EP3584529A1 - Device for generating an unlocking criterion, igniter and ammunition - Google Patents

Abstract

A device (12) for generating an unlocking criterion (10b) for a detonator (8) for a partially swirling ammunition (2) with the first part (4a) with swirl (D) and second part (4b) without or with less swirl (D) , contains a sensor (14) for outputting a parameter (K) for a relative rotation (R) between the first (4a) and second part (4b) and a control unit (16) for generating the unlocking criterion (10b) if the parameter (K) The device (12) according to the invention for providing the or one of the unlocking criteria contains an igniter (8) for the partially rotating ammunition (2) which has at least one unlocking criterion (10a, 10b). 2) contains a device (12) according to the invention.

Description

The invention relates to a device for generating an unlocking criterion for a detonator for a partially swirling ammunition, which has a first part, which has a swirl around its central longitudinal axis during its intended flight, and which has a second part, which has no movement or only a rolling movement less than the twist around the central longitudinal axis. The invention also relates to a corresponding detonator and ammunition.

A partially swirling ammunition is e.g. B. from the DE 103 41 713 B3 known. It describes a spin-stabilized artillery projectile with a projectile body and a projectile tip with an igniter, which has an igniter housing and an igniter inner part. The detonator is supplied with electrical energy by means of a generator during the flight of the artillery projectile. The projectile tip is designed in such a way that it has a smaller rotational speed than the rotational speed of the swirling projectile body in relation to the projectile body swirling during flight, the generator supplying the detonator with electrical energy due to the relative rotational speed between the swirling projectile body and the slowed projectile tip is driven.

The functioning of a generator with a motor function with a decoupled tip is also known from the document.

A safety device for an igniter is such. B. from the DE 10 2007 054 777 B3 known. A safety device for an igniter is assumed comprising an ignition chain with an ignition means and a barrier, which is locked in its securing by a first securing means and one by the first independent second securing means, which are provided for an unlocking action on the basis of two independent physical unlocking parameters. It is proposed that the ignition chain comprises a second ignition device and that the barrier blocks an intermediate space between the two ignition devices and can be brought into focus by a release movement that releases the intermediate space.

In other words, the mode of operation and the logic of a "MEMSAD" (micro-electromechanical safe and arm device) safety device for an igniter are known from this.

The object of the invention is to provide improvements in relation to an unlocking criterion, a detonator and an ammunition.

The object is achieved by a device according to claim 1 for generating an unlocking criterion. The safety criterion is one that can be supplied to or used in an igniter in order to unlock the igniter. In particular, the device is designed for a specific detonator or a specific type of detonator or is specifically designed for this. The device is then one which is intended to be used in or with a corresponding detonator and thus knows and uses the properties of the detonator. In particular, the unlocking criterion is one of several unlocking criteria in a detonator, all of which must be present together in order to unlock the igniter. The same applies to the detonator: as intended, the detonator is one for a partially rotating ammunition. Such ammunition has a first part which, during the intended flight of the ammunition after the launch, has a swirl around the central longitudinal axis (direction of flight) of the ammunition. The ammunition has a second part which, during flight, has no movement or only a rolling movement less than the twist around the central longitudinal axis. The number of revolutions of the rolling motion (e.g. 0 to 5 Hz) is therefore less than the number of revolutions of the swirl (e.g. approx. 300 Hz).

The device contains a sensor. This is used to record a relative rotation (e.g. rotation present or not / speed) or relative position (e.g. angle) about the central longitudinal axis between the first and second part of the ammunition. The sensor also serves to output a parameter for the detected relative rotation. The parameter therefore reflects the characteristic data of the relative rotation and is, for example, a speed (Hz), a rotation angle (degrees), an electrical voltage or current that relates to the relative rotation with regard to its amplitude, frequency, etc. or an important aspect in the context of the unlocking the relative rotation (e.g. "present or not", duration of the rotation).

The device contains a control unit which is connected to the sensor. The connection is used, among other things, to transmit the parameter. The control unit is set up (e.g. by integrating a corresponding execution program, hard-wired logic, etc.) to only generate the unlocking criterion if the detected parameter fulfills a flight criterion.

In particular, the device is therefore designed as intended for an overall system consisting of a certain detonator (type) and a certain ammunition (a certain type), i. H. intended for installation in these. Corresponding properties of detonator / ammunition are therefore assumed to be known, i. H. the device is aligned or designed accordingly.

A corresponding detonator is, for example, in principle the one mentioned above, which comes from the DE 10 2007 054 777 B3 is known. With regard to its first unlocking criterion (firing shock), this could in principle remain unchanged. The invention could then provide the second unlocking criterion (originally from environmental criteria): The device according to the invention could be used for the second unlocking criterion in the correspondingly modified igniter as at least part of the control unit in connection with the sensor described there (electrical triggering of a pyrotechnic charge).

In terms of the above-mentioned suitability as intended, properties of the detonator and ammunition are therefore also described in the context of the application, although the actual components are not strictly part of the claimed properties The subject matter is, however, related to the invention according to a "key-lock principle". However, these statements also apply mutatis mutandis to the detonator and ammunition according to the invention described below and, if necessary, are not explicitly repeated there.

The invention is based on the knowledge that, for example, steering ammunition is not fired fully swirling. Therefore, the swirl cannot be used (at least not immediately if a corresponding safety device does not swirl) as a safety criterion for a safe and arm unit (detonator). The task thus arises to find a release criterion for non-swirling (partially swirling) steering ammunition. "Not swirling" is to be understood here in such a way that the part in which the igniter or the device for generating the unlocking criterion is accommodated does not swirl, but, for example, rests rotationally or only rolls (rolling: "swirl" with rotational frequencies of e.g. E.g. less than 1, 3, 5, 10, 50, 100, ... Hz).

The invention is further based on the knowledge that it is known from practice that guided ammunition with reduced swirl or with a low roll rate is fired from a weapon system with a tube with swirl trains. The swirl reduction or low roll rate is required in order to be able to intervene in the trajectory in a targeted manner based on information for orientation.

The invention is also based on the knowledge that an electronic unit of an igniter (e.g. MEMSAD) requires two digital signals (0 or 1) on the channels of the unlocking criteria. For the first unlocking criterion, e.g. B. a mechanical signal, namely the opening of a switch on a double bolt system during the launch shock, converted into an electronic or digital signal within the MEMSAD. For the second unlocking criterion - as is known in practice - a digital signal is generated using an environmental sensor board (data from the ammunition environment) or external measurement electronics (measurement while the ammunition is in flight), which clearly indicates a state in flight ( can clearly distinguish whether the ammunition is actually in flight after a shot or not).

The invention is based on the idea that if there is a swirl-decoupled part (second part) of the ammunition, the relative movement between the fully swirling (first part) and un-swirled (second) part can be used as a criterion for unlocking (unlocking criterion).

Since the two parts (which are, for example, part of a generator or contain these parts) are fixed for firing and cannot be moved manually in such a way that a manual unlocking signal is generated, the "Relative movement present" signal is output the sensor (especially the Hall sensor, see below) clearly shows the status "projectile is on the trajectory (in flight after the launch)" and can therefore be used for unlocking. At the same time, this is an environmental criterion that is physically independent of the launch shock (if this is used as a further safety criterion) (criterion from the environment of the ammunition) and thus meets the requirements of the STANAG 4187 safety directive.

According to the invention, the relative rotation or rolling movement of two ammunition parts is determined (in particular by using a Hall sensor, see below) and this state is used as a (in particular second) criterion for unlocking a safe and arm unit (detonator).

The invention offers in particular the advantage of a small space and an inexpensive solution.

According to the invention, therefore, an in particular second unlocking criterion for ammunition, in particular guided ammunition, is generated or a corresponding device is proposed.

In a preferred embodiment, the sensor is a non-contact sensor. "Contactless" means that the sensor in the installed case is at most mounted on one of the parts and works without touching the other part. In particular, the sensor is attached to a third part of the ammunition: in this case it works without contact with the first and the second part of the ammunition. By the The sensor does not, or only minimally or imperceptibly, interfere with the other movements in the ammunition without contact.

In a preferred embodiment, the sensor is a magnetically operating sensor. This works, in particular without contact, via the effect or detection of magnetic fields. The sensor is in particular mounted in a (first, second, third, see above) part of the ammunition, another part then has a magnetic field which is detected differently by the sensor for at least two different rotational positions (Hall sensor, see below), i.e. H. is different or changeable depending on the relative rotation. In particular, there is a permanent magnet in the other part or parts. The rotation moves the magnetic field (or the magnet) in relation to the sensor, which can then be detected.

In a preferred variant of this embodiment, the sensor is a Hall sensor. Hall sensors are particularly inexpensive and commercially available. According to this variant of the invention, the use of a standard component for a safety-related application, namely the present device, results.

In a preferred embodiment, the flight criterion is the following condition, which is transformed into the characteristic variable: The condition is that there has been a minimum number of revolutions between the first and second part and / or a minimum rotational frequency of the relative rotation is present. Transformed into the parameter means that the fulfillment or non-fulfillment of the condition can be distinguished on the basis of the parameter or its evaluation. The flight criterion is therefore to be understood in connection with the parameter when used as intended. For example, the parameter is an output voltage of a Hall sensor. For each rotation between the first and second part, this then detects a positively or negatively directed magnetic field in the intended installation and use. For one revolution, there are zero crossings in the Hall voltage. The flight criterion is then the determination of a minimum number of zero crossings of the voltage or the frequency of a time course of the voltage. The minimum number can be less than one, one or a larger number of revolutions. The frequency is e.g. B. at least 50, 100, 150, 200, 250, or 300 Hz.

The object of the invention is also achieved by an igniter according to claim 6 for a partially swirling ammunition. Detonator and ammunition correspond to the above description in connection with the device according to the invention. The ammunition thus has the first part, which has a swirl around its central longitudinal axis during its intended flight, and a second part, which has no movement or only a rolling movement smaller than the swirl around the central longitudinal axis. The detonator has at least one unlocking criterion that must be met in order to unlock the detonator. The igniter contains a device according to the invention. The device provides the releasing criterion as the or one of the detonator releasing criteria. The igniter is in particular, as described above, principally from the DE 10 2007 054 777 B3 known and modified as explained above according to the invention.

The igniter and at least some of its embodiments and the respective advantages have already been explained in connection with the device according to the invention.

In a preferred embodiment, the detonator has the unlocking criterion generated by the device as the first criterion. The detonator has a second unlocking criterion based on a physical effect that is different from the relative rotation between the parts. The second criterion is based in particular on the launch shock of the ammunition when it was fired. In particular, the independence of the unlocking criteria required by STANAG 4187 is fulfilled.

In a preferred embodiment, the sensor is at least relative to the igniter and is in particular attached to the igniter. Because the detonator is then fastened as intended in the ammunition (in particular in a part of it) or rests there with respect to at least part of the ammunition, the sensor is also fastened in the ammunition and can detect a corresponding relative movement between the two parts ,

The object of the invention is also achieved by an ammunition as described above, which has a first part, during which Intended flight has a swirl about its central longitudinal axis, and which has a second part, which has no movement or only a rolling movement smaller than the swirl around the central longitudinal axis. The ammunition contains a device according to the invention, as described above. The sensor is accordingly arranged or fastened in the ammunition or rests in this or at least in part of the ammunition. According to the invention, a corresponding ammunition is in particular also an ammunition part, for example a 2-D steering module with a decoupled tip or a steering ammunition with a decoupled rear.

The ammunition and at least some of its embodiments and the respective advantages have already been explained in connection with the detonator according to the invention and / or the device according to the invention.

In a preferred embodiment, the ammunition contains a detonator according to the invention, as has already been explained above.

In a preferred embodiment, the sensor and / or the control device of the device and / or the detonator are arranged in the second part of the ammunition. The corresponding components are therefore not subjected to any rotation or only a rolling movement.

In a preferred embodiment, the sensor is a magnetic sensor that is mounted in one (the first or second) of the parts. A magnetic field source for a time-constant magnetic field is mounted in the other (second or first) of the parts. The magnetic field is detected by the sensor in at least a first rotational position. No or a changed magnetic field is then detected in at least one second rotational position. This ensures that the sensor can detect or differentiate between individual rotation positions and thus also the rotation between the two parts. By mounting (at rest) in one part, the sensor also reproduces the direct relative movement to the other part.

In a preferred variant of this embodiment, the magnetic field source contains or is at least one permanent magnet. This leads to a particularly simple and reliable embodiment of the ammunition.

In a preferred variant of this embodiment, the magnetic field source is that of a generator and / or motor which is divided into two components in the first and second parts. "Two-component" means that a first part of the motor / generator is fastened or rests in one part of the ammunition (eg a stator) and a second part (eg rotor) in the second part of the ammunition. The parts of the motor / generator are then rotated relative to one another by the relative rotation. A corresponding ammunition with generator / engine is in principle z. B. from the DE 103 41 713 B3 known, as explained above. In this regard, the invention is based on the knowledge that such a generator at the decoupling point in the ammunition (between the first and second part) makes use of the relative movement of the decoupled ammunition parts, for example projectile body and detonator tip or projectile body and tail, for energy generation. In order to use this generator as a motor at the same time, Hall sensors are used anyway. With this, the decoupled part can be rotated in a specific position or phase position with respect to the swirling part by means of a control algorithm. Hall sensors do not have a large installation volume, so that a second Hall sensor (as a sensor of the device) can easily be used at this interface, from which a signal for unlocking is then derived from the relative movement. A second Hall sensor is therefore used so that the unlocking criterion of the ignition chain is not coupled with the control algorithms for influencing the flight path.

In a preferred variant of this embodiment, the device according to the invention therefore has a first Hall sensor as a sensor and the generator and / or motor has a second magnetic field sensor as a Hall sensor.

Figur 1

eine Munition mit Zünder mit erfindungsgemäßer Vorrichtung im Blockdiagramm.

Further features, effects and advantages of the invention result from the following description of a preferred exemplary embodiment of the invention and the attached figures. Show, each in a schematic sketch:

Figure 1

an ammunition with detonator with the inventive device in the block diagram.

Figure 1 shows a partially swirling ammunition 2, which comprises a first part 4a and a second part 4b. The Figure 1 shows the ammunition 2 after its firing, ie during the flight towards a target, not shown.

As intended, the first part 4a has a swirl D about a central longitudinal axis 6 of the ammunition 2. The ammunition flies in the direction of the central longitudinal axis 6. According to the swirl D, the first part 4a rotates at 300 revolutions per second (Hz) around the central longitudinal axis 6. The second part 4b, on the other hand, is rotationally at rest, ie. H. does not rotate about the central longitudinal axis 6. First 4a and second part 4b thus rotate in a relative rotation R (indicated by a double arrow) relative to one another, here at 300 Hz, about the central longitudinal axis 6.

The second part 4b of the ammunition 2 contains an igniter 8 in order to detonate the ammunition at a suitable point in time, which is not explained in more detail here. However, this only happens when the detonator is unlocked. This requires the existence of two unlocking criteria 10a, 10b. A first unlocking criterion 10a already exists in the flight shown, since this was generated when the ammunition 2 was fired.

In order to generate the second unlocking criterion 10b, the igniter 8 contains a device 12 which is shown in FIG Figure 1 is shown outside the igniter 8. The device 12 contains a sensor 14 (also indicated by dashed lines in part 4b) which detects the relative rotation R between the first 4a and the second part 4b about the central longitudinal axis 6. The sensor 14 is fixed in place in part 4b and outputs a characteristic variable K which reflects the relative rotation R. In the example, sensor 14 is a non-contact and magnetically operating Hall sensor. The sensor 14 detects a magnetic field dependent on the angle of rotation of a magnetic field source 18 which is fixedly mounted in part 4a.

The characteristic variable K is the Hall voltage emitted by the sensor 14, or its course over time t. In the example, the sensor system is designed such that a sine oscillation of the Hall voltage results in the case of a relative rotation R in the form of a single rotation. The sensor 14 is fixedly attached to the igniter 8. The sensor 14, the control unit 16 and the entire detonator 8 are thus arranged in the second part 4b of the ammunition 2 or fixed in place there.

In order to form a corresponding sensor system, the magnetic field source 18, here a permanent magnet, is fixed in place in the first part 4a of the ammunition 2. The magnetic field source 18 generates a time-constant magnetic field. In the event of a rotation or relative rotation R, the magnetic field source 18 generates a variable magnetic field in the sensor 14. The current magnetic field or the corresponding change is reflected in the parameter K or its time profile over the time t.

The magnetic field source 18 is part of a generator 20 of the ammunition 2, which is distributed in the first 4a and second part 4b of the ammunition 2. For this purpose, the generator 20 contains a counterpart 22 (not explained in more detail), here a coil arrangement, in the second part 4b. The generator 20 can also be operated as a motor. In order to implement a corresponding control of the motor, a further magnetic field sensor 24, here also a Hall sensor, is provided, which likewise interacts with the magnetic field source 18 in order to control the relative position between the first part 4a and the second part 4b in a manner not explained in more detail To accomplish ammunition 2. In the present case, given a swirl D of the first part 4a, the second part 4b is controlled in such a way that it remains at rest with respect to rotation about the central longitudinal axis 6.

The device 12 also contains a control unit 16. This is set up or configured as follows by means of electronic components or corresponding programming (not explained in more detail):
The control unit 16 monitors the characteristic variable K for a flight criterion F. As long as this is not present ("N"), the monitoring is continued, as soon as it is present ("J"), the unlocking criterion 10b is generated.

The flight criterion F is designed in such a way that it is only fulfilled after the ammunition 2 flight. In the present case, the flight criterion F includes that an alternating signal with a frequency of at least 250 Hz is present in the parameter K over time t for at least 1 second. This condition is fulfilled a good 1 second after the ammunition 2 has been fired, since the swirl D and thus the frequency of the characteristic variable K after the firing from 0 Hz to 300 Hz until the barrel is left increases and in any case remains above 250 Hz in flight. The delay of 1 second results in a corresponding downtube security.

LIST OF REFERENCE NUMBERS

2

ammunition

4a, 4b

first, second part

6

central longitudinal axis

8th

fuze

10a, 10b

arming

12

contraption

14

Hall sensor

16

control unit

18

magnetic field source

20

generator

22

counterpart

24

Magnetic field sensor (Hall sensor)

D

twist

R

relative rotation

t

time

K

parameter

F

flight criterion

Claims (15)

Device (12) for generating an unlocking criterion (10b) for a detonator (8) for a partially swirling ammunition (2), which has a first part (4a) which has a swirl (D) around its central longitudinal axis (6) during its intended flight and which has a second part (4b) which has no movement or only a rolling movement smaller than the twist (D) about the central longitudinal axis (6), - With a sensor (14) for detecting a relative rotation (R) about the central longitudinal axis (6) between the first (4a) and second part (4b) of the ammunition (2) and for outputting a parameter (K) for the detected relative rotation (R ) - And with a sensor (14) connected to the control unit (16), which is set up to generate the unlocking criterion (10b) only when the detected parameter (K) fulfills a flight criterion (F). Device (12) according to claim 1,
characterized,
that the sensor (14) is a non-contact sensor. Device (12) according to one of the preceding claims,
characterized,
that the sensor (14) is a magnetically working sensor. Device (12) according to claim 3,
characterized,
that the sensor (14) is a Hall sensor. Device (12) according to one of the preceding claims,
characterized,
that the flight criterion (F) is the condition transformed into the parameter (K), that there has been a minimum number of revolutions between the first (4a) and second part (4b) and / or that there is a minimum rotational frequency of the relative rotation (R). Detonator (8) for a partially swirling ammunition (2) which has a first part (4a) which has a swirl (D) around its central longitudinal axis (6) during its intended flight, and which has a second part (4b) which there is no movement or only a rolling movement smaller than the twist (D) about the central longitudinal axis (6), the igniter (8) having at least one unlocking criterion (10a, 10b), with a device (12) according to one of the preceding claims provides the unlocking criterion (10b) as one of the unlocking criteria (10a, 10b) of the detonator (8). Detonator (8) according to claim 6,
characterized,
that the igniter (8) has the unlocking criterion (10b) to be generated by the device (12) as the first criterion and has a second unlocking criterion (10a) which is based on a physical effect resulting from the relative rotation (R) between the two parts (4a, 4b) is different. Detonator (8) according to one of claims 6 to 7,
characterized,
that the sensor (14) is attached to the igniter (8). Ammunition (2) which has a first part (4a) which has a swirl (D) about its central longitudinal axis (6) during its intended flight, and which has a second part (4b) which has no movement or only a rolling movement smaller than the twist (D) around the central longitudinal axis (6), with a device (12) according to one of claims 1 to 5. Ammunition (2) according to claim 9,
characterized,
that it contains an igniter (8) according to one of claims 6 to 8. Ammunition (2) according to one of Claims 9 to 10,
characterized,
that the sensor (14) and / or the control unit (16) of the device (12) and / or the igniter (8) are arranged in the second part (4b) of the ammunition (2). Ammunition (2) according to one of claims 9 to 11,
characterized,
that the sensor (14) is a magnetic sensor which is fastened in one of the parts (4a, b) and in the other of the parts (4b, a) a magnetic field source (18) for a time-constant magnetic field is mounted. Ammunition (2) according to claim 12,
characterized,
that the magnetic field source (18) contains at least one permanent magnet. Ammunition (2) according to one of claims 12 to 13,
characterized,
that the magnetic field source (18) is that of a generator (20) and / or motor which is divided into two components in the first (4a) and second part (4b). Ammunition (2) according to claim 14,
characterized,
that the device (12) has a first Hall sensor as a sensor (14) and the generator (20) and / or motor has a magnetic field sensor (24) as a second Hall sensor.

Images