EP1736729A1 - Safety device for fuze for spin-stabilized projectile - Google Patents

Abstract

A safety unit for a detonator, comprises a detonator body (12) and a bearing member (14) which together form a hollow spherical chamber (16). The chamber houses a spherical rotor (18) that contains the detonator (20). The rotor is surrounded by a securing ring, which uses an acceleration ring and a securing ring spring to prevent the rotor from rotating. The securing ring has a slot.

Description

The invention relates to a safety device according to the preamble of claim 1 for a spin lump igniter.

As safety devices for a Vortex igniter bolt systems with centrifugal bolts and stop are known, for example.

A safety device for a Vortex projectile igniter is for example in the EP 0 360 187 B1 described. In this known securing device, a retaining ring is formed with a keyway having radially inwardly oriented support tabs and between these recesses. The support tabs and the recesses have approximately the same size footprint dimensions. This has an effect on the swirl-ie centrifugal force-related spreading behavior of the retaining ring. This known safety device also has a spring device which is formed by a conical spiral compression spring.

The invention has for its object to provide a safety device of the type mentioned for a Vortex projectile igniter, especially for a medium-caliber weapon system, which is suitable for relatively high piecing and Zuführbeschleunigungen.

This object is achieved according to the invention in a safety device of the type mentioned by the features of the characterizing part of claim 1. Preferred embodiments or further developments of this securing device according to the invention are characterized in the subclaims 2 to 8.

The object underlying the invention can also be achieved by the features of claim 9 according to the invention. Preferred embodiments or further developments of such a securing device according to the invention are characterized in the claims 10 to 16.

The safety device according to the invention has the advantage that the rotor for the detonator provided in the igniter body is released only when the launch acceleration and the spin-induced rotational acceleration is applied. This means that short-term pulses, such as those that occur in a drop test, are not detected as sufficient for ignition, so that the rotor remains in safety. In particular, extremely high feed and Ansetzbeschleunigungen be collected with the inventive securing device in an advantageous manner and not transmitted via the rotor to the internal structure. This leads advantageously to a high functional reliability.

Further details, features and advantages will become apparent from the following description of two illustrated in the drawings embodiments of the safety device according to the invention.

Show it:

FIG. 1

in sections, in a longitudinal section, a first embodiment of the securing device in the securing,

FIG. 2

a cross section through the securing device according to Figure 1 in the security,

FIG. 3

1 similar longitudinal sectional view of the securing device in the unlocked position,

FIG. 4

a cross section through the safety device,

FIG. 5

a longitudinal sectional view of a second embodiment of the securing device, wherein only the igniter body, but not also the bearing body of the securing device is shown, and

FIG. 6

a cross section through the securing device according to Figure 5.

FIG. 1 shows sections of a longitudinal section of an embodiment of the securing device 10 for a twisted roundabout igniter. The safety device 10 has a detonator body 12 drawn in sections and also a bearing body 14, which is also drawn only in sections. The igniter body 12 and the bearing body 14 are each formed with a hemispherical cavity, so that in the assembled state between the igniter body 12 and the bearing body 14, a spherical cavity 16 results. In the spherical cavity 16, a ball-like rotor 18 is rotatably mounted. In the spherical rotor 18, a detonator 20 is arranged. The ball-like rotor 18 is also formed with a recess 22 into which in the drawn in Figure 1 securing - and also in the drawn in Figure 3 Entsicherungsstellung - a socket 24 positively rests, which is connected to a (not shown) second arming system. In the socket 24 for piercing the detonator 20 - after an adjustment of the rotor 18 in the axial in focus - a piercing needle 26 is arranged.

The ball-like rotor 18 is surrounded by a rotor locking ring 28 which prevents the rotor 18 by means of an accelerator ring 30 and a positive locking the spring ring 28 with the rotor locking ring 28 positively locking spring element 32 in the assurance (see Figure 1) to a rotation in the armed position. The rotor locking ring 28 is for rotationally and centrifugally induced spreading in a free space 34 inside, with a slot 36 (see Figure 2) is formed. In order to facilitate the rotational and centrifugal force-spreading of the rotor locking ring 28 into the free space 34 inside, the rotor locking ring 28 is formed diametrically opposite the slot 36 with a notch 38. This notch 38 causes a corresponding material weakening 40 of the rotor locking ring 28, whereby the mentioned spreading of the rotor locking ring 28 is facilitated.

As can also be seen from FIG. 1, the rotor locking ring 28 is provided in the equatorial connection region 42 between the igniter body 12 and the bearing body 14, which can be expanded in terms of rotation and centrifugal force. The rotor securing ring 28 is arranged in a recess 44 which is formed on the end face 46 of the bearing body 14 which adjoins the igniter body 12. The Recess 44 has the free space 34 for the rotationally and centrifugally spread rotor locking ring 28.

The igniter body 12 is formed with an annular, axially oriented receiving space 48 for the spring element 32 and the accelerating ring 30. The acceleration ring 30 is axially movably guided along an axially oriented cylindrical guide surface 50 delimiting the receiving space 48 on the inside. On the outside, the receiving space 48 is formed with a stepped profile 52. The stepped profile 52 results in an inside bearing portion 54 for the spring element 32 and an externally axially adjacent guide portion 56 for the acceleration ring 30. The acceleration ring 30 has an L-shaped cross-sectional profile with a plant leg 58 for the spring element 32 and a holding leg 60th for the rotor locking ring 28.

• In der in den Figuren 1 und 2 gezeichneten Sicherstellung fixiert der Rotorsicherungsring 28 den kugelartigen Rotor 18. Der Beschleunigungsring 30 verhindert, dass sich der Rotorsicherungsring 28 öffnen kann. Das Federelement 32 ist gegen den Beschleunigungsring 30 gezwängt, so dass es den Beschleunigungsring 30 in der Sicherstellung hält.
• Wenn beispielsweise bei der Durchführung eines Falltests eine kurzzeitige Beschleunigung auftritt, kann der Beschleunigungsring 30 das Federelement 32 zusammendrücken. Dabei wird der Formschluss zwischen dem Beschleunigungsring 30 und dem Rotorsicherungsring 28 aufgehoben und der Rotorsicherungsring 28 freigegeben. Diese Freigabe bewirkt jedoch kein Öffnen des Rotorsicherungsringes, d.h. kein Aufspreizen desselben, weil keine Rotation stattfindet. Der Rotor 18 kann sich also nicht in die axiale Scharfstellung drehen.
• Nach Abklingen der besagten kurzzeitigen translatorischen Beschleunigung wird der Beschleunigungsring 30 durch Entspannung des Federelementes 32 wieder in die in den Figuren 1 und 2 gezeichnete Sicherstellung bewegt.
• Figur 2 verdeutlicht die rotationssymmetrische Ausbildung der Sicherungseinrichtung und insbesondere die Ausbildung des Rotorsicherungsringes 28 mit dem Schlitz 36 und der Einkerbung 38 und die durch die Einkerbung 38 bewirkte Materialschwächung 40.
• Die Figuren 3 und 4 verdeutlichen die Entsicherungsstellung der Sicherungseinrichtung 10. Dabei wird das ausgelöste Federelement 32 durch den Beschleunigungsring 30 bei anhaltender Abschussbeschleunigung zusammengedrückt. Beim Auftreten der drallbedingten Rotation und der daraus resultierenden Fliehkraft wird der Rotorsicherungsring 28 radial nach außen in den Freiraum 34 bewegt, wie aus Figur 4 deutlich ersichtlich ist, und der Rotor 18 freigegeben.
• Beim Absinken der Abschussbeschleunigung entspannt sich das Federelement 32 wieder und bewegt den Beschleunigungsring 30 wieder in Richtung Sicherstellung. Der Beschleunigungsring 30 kann sich jedoch nicht wieder in die in Figur 1 gezeichnete Sicherstellung zurückbewegen, weil er nun von dem aufgespreizten Rotorsicherungsring 28 blockiert wird, d.h. mit seinem Halteschenkel 60 am aufgespreizten Rotorsicherungsring 28 zur Anlage kommt. Das Federelement 32 spannt somit über den Beschleunigungsring 30 den Rotorsicherungsring 28 in seiner Lage. Der Rotor 18 kann sich jedoch erst in seine axiale Scharfstellung drehen, wenn über ein (nicht dargestelltes) zweites Entsicherungssystem die Buchse 24 freigegeben wird und sich vom Rotor 18 wegbewegt.
• Die Figur 4 verdeutlicht den deformierten, d.h. aufgespreizten Rotorsicherungsring 28, der sich bei einer schnellen Rotation fliehkraftbedingt öffnet und den Rotor 18 freigibt.
• Die Figuren 5 und 6 verdeutlichen eine zweite Ausführungsform der Sicherungseinrichtung 10, wobei auf die Darstellung des Lagerkörpers 14 verzichtet wurde. Es ist nur der Zylinderkörper 12 mit seiner halbkugelförmigen Aussparung verdeutlicht.
• Mit der Bezugsziffer 18 ist auch in den Figuren 5 und 6 der kugelartige Rotor bezeichnet, in dem ein Detonator 20 angeordnet ist.
• Wie aus Figur 6 ersichtlich ist, weist der Rotor 18 drei Ausnehmungen 62 auf, die in Umfangsrichtung gleichmäßig verteilt und radial orientiert sind. In die jeweilige Ausnehmung 62 steht in der in den Figuren 5 und 6 gezeichneten Sicherstellung ein zugehöriger radial orientierter Querbolzen 64 hinein. Der jeweilige Querbolzen 64 ist in einem zugehörigen, im Zünderkörper 12 ausgebildeten Querbolzen-Führungsloch 66 linear beweglich geführt.
• An seinem vom Rotor 18 abgewandten Endabschnitt ist jeder Querbolzen 64 mit einem axial orientierten Durchgangsloch abgebildet, das zur Aufnahme eines axial orientierten Beschleunigungsbolzens 70 vorgesehen ist. Mit dem jeweiligen Beschleunigungsbolzen 70 ist ein Federelement 72 (siehe Figur 5) verbunden.
• Die Querbolzen 64 sind an ihrem radial äußeren Endabschnitt außerdem jeweils mit einem Durchgangsloch 74 ausgebildet. Ein zweites Federelement 76, das als Ringfeder ausgebildet ist, erstreckt sich durch die Durchgangslöcher 74 der radial orientierten Querbolzen 64. Das zweite Federelementes 76 ist in einer Ringnut 78 des Zünderkörpers 12 ausgebildet.
• Mit der Bezugsziffer 22 ist auch in Figur 5 die im Rotor 18 ausgebildete Ausnehmung bezeichnet, in der in der Sicherstellung der Sicherungseinrichtung 10 eine Buchse 24 hineinsteht.
• Die Funktionsweise der Sicherungseinrichtung 10 gemäß den Figuren 5 und 6 ist wie folgt:
  • Bei dieser Ausbildung der Sicherungseinrichtung 10 ist wenigstens ein Querbolzen 64 vorgesehen, oder es sind beispielsweise drei Querbolzen 64 - je nach den zu erwartenden mechanischen Belastungen - vorgesehen, um für extrem hohe Zuführ-und Ansetzbeschleunigungen geeignet zu sein.
  • In der Sicherstellung der Sicherungseinrichtung 10 hält das jeweilige Federelement 72 den zugehörigen axial orientierten Beschleunigungsbolzen im zugehörigen Beschleunigungsbolzen-Führungsloch 68, so dass der jeweilige Querbolzen 64, in den Rotor 18 formschlüssig hineinstehend, fixiert ist. Bei Auftreten einer kurzzeitigen Beschleunigung, wie sie beispielsweise bei einem Falltest auftritt, kann der jeweilige Beschleunigungsbolzen 70 das zugehörige Federelement 72 zusammendrücken. Die Querbolzen 64 verbleiben jedoch in der formschlüssigen Sicherstellung mit dem Rotor 18, weil das zweite Federelement 76 die Querbolzen 64 in der Sicherstellung hält.
  • Figur 6 verdeutlicht den rotationssymmetrischen Aufbau der Sicherungseinrichtung 10.
  • Bei Wirksamwerden einer Abschussbeschleunigung drücken die Beschleunigungsbolzen 70 die zugehörigen Federelemente 72 zusammen, so dass die radial orientierten Querbolzen 64 von den Beschleunigungsbolzen 70 freigegeben sind. Bei der folgenden Rotation werden die radial orientierten Querbolzen 64 fliehkraftbedingt nach außen bewegt. Dabei drücken die Querbolzen 64 das zweite Federelement 76 radial nach außen, so dass das zweite Federelement 76 auseinander bewegt wird. Damit wird der Rotor 18 freigegeben.
  • Die radial orientierten Querbolzen. 64 bewegen sich in der Ringnut 78 nach außen und können dann an einem äußeren, nicht dargestellten Gehäuse anliegen. Die Querbolzen 64 sind dabei immer noch geführt, so dass sie sich in ihre Ausgangslage zurückbewegen können. Der Rotor 18 kann sich aber erst in die axiale Lage, d.h. in die Scharfstellung der Sicherungseinrichtung 10 drehen, wenn über ein nicht dargestelltes zweites Entsicherungssystem die Buchse 24 freigegeben wird und sich vom Rotor 18 wegbewegt.

The operation of the securing device 10 will be explained below with reference to FIGS. 1 to 4, in which identical details are designated by the same reference numerals, so that it is unnecessary to describe in detail with reference to FIGS. 1 to 4 each detail:

• In the illustrated in Figures 1 and 2 assurance of the rotor locking ring 28 fixes the ball-like rotor 18. The acceleration ring 30 prevents the rotor locking ring 28 can open. The spring member 32 is urged against the accelerating ring 30 so as to hold the accelerating ring 30 in the securing position.
• For example, if a short-term acceleration occurs when performing a drop test, the accelerator ring 30 may compress the spring member 32. In this case, the positive connection between the acceleration ring 30 and the rotor locking ring 28 is released and the rotor locking ring 28 is released. However, this release causes no opening of the rotor locking ring, ie no spreading of the same, because no rotation takes place. The rotor 18 can not rotate so in the axial focus.
• After the abovementioned short-term translational acceleration of the acceleration ring 30 is moved by relaxation of the spring element 32 back into the drawn in Figures 1 and 2 securement.
• Figure 2 illustrates the rotationally symmetrical design of the securing device and in particular the formation of the rotor locking ring 28 with the slot 36 and the notch 38 and caused by the notch 38 material weakening 40th
• Figures 3 and 4 illustrate the Entsicherungsstellung the safety device 10. In this case, the triggered spring element 32 is compressed by the accelerating ring 30 at sustained launch acceleration. Upon the occurrence of spin-rotation and the resulting centrifugal force of the rotor locking ring 28 is moved radially outwardly into the free space 34, as clearly shown in Figure 4, and the rotor 18 is released.
• When the launch acceleration drops, the spring element 32 relaxes again and moves the acceleration ring 30 again in the direction of securing. However, the acceleration ring 30 can not move back into the drawn in Figure 1 assurance, because it is now blocked by the spread rotor locking ring 28, that comes with its holding leg 60 on the spread rotor locking ring 28 to the plant. The spring element 32 thus biases over the acceleration ring 30, the rotor locking ring 28 in its position. However, the rotor 18 can rotate only in its axial focus when the socket 24 is released via a (not shown) second Entsicherungssystem and moves away from the rotor 18.
• FIG. 4 illustrates the deformed, ie spread-out rotor locking ring 28, which opens with a fast rotation due to centrifugal force and releases the rotor 18.
• Figures 5 and 6 illustrate a second embodiment of the securing device 10, wherein the representation of the bearing body 14 has been omitted. Only the cylinder body 12 with its hemispherical recess is illustrated.
• Reference numeral 18 also designates the spherical rotor in FIGS. 5 and 6, in which a detonator 20 is arranged.
• As can be seen from FIG. 6, the rotor 18 has three recesses 62, which are uniformly distributed in the circumferential direction and radially oriented. In the respective Recess 62 is in the drawn in Figures 5 and 6 assurance an associated radially oriented transverse pin 64 into it. The respective transverse pin 64 is guided linearly movable in an associated, formed in the igniter body 12 transverse pin guide hole 66.
• At its end portion facing away from the rotor 18 each transverse pin 64 is imaged with an axially oriented through hole, which is provided for receiving an axially oriented acceleration pin 70. A spring element 72 (see FIG. 5) is connected to the respective acceleration bolt 70.
• The transverse pins 64 are also each formed with a through hole 74 at its radially outer end portion. A second spring element 76, which is designed as an annular spring, extends through the through holes 74 of the radially oriented transverse pin 64. The second spring element 76 is formed in an annular groove 78 of the igniter body 12.
• The reference numeral 22 designates the recess formed in the rotor 18 in FIG. 5, in which a bush 24 is located in the securing of the securing device 10.
• The operation of the securing device 10 according to FIGS. 5 and 6 is as follows:
  • In this embodiment of the securing device 10, at least one transverse pin 64 is provided, or, for example, three transverse pins 64 are provided, depending on the mechanical loads to be expected, in order to be suitable for extremely high feeding and setting accelerations.
  • In securing the securing device 10, the respective spring element 72 holds the associated axially oriented acceleration bolt in the associated acceleration bolt guide hole 68, so that the respective transverse pin 64, fixed in the rotor 18 in a form-fitting manner, is fixed. If a brief acceleration occurs, as occurs, for example, in a drop test, the respective acceleration bolt 70 can compress the associated spring element 72. However, the cross pin 64 remain in the positive locking with the rotor 18, because the second spring element 76 holds the cross pin 64 in the securing.
  • FIG. 6 illustrates the rotationally symmetrical structure of the securing device 10.
  • When a firing acceleration takes effect, the acceleration bolts 70 compress the associated spring elements 72, so that the radially oriented transverse bolts 64 are released from the acceleration bolts 70. In the following rotation, the radially oriented transverse pins 64 are moved outwards due to centrifugal force. The transverse pins 64 press the second spring element 76 radially outward, so that the second spring element 76 is moved apart. Thus, the rotor 18 is released.
  • The radially oriented cross pins. 64 move in the annular groove 78 to the outside and can then rest against an outer housing, not shown. The transverse pins 64 are still guided, so that they can move back to their original position. However, the rotor 18 can rotate only in the axial position, ie in the armed position of the safety device 10 when the socket 24 is released via a not shown second Entsicherungssystem and moves away from the rotor 18.

List of reference numerals:

10

safety device

12

Igniter body (from 10)

14

Bearing body (from 10)

16

Spherical cavity (between 12 and 14)

18

Ball-like rotor (in 16)

20

Detonator (in 18)

22

Recess (in 18 for 24)

24

Socket (for 26)

26

Injection needle (in 24)

28

Rotor Locking Ring (for 18 in 34)

30

Acceleration ring (for 28)

32

Spring element (for 30)

34

Free space (for 28)

36

Slot (in 28)

38

Notching (in 28)

40

Material weakening (at 38)

42

Equatorial connection area (between 12 and 14)

44

Recess (in 14 for 28)

46

Front side (of 14)

48

Recording room (for 32)

50

Cylindrical guide surface (from 48 to 30)

52

Graduated profile (from 48)

54

Bearing section (from 48 for 32)

56

Leaders section (from 48 for 30)

58

Plant leg (from 30 to 32)

60

Holding thighs (from 30 to 28)

62

Recess (in 18 for 64)

64

Cross Pins (from 10)

66

Cross pin guide hole (in 14 for 64)

68

Acceleration Pin Guide Hole (in 64 for 70)

70

Acceleration bolt (from 10)

72

Spring element (for 70)

74

Through hole (in 64)

76

Second spring element (in 74 for 64)

78

Ring groove (for 76)

Claims (17)

A fuse device for a turret igniter, comprising an igniter body (12) and a bearing body (14) defining between them a spherical cavity (16) in which a ball-like rotor (18) is rotatably mounted, in which a detonator (20) is provided .
characterized,
in that the rotor (18) is surrounded by a rotor securing ring (28) which in securing the securing device (10) connects the rotor (18) in an interlocking manner by means of an acceleration ring (30) and an acceleration ring (30) with the rotor locking ring (28) Spring element (32) prevents rotation, wherein the rotor locking ring (28) for rotational and centrifugal force-spreading in a free space (34) into formed with a slot (36). Safety device according to claim 1,
characterized,
in that the rotor securing ring (28) is formed diametrically opposite the slot (36) with a notch (38) facilitating spreading. Safety device according to claim 1,
characterized,
in that the rotor securing ring (28) is provided in the equatorial connection region (42) between the igniter body (12) and the bearing body (14) in such a way that it can be spread apart due to the forces of rotation and centrifugal force. Safety device according to claim 3,
characterized,
in that the rotor securing ring (28) is arranged in a recess (44) which is formed on the end face (46) of the bearing body (14) adjoining the igniter body (12) and which causes the free space (34) for the rotational and centrifugal forces having expandable rotor locking ring (28). Safety device according to claim 1,
characterized,
that the igniter body (12) is formed with an annular, axially oriented receiving space (48) for the spring element (32) and the accelerating ring (30), wherein the accelerating ring (30) along an axially oriented cylindrical inside the receiving space (48) Guide surface (50) is guided axially movable. Safety device according to claim 5,
characterized,
in that the receiving space (48) is formed on the outside with a stepped profile (52), whereby a bearing section (54) for the spring element (33) and a guide section (56) for the acceleration ring (30) are determined axially adjacent to one another. Safety device according to one of claims 1 to 6,
characterized,
in that the acceleration ring (30) has an L-shaped cross-sectional profile with a bearing limb (58) for the spring element (32) and a retaining limb (60) for the rotor locking ring (28). Safety device according to one of claims 1 to 7,
characterized,
that the spring element (32) is a cylindrical helical compression spring. Safety device according to the preamble of claim 1,
characterized,
in that the rotor (18) has at least one recess (62) into which a radially oriented transverse pin (64) can be secured in order to secure the securing device. positively in that the at least one transverse pin (64) is retained in the recess (62) by means of an acceleration pin (70) and a first spring element (72), which are oriented axially, and that with the at least one transverse pin (64). 64) also a second spring element (76) is connected. Safety device according to claim 9,
characterized,
in that the at least one transverse bolt (64) is guided radially movably in a transverse bolt guide hole (68) formed in the igniter body (12). Safety device according to claim 9,
characterized,
in that the acceleration bolt (70) belonging to the at least one transverse bolt (64) is guided in an axially movable manner in an acceleration bolt guide hole (68) formed in the igniter body (12). Safety device according to claim 11,
characterized,
in that the first spring element (72) connected to at least one acceleration bolt (70) is arranged in the acceleration bolt guide hole (68). Safety device according to one of claims 9 to 12,
characterized,
in that the / each first spring element (72) is a cylindrical screw compression spring. Safety device according to claim 9,
characterized,
that the second spring element (76) is an annular spring. Safety device according to one of claims 9 to 14,
characterized,
that the rotor (18) evenly distributed in the circumferential direction comprises a number of recesses (62), in each recess (62), an associated transverse pin (64) is inside. Safety device according to one of the preceding claims,
characterized,
the nodular rotor (18) has a recess (22), a sleeve (24) is in form-fitting manner in which in the safe position of the safety device which is connected to a second arming system. Safety device according to claim 16,
characterized,
in that a piercing needle (26) provided for piercing the detonator (20) is provided in the bushing (24).

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