EP1826527B1 - Mechanical rocket fuse - Google Patents

Abstract

Mechanical rocket igniter comprises a rotor (20) arranged between an igniter needle (14) and an igniter translator (16) and connected to a counter torsion spring. The rotor is adjusted into a shooting position against the spring force of the torsion spring. A manually adjustable device delimits the rotor about an axis of rotation to selectively close the rotor in the shooting position.

Description

The invention relates to a mechanical rocket detonator according to the preamble of claim 1.

From the DE 2 132 106 A1 is an impact fuze for projectiles known. The detonator has a rotatably mounted, designed as a rotor Zündpillenträger, which is rotatable by a spring force from a secure position in an armed position. In addition, the igniter on a transport protection in the form of an axially displaceable locking pin. By means of a rotatable in two different positions Umstellbolzens is adjustable whether an instantaneous ignition or a delayed ignition of the impact fuze is to take place. After unlocking of the igniter by the 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. In order to prevent rotation of the rotor from launch, 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. However, 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.

From the EP 0 327 706 A2 is a projectile fuze with a spring tension system for a rotor arming known. In the safeguard, a spring engaged with the rotor is untensioned. Upon firing of the projectile fuse, one leg of the spring is biased by the cone of a recoil bolt. After release of the rotor then the second, engaging in a recess of the rotor leg of the spring moves the rotor in the armed position.

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 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.

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.

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.

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.

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 in Fig.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.

Show it:

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 in Figure 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.

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.

Between the housing 22 of the igniter assembly 24 and the igniter tip 26, 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. For this purpose, 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.

Like from the Figures 3 . 7 and 8th it can be seen, 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 Drehwinkelkbereiches 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. For this purpose, 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.

In order to keep the rotor 20 in the safe, it is associated with 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.

Thus, 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 ).

As for example from Fig.1 - or from the Figures 5 and 6 As can be seen, 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.

In ensuring the fuse 10 (see Fig.1 ) is 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. At the first securing bolt 84 engages in securing the igniter 10, a bolt lever 100 (see, for example. Figure 3 ), which is verschenkbar about an axially oriented axis 102. For positive engagement of the bolt lever 100 on the first securing bolt 84 in the securing of the igniter 10, 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.

Like from the FIGS. 1 . 5 and 6 it can be seen, 84 and 86, 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.

However, it is preferred if 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 ). In the securing and in the Vorentsicherungsstellung 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. In the securing and in the Vorentsicherungsstellung is in the second recess 120 of the second locking bolt 86, a detent spring 122 into it. In the in Figure 6 drawn focus, 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. For this purpose, 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.

From the top 130 of the rotor 20 protrudes a spring-loaded detent pin 132, which in the "MV focus" of the rotor 20 (see Figure 8 ) engages positively in a formed in the cover plate 30 detent hole to the "MV detonator" 54 with the firing pin 14 congruent to position axially aligned.

Same details are in the 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. As a result, the igniter 10 has the required handling, transport, fire and Vorrohrsicherheit.

The igniter 10 fulfills, for example, the provisions of STANAG 4187.

To ensure the ignition chain 12 is pyrotechnic interrupted by the two not aligned with the firing needle 14 axially piercing puncturing 52 and 54 in the rotor 20. 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 setting of an optional Zündverzugszeit takes place for the OV position and the MV position by the adjusting bolt 44 of the adjusting device 42nd

For focusing, 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. In addition, 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. Depending on the choice of ignition delay time on the adjusting bolt 44, the rotational angle range of the rotor 20 is defined defined about its axis of rotation 38 and set in the desired position. When turning into the MV position of the locking bolt 132, which protrudes from the top 130 of the rotor 20, engages in the cover plate 30 and the MV detonator 54 is axially aligned with the firing pin 14.

In the OV position, the spring-mounted on the circumference of the rotor 20 pin element 126 engages in the slot 128 of the adjusting bolt 44 and the OV detonator 52 is axially aligned with the firing pin 14.

At the target impact, by firing the igniter tip 26, 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. At a MV setting of the igniter 10th For example, 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, and the ignition amplifier 18 is, for example, an ignition amplifier of the type 586.00-55.00.

List of reference numerals:

10

fuze

12

Igniter Chain (from 10)

14

Firing pin (from 10 to 12)

16

Ignition transformer (from 12)

18

Ignition Amplifier (from 12)

20

Rotor (between 14 and 12)

22

Housing (from 24)

24

Ignition Assembly (of 10)

26

Ignition tip (from 10 to 24)

28

Screw connection (from 26 and 22)

30

Cover board (between 22 and 26)

32

End section (from 14)

34

Through hole (in 30 for 14)

36

Blind hole (in 20 for 32)

38

Rotation axis (from 20)

40

Counter-rotating spring (for 20)

42

Actuator (from 10 for 52, 54)

44

Adjusting bolt (from 42)

46

Groove (in 44)

48

Pen (from 22)

50

Longitudinal central axis (from 48)

52

Puncture detonator OV (from 20)

54

Puncture detonator MV (from 20)

56

Safety device (from 10 to 20)

58

first safety lever (from 56)

60

second safety lever (from 50)

62

Axis (from 58)

64

Axis (from 60)

66

Latching element (from 58 for 68)

68

Recess (in 20 for 66)

70

Latching organ (from 60 for 72)

72

Recess (in 20 for 70)

74

Spring element (for 58 and 60)

76

first thigh (from 74)

78

second end section (from 58)

80

second leg (from 74)

82

second end section (from 60)

84

first safety bolt (from 56)

86

second safety bolt (from 56)

88

Bolt spring element (for 84)

90

Bolt spring element (for 86)

92

Blind hole (in 22 for 86 and 90)

94

Blind hole (in 22 for 86 and 90)

96

Hole (in 30 for 84)

98

Recess (in 30 for 86)

100

Bolt lever (for 84)

102

Axis (from 100)

104

Bolt lever spring (for 100)

106

Coupling body (between 84 and 86)

108

Ball (of 106)

110

Recess (from 84)

112

conically tapered section (from 110)

114

Head section (from 86)

115

Head section (from 84)

116

Recess (in 20 for 86)

118

first recess (in 86)

120

second recess (in 86)

122

Detent spring (for 86)

124

Fret (between 118 and 120 for 122)

126

spring loaded pin element (from 20 for 128)

128

Slot recess (in 44 for 126)

130

Top (from 20)

132

spring-loaded stop pins (from 20 to 130)

Claims (15)

1. 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 that

   a) 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) and

   c) 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.
2. Mechanical rocket fuze according to Claim 1,
   characterized in that
   the adjusting device (42) has an adjusting bolt (44).
3. 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.
4. 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).
5. 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).
6. Mechanical rocket fuze according to Claim 5, characterized in that
   the coupling body (106) is formed by a ball (108).
7. 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.
8. 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.
9. 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.
10. 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).
11. 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.
12. 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).
13. 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).
14. 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).
15. Mechanical rocket fuze according to Claim 14,
    characterized in that
    the sprung pin element (126) projects out of the circumference of the rotor (20).

Images