EP2071274A2 - Safety device for a projectile fuse - Google Patents

Abstract

The device has an ignition unit for transmitting ignition energy to another ignition unit, and a rotor (60) for interrupting the transmission of the ignition energy. The rotor is locked in a locking condition of a safety unit (62), which is provided to an unlocking action due to a physical unlocking parameter i.e. apogee parameter. The safety unit senses the apogee parameter, which is caused by fly through of a projectile over an apogee of a projectile trajectory. A locking unit (66) mechanically blocks the unlocking action in a safety location. The apogee parameter is selected from force, direction change of the projectile, lateral acceleration of the fuse, minimum in a longitudinal acceleration of the fuse, velocity of the projectile, or a direction of earth's magnetic field of the fuse.

Description

The invention relates to a safety device for a detonator of a projectile, comprising an ignition means for transmitting ignition energy to another ignition means and a barrier for interrupting the transmission, which is locked in a locked state by a securing means, which is provided for an unlocking action due to a physical Entsicherungsparameters ,

A safety device for an igniter is used to prevent inadvertent activation of a main charge of a projectile, but an activation of the main charge after a release should be possible. The safety device is part of a detonator for igniting the main charge, which is provided with a detonating chain of two or more ignition means. To ignite the main charge, first the first ignition means is activated, e.g. a puncture-sensitive mini-detonator that is pierced by a puncture needle. Explosive energy of the first ignition means is transmitted by a corresponding arrangement of the first two ignition means to the second ignition means, which may be designed as a booster. This can transfer its explosive energy to an initial charge or main charge.

Previous detonators, especially simple projectiles, such as mortar shells, have as a first securing means a Vorstecker and second securing means on a device which detects the launch shock. The disadvantage of this securing means is that before loading the mortar shell, the Vorstecker must be pulled manually. Relatively often it happens that the pulling of the Vorsteckers is forgotten and the mortar shell becomes a dud.

It is an object of the present invention to provide a safety device for a detonator of a projectile, which uses a physical Entsicherungsparameter independent of a launch parameter for unlocking the securing means without a Vorstecker must be pulled.

This object is achieved by a safety device of the type mentioned, in which the Entsicherungsparameter is a Apogäumparameter, which is caused by the flying through of the projectile through the apogee of a projectile trajectory. It exploits a parameter which is independent of a launch parameter and which, in conjunction with the use of the launch parameter, can provide high security against unwanted firing.

The invention is particularly suitable for projectiles designed as mortar shells. Mortars are usually fired at an angle of> 45 ° to the horizontal, whereby the course of the trajectory is approximately characterized by a parabolic flight, which has a pronounced reversal point in apogee. An effect of the reversal point on a bullet passing the reversal point can be used as an apogee parameter.

The apogee parameter is a parameter that allows recognition of a passage of the projectile through the apogee. Expediently, the use as a release parameter presupposes that the apogee parameter is scanned by the securing means or otherwise evaluated in such a way that the traversing of the apogee is at least implicitly recognized. The apogee parameter may be a course of velocity or deceleration and / or rotation of the projectile about an axis transverse to the direction of flight. The rotation may be due to inertia or other parameters, e.g. a magnetic field direction, are detected. Also, a profile of a height of the igniter above a reference, e.g. the soil, can be an apogee parameter. Since the presence of the apogee parameter indicates that the projectile is far away from the launcher, high pre-pipe safety can be achieved. Other arming parameters may be an acceleration, a spin, a dynamic pressure, a time after a launch or an impact pressure.

The barrier serves to receive and / or redirect ignition energy of the first ignition means such that ignition of the second ignition means is reliably prevented by ignition energy of the first ignition means. In addition to the securing means is advantageously provided by the first independent second securing means which locks the barrier. The two securing means are expediently provided for unlocking due to two independent physical arming parameters. The securing means - expediently both securing means - is used for the particular mechanical locking of the barrier such that, for example, a movement of the barrier from its securing in the armed position is reliably prevented. By unlocking the barrier can be released from the corresponding securing means in such a way that it is movable in the focus, either for example, by inertia independently, or powered by a means of movement.

In an advantageous embodiment of the invention, the apogee parameter is a force. A force can simply be sampled and the presence of the apogee parameter can be easily detected.

The securing means may be robust and susceptible to interference when intended for mechanical scanning of the apogee parameter.

Advantageously, the securing means comprises a locking means, which triggers an unlocking action by changing its position in the igniter when passing through the apogee. The securing means can be easily manufactured in this way. With the same advantage, the locking means in its securing position advantageously mechanically locks an unlocking action.

A simple scanning of the Apogäumparameters can be achieved if the locking means is provided for the position change by its inertia. The locking means is advantageously a piece of metal, in particular a piece of shear metal, which reacts particularly fine on acceleration due to its high specific gravity.

If the locking means releases an unlocking space due to its change in position, into which part of a bolt for carrying out the unlocking action can be introduced, locking and unlocking can be achieved easily.

In a further embodiment of the invention, the securing means comprises a magnet, which triggers an unlocking action by changing its position in the igniter when passing through the apogee. It can be a mechanical step at one Entriegelaktion be achieved by a magnetically effected step, whereby an unlocking mechanism can be kept simple.

In order to avoid unwanted and premature unlocking of the securing means, the securing means for unlocking by the presence of the Apogäumparameters expediently requires a previous unlocking, which is dependent on another Entsicherungsparameter

A security against unintentional unlocking of the second securing means can be further increased if the unlocking of the securing means is blocked by another securing means. The unlocking of the securing means can be carried out, for example, only if an unlocking action has previously been carried out. Appropriately, this is the Entsicherungsparameter effected by a launch of the projectile. Thus, the securing means can unlock only after the bullet has been fired.

A particularly reliable further securing means is a mechanical double-bolt system which unlocks by a launch acceleration.

A reliably acting barrier can be achieved if the barrier is a rotor and the second securing means is provided for locking the rotor.

In apogee, the projectile reaches the vertex of its trajectory. By the shaping of a projectile, if necessary in addition by a rear rudder, the projectile changes in the vertex its orientation and lowers the igniter down to the earth. This change in direction can be reliably used as an apogee parameter.

If the securing means is clearly in front of e.g. Arranged by air resistance fulcrum of the projectile, so is caused by the change in direction a slight transverse acceleration transverse to the direction of flight of the projectile. This lateral acceleration can be sensed mechanically or electronically as a feature of the change in direction and used as an apogee parameter.

Another characteristic of the railway vertex is a minimum in the speed of a steeply fired projectile. Since the projectile experiences during its flight a braking acceleration, which by the of Projectile caused air resistance, this braking acceleration is the lowest at minimum speed. The minimum speed is reached at the apex - or because of a general deceleration of the projectile during the flight shortly thereafter, when the acceleration of the fall compensates the general deceleration. When this minimum acceleration is sensed, a minimum in longitudinal acceleration of the detonator around the vertex can be used as the apogee parameter.

A velocity of the projectile can also be used as an apogee parameter if it is measured by an evaluation means around the apogee and the velocity minimum is recognized. Appropriately, the evaluation is an electronic evaluation.

In particular, for detecting and evaluating particularly small forces, an electrical or electronic sensor may be advantageous. Since its evaluation requires an electronic evaluation means, when using such a sensor, there is already a corresponding evaluation means, which in this case can also control an unlocking. An unlocking of the second securing means is expediently controlled electronically.

In particular, when using an electronic evaluation means, the direction of the earth's magnetic field can be measured relative to an igniter direction and it can be concluded that a change in direction of the projectile. If the change in direction per unit of time reaches a maximum, the projectile has reached or just exceeded the apogee. The use of the direction of the earth's magnetic field relative to an igniter direction and / or its change in direction can hereby be reliably measured and used as an apogee parameter, in particular by an electronic evaluation means which is prepared accordingly.

The invention will be explained in more detail with reference to exemplary embodiments, which are illustrated in the drawings.

Show it:

Fig. 1

a schematic representation of a trajectory of a projectile and an apogee,

Fig. 2

Accelerations in the projectile upon reaching the apogee,

Fig. 3

a diagram in which longitudinal accelerations of the projectile are plotted over a time of flight,

Fig. 4

an igniter in a sectional view with a securing means for sensing an apogee parameter,

Fig. 5

the detonator Fig. 4 in a secured state,

Fig. 6

a rotor of another igniter in a locked position,

Fig. 7

off the rotor Fig. 6 in a partially unlocked position,

Fig. 8

off the rotor Fig. 6 in a further unlocked position and

Fig. 9

off the rotor Fig. 6 in a fully unlocked position.

Fig. 1 shows a trajectory 2 a projectile 4 with an igniter 6. After the launch of the projectile 4, it travels through a web which is ideally a parabola and deviates somewhat from the parabolic trajectory by a frictional resistance in the air. In flight on a parabolic trajectory, all elements of the projectile 4 are equally affected by gravity, so that all elements are accelerated equally to Earth. In the reference system of projectile 4, therefore, during flight all the elements are without acceleration and thus weightless.

• bewirkt durch die Form des Geschosses 4 und ggf. unterstützt durch ein Leitwerk - von einer nach oben gerichteten Ausrichtung in eine nach unten gerichtete Ausrichtung bewegt wird. Diese Richtungsänderung bewirkt im Zünder 6 eine Beschleunigung, die Abhängig ist von der Position des Geschosses 4 auf seiner Flugbahn. Im Apogäum 8 ist diese Beschleunigung am größten. Ist der Umkehrpunkt bzw. die Krümmung der Flugbahn 2 im Apogäum 8 besonders ausgeprägt, z.B. durch einen steilen Abschusswinkel von über 45° zur Erdoberfläche, kann die Beschleunigung in einem Bereich 10 um das Apogäum 8 gut detektiert und ausgewertet werden.
  In Fig. 2 sind Beschleunigungen dargestellt, die während des Flugs - zusätzlich zu der Gravitationsbeschleunigung - auf das Geschoss 4 und seine Elemente wirken. Durch die Richtungsänderung des Geschosses 4 im Apogäum 8 bzw. im Bereich 10 um das Apogäum 8 herum wird das Geschoss 4 in einer Rotationsrichtung 12 rotiert, so dass in einer Entfernung von einem Drehpunkt 14 bzw. Drehachse eine Querbeschleunigung 16 auf Elemente des Geschosses 4 wirkt, insbesondere auf Elemente des Zünders 6, der weit vom Drehpunkt 14 entfernt ist. Außerdem wird das Geschoss 4 durch Luftwiderstand in seinem Flug gebremst, so dass auf seine Elemente eine Längsbeschleunigung 18 wirkt, die nach hinten gerichtet ist.
  Die Längsbeschleunigung 18 ist in Fig. 3 in einem Diagramm als Beschleunigung a über die Flugzeit t aufgetragen. Die Beschleunigung a ist in Bezug zum Geschoss 4 nach hinten gerichtet. Beim Abschuss des Geschosses 4 wirkt eine sehr starke Beschleunigung nach vorne auf das Geschoss 4, die in Fig. 3 nach unten angedeutet ist. Sehr schnell nach Verlassen des Abschussrohres wird das Geschoss 4 abgebremst und die in Fig. 3 aufgetragene Beschleunigung a wird positiv und nimmt ein Maximum ein, da das Geschoss 4 zu Beginn seines Flugs die größte Geschwindigkeit und damit den größten Luftwiderstand hat. Da der Luftwiderstand proportional zur Geschwindigkeit des Geschosses 4 ist, entsprechen die in Fig. 3 dargestellten Kurven auch der Geschwindigkeit des Geschosses 4.
  Die unterste Kurve stellt die Längsbeschleunigung 18 in einem senkrechten Flug dar, in dem das Geschoss 4 am oberen Umkehrpunkt zum Stillstand kommt bevor es wieder nach unten fällt. Die mittlere Kurve wird bei einem steilen Abschuss, z.B. von 50° erreicht und die oberste Kurve bei einem flachen Abschuss. Je steiler der Abschuss ist, desto ausgeprägter ist die Änderung der Beschleunigung im Apogäum 8 oder im Bereich 10, der in Fig. 3 als zeitlicher Bereich zwischen den Zeitpunkten t₁ und t₂ durch eine gestrichelte Linie dargestellt ist. Die Änderung der Beschleunigung ist in der Krümmung der Kurven in Fig. 3 dargestellt. Zum Zeitpunkt t₃ erreicht das Geschoss 4 den Boden und wird durch den Aufschlag extrem nach hinten beschleunigt, was in Fig. 3 durch den nach oben gerichteten Pfeil angedeutet ist.
  Fig. 4 zeigt den Zünder 6 in einer vereinfachten Schnittdarstellung. Der Zünder 6 ist als Aufschlagzünder ausgeführt. Der Zünder 6 umfasst ein Gehäuse 20 aus zwei Teilen 22, 24, dessen unterer Teil 24 in den Rumpf des Geschosses 4 eingeschraubt wird und der eine Übertragungsladung 26 aufweist. Diese wird von einem in Fig. 5 dargestellten Zündmittel 58 gezündet, das in einem Rotor 28 angeordnet ist, und dessen Zündenergie in einer entsicherten Stellung des Rotors 28 durch einen Kanal 30 auf die Übertragungsladung 26 übertragen wird.
  In Fig. 4 ist der Rotor 28 in seiner gesicherten Stellung dargestellt. In dieser Stellung wird er durch ein schematisch angedeutetes Sicherungsmittel 32 gehalten, das ein Doppelbolzensystem mit zwei Sicherungsbolzen ist, das in der EP 1 826 527 A1 detailliert dargestellt und beschrieben ist, auf die hiermit explizit Bezug genommen wird. Dieses Doppelbolzensystem arretiert den Rotor 28 in seiner gesicherten Stellung. Die Arretierung wird durch die Abschussbeschleunigung entriegelt. Zusätzlich bleibt der Rotor 28 durch einen Riegel 34 in seiner Sicherstellung arretiert, die in eine Öffnung 36 des Rotors 28 eingreift. Der Riegel 34 ist gleichzeitig die Anstichnadel des Zünders 6. Der Riegel 34 ist wiederum durch ein zweites Sicherungsmittel 38 in ihrer gesicherten Stellung arretiert, das mit einem Riegelmittel 40 in Form eines Bolzens in eine Ausnehmung 42 des Riegels 34 eingreift.
  Das zweite Sicherungsmittel 38 umfasst außerdem ein Auswertemittel 44 und einen Sensor 46, der einen Fühler 48 und ein Erfassungsmittel 50 aufweist. Der Fühler 48 ist ein Stück elastisches Schwermetall, das durch eine Längsbeschleunigung 18 eine durch einen Doppelpfeil angedeutete Kraft erfährt, die es durch eine entsprechende Lagerung im Erfassungsmittel 50 verstärkt auf das Erfassungsmittel 50 überträgt. Die Kraft wird vom Erfassungsmittel 50 erfasst und vom Auswertemittel 44 ausgewertet, das hierzu eine Energiequelle 52 aufweist, die aus Flüssigkeiten, die durch den Abschussschock gemischt werden und dann elektrische Energie für eine kurze Weile freigeben, während des Flugs Energie bezieht. Da beim Abschuss eine sehr hohe Kraft nach unten bzw. hinten auf den Fühler 48 wirkt, ist in einem geringen Abstand vom Fühler 48 eine Stufe 54 in das Teil 22 eingearbeitet, auf der sich der Fühler 48 während des Abschussschocks abstützen kann. Um hierbei nicht zu verbiegen, ist der Fühler 48 ausreichend elastisch ausgeführt, so dass er sich nach dem Abschussschock selbständig wieder von der Stufe 54 entfernt und zur Messung der Kraft zur Verfügung steht.
  Das Auswertemittel 44 wertet den Verlauf der Kraft auf den Fühler 48 auf ein Minimum aus. Diese beruht auf dem Geschwindigkeitsminimum im Apogäum 8 und dem damit verbundenen geringsten Luftwiderstand. Ein Rauschen im Verlauf, das durch Schwingungen des Geschosses 4 während des Flugs erzeugt werden kann, wird hierbei vom Auswertemittel 44 unterdrückt bzw. nicht ausgewertet. Ist das Minimum erkannt, wird das Riegelmittel 40 durch einen Mikromotor aus der Ausnehmung 42 herausgezogen. Durch diese Entriegelaktion wird das Sicherungsmittel 38 entsichert und den Riegel 34 freigegeben, die durch eine Feder 56 nach vorn getrieben wird, so dass ihre Spitze aus der Öffnung 36 gezogen wird. Nun ist der Rotor 28 vollständig entriegelt und wird motor- oder federgetrieben in seine Scharfstellung gedreht.
  Die Scharfstellung ist in Fig. 5 dargestellt. Das Zündmittel 58 ist so ausgerichtet, dass es in Anstichrichtung der Anstichnadel liegt und auf den Kanal 30 und die Übertragungsladung 26 ausgerichtet ist. Bei einem Aufschlag des Geschosses 4 wird die Anstichnadel nach hinten gedrückt, sticht das Zündmittel 58 an, dieses zündet und setzt Zündenergie frei, die auf die Übertragungsladung 26 trifft und diese zündet. Die Übertragungsladung 26 zündet wiederum eine Hauptladung des Geschosses 4.
  Anstelle des Fühlers 48 kann der Sensor 46 ein Mittel zum Bestimmen eines Winkels zwischen der Richtung des Erdmagnetfelds und einer Richtung des Zünders 6 aufweisen. Hierfür kann der Sensor 46 einen ein Stück magnetisiertes oder nicht magnetisiertes ferromagnetisches Metall umfassen, auf den das Erdmagnetfeld eine Kraft ausübt. Die Kraft und/oder die Richtung der Kraft kann erfasst und als mit dem Winkel in Verbindung stehende Größe ausgewertet werden. Das Auswertemittel 44 ist dann zum Bestimmen eines Maximums der Geschwindigkeit der zeitlichen Änderung des Winkels vorbereitet und detektiert so das Apogäum 8. Die entsprechende Kraft, der Winkel oder seine Änderungsgeschwindigkeit bildet dann den Apogäumparameter.
  In den Figuren 6 bis 9 ist ein anderer Rotor 60 für einen ansonsten nicht dargestellten Zünder gezeigt, der als Aufschlagzünder wie Zünder 6 oder als Zeitzünder ausgeführt sein kann. Die nachfolgende Beschreibung beschränkt sich im Wesentlichen auf die Unterschiede zum Ausführungsbeispiel in den Figuren 4 und 5, auf das bezüglich gleich bleibender Merkmale und Funktionen verwiesen wird. Im Wesentlichen gleich bleibende Bauteile sind grundsätzlich mit den gleichen Bezugszeichen beziffert.
  Der Rotor 60 beherbergt ein Sicherungsmittel 62, das in Verbindung mit einem anderen, nicht dargestellten Sicherungsmittel 32 den Rotor 60 freigibt. Das andere Sicherungsmittel 32 kann ein Doppelbolzensystem sein, das den Rotor 60 verriegelt. Das Sicherungsmittel 62 umfasst einen Riegel 64 in Form eines Bolzens, der in eine entsprechende Ausnehmung im zweiten Teil 24 des Gehäuses 20 eingreift und den Rotor 60 auch nach Entriegeln des anderen Sicherungsmittels 32 im Gehäuse 20 arretiert hält. Das Sicherungsmittel 62 umfasst außerdem eine Kugel als Riegelmittel 66 und zwei Haltemittel 68, 70, die die Kugel von zwei gegenüberliegenden Seiten halten.
  Die Kugel ist lose zwischen dem Riegel 64 und einem weiteren Bolzen 72 gehalten, wobei ein kleines Spiel zwischen Kugel und Riegel 64, 72 ist, so dass die Kugel nicht eingeklemmt wird. Sie ruht in einer schalenförmigen Vertiefung des Haltemittels 68, auch dort mit etwas Spiel, und ist durch das Zusammenwirken von Haltemittel 68 und Riegel 64, 72 leicht beweglich in ihrer Arretierposition gehalten, die ein Herausbewegen des Riegels 64 aus der Ausnehmung im zweiten Teil 24 des Gehäuses 20 verhindert.
  Fig. 7 zeigt den Rotor 60 bei einem Abschuss des Geschosses 4. Das nicht dargestellte andere Sicherungsmittel 32 entriegelt und gibt eine Arretierung des Rotors 60 frei, der jedoch weiterhin durch den Riegel 64 in seiner Sicherstellung arretiert bleibt. Durch den Abschussschock wird auch das unter Haltemittel 68 gegen eine Feder 74 nach unten gedrückt und arretiert dort mit Hilfe eines Arretiermittels 76, das in das Haltemittel 68 eingreift und es entriegelt hält. Gleichzeitig wird das andere Haltemittel 70 gegen eine Feder 78 nach unten in eine Arretierstellung gedrückt, so dass die Kugel immer noch in ihrer Position gehalten bleibt, nun jedoch durch eine schalenförmige Vertiefung im zweiten Haltemittel 70.
  Nach Ende der Abschussbeschleunigung des Zünders 6 wird das obere Haltemittel 70 durch die Feder 78 wieder nach oben, also von der Kugel weg, gedrückt, so dass es die Kugel freigibt, wie in Fig. 8 dargestellt ist. Dieser Vorgang der Freigabebewegung des Haltemittels 70 läuft jedoch verzögert ab, so dass die Kugel noch eine kleine Weile nach dem Abschuss in der schalenförmigen Vertiefung des Haltemittels 70 gehalten bleibt. Die Verzögerung wird durch einen relativ dichten Luftraum 80 bewirkt, aus dem die eingeschlossene Luft nur langsam entweichen kann, so dass das Haltemittel 70 nur langsam, z.B. in einem Zeitraum von wenigen Sekunden, nach oben in seine Ausgangsposition zurück kann. Das Einströmen der Luft in den Luftraum 80 während des Abschussschocks wird durch die sehr hohe Kraft begünstigt, mit der das Haltemittel 70 in dem Moment gegen die Feder 78 nach unten gedrückt wird. Unterstützend kann ein Ventil vorgesehen sein, dass die Luft einfach in den Luftraum 80 eindringen lässt und ein Herausweichen verhindert oder verzögert.
  Auf diese Weise bleibt die Kugel noch eine Weile nach dem Abschuss in ihrer Arretierstellung gehalten, so dass eine kurz nach dem Abschuss noch vorliegende Unruhe des Geschosses 4 im Flug die Kugel nicht vorzeitig entsichert. Erst wenn sich der Flug des Geschosses 4 stabilisiert hat, ist die Kugel freigegeben. Auf diese Weise kann eine Vorrohrsicherheit gewährleistet werden.
  Ist die Kugel von beiden Haltemitteln 68, 70 freigegeben, wie in Fig. 8 dargestellt ist, so bleibt sie dennoch zunächst in ihrer Arretierstellung gehalten. Dies wird durch eine Vertiefung 82 im Riegel 64 bewirkt, in der die Kugel lagert. Durch die noch hohe Bremsbeschleunigung während des ersten Teils des Flugs wird der Riegel 64 nach oben, also im Zünder 6 nach vorne, gedrückt, so dass er leicht gegen die Kugel drückt und die Vertiefung 82 die Kugel hält. Erst wenn die Bremsbeschleunigung im Apogäum 8 oder im Bereich 10 - je nachdem wie ausgeprägt der Umkehrpunkt der Flugbahn ist - auf ein Minimum abgesunken ist, ist dieser leichte Druck des Riegels 64 auf die Kugel so gering geworden, dass die Kugel leicht aus der Vertiefung 82 ausgelenkt werden kann.
  Im Apogäum 8, oder im Bereich 10, wirkt die Querbeschleunigung 16 auf die Kugel und drückt diese aus ihrer Arretierstellung heraus, wie in Fig. 9 gezeigt ist. Nun ist der Riegel 64 freigegeben, so dass er durch eine ansteigende Bremsbeschleunigung - auch eine leicht unterstützende Federkraft ist denkbar - nach vorne aus seiner Ausnehmung aus dem zweiten Teil 24 des Gehäuses 20 herausgezogen wird und den Rotor 60 somit vollständig entsichert. Dieser kann nun feder- oder motorgetrieben in seiner Freigabestellung bewegt werden, wie dies z.B. zu Fig. 5 beschrieben ist. Der Zünder 6 ist entsichert und kann durch einen Aufschlag oder eine Zeiteinstellung gezündet werden.

By a steep launch angle of over 45 ° to the earth's surface or to the horizontal, for example, of about 50 °, the projectile 4 passes through the apogee 8 or at the apex of the trajectory 2 a pronounced reversal point in which the igniter. 6

• caused by the shape of the projectile 4 and possibly supported by a tail - is moved from an upward orientation in a downward orientation. This change in direction causes an acceleration in the igniter 6, which is dependent on the position of the projectile 4 on its trajectory. In apogee 8, this acceleration is greatest. If the reversal point or the curvature of the trajectory 2 in the apogee 8 is particularly pronounced, for example due to a steep launch angle of more than 45 ° to the earth's surface, the acceleration in a region 10 around the apogee 8 can be well detected and evaluated.
  In Fig. 2 accelerations are shown, which act on the projectile 4 and its elements during the flight in addition to the gravitational acceleration. As a result of the change in direction of the projectile 4 in the apogee 8 or in the region 10 around the apogee 8, the projectile 4 is rotated in a direction of rotation 12 so that a transverse acceleration 16 acts on elements of the projectile 4 at a distance from a pivot point 14 or axis of rotation , in particular to elements of the igniter 6, which is far away from the fulcrum 14. In addition, the projectile 4 is braked by air resistance in its flight, so that acts on its elements a longitudinal acceleration 18, which is directed to the rear.
  The longitudinal acceleration 18 is in Fig. 3 plotted on a graph as acceleration a over the time of flight t. The acceleration a is directed in relation to the projectile 4 to the rear. When launching projectile 4, a very strong acceleration acts forward on projectile 4, which in Fig. 3 is indicated below. Very quickly after leaving the launching tube, the projectile 4 is braked and the in Fig. 3 applied acceleration a becomes positive and assumes a maximum, since the projectile 4 at the beginning of its flight has the highest speed and thus the highest air resistance. Since the air resistance is proportional to the velocity of the projectile 4, the in Fig. 3 also shown the velocity of the projectile 4.
  The lowest curve represents the longitudinal acceleration 18 in a vertical flight in which the projectile 4 comes to a stop at the upper reversal point before it falls down again. The middle curve is reached at a steep launch, eg of 50 °, and the uppermost curve at a flat launch. The steeper the launch, the more pronounced the change in acceleration in the apogee 8 or in the area 10, which is in Fig. 3 is shown as a time range between the times t ₁ and t ₂ by a dashed line. The change in acceleration is in the curvature of the curves in Fig. 3 shown. At the time t ₃ , the projectile 4 reaches the ground and is accelerated by the impact extremely backwards, which in Fig. 3 is indicated by the upward arrow.
  Fig. 4 shows the igniter 6 in a simplified sectional view. The igniter 6 is designed as an impact fuze. The igniter 6 comprises a housing 20 of two parts 22, 24, the lower part 24 is screwed into the hull of the projectile 4 and having a transfer charge 26. This is from an in Fig. 5 shown Ignition means 58 ignited, which is arranged in a rotor 28, and the ignition energy is transmitted in an unlocked position of the rotor 28 through a channel 30 to the transfer charge 26.
  In Fig. 4 the rotor 28 is shown in its secured position. In this position, it is held by a schematically indicated securing means 32, which is a double-bolt system with two securing bolts, which in the EP 1 826 527 A1 is shown and described in detail, which is hereby incorporated by reference. This double bolt system locks the rotor 28 in its secured position. The lock is unlocked by the launch acceleration. In addition, the rotor 28 is locked by a latch 34 in its securement, which engages in an opening 36 of the rotor 28. The latch 34 is at the same time the puncture needle of the igniter 6. The latch 34 is in turn locked by a second securing means 38 in its secured position, which engages with a locking means 40 in the form of a bolt in a recess 42 of the bolt 34.
  The second securing means 38 also comprises an evaluation means 44 and a sensor 46, which has a sensor 48 and a detection means 50. The sensor 48 is a piece of elastic heavy metal, which undergoes a longitudinal acceleration 18 indicated by a double arrow force, which it amplifies by a corresponding storage in the detection means 50 transmits to the detection means 50. The force is detected by the detection means 50 and evaluated by the evaluation means 44, which for this purpose has an energy source 52, which draws energy from liquids which are mixed by the launch shock and then release electrical energy for a short while during the flight. Since the launch has a very high force acting down or back on the sensor 48, a step 54 is incorporated in the part 22 at a small distance from the sensor 48, on which the sensor 48 can be supported during the launch shock. In order not to bend in this case, the sensor 48 is sufficiently elastic, so that it is automatically removed again after the launch shock of the step 54 and is available for measuring the force.
  The evaluation means 44 evaluates the course of the force on the sensor 48 to a minimum. This is based on the speed minimum in the apogee 8 and the associated lowest air resistance. Noise in the course, which can be generated by vibrations of the projectile 4 during the flight, is in this case suppressed by the evaluation means 44 or not evaluated. Is the minimum recognized, the locking means 40 is pulled out of the recess 42 by a micromotor. By this unlocking action, the securing means 38 is released and the latch 34 is released, which is driven by a spring 56 to the front, so that its tip is pulled out of the opening 36. Now the rotor 28 is completely unlocked and is rotated motor or spring-driven in its focus.
  The focus is in Fig. 5 shown. The ignition means 58 is oriented so that it lies in the piercing direction of the puncture needle and is aligned with the channel 30 and the transfer charge 26. At an impact of the projectile 4, the tapping needle is pushed backwards, the ignition means 58 stings, this ignites and releases ignition energy, which hits the transfer charge 26 and ignites it. The transfer charge 26 in turn ignites a main charge of the projectile. 4
  Instead of the sensor 48, the sensor 46 may include means for determining an angle between the direction of the earth's magnetic field and a direction of the igniter 6. For this purpose, the sensor 46 may comprise a piece of magnetized or non-magnetized ferromagnetic metal on which the earth's magnetic field exerts a force. The force and / or direction of the force can be detected and evaluated as a magnitude related to the angle. The evaluation means 44 is then prepared for determining a maximum of the speed of the temporal change of the angle and thus detects the apogee 8. The corresponding force, the angle or its rate of change then forms the apogee parameter.
  In the FIGS. 6 to 9 another rotor 60 is shown for an igniter, not otherwise shown, which may be implemented as an impact fuze such as igniter 6 or as a time fuse. The following description is essentially limited to the differences from the exemplary embodiment in FIGS FIGS. 4 and 5 which is referred to with regard to features and functions that remain the same. Substantially identical components are basically numbered with the same reference numerals.
  The rotor 60 houses a securing means 62 which, in conjunction with another securing means 32, not shown, releases the rotor 60. The other securing means 32 may be a double-bolt system that locks the rotor 60. The securing means 62 comprises a bolt 64 in the form of a bolt, which engages in a corresponding recess in the second part 24 of the housing 20 and the rotor 60 is locked even after unlocking the other securing means 32 in the housing 20. The securing means 62 also includes a ball as a locking means 66 and two holding means 68, 70 which hold the ball from two opposite sides.
  The ball is loosely held between the latch 64 and another bolt 72 with a small clearance between the ball and latch 64, 72 so that the ball is not pinched. It rests in a cup-shaped recess of the holding means 68, even there with some play, and is held by the interaction of holding means 68 and latch 64, 72 slightly movable in its locking position, which moves out of the latch 64 from the recess in the second part 24 of Housing 20 prevents.
  Fig. 7 shows the rotor 60 at a launch of the projectile 4. The other securing means 32, not shown unlocks and releases a locking of the rotor 60, but still remains locked by the latch 64 in its security. The launching shock also pushes down under retaining means 68 against a spring 74 and locks there with the aid of a locking means 76, which engages in the retaining means 68 and keeps it unlocked. At the same time the other holding means 70 is pressed against a spring 78 down into a locking position, so that the ball is still held in position, but now by a cup-shaped depression in the second holding means 70th
  After the end of the firing acceleration of the igniter 6, the upper retaining means 70 is pressed by the spring 78 back up, so away from the ball, so that it releases the ball, as in Fig. 8 is shown. However, this process of the release movement of the holding means 70 is delayed, so that the ball remains a little while after shooting in the cup-shaped recess of the holding means 70 remains. The delay is caused by a relatively dense air space 80, from which the trapped air can escape only slowly, so that the retaining means 70 can only slowly, for example in a period of a few seconds, back up to its original position. The inflow of air into the air space 80 during the launch shock is favored by the very high force with which the retaining means 70 is pressed in the moment against the spring 78 down. Supporting a valve may be provided that the air can easily penetrate into the air space 80 and prevents or retards escape.
  In this way, the ball remains a while after firing held in its locked position, so that a shortly after the launch still present Bullet 4 agitation in flight does not release the ball prematurely. Only when the flight of the projectile 4 has stabilized, the ball is released. In this way, a Vorrohrsicherheit can be ensured.
  Is the ball of both holding means 68, 70 released, as in Fig. 8 is shown, it still remains initially held in its locked position. This is effected by a recess 82 in the latch 64, in which the ball is stored. Due to the still high braking acceleration during the first part of the flight, the bolt 64 is pushed upward, ie in the igniter 6 forward, so that it presses lightly against the ball and the recess 82 holds the ball. Only when the braking acceleration in Apogäum 8 or in the range 10 - depending on how pronounced the reversal point of the trajectory - has dropped to a minimum, this slight pressure of the bolt 64 has become so low on the ball that the ball easily from the recess 82nd can be deflected.
  In the apogee 8, or in the area 10, the lateral acceleration 16 acts on the ball and pushes it out of its locked position, as in Fig. 9 is shown. Now, the latch 64 is released so that it is pulled out of its recess from the second part 24 of the housing 20 by an increasing braking acceleration - even a slightly supportive spring force is conceivable - and thus fully unlocked the rotor 60. This can now be moved spring or motor driven in its release position, as for example to Fig. 5 is described. The igniter 6 is unlocked and can be ignited by an impact or a time setting.

LIST OF REFERENCE NUMBERS

2

trajectory

4

bullet

6

Igniter (for 4)

8th

apogee

10

Area

12

Direction of rotation (of 4)

14

Fulcrum (of 4)

16

Lateral acceleration (from 6)

18

Longitudinal acceleration (from 6)

20

Housing (from 6)

22

Part (of 6)

24

Part (of 6)

26

Transfer charge (from 6)

28

Rotor (from 6)

30

Channel (from 24)

32

Securing means (of 6)

34

Bar (from 28)

36

Opening (from 28)

38

Securing means (of 6)

40

Barrier means (from 38)

42

Recess (from 34)

44

Evaluation means (from 6)

46

Sensor (from 6)

48

Feeler (from 46)

50

Detection means (of 46)

52

Energy source (from 44)

54

Level (from 22)

56

Spring (for 34)

58

Ignition (from 28)

60

Rotor (from 6)

62

Securing means (of 6)

64

Bar (from 60)

66

Barrier means (of 62)

68

Holding means (from 62)

70

Holding means (from 62)

72

Bolt (from 62)

74

Spring (for 68)

76

Locking means (from 68)

78

Spring (for 70)

80

Airspace (for 70)

82

Deepening (from 64)

Claims (16)

Securing means for a detonator (6) of a projectile (4), comprising an ignition means (58) for transmitting ignition energy to another ignition means and a barrier for interrupting transmission, locked in a locking state by a securing means (38, 62), which is intended for unlocking due to a physical arming parameter,
characterized,
in that the arming parameter is an apogee parameter which is caused by the flying through of the projectile (4) by the apogee (8) of a projectile trajectory. Safety device according to claim 1,
characterized,
that the Apogäumparameter is a force. Safety device according to claim 1 or 2,
in that the securing means (38, 62) are provided for the mechanical scanning of the apogee parameter. Safety device according to one of the preceding claims,
characterized,
in that the securing means (38, 62) comprises a locking means (40, 66) which triggers an unlocking action by changing its position in the igniter (6) when passing through the apogee (8). Safety device according to claim 4,
characterized,
that the locking means (40, 66) in its securing position blocks a mechanical unlocking. Safety device according to claim 4 or 5,
characterized,
in that the locking means (66) is provided for positional change by its inertia. Safety device according to one of claims 4 to 6,
characterized,
that the locking means (40, 66) releases a Entriegelraum by its change in position, in which a part of a bolt (34, 64) for carrying out the unlocking action can be introduced. Safety device according to one of the preceding claims,
characterized
in that the securing means comprises a magnet which triggers an unlocking action by changing its position in the igniter when passing through the apogee (8). Safety device according to one of the preceding claims,
characterized,
in that the locking means (38, 62) for unlocking by the presence of the apogee parameter requires a previous unlocking which depends on another arming parameter. Safety device according to one of the preceding claims,
characterized,
in that the securing means (38, 62) is released for unlocking by an unlocking action effected by another securing means, and the other securing means brings about the release by firing the projectile. Safety device according to one of the preceding claims,
characterized,
in that the barrier is a rotor (28, 60) and the securing means (38, 62) is provided for locking the rotor (28, 60). Safety device according to one of the preceding claims,
characterized,
that the Apogäumparameter is a change in direction of the projectile (4). Safety device according to one of the preceding claims,
characterized,
that the Apogäumparameter is a lateral acceleration of the detonator (6). Safety device according to one of the preceding claims,
characterized,
that the Apogäumparameter is a minimum in a longitudinal acceleration (18) of the igniter (6). Safety device according to one of the preceding claims,
characterized,
that the Apogäumparameter is a velocity of the projectile (4). Safety device according to one of the preceding claims,
characterized,
that the direction of the earth's magnetic field is a Apogäumparameter relative to a detonator direction.

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