EP1826527B1 - Mechanical rocket fuse - Google Patents
Mechanical rocket fuse Download PDFInfo
- Publication number
- EP1826527B1 EP1826527B1 EP07002490A EP07002490A EP1826527B1 EP 1826527 B1 EP1826527 B1 EP 1826527B1 EP 07002490 A EP07002490 A EP 07002490A EP 07002490 A EP07002490 A EP 07002490A EP 1826527 B1 EP1826527 B1 EP 1826527B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- rotor
- bolt
- safety
- spring
- firing
- 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.)
- Not-in-force
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
- F42C1/00—Impact fuzes, i.e. fuzes actuated only by ammunition impact
- F42C1/02—Impact fuzes, i.e. fuzes actuated only by ammunition impact with firing-pin structurally combined with fuze
- F42C1/08—Impact fuzes, i.e. fuzes actuated only by ammunition impact with firing-pin structurally combined with fuze with delayed action after ignition of fuze or after impact
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- 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
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- 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
- F42C15/18—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a carrier for an element of the pyrotechnic or explosive train is moved
- F42C15/188—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a carrier for an element of the pyrotechnic or explosive train is moved using a rotatable carrier
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- 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
- F42C15/24—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein the safety or arming action is effected by inertia means
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- 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
- F42C15/24—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein the safety or arming action is effected by inertia means
- F42C15/26—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein the safety or arming action is effected by inertia means using centrifugal force
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- 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
- F42C15/34—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein the safety or arming action is effected by a blocking-member in the pyrotechnic or explosive train between primer and main charge
Definitions
- the invention relates to a mechanical rocket detonator according to the preamble of claim 1.
- the detonator has a rotatably mounted, designed as a rotor Zündpillenarme, which is rotatable by a spring force from a secure position in an armed position.
- the igniter on a transport protection in the form of an axially displaceable locking pin.
- the rotor rotates in focus, in which the igniter axis coincides with the axis of the intended for the instantaneous ignition squib. If the changeover pin is in the instantaneous ignition position, then this squib is pierced by a firing pin when the igniter strikes. However, if the Umstellbolzen in the delayed ignition position, the aforementioned squib is not pierceable over the ignition pin lying on the igniter axis. In this case, a detonator intended for delayed ignition is pierced by a firing pin not located on the detonator axis. Each squib must therefore be pierced over its associated firing pin.
- the US 2,664,822 A which forms a starting point for the independent claim 1, relates to an igniter for projectiles rotating during their flight.
- the igniter has a rotor with two detonators, one for instantaneous ignition and one for delayed ignition.
- spring-loaded locking pins are provided, which are in holes located in the rotor inside. With sufficient centrifugal force, the locking pins release the rotor.
- the rotor does not begin to rotate until enough fluid has escaped from a capsule in the rotor that was pierced by a needle when it was fired, thereby changing the center of gravity of the rotor. ever after setting a stop screw, the rotor then rotates to a position in which the axis of one of the two detonators is aligned with the axis of a firing pin.
- the DE 17 03 016 A1 shows a projectile fuse with a rotor which is secured in the securing over two engaging in the circumference of the rotor latch. Furthermore, the projectile fuze has an inhibitor, in which two pivotable bolt can engage in a spring housing by corresponding springs in the locked position.
- the invention has for its object to provide a mechanical rocket igniter of the type mentioned, which is based on an existing mortar fuse, but has a more reliable safety device.
- the invention has the advantage that a closed system is realized, whereby both conditions according to MIL-STD and STANAG 4187 are fulfilled by two tumblers.
- Fig.1 shows longitudinally sectioned an embodiment of the igniter 10, which has a firing chain 12, which can be initiated by means of a firing needle 14.
- the ignition chain 12 has an ignition transformer 16 and an ignition amplifier 18. Between the firing pin 14 and the ignition transformer 16 of the ignition chain 12, a rotor 20 is provided, which is provided with a counter-rotating spring 40 (see Figure 3 ) connected is.
- the counter-torsion spring 40 is fixed between the rotor 20 and the igniter 10, ie, a housing 22 of an igniter assembly 24.
- An igniter tip 26 is fixedly connected to the housing 22 of the igniter assembly 24 on the front side. This connection is realized by a screw 28.
- a cover plate 30 is fixed, into which the firing needle 14 is in the assurance of the igniter with its end portion 32 into it.
- the cover plate 30 is formed with a through hole 34.
- the rotor 20 is formed with a blind hole 36 which is axially aligned in the assurance of the igniter with the through hole 34 of the pressure plate 30 and thus with the firing needle 14. This will Reliably prevents it from initiating an inadvertent impact of the igniter.
- the rotor 20 about an axis of rotation 38 of the ignition chain 12 interrupting ie non-initiating assurance launch and spin due to the spring force of the above-mentioned counter-torsion spring 40 of the rotor 20 in a firing chain 12 releasing focus adjustable.
- a manually adjustable adjusting device 42 (see the Figures 2 . 7 and 8th ) is used to set the Drehwinkelk Schemees of the rotor 20 about its axis of rotation 38 and thus for optional positioning of the rotor 20 in a focus without delay (see Figure 7 ), ie in the "OV position", or in a retarded position (see Figure 8 ), ie in the "MV position".
- the adjusting device 42 has an adjusting bolt 44 with which the ignition delay time of the igniter 10 is set as desired.
- the adjusting bolt 44 is formed, for example, with a groove 46 and the housing 22 of the igniter assembly 24 is provided with a pin 48, which projects into the groove 46 and defines the rotation of the adjusting bolt 44 around its longitudinal central axis 50 - in the "OV". Position "or" MV position "- limited.
- the rotor 20 is provided with a puncture detonator 52 without delay, i. with an "OV detonator”, and with a puncture detonator 54 with delay, i. provided with an "MV detonator”.
- the "OV detonator” 52 and the “MV detonator” 54 are spaced from the axis of rotation 38 of the rotor 20 radially equidistant and circumferentially of the rotor 20 from each other.
- a securing determining securing device 56 having a first locking lever 58 and a second locking lever 60 (see Figure 3 ).
- the first locking lever 58 is about an axially oriented axis 62 and the second locking lever 60 is pivotable about an axially oriented axis 64.
- the first securing lever 58 engages in the securing with a latching member 66 in a recess 68 which is formed in the rotor 20.
- the second locking lever 60 engages in the securing with a latching member 70 in an associated second recess 72 of the rotor 20 a.
- the first and the second locking lever 58 and 60 are squeezed in the assurance with their Einrastorganen 66, 70 in the associated recesses 68, 72 of the rotor 20, engages the two safety levers 58 and 60, a spring element 74, as a two-armed leg torsion spring is trained.
- the one leg 76 of the spring element 74 engages on the latching member 66 with respect to the axis 72 opposite the second end portion 78 of the first safety lever 58 at.
- the second leg 80 of the spring element 74 engages on the latching member 70 with respect to the axis 64 opposite the second end portion of the second locking lever 60 at.
- the spring element 74 acts on the first locking lever 58 in the clockwise direction and on the second locking lever 60 in the counterclockwise direction (see, for example, the Figure 3 ).
- the securing device 56 also has a first securing bolt 84 and a second securing bolt 86, which are oriented in the axial direction of the igniter 10 and radially spaced from one another (see FIGS Figures 5 and 6 ).
- a bolt spring element 88 and the second securing bolt 86 are associated with a bolt spring element 90, which are arranged in associated blind holes 92 and 94, respectively, which are formed in the housing 22 of the igniter assembly 24.
- the bolt spring elements 88 and 90 are helical compression springs in the illustrated embodiment.
- the first locking pin 84 positively in a formed in the cover plate 30 hole 96 and the second locking pin 86 in a form-fitting manner in a formed in the pressure plate 30 recess 98 inside.
- a bolt lever 100 (see, for example. Figure 3 ), which is Drainenkbar about an axially oriented axis 102.
- a pin lever spring 104 is provided, which - similar to the spring element 74 for the two safety levers 58 and 60 - is designed as a two-armed leg torsion spring.
- a coupling body 108 is disposed between the first and second locking pins.
- This coupling body 106 may, for example, be designed as a cylinder, ie a roller body.
- the coupling body 106 is formed as a small ball 108.
- the first securing bolt 84 has a circumferential recess 110 with a conically tapered portion 112 and a head 114, on which the bolt lever 100 in the pre-release position (see Figure 5 ) of the double bolt system is applied.
- the second securing bolt 86 has a head section 115 which engages positively in the securing of the igniter 10 into a recess 116 formed in the rotor 20 on its circumference (see FIGS FIGS. 1 and 3 ).
- the second securing bolt 86 has two spaced-apart recesses 118 and 120 (see, for example, the Figures 5 and 6 ).
- the coupling body 106 formed by the ball 108 is in the adjoining the head portion 114 first recess 118 of the second locking bolt 86 in and he is on the first locking pin 84 on the outside.
- a detent spring 122 is in the second recess 120 of the second locking bolt 86, a detent spring 122 into it.
- the detent spring 122 is then applied to a collar 124 between the first and the second recess 118 and 120 of the second locking bolt 86, so that in the in Figure 6 drawn unlocked position of the rotor 20, the manually adjusted position of the adjusting device 42 accordingly, in the "MV or OV position” can rotate.
- a spring-loaded pin element 126 is provided on the rotor 20, which in the "OV-focus” (see Figure 7 ) engages in a recess formed in the adjusting bolt 44 of the adjusting 42 slot recess 128. In this position, the "OV detonator" with the firing pin 14 congruent ie axially aligned positioned.
- the spring-loaded pin element 126 protrudes from the rotor 20 on the circumference.
- FIGS. 1 to 8 each with the same reference numerals, so that it is unnecessary, in conjunction with all figures to describe all the details in detail.
- the operation of the igniter 10 according to the invention is as follows:
- Igniter 10 is a mechanical rocket detonator constructed on the basis of a mortar fuse.
- the adjustment 42 allows a default and thus an optional Verschuß in the OV position as a highly sensitive Aufzungszünder without delay, which responds immediately after the focus, or a shoot in the MV position as Aufschlagzünder with a delay to strike through eg. Of coverings.
- the adjusting device 42 is designed as an adjusting bolt 44.
- the ignition chain 12 is interrupted in the assurance by the rotor 20, wherein the rotor 20 is secured by the two series-connected locking pins 84 and 86 and by the two locking levers 58 and 60.
- the igniter 10 has the required handling, transport, fire and VorrohrScience.
- the igniter 10 fulfills, for example, the provisions of STANAG 4187.
- the securing is positively secured by the second securing bolt 86 and by the two locking levers 58 and 60 in the rotor 20, which also guarantees that the rotor 20 can only be mounted in the securing position.
- the second securing bolt 86 is positively connected via the coupling body 106 formed as a ball 108 to the first securing bolt 84, wherein the first securing bolt 84 is held in the securing position by the bolt lever 100 and the associated bolt lever spring 104.
- the two locking levers 58 and 60 are prevented in the assurance by the spring element 74 at a pivoting and releasing the rotor 20.
- the firing pin 14 is secured in the igniter tip 26 and protrudes into the cover plate 30. In the assurance is located at this position in the rotor 20, the blind hole 36, so that in an unintentional impact of the igniter 10, neither of the two puncture detonators 52 or 54 can be initiated.
- the first securing bolt 84 moves against the associated bolt spring element 88 until it reaches its head portion 114 on the bolt lever 100 (see FIG Figure 5 ). Only when then the bolt lever 100 pivots out by the rotation of the rocket against the spring force of the pin lever spring 104, the first locking bolt 84 can continue to move against the associated bolt spring element 88, so that now the ball 108 in the tapered portion 112 of the first locking bolt 84th can move in (see Figure 6 ) and thus the second locking pin 86 releases, so that this can move by the upcoming axial acceleration against the associated bolt spring element 90 until the detent spring 122 bears against the back of the collar 124 of the second locking bolt 86, whereby the second locking pin 86 and the detent spring 122 are locked.
- the safety levers 58 and 60 pivot by the rotation of the rocket with their Einrastorganen 66 and 70 radially away from the rotor 20 and overcome centrifugal force the spring force of the spring element 74.
- the rotor 20 is now so released and rotates against the upcoming force of the counter-torsion 40th in focus.
- the rotational angle range of the rotor 20 is defined about its axis of rotation 38 and set in the desired position.
- the firing needle 14 is driven into the puncture detonator 52 or 54 selected before firing, and initiation of the firing chain 12 is initiated.
- the ignition chain 12 operates with a detonator delay time of 60 ⁇ 30 msec, so that coverages can be penetrated.
- the igniter chain 12 consists of two different detonators 52 and 54 on the piercing side.
- the OV detonator 52 is, for example, a DM 1019 detonator and the MV detonator is, for example, a DM detonator
- the ignition transformer 16 is, for example, an ignition transformer of the type DM 1015 B1
- the ignition amplifier 18 is, for example, an ignition amplifier of the type 586.00-55.00.
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
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Abstract
Description
Die Erfindung betrifft einen mechanischen Raketenzünder gemäß dem Oberbegriff des Anspruches 1.The invention relates to a mechanical rocket detonator according to the preamble of claim 1.
Aus der
Die
Die
Aus der
Bekannte Zünder, die MIL-STD und STANAG erfüllen, arbeiten mit WRG, d. h. mit einem Windgenerator, d. h. mit einem vom Fallwind angetriebenen Schärfmechanismus, und haben dadurch eine relativ geringe Zuverlässigkeit.Known detonators that meet MIL-STD and STANAG work with WRG, d. H. with a wind generator, d. H. with a powered by the falling wind sharpening mechanism, and thus have a relatively low reliability.
In Kenntnis dieser Gegebenheiten liegt der Erfindung die Aufgabe zugrunde, einen mechanischen Raketenzünder der eingangs genannten Art zu schaffen, der auf einem vorhandenen Mörserzünder basiert, aber über eine zuverlässigere Sicherungseinrichtung verfügt.In view of these circumstances, the invention has for its object to provide a mechanical rocket igniter of the type mentioned, which is based on an existing mortar fuse, but has a more reliable safety device.
Diese Aufgabe wird erfindungsgemäß durch die Merkmale des Anspruches 1 gelöst. Bevorzugte Aus- bzw. Weiterbildungen des erfindungsgemäßen mechanischen Raketenzünders sind in den Unteransprüchen gekennzeichnet.This object is achieved by the features of claim 1. Preferred embodiments or further developments of the mechanical rocket igniter according to the invention are characterized in the subclaims.
Die Erfindung weist den Vorteil auf, dass ein geschlossenes System realisiert wird, wobei durch zwei Zuhaltungen sowohl die Bedingungen nach MIL-STD als auch nach STANAG 4187 erfüllt werden.The invention has the advantage that a closed system is realized, whereby both conditions according to MIL-STD and STANAG 4187 are fulfilled by two tumblers.
Weitere Einzelheiten, Merkmale und Vorteile ergeben sich aus der nachfolgenden Beschreibung eines in der Zeichnung dargestellten Ausführungsbeispieles des erfindungsgemäßen mechanischen Raketenzünders.Further details, features and advantages will become apparent from the following description of an embodiment of the mechanical rocket igniter according to the invention shown in the drawing.
Es zeigen:
- Fig. 1
- eine Längsschnittdarstellung des Zünders in der Sicherstellung,
- Fig. 2
- eine Längsschnittdarstellung der Zünderbaugruppe des Zünders gemäß
Fig.1 (- entlang der abgewinkelten Schnittlinie II-II inFig.3 ), - Fig. 3
- einen Querschnitt entlang der Schnittlinie III-III in
Fig.2 , - Fig. 4
- einen Schnitt entlang der Schnittlinie C-C in
Fig.3 - zur Verdeutlichung insbesondere des gefederten Rastbolzens, - Fig. 5
- eine der
Fig.2 ähnliche Längsschnittdarstellung zur Verdeutlichung des Doppelbolzensystems im vorentsicherten Zustand, - Fig. 6
- eine der
Fig.5 ähnliche Längsschnittdarstellung zur Verdeutlichung des entsicherten Doppelbolzensystems, - Fig. 7
- teilweise aufgeschnitten eine Ansicht des Zünders in der "OV-Stellung", d.h. in der Scharfstellung ohne Verzögerung, und
- Fig. 8
- eine der
Fig.7 ähnliche Darstellung zur Verdeutlichung der "MV-Stellung", d.h. der Scharfstellung mit Verzögerung.
- Fig. 1
- a longitudinal sectional view of the igniter in the security,
- Fig. 2
- a longitudinal sectional view of the igniter assembly of the igniter according to
Fig.1 (- along the angled section line II-II inFigure 3 ) - Fig. 3
- a cross section along the section line III-III in
Fig.2 . - Fig. 4
- a section along the section line CC in
Figure 3 to clarify in particular the sprung locking bolt, - Fig. 5
- one of the
Fig.2 similar longitudinal sectional view to illustrate the double pin system in the pre-safe state, - Fig. 6
- one of the
Figure 5 similar longitudinal section to illustrate the unlocked double pin system, - Fig. 7
- partially cut open a view of the detonator in the "OV position", ie in the focus without delay, and
- Fig. 8
- one of the
Figure 7 similar representation to clarify the "MV position", ie the focus with delay.
Die Zündkette 12 weist einen Zündübertrager 16 und einen Zündverstärker 18 auf. Zwischen der Zündnadel 14 und dem Zündübertrager 16 der Zündkette 12 ist ein Rotor 20 vorgesehen, der mit einer Gegendrehfeder 40 (siehe
Zwischen dem Gehäuse 22 der Zünderbaugruppe 24 und der Zünderspitze 26 ist eine Deckplatine 30 festgelegt, in die die Zündnadel 14 in der Sicherstellung des Zünders mit ihrem Endabschnitt 32 hinein steht. Zu diesem Zwecke ist die Deckplatine 30 mit einem Durchgangsloch 34 ausgebildet. Der Rotor 20 ist mit einem Sackloch 36 ausgebildet, das in der Sicherstellung des Zünders mit dem Durchgangsloch 34 der Druckplatine 30 und somit mit der Zündnadel 14 axial fluchtet. Dadurch wird zuverlässig verhindert, dass bei einem unbeabsichtigten Aufschlag des Zünders eine Initiierung desselben erfolgt.Between the
Wie aus den
Die Verstelleinrichtung 42 weist einen Stellbolzen 44 auf, mit welchem die Zündverzugszeit des Zünders 10 wunschgemäß einstellbar ist. Zu diesem Zwecke ist der Stellbolzen 44 bspw. mit einer Rille 46 ausgebildet und das Gehäuse 22 der Zünderbaugruppe 24 mit einem Stift 48 versehen, der in die Rille 46 hineinsteht und die Verdrehung des Stellbolzens 44 um seine Längsmittelache 50 definiert - in der "OV-Stellung" oder der "MV-Stellung" - begrenzt.The adjusting
Der Rotor 20 ist mit einem Anstichdetonator 52 ohne Verzögerung, d.h. mit einem "OV-Detonator", und mit einem Anstichdetonator 54 mit Verzögerung, d.h. mit einem "MV-Detonator" versehen. Der "OV-Detonator" 52 und der "MV-Detonator" 54 sind von der Drehachse 38 des Rotors 20 radial gleich weit und in Umfangsrichtung des Rotors 20 voneinander beabstandet.The
Um den Rotor 20 in der Sicherstellung zu halten, ist ihm eine die Sicherstellung bestimmende Sicherungseinrichtung 56 zugeordnet, die einen ersten Sicherungshebel 58 und einen zweiten Sicherungshebel 60 aufweist (siehe
Damit der erste und der zweite Sicherungshebel 58 und 60 in der Sicherstellung mit ihren Einrastorganen 66, 70 in die zugehörigen Ausnehmungen 68, 72 des Rotors 20 hinein gezwängt werden, greift an den beiden Sicherungshebeln 58 und 60 ein Federelement 74 an, das als zweiarmige Schenkeldrehfeder ausgebildet ist. Der eine Schenkel 76 des Federelementes 74 greift an dem dem Einrastorgan 66 in Bezug zur Achse 72 gegenüberliegenden zweiten Endabschnitt 78 des ersten Sicherungshebels 58 an. Der zweite Schenkel 80 des Federelementes 74 greift an dem dem Einrastorgan 70 in Bezug zur Achse 64 gegenüberliegenden zweiten Endabschnitt des zweiten Sicherungshebels 60 an. Das Federelement 74 wirkt auf den ersten Sicherungshebel 58 im Uhrzeigersinn und auf den zweiten Sicherungshebel 60 im entgegengesetzten Uhrzeigersinn (siehe bspw. die
Die Sicherungseinrichtung 56 weist außerdem einen ersten Sicherungsbolzen 84 und einen zweiten Sicherungsbolzen 86 auf, die in axialer Richtung des Zünders 10 orientiert und voneinander radial beabstandet sind (siehe die
Wie bspw. aus
In der Sicherstellung des Zünders 10 (siehe
Wie aus den
Bevorzugt ist es jedoch, wenn der Kupplungskörper 106 als kleine Kugel 108 ausgebildet ist.However, it is preferred if the coupling body 106 is formed as a small ball 108.
Der erste Sicherungsbolzen 84 weist eine umlaufende Ausnehmung 110 mit einem sich konisch verjüngenden Abschnitt 112 und einen Kopf 114 auf, an dem der Bolzenhebel 100 in der Vorentsicherungsstellung (siehe
Der zweite Sicherungsbolzen 86 weist einen Kopfabschnitt 115 auf, der in der Sicherstellung des Zünders 10 in eine im Rotor 20 an dessen Umfang ausgebildete Ausnehmung 116 formschlüssig eingreift (siehe die
Der zweite Sicherungsbolzen 86 weist zwei voneinander beabstandete Ausnehmungen 118 und 120 auf (siehe bspw. die
Das gefederte Stiftelement 126 ragt aus dem Rotor 20 umfangsseitig heraus.The spring-loaded
Aus der Oberseite 130 des Rotors 20 ragt ein gefederter Rastbolzen 132 heraus, der in der "MV-Scharfstellung" des Rotors 20 (siehe
Gleiche Einzelheiten sind in den
Die Funktionsweise des erfindungsgemäßen Zünders 10 ist wie folgt:The operation of the
Bei dem Zünder 10 handelt es ich um einen mechanischen Raketenzünder, der auf der Basis eines Mörserzünders konstruiert ist. Die Verstelleinrichtung 42 erlaubt eine Voreinstellung und somit einen wahlweisen Verschuss in der OV-Stellung als hochempfindlicher Aufschlagzünder ohne Verzögerung, der nach erfolgter Scharfstellung sofort anspricht, oder einen Verschuss in der MV-Stellung als Aufschlagzünder mit einer Verzögerung zum Durchschlagen bspw. von Deckungen. Die Verstelleinrichtung 42 ist als Stellbolzen 44 ausgebildet.
Die Zündkette 12 ist in der Sicherstellung durch den Rotor 20 unterbrochen, wobei der Rotor 20 durch die beiden hintereinander geschalteten Sicherungsbolzen 84 und 86 und durch die beiden Sicherungshebel 58 und 60 gesichert ist. Dadurch besitzt der Zünder 10 die erforderliche Handhabungs-, Transport-, Beschuss- und Vorrohrsicherheit.The
Der Zünder 10 erfüllt bspw. die Vorschriften der STANAG 4187.The
In der Sicherstellung ist die Zündkette 12 durch die beiden nicht mit der Zündnadel 14 axial fluchtenden Anstichdetonatoren 52 und 54 im Rotor 20 pyrotechnisch unterbrochen. Die Sicherstellung ist durch den zweiten Sicherungsbolzen 86 und durch die beiden Sicherungshebel 58 und 60 im Rotor 20 formschlüssig gesichert, wodurch auch garantiert wird, dass der Rotor 20 nur in der Sicherstellung montiert werden kann. Der zweite Sicherungsbolzen 86 ist über den als Kugel 108 ausgebildeten Kupplungskörper 106 mit dem ersten Sicherungsbolzen 84 formschlüssig verbunden, wobei der erste Sicherungsbolzen 84 durch den Bolzenhebel 100 und die zugehörige Bolzenhebelfeder 104 in der Sicherstellung gehalten wird. Die beiden Sicherungshebel 58 und 60 werden in der Sicherstellung durch das Federelement 74 an einem Ausschwenken und Freigeben des Rotors 20 gehindert.To ensure the
Die Zündnadel 14 ist in der Zünderspitze 26 befestigt und ragt in die Deckplatine 30 hinein. In der Sicherstellung befindet sich an dieser Position im Rotor 20 das Sackloch 36, so dass bei einem unbeabsichtigten Aufschlag des Zünders 10 keiner der beiden Anstichdetonatoren 52 oder 54 initiiert werden kann.The
Die Einstellung einer wahlweisen Zündverzugszeit erfolgt für die OV-Stellung und die MV-Stellung durch den Stellbolzen 44 der Stelleinrichtung 42.The setting of an optional Zündverzugszeit takes place for the OV position and the MV position by the adjusting
Zur Scharfstellung bewegt sich durch die beim Abschuss anstehende axiale Beschleunigung der erste Sicherungsbolzen 84 gegen das zugehörige Bolzenfederelement 88 bis sein Kopfabschnitt 114 am Bolzenhebel 100 anliegt (siehe
In der OV-Stellung rastet das am Umfang des Rotors 20 angebrachte gefederte Stiftelement 126 in den Schlitz 128 des Stellbolzens 44 ein und der OV-Detonator 52 befindet sich mit der Zündnadel 14 axial in Fluchtung.In the OV position, the spring-mounted on the circumference of the
Beim Zielaufschlag wird durch Verformung der Zünderspitze 26 die Zündnadel 14 in den vor dem Abschuss gewählten Anstichdetonator 52 oder 54 getrieben und die Initiierung der Zündkette 12 eingeleitet. Bei einer MV-Einstellung des Zünders 10 arbeitet die Zündkette 12 bspw. mit einer Detonator-Zündverzugszeit von 60 ± 30 msec, so dass Deckungen durchschlagen werden können.At the target impact, by firing the
Die Zündkette 12 besteht an der Anstichseite aus zwei verschiedenen Detonatoren 52 und 54. Bei dem OV-Detonator 52 handelt es sich bspw. um einen Detonator des Typs DM 1019 und bei dem MV-Detonator handelt es sich bspw. um einen Detonator des Typs DM 1344.Der Zündübertrager 16 ist bspw. ein Zündübertrager des Typs DM 1015 B1 und bei dem Zündverstärker 18 handelt es sich bspw. um einen Zündverstärker des Typs 586.00-55.00.The
- 1010
- Zünderfuze
- 1212
- Zünderkette (von 10)Igniter Chain (from 10)
- 1414
- Zündnadel (von 10 für 12)Firing pin (from 10 to 12)
- 1616
- Zündübertrager (von 12)Ignition transformer (from 12)
- 1818
- Zündverstärker (von 12)Ignition Amplifier (from 12)
- 2020
- Rotor (zwischen 14 und 12)Rotor (between 14 and 12)
- 2222
- Gehäuse (von 24)Housing (from 24)
- 2424
- Zündbaugruppe (von 10)Ignition Assembly (of 10)
- 2626
- Zünderspitze (von 10 an 24)Ignition tip (from 10 to 24)
- 2828
- Verschraubung (von 26 und 22)Screw connection (from 26 and 22)
- 3030
- Deckplatine (zwischen 22 und 26)Cover board (between 22 and 26)
- 3232
- Endabschnitt (von 14)End section (from 14)
- 3434
- Durchgangsloch (in 30 für 14)Through hole (in 30 for 14)
- 3636
- Sackloch (in 20 für 32)Blind hole (in 20 for 32)
- 3838
- Drehachse (von 20)Rotation axis (from 20)
- 4040
- Gegendrehfeder (für 20)Counter-rotating spring (for 20)
- 4242
- Stelleinrichtung (von 10 für 52, 54)Actuator (from 10 for 52, 54)
- 4444
- Stellbolzen (von 42)Adjusting bolt (from 42)
- 4646
- Rille (in 44)Groove (in 44)
- 4848
- Stift (von 22)Pen (from 22)
- 5050
- Längsmittelachse (von 48)Longitudinal central axis (from 48)
- 5252
- Anstichdetonator OV (von 20)Puncture detonator OV (from 20)
- 5454
- Anstichdetonator MV (von 20)Puncture detonator MV (from 20)
- 5656
- Sicherungseinrichtung (von 10 für 20)Safety device (from 10 to 20)
- 5858
- erster Sicherungshebel (von 56)first safety lever (from 56)
- 6060
- zweiter Sicherungshebel (von 50)second safety lever (from 50)
- 6262
- Achse (von 58)Axis (from 58)
- 6464
- Achse (von 60)Axis (from 60)
- 6666
- Einrastorgan (von 58 für 68)Latching element (from 58 for 68)
- 6868
- Ausnehmung (in 20 für 66)Recess (in 20 for 66)
- 7070
- Einrastorgan (von 60 für 72)Latching organ (from 60 for 72)
- 7272
- Ausnehmung (in 20 für 70)Recess (in 20 for 70)
- 7474
- Federelement (für 58 und 60)Spring element (for 58 and 60)
- 7676
- erster Schenkel (von 74)first thigh (from 74)
- 7878
- zweiter Endabschnitt (von 58)second end section (from 58)
- 8080
- zweiter Schenkel (von 74)second leg (from 74)
- 8282
- zweiter Endabschnitt (von 60)second end section (from 60)
- 8484
- erster Sicherungsbolzen (von 56)first safety bolt (from 56)
- 8686
- zweiter Sicherungsbolzen (von 56)second safety bolt (from 56)
- 8888
- Bolzenfederelement (für 84)Bolt spring element (for 84)
- 9090
- Bolzenfederelement (für 86)Bolt spring element (for 86)
- 9292
- Sackloch (in 22 für 86 und 90)Blind hole (in 22 for 86 and 90)
- 9494
- Sackloch (in 22 für 86 und 90)Blind hole (in 22 for 86 and 90)
- 9696
- Loch (in 30 für 84)Hole (in 30 for 84)
- 9898
- Ausnehmung (in 30 für 86)Recess (in 30 for 86)
- 100100
- Bolzenhebel (für 84)Bolt lever (for 84)
- 102102
- Achse (von 100)Axis (from 100)
- 104104
- Bolzenhebelfeder (für 100)Bolt lever spring (for 100)
- 106106
- Kupplungskörper (zwischen 84 und 86)Coupling body (between 84 and 86)
- 108108
- Kugel (von 106)Ball (of 106)
- 110110
- Ausnehmung (von 84)Recess (from 84)
- 112112
- konisch verjüngter Abschnitt (von 110)conically tapered section (from 110)
- 114114
- Kopfabschnitt (von 86)Head section (from 86)
- 115115
- Kopfabschnitt (von 84)Head section (from 84)
- 116116
- Ausnehmung (in 20 für 86)Recess (in 20 for 86)
- 118118
- erste Ausnehmung (in 86)first recess (in 86)
- 120120
- zweite Ausnehmung (in 86)second recess (in 86)
- 122122
- Rastfeder (für 86)Detent spring (for 86)
- 124124
- Bund (zwischen 118 und 120 für 122)Fret (between 118 and 120 for 122)
- 126126
- gefedertes Stiftelement (von 20 für 128)spring loaded pin element (from 20 for 128)
- 128128
- Schlitzausnehmung (in 44 für 126)Slot recess (in 44 for 126)
- 130130
- Oberseite (von 20)Top (from 20)
- 132132
- gefederter Rastbolzen (von 20 an 130)spring-loaded stop pins (from 20 to 130)
Claims (15)
- Mechanical rocket fuze having a firing chain (12) which can be initiated by means of a firing needle (14) and has a firing relay (16) and a firing booster (18),
characterized in thata) a rotor (20) is provided between the firing needle (14) and the firing relay (16), is connected to an opposing rotary spring (40) and can be moved about a rotation axis (38) from a safe position, which keeps the firing chain (12) interrupted, by firing and spinning, against the spring force of the opposing rotary spring (40) to an armed position which enables the firing chain (12) with a manually adjustable adjusting device (42) being provided for defined limiting of the rotation angle range of the rotor (20) about its rotation axis (38), and therefore for selective positioning of the rotor (20) in an armed position without a delay ("OV position") or in an armed position with a delay ("MV position"),b) the rotor (20) is associated with a safety and arming device (56), which governs the safe position and has a first and a second safety lever (58, 60), each of which are mounted such that they can pivot about an associated axially oriented axis (62, 64) and which, in the safe position, each have a latching member (66, 70) which engages by means of a spring element (74) in an associated recess (68, 72) in the rotor (20) andc) the safety and arming device (56) has a first and a second safety bolt (84, 86), which are oriented in the axial direction and are separated from one another, and each of which is associated with a bolt spring element (88, 90), with a bolt lever (100), which can pivot about an axially oriented axis as a result of rotation of a rocket, acting by means of a bolt lever spring (104) on the first safety bolt (84) when in the safe position. - Mechanical rocket fuze according to Claim 1,
characterized in that
the adjusting device (42) has an adjusting bolt (44). - Mechanical rocket fuze according to Claim 1 or 2,
characterized in that
the rotor (20) has a piercing detonator (52) without a delay ("OV detonator") and a piercing detonator (54) with a delay ("MV detonator"), which are separated radially by the same distance from the rotation axis (38) of the rotor (20), and are separated from one another in the circumferential direction. - Mechanical rocket fuze according to one of the preceding claims,
characterized in that
the safety levers (58, 60) are each in the form of twoarmed safety levers, with the latching member (66, 70) being formed at one end of the respective safety lever (58, 60), and with a rotating spring clip, which forms the spring element (74), being forced against the opposite second end sections (78, 82) of the two safety levers (58, 60). - Mechanical rocket fuze according to one of the preceding claims,
characterized in that
a coupling body (106) is provided between the first and the second safety bolts (84, 86). - Mechanical rocket fuze according to Claim 5, characterized in that
the coupling body (106) is formed by a ball (108). - Mechanical rocket fuze according to one of the preceding claims,
characterized in that
the first safety bolt (84) has a recess (110) in which the bolt lever (100) engages in an interlocking manner when in the safe position. - Mechanical rocket fuze according to one of the preceding claims,
characterized in that
the bolt spring element (88, 90) which is associated with the respective safety bolt (84, 86) is formed by a helical compression spring. - Mechanical rocket fuze according to one of the preceding claims,
characterized in that
the bolt lever spring (104) is formed by a rotating spring clip. - Mechanical rocket fuze according to one of Claims 5 to 9,
characterized in that
the second safety bolt (86) has a head section (115), which engages in an interlocking manner in a recess (116) which is formed in the rotor (20), when in the safe position, and has two recesses (118, 120), which are axially separated from one another, with the coupling body (106) projecting into the first recess (118), which is adjacent to the head section (115), of the second safety bolt (86) when in the safe position, and resting on the first safety bolt (84). - Mechanical rocket fuze according to Claim 10,
characterized in that
a latching spring (122) is provided, which projects into the second recess (120) in the second safety bolt (86) when in the safe position, and rests on a collar (124) between the first and the second recesses (118, 120) in the second safety bolt (86) when in the armed position. - Mechanical rocket fuze according to one of the preceding claims,
characterized in that
a sprung latching bolt (132) is provided on the rotor (20) and latches into a latching hole, which is formed in a cover plate (30) adjacent to the rotor (20), when the rotor (20) is in the MV position, in order to position the MV detonator (54) to be coincident with the firing needle (14). - Mechanical rocket fuze according to Claim 12,
characterized in that
the sprung latching bolt (132) projects out of the upper face (130), which faces the cover plate (30), of the rotor (20). - Mechanical rocket fuze according to one of Claims 2 to 13,
characterized in that
a sprung pin element (126) is provided on the rotor (20) and latches into a slot recess (128), which is formed in the adjusting bolt (44) of the adjusting device (42), when the rotor (20) is in the OV position, in which the OV detonator (52) is positioned to be coincident with the firing needle (14). - Mechanical rocket fuze according to Claim 14,
characterized in that
the sprung pin element (126) projects out of the circumference of the rotor (20).
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102006008809A DE102006008809B4 (en) | 2006-02-25 | 2006-02-25 | Mechanical rocket detonator |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1826527A1 EP1826527A1 (en) | 2007-08-29 |
EP1826527B1 true EP1826527B1 (en) | 2011-11-23 |
Family
ID=38066694
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP07002490A Not-in-force EP1826527B1 (en) | 2006-02-25 | 2007-02-06 | Mechanical rocket fuse |
Country Status (4)
Country | Link |
---|---|
EP (1) | EP1826527B1 (en) |
AT (1) | ATE534883T1 (en) |
CL (1) | CL2007000484A1 (en) |
DE (1) | DE102006008809B4 (en) |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
KR20100105611A (en) * | 2007-11-28 | 2010-09-29 | 사우디 아라비안 오일 컴퍼니 | Process to upgrade highly waxy crude oil by hot pressurized water |
DE102007060567B4 (en) | 2007-12-15 | 2009-08-27 | Junghans Microtec Gmbh | Safety device for an igniter of a projectile |
DE102008053990B4 (en) * | 2008-10-30 | 2010-07-22 | Junghans Microtec Gmbh | Igniter for a projectile |
US8394260B2 (en) | 2009-12-21 | 2013-03-12 | Saudi Arabian Oil Company | Petroleum upgrading process |
US9382485B2 (en) | 2010-09-14 | 2016-07-05 | Saudi Arabian Oil Company | Petroleum upgrading process |
DE102022106883A1 (en) | 2022-03-23 | 2023-09-28 | Rheinmetall Air Defence Ag | Fuse unit for a detonator, use of the fuse unit and method for activating a detonator with this fuse unit |
CN115077310B (en) * | 2022-06-30 | 2024-08-16 | 江苏永康智能防务科技股份有限公司 | Multi-insurance fuming fuze |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2537855A (en) * | 1944-06-09 | 1951-01-09 | Henry H Porter | Point contact fuse |
US2664822A (en) * | 1950-01-03 | 1954-01-05 | Frank B Hale | Fuze |
DE1135798B (en) * | 1958-06-14 | 1962-08-30 | Industrial Holding Ets | Igniter for bullets without twist |
DE1082164B (en) * | 1958-08-22 | 1960-05-19 | E H Helmut Junghans Dr Ing | Impact fuse with and without delay for twistless projectiles, especially throwing mines |
GB944164A (en) * | 1960-02-17 | 1963-12-11 | Junghans Geb Ag | Percussion fuze with or without delay mechanism for unrotated projectiles, more especially mortar bombs |
BE711656A (en) | 1967-03-31 | 1968-07-15 | ||
CH525465A (en) * | 1970-06-26 | 1972-07-15 | Oerlikon Buehrle Ag | Impact fuse for projectiles |
US3721195A (en) * | 1971-06-01 | 1973-03-20 | Honeywell Inc | Liquid revolution counter for fuze arming |
DE3015424A1 (en) * | 1980-04-22 | 1981-10-29 | Diehl GmbH & Co, 8500 Nürnberg | Spin-less missile fuse safety device - has rotor recesses for recoil bolts and spring-loaded double-armed catch |
SE442446B (en) * | 1980-09-25 | 1985-12-23 | Bofors Ab | TENDROR CIRCUIT WITH TWO RESTRICTIONS WITH PREDICTED TIMELINE FOR TRANSMISSION |
DE3742575A1 (en) | 1987-12-16 | 1989-07-06 | Junghans Gmbh Geb | ZENDER |
-
2006
- 2006-02-25 DE DE102006008809A patent/DE102006008809B4/en not_active Expired - Fee Related
-
2007
- 2007-02-06 EP EP07002490A patent/EP1826527B1/en not_active Not-in-force
- 2007-02-06 AT AT07002490T patent/ATE534883T1/en active
- 2007-02-22 CL CL2007000484A patent/CL2007000484A1/en unknown
Also Published As
Publication number | Publication date |
---|---|
EP1826527A1 (en) | 2007-08-29 |
DE102006008809B4 (en) | 2008-04-24 |
DE102006008809A1 (en) | 2007-08-30 |
ATE534883T1 (en) | 2011-12-15 |
CL2007000484A1 (en) | 2009-03-27 |
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