07019217A EP 07019217 A EP07019217 A EP 07019217A EP 1909056 A1 EP1909056 A1 EP 1909056A1
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EP
European Patent Office
Prior art keywords
igniter
projectile
sensors
criterion
pressure
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.)
Withdrawn
Application number
EP07019217A
Other languages
German (de)
French (fr)
Inventor
Alexander Zinell
Johann Dr. Pannhorst
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.)
Junghans Microtec GmbH
Original Assignee
Junghans Microtec 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 Junghans Microtec GmbH filed Critical Junghans Microtec GmbH
Publication of EP1909056A1 publication Critical patent/EP1909056A1/en
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/28—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges operated by flow of fluent material, e.g. shot, fluids
    • F42C15/29—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges operated by flow of fluent material, e.g. shot, fluids operated by fluidic oscillators; operated by dynamic fluid pressure, e.g. ram-air operated
    • 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
    • F42C15/005—Combination-type safety mechanisms, i.e. two or more safeties are moved in a predetermined sequence to each other
    • 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

Definitions

  • the invention relates to an igniter for a projectile, in particular for a swirl-free projectile, according to the preamble of claim 1.
  • a wind turbine or a turbine wheel which is mounted in the igniter and senses the air flow after the launch.
  • the wind or turbine wheel must be flowed through a channel having an inlet and an outlet.
  • This channel as well as the mounting of the wind or turbine wheel are sensitive to soiling and icing and therefore e.g. unfit under sandy or dusty conditions and environments.
  • the invention has for its object to provide a detonator for a projectile, especially for a spin-free projectile, with a second arming criterion, with no continuous channel to the security device is available, and with simple means an automatic release is possible.
  • pressure sensors and / or temperature sensors are preferably mounted on the igniter tip and on the igniter circumference, which are suitable for carrying out a pressure difference measurement and / or a temperature difference measurement during an air flow during the flight phase of the projectile, and unambiguously the respective flight phase of the airfoil as a function of a predefined threshold value Projectile to detect.
  • a corresponding comparison signal between the predetermined threshold value and the pressure and / or temperature difference measurement signal forms the second arming criterion for the igniter according to the invention. This signal is thus used as a second arming criterion, and leads to the automatic arming of the igniter according to the invention.
  • the advantages achieved by the invention are that the safety of the user and the reliability are significantly improved because the fuse of the igniter is done automatically, and because openings are avoided in the interior of the igniter inside.
  • the figure illustrates an igniter 10 of a projectile 12.
  • the igniter 10 has a safety device 14 with a first and a second arming criterion.
  • the first safety criterion uses the launch acceleration of the projectile 12.
  • an acceleration sensor 16 For detecting the launch acceleration is an acceleration sensor 16, which is operatively connected to the securing device 14. This operative connection is indicated by the angled arrow 18.
  • the igniter 10 has sensors 20 spaced from each other.
  • a sensor 20 is provided at the igniter tip 22 and further sensors 20 are spaced therefrom along the circumference of the igniter 10 from each other evenly spaced.
  • the sensors 20 are pressure sensors and / or temperature sensors.
  • the pressure sensors 20 are suitable, according to the Bernoulli.
  • the pressure difference and / or the temperature sensors are adapted to measure the temperature difference at an air flow of the igniter 10 during the flight phase of the projectile and to detect depending on a predetermined threshold clearly the flight phase of the projectile 12.
  • the measurement signals generated by the sensors 20 are compared in a comparator 24 with the said threshold value.
  • the threshold value is indicated by the arrow 26.
  • the operative connection between the sensors 20 and the comparator 24 is illustrated by the angled arrow lines 28.
  • the corresponding comparison signal forms the second arming criterion of the safety device 14 of the igniter 10. This comparison signal is indicated by the arrow 30.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Measuring Temperature Or Quantity Of Heat (AREA)
  • Measuring Fluid Pressure (AREA)
  • Control Of Turbines (AREA)

Abstract

The igniter (10) for a spin-free projectile (12), comprises a first and a second unlocking criterion for safety mechanism (14) of the igniter, and sensors (20) spaced from each other for pressure and/or the temperature difference measurement. The first unlocking criterion is used for firing acceleration of the igniter. The respective pressure and/or temperature difference measured value is compared by a comparator with a given threshold value (26). The corresponding comparison signal forms the second unlocking criterion. The igniter (10) for a spin-free projectile (12), comprises a first and a second unlocking criterion for safety mechanism (14) of the igniter, and sensors (20) spaced from each other for pressure and/or the temperature difference measurement. The first unlocking criterion is used for firing acceleration of the igniter. The respective pressure and/or temperature difference measured value is compared by a comparator with a given threshold value (26). The corresponding comparison signal forms the second unlocking criterion. A sensor at the igniter point and sensors of the igniter point are axially intended uniformly spaced along the circumference of the igniter.

Description

Die Erfindung betrifft einen Zünder für ein Geschoss, insbesondere für ein drallfreies Geschoss, gemäß dem Oberbegriff des Anspruches 1.The invention relates to an igniter for a projectile, in particular for a swirl-free projectile, according to the preamble of claim 1.

Bei drallfreien Geschossen wie Mörsern o. dgl. wird als erstes Entsicherungskriterium die Abschussbeschleunigung benutzt. Als zweites Entsicherungskriterium kommt bspw. ein Vorstecker zur Anwendung, der vor dem Abschuss des Geschosses gezogen werden muss. Ein wesentlicher Mangel eines derartigen Vorsteckers besteht darin, dass der Zünder des Geschosses nach dem Ziehen des Vorsteckers nur noch einfach gesichert ist und trotzdem noch gehandhabt werden muss. Das bedeutet für das Bedienpersonal ein erhöhtes Risiko. Außerdem sind solche Vorstecker für automatische Waffen bzw. Abschusssysteme nicht geeignet.In spin-free bullets such as mortars o. The like. As the first arming criterion, the launch acceleration is used. As a second arming criterion, for example, a lug is used, which must be pulled before the launch of the projectile. A major shortcoming of such Vorsteckers is that the detonator of the projectile is only easily secured after pulling the Vorsteckers and still needs to be handled. This represents an increased risk for the operating personnel. In addition, such pins are not suitable for automatic weapons or Abschusssysteme.

Eine andere Möglichkeit besteht bislang darin, als zweites Entsicherungskriterium bspw. ein Windrad bzw. ein Turbinenrad vorzusehen, das im Zünder gelagert ist und die Luftströmung nach dem Abschuss sensiert. Zu diesem Zwecke muss das Wind- bzw. Turbinenrad über einen Kanal angeströmt werden, der einen Einlass und einen Auslass besitzt. Dieser Kanal sowie die Lagerung des Wind- bzw. Turbinenrades sind gegen Verschmutzungen und gegen Vereisung empfindlich und deshalb z.B. unter sandigen oder staubigen Einsatzbedingungen und -umgebungen untauglich.Another possibility has hitherto been to provide as a second arming criterion, for example, a wind turbine or a turbine wheel, which is mounted in the igniter and senses the air flow after the launch. For this purpose, the wind or turbine wheel must be flowed through a channel having an inlet and an outlet. This channel as well as the mounting of the wind or turbine wheel are sensitive to soiling and icing and therefore e.g. unfit under sandy or dusty conditions and environments.

In Kenntnis dieser Gegebenheiten liegt der Erfindung die Aufgabe zugrunde, einen Zünder für ein Geschoss, insbesondere für ein drallfreies Geschoss, mit einem zweiten Entsicherungskriterium zu schaffen, wobei kein durchgehender Kanal zur Sicherungseinrichtung vorhanden ist, und mit einfachen Mitteln eine automatische Entsicherung möglich ist.In view of these circumstances, the invention has for its object to provide a detonator for a projectile, especially for a spin-free projectile, with a second arming criterion, with no continuous channel to the security device is available, and with simple means an automatic release is possible.

Diese Aufgabe wird erfindungsgemäß durch die Merkmale des Anspruches 1 gelöst. Bevorzugte Aus- bzw. Weiterbildungen der Erfindung sind in den Unteransprüchen gekennzeichnet.This object is achieved by the features of claim 1. Preferred embodiments or further developments of the invention are characterized in the subclaims.

Erfindungsgemäß sind vorzugsweise an der Zünderspitze und am Zünderumfang Drucksensoren und/oder Temperatursensoren angebracht, die dazu geeignet sind, bei einer Luftanströmung während der Flugphase des Geschosses eine Druckdifferenzmessung und/oder eine Temperaturdifferenzmessung vorzunehmen, und in Abhängigkeit von einem vorgegebenen Schwellwert eindeutig die jeweilige Flugphase des Geschosses zu detektieren. Ein entsprechendes Vergleichssignal zwischen dem vorgegebenen Schwellwert und dem Druck- und/oder Temperatur-Differenzmesssignal bildet für den erfindungsgemäßen Zünder das zweite Entsicherungskriterium. Dieses Signal wird also als zweites Entsicherungskriterium genutzt, und führt zur automatischen Scharfstellung des erfindungsgemäßen Zünders.According to the invention, pressure sensors and / or temperature sensors are preferably mounted on the igniter tip and on the igniter circumference, which are suitable for carrying out a pressure difference measurement and / or a temperature difference measurement during an air flow during the flight phase of the projectile, and unambiguously the respective flight phase of the airfoil as a function of a predefined threshold value Projectile to detect. A corresponding comparison signal between the predetermined threshold value and the pressure and / or temperature difference measurement signal forms the second arming criterion for the igniter according to the invention. This signal is thus used as a second arming criterion, and leads to the automatic arming of the igniter according to the invention.

Die mit der Erfindung erzielten Vorteile bestehen darin, dass die Sicherheit beim Anwender und die Zuverlässigkeit wesentlich verbessert sind, weil die Entsicherung des Zünders automatisch erfolgt, und weil Öffnungen in das Innere des Zünders hinein vermieden werden.The advantages achieved by the invention are that the safety of the user and the reliability are significantly improved because the fuse of the igniter is done automatically, and because openings are avoided in the interior of the igniter inside.

Weitere Einzelheiten, Merkmale und Vorteile ergeben sich aus der nachfolgenden Beschreibung eines in der Zeichnung schematisch verdeutlichten Ausführungsbeispieles eines abschnittweise gezeichneten Zünders eines Geschosses, insbesondere eines drallfreien Geschosses.Further details, features and advantages will become apparent from the following description of a schematically illustrated in the drawing embodiment of a sectionally drawn detonator of a projectile, in particular a twist-free projectile.

Die Figur verdeutlicht einen Zünder 10 eines Geschosses 12. Der Zünder 10 weist eine Sicherungseinrichtung 14 mit einem ersten und einem zweiten Entsicherungskriterium auf. Das erste Sicherungskriterium benutzt die Abschussbeschleunigung des Geschosses 12. Zum Erfassen der Abschussbeschleunigung dient ein Beschleunigungssensor 16, der mit der Sicherungseinrichtung 14 wirkverbunden ist. Diese Wirkverbindung ist durch den abgewinkelten Pfeil 18 angedeutet.The figure illustrates an igniter 10 of a projectile 12. The igniter 10 has a safety device 14 with a first and a second arming criterion. The first safety criterion uses the launch acceleration of the projectile 12. For detecting the launch acceleration is an acceleration sensor 16, which is operatively connected to the securing device 14. This operative connection is indicated by the angled arrow 18.

Der Zünder 10 weist voneinander beabstandet Sensoren 20 auf. Ein Sensor 20 ist an der Zünderspitze 22 vorgesehen und weitere Sensoren 20 sind davon beabstandet entlang des Umfangs des Zünders 10 voneinander gleichmäßig beabstandet angeordnet. Bei den Sensoren 20 handelt es sich um Drucksensoren und/oder um Temperatursensoren. Die Drucksensoren 20 sind dazu geeignet, nach dem Bernoulli-.The igniter 10 has sensors 20 spaced from each other. A sensor 20 is provided at the igniter tip 22 and further sensors 20 are spaced therefrom along the circumference of the igniter 10 from each other evenly spaced. The sensors 20 are pressure sensors and / or temperature sensors. The pressure sensors 20 are suitable, according to the Bernoulli.

Gesetz die Druckdifferenz und/oder die Temperatursensoren sind dazu geeignet, die Temperaturdifferenz bei einer Luftanströmung des Zünders 10 während der Flugphase des Geschosses zu messen und in Abhängigkeit von einem vorgegebenen Schwellwert eindeutig die Flugphase des Geschosses 12 zu detektieren. Zu diesem Zwecke werden die von den Sensoren 20 erzeugten Messsignale in einem Komparator 24 mit dem besagten Schwellwert verglichen. Der Schwellwert ist durch den Pfeil 26 angedeutet. Die Wirkverbindung zwischen den Sensoren 20 und dem Komparator 24 ist durch die abgewinkelten Pfeillinien 28 verdeutlicht.Law the pressure difference and / or the temperature sensors are adapted to measure the temperature difference at an air flow of the igniter 10 during the flight phase of the projectile and to detect depending on a predetermined threshold clearly the flight phase of the projectile 12. For this purpose, the measurement signals generated by the sensors 20 are compared in a comparator 24 with the said threshold value. The threshold value is indicated by the arrow 26. The operative connection between the sensors 20 and the comparator 24 is illustrated by the angled arrow lines 28.

Ist die Flugphase des Geschosses 12 mit Hilfe der Sensoren 20 eindeutig detektiert, so bildet das entsprechende Vergleichssignal das zweite Entsicherungskriterium der Sicherungseinrichtung 14 des Zünders 10. Dieses Vergleichssignal ist durch den Pfeil 30 angedeutet.If the flight phase of the projectile 12 is clearly detected with the aid of the sensors 20, then the corresponding comparison signal forms the second arming criterion of the safety device 14 of the igniter 10. This comparison signal is indicated by the arrow 30.

Bezugsziffernliste:List of reference numerals:

1010
Zünder (für 12)Igniter (for 12)
1212
Geschossbullet
1414
Sicherungseinrichtung (von 10)Safety device (of 10)
1616
Beschleunigungssensor (von 10 für 14)Accelerometer (from 10 to 14)
1818
Pfeil/Wirkverbindung/erstes Entsicherungskriterium (für 14)Arrow / working connection / first arming criterion (for 14)
2020
Sensoren (von 10)Sensors (out of 10)
2222
Zünderspitze (von 10)Igniter tip (from 10)
2424
Komparator (von 10 für 20)Comparator (from 10 to 20)
2626
Schwellwert (für 24)Threshold (for 24)
2828
Pfeil/Wirkverbindung (zwischen 20 und 24)Arrow / working connection (between 20 and 24)
3030
Pfeil/Vergleichssignal/zweites Entsicherungskriterium (für 14)Arrow / comparison signal / second arming criterion (for 14)

Claims (3)

Zünder für ein Geschoss, insbesondere für ein drallfreies Geschoss, mit einem ersten und einem zweiten Entsicherungskriterium seiner Sicherungseinrichtung (14), wobei das erste Entsicherungskriterium die Abschussbeschleunigung des Zünders (10) benutzt,
dadurch gekennzeichnet,
dass der Zünder (10) voneinander beabstandet Druck- und/oder Temperatursensoren (20) zur Differenzmessung des Druckes und/oder der Temperatur aufweist, wobei der jeweilige Differenz-Messwert mittels eines Komparators (24) mit einem vorgegebenen Schwellwert (26) verglichen wird, und das entsprechende Vergleichssignal (28) das zweite Entsicherungskriterium für die Sicherungseinrichtung (14) des Zünders (10) des Geschosses (12) bildet.An igniter for a projectile, in particular for a swirl-free projectile, with a first and a second arming criterion of its securing device (14), the first unlocking criterion using the launching acceleration of the igniter (10),
characterized,
that the igniter (10) spaced apart pressure and / or has temperature sensors (20) for differential measurement of the pressure and / or temperature, whereby the respective difference measured value by a comparator (24) with a predetermined threshold (26) is compared, and the corresponding comparison signal (28) forms the second arming criterion for the securing device (14) of the igniter (10) of the projectile (12). Zünder nach Anspruch 1,
dadurch gekennzeichnet,
dass mindestens ein Sensor (20) an der Zünderspitze (22) und eine Anzahl Sensoren (20) von der Zünderspitze (22) axial beabstandet entlang des Umfangs des Zünders (10) vorgesehen sind.Igniter according to claim 1,
characterized,
in that at least one sensor (20) is provided at the igniter tip (22) and a number of sensors (20) are provided axially spaced from the igniter tip (22) along the circumference of the igniter (10). Zünder nach Anspruch 2,
dadurch gekennzeichnet,
dass die Sensoren (20) entlang des Umfangs des Zünders (10) gleichmäßig beabstandet vorgesehen sind.Igniter according to claim 2,
characterized,
in that the sensors (20) are provided uniformly spaced along the circumference of the igniter (10).
EP07019217A 2006-10-07 2007-09-29 Fuse for a projectile Withdrawn EP1909056A1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102006047549A DE102006047549B4 (en) 2006-10-07 2006-10-07 Igniter for a spin-free projectile

Publications (1)

Publication Number Publication Date
EP1909056A1 true EP1909056A1 (en) 2008-04-09

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EP07019217A Withdrawn EP1909056A1 (en) 2006-10-07 2007-09-29 Fuse for a projectile

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US (1) US20080210115A1 (en)
EP (1) EP1909056A1 (en)
DE (1) DE102006047549B4 (en)
ZA (1) ZA200708509B (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11125546B2 (en) * 2018-03-07 2021-09-21 Bae Systems Plc Fuse system
EP3537096A1 (en) * 2018-03-07 2019-09-11 BAE SYSTEMS plc Fuse system
GB2571750B (en) * 2018-03-07 2022-03-30 Bae Systems Plc Fuse system
FR3092660B1 (en) 2019-02-13 2022-04-01 Nexter Munitions ROCKET FOR A PROJECTILE INTENDED TO BE FIRED BY A CANNON

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US4089268A (en) * 1977-03-30 1978-05-16 The United States Of America As Represented By The United States Department Of Energy Safe arming system for two-explosive munitions
GB2070739A (en) * 1980-02-01 1981-09-09 Diehl Gmbh & Co A projectile having a thermo- electrical generator
GB2380782A (en) 1997-07-16 2003-04-16 Royal Ordnance Plc A fuze
US20060060102A1 (en) * 2000-03-17 2006-03-23 Boucher Craig J Ordinance firing system for land vehicle

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US3416451A (en) * 1967-09-11 1968-12-17 Air Force Usa Battery activator system
US4378740A (en) * 1980-10-15 1983-04-05 Calspan Corporation Munition fuse system having out-of-line safety device
US4541341A (en) * 1983-10-28 1985-09-17 The United States Of America As Represented By The Secretary Of The Navy Self-checking arming and firing controller
KR960011912A (en) * 1994-09-01 1996-04-20 야마구찌 이와오 Electrophotographic photosensitive member
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US6000340A (en) * 1997-01-07 1999-12-14 Raytheon Company Rocket launching system employing thermal-acoustic detection for rocket ignition
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Patent Citations (4)

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Publication number Priority date Publication date Assignee Title
US4089268A (en) * 1977-03-30 1978-05-16 The United States Of America As Represented By The United States Department Of Energy Safe arming system for two-explosive munitions
GB2070739A (en) * 1980-02-01 1981-09-09 Diehl Gmbh & Co A projectile having a thermo- electrical generator
GB2380782A (en) 1997-07-16 2003-04-16 Royal Ordnance Plc A fuze
US20060060102A1 (en) * 2000-03-17 2006-03-23 Boucher Craig J Ordinance firing system for land vehicle

Also Published As

Publication number Publication date
ZA200708509B (en) 2008-10-29
US20080210115A1 (en) 2008-09-04
DE102006047549A1 (en) 2008-04-10
DE102006047549B4 (en) 2010-04-22

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