EP2513594B1 - Dispositif de sécurité pour une amorce de projectile - Google Patents

Dispositif de sécurité pour une amorce de projectile Download PDF

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Publication number
EP2513594B1
EP2513594B1 EP10784255.1A EP10784255A EP2513594B1 EP 2513594 B1 EP2513594 B1 EP 2513594B1 EP 10784255 A EP10784255 A EP 10784255A EP 2513594 B1 EP2513594 B1 EP 2513594B1
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Prior art keywords
signal
acceleration
projectile
output
sensor
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EP10784255.1A
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German (de)
English (en)
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EP2513594A1 (fr
Inventor
Karl Kautzsch
Siegfried Lauble
Robert HÜTTNER
Andreas Schellhorn
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Junghans Microtec GmbH
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Junghans Microtec GmbH
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/18—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a carrier for an element of the pyrotechnic or explosive train is moved
    • F42C15/184—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a carrier for an element of the pyrotechnic or explosive train is moved using a slidable carrier
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/24—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein the safety or arming action is effected by inertia means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/40—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein the safety or arming action is effected electrically

Definitions

  • the invention relates to a safety device for an igniter of a projectile, which has an ignition device for igniting the igniter, comprising a safety device with a process means for securing an ignition process of the ignition device.
  • 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 may be provided with a detonating chain of two or more ignition means.
  • the first ignition means is first activated, z.
  • B. a tap-sensitive Minidetonator that is pierced by a piercing 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.
  • an arming unit or safety device in which a speed is determined by means of an acceleration sensor and an integrator and compared with a reference speed. Arming is initialized only when the reference speed is reached within a given time slot.
  • the US Pat. No. 7,191,707 B1 deals with a round, rolling weapon in the form of a bomb.
  • the bomb has a fuse unit where either arming is triggered by computer or is in the presence of a motion profile indicating that the bomb is not moving.
  • the bomb may be equipped with three motion sensors, with a release takes place only if none of the sensors detects a movement.
  • it can be provided that, although a release is made, but only then a detonation is possible if no rolling motion of the bomb is more detectable.
  • a fuse for a projectile of a projectile which has a detonation chain for igniting the igniter and an interrupting means for interrupting the ignition chain
  • the safety device comprises a sensor unit which is prepared, in an accelerated state in the detonator, which is at least a predetermined acceleration value below the acceleration due to gravity, to output a release signal, and a processing means which is prepared to output a control signal for releasing the interruption means in response to the presence of the release signal.
  • the weightlessness or a state of low severity, ie low acceleration can be used.
  • This parameter is independent of a launch parameter and can be used with it, eg. B. in connection with the use of a launch parameter, a high security against unwanted ignition can be achieved.
  • a ballistic flight is characterized by a substantially weightless state of the projectile
  • the sensing of the weightless state or a state of low acceleration may serve as a release parameter be used. If a predetermined acceleration state is registered in the igniter or detonator by an acceleration sensor, which, for example, is far below the acceleration due to gravity, then it can be deduced that the flight phase is present and the interrupting means can be released.
  • the invention is particularly suitable for ballistic missiles, such as missiles, in particular mortar shells, missiles with a non-powered flight phase, bombs and the like.
  • Ballistic missiles fly through a trajectory that is approximately characterized by a parabolic parabola and in which the missile is in a weightless state, apart from the deceleration acceleration due to air resistance.
  • the ignition device may contain a priming charge. In particular, it may be part of or contain a detonating chain for igniting the detonator.
  • the fuse unit serves to secure the ignition process, in particular against inadvertent release of the igniter. It may be embodied purely electronically, for example by processing signals from sensors which measure physical parameters and, in the presence of a predetermined signal state or a corresponding physical state of the igniter, initiating a release by issuing a control signal.
  • the securing unit may comprise mechanical securing means, for. B. an interruption means for breaking the ignition chain.
  • the interrupting means can serve for receiving and / or deflecting the ignition energy of an ignition means, so that ignition of the further ignition means is reliably prevented by ignition energy of the first ignition means.
  • the interrupting means may be a barrier, a means for extinguishing two firing means, or any other means for preventing or interrupting firing by the firing chain.
  • the interruption means may comprise a plurality of securing means which unlock a barrier and advantageously have to be activated independently of one another.
  • the ignition device comprises a firing chain with a primer for igniting the igniter and the fuse unit comprises an interrupting means for interrupting the ignition chain.
  • the acceleration state may be the instantaneous acceleration of the sensor unit and / or the igniter.
  • the specified acceleration state is in particular an acceleration state in the igniter. It is at least below a specified acceleration value below the acceleration due to gravity, that is to say below a limiting value which is below the acceleration due to gravity, and may be any value below the gravitational acceleration or gravitational acceleration which is approximately 9.81 m / s 2 .
  • An acceleration range below the acceleration due to gravity is also possible, for example between 0 m / s 2 and 5 m / s 2 .
  • the predetermined acceleration state in the longitudinal direction or flight direction of the projectile is below 5 m / s 2 , it is expediently below this value in all three spatial directions, in particular the overall acceleration is below this value.
  • the specified acceleration state or limit value or acceleration value can be determined by a corresponding setting in the securing device, for example, the sensor unit and / or the process means, or be deposited in another unit.
  • the sensor unit expediently contains an acceleration sensor which may be prepared to compensate for the instantaneous acceleration, e.g. B. in the igniter to measure.
  • the acceleration may be measured due to a force acting on the acceleration sensor as a result of gravity and / or as a result of a change in the speed of the sensor as it moves through the space.
  • the sensor unit can measure the acceleration state as one-dimensional acceleration. Expediently, the acceleration state is measured multidimensionally, in particular three-dimensionally.
  • the sensor unit is designed so that a release process begins when the acceleration state falls below the limit.
  • the release process may begin by one or more signals that are output below the limit as the acceleration falls.
  • the release process results in the enable signal, but may not until further conditions exist, e.g. the acceleration state is below the threshold for a predetermined period of time or it is aborted, e.g. if the acceleration state rises too fast again above the limit value.
  • the process means is prepared to check the presence of the enable signal and, depending on its presence, to output the control signal for unlocking.
  • a preparation can be provided by a corresponding control program, the sequence of which-for example in conjunction with the input signals from the acceleration sensor-effects such a control.
  • the control signal is expediently an electrical signal on a data line which can trigger a release in conjunction with a corresponding arming device.
  • the enable signal is expediently also an electrical signal which is transmitted to the process agent via a data line.
  • the sensor unit is prepared for measuring three directional accelerations in three mutually orthogonal spatial directions. In this way, a total acceleration or an acceleration state in the igniter can be calculated in a simple manner from the three direction accelerations.
  • the release signal takes place only when each of the three directional accelerations is at least one fixed acceleration value below the acceleration due to gravity.
  • the sensor unit may comprise a logical AND link, which is only fulfilled when each directional acceleration is at least by the respective predetermined acceleration value below the gravitational acceleration.
  • the specified acceleration value in the direction of flight be different than the specified value in the two other directions which are expediently orthogonal thereto. Whether the specified acceleration value in the direction of flight is chosen to be greater or smaller than the specified value in the other two directions can be made dependent on the missile or on mission data. If the missile is possibly subject to major imbalance or vibration during flight, it is advantageous to increase the values perpendicular to the direction of flight to ensure detente during the flight despite the disturbances. If the missile is very fast, it also experiences a relatively large negative acceleration due to the air resistance, during which it is permanently decelerated, even during the ballistic flight, which in itself is not heavy. In this case, the value in the direction of flight can be selected to be larger, so that the release signal can already take place if the acceleration state in the direction of flight is still somewhat greater.
  • a further advantageous embodiment of the invention provides that the specified acceleration state is below the gravitational acceleration by at least one specified acceleration value and the processing means is prepared to monitor the acceleration value in the direction of flight and to detect an absolute minimum in the course of the acceleration value.
  • the absolute minimum indicates the lowest air resistance during the flight and thus the achievement of the vertex of the trajectory of the projectile. If the presence of this absolute minimum is used as the arming criterion which must be present for the output of the control signal, in particular simultaneously with the presence of the enable signal, the control signal is not carried out until the projectile has passed the vertex of its path. This allows a high Vorrohr be ensured. Accordingly, the process means checks for the presence of the minimum before it outputs the control signal.
  • a simple check of the acceleration state to a value below the limit value, ie at least the specified acceleration value under acceleration due to gravity, can be achieved with a comparator with which the acceleration value or limit value can be set.
  • a signal of an acceleration sensor can be compared with a preset value and a corresponding release signal can be output if the specified signal value is exceeded or fallen short of.
  • the securing device advantageously comprises a time element for specifying a time interval, wherein the processing means expediently outputs the control signal only when the release signal is present during the time interval, in particular is present uninterrupted.
  • the time element may be part of the sensor unit, part of the process means or separately.
  • a particularly inexpensive circuit can be achieved if the time element is prepared to block the enable signal of the sensor unit during the time interval.
  • the time element can be made particularly inexpensive and reliable.
  • the time interval is greater than one second, so that a free fall must be longer than 5 m in order to use the enable signal to generate the control signal can. If the time interval is greater than two seconds, an unlocking case must be more than 19.62 m.
  • a further advantageous embodiment of the invention is based on the following considerations.
  • a low-power condition of the igniter can be detected during the flight of the projectile.
  • the low-energy state can be characterized by an acceleration state in which the total acceleration of the igniter is below the limit value.
  • a state "flight" can be distinguished from the state "ground” to generate the control signal as a release criterion, in particular as a further arming criterion according to a first arming criterion.
  • Projectiles usually spin around their longitudinal axis during a flight, even if they are fired without a spin.
  • a usual roll rate is up to 2 Revolutions per second, whereby modern ammunition for flight stabilization by a tail unit during flight is brought up to 20 revolutions per second.
  • the sensor unit is not located exactly in the axis of rotation of the projectile during flight, it is subject to a centrifugal force of the projectile in the air, which acts as a lateral acceleration and is measured by the sensor unit accordingly.
  • the sensor unit can be mounted sufficiently accurately in the longitudinal axis of the projectile, since manufacturing tolerances can be kept low.
  • the geometric longitudinal axis of the projectile is usually not in the axis of rotation of the projectile, ie the axis about which the projectile rolls during the flight.
  • the deviation can result from an asymmetrical loading of the projectile with other components and above all disintegration agents, which draw the center of gravity of the projectile from the geometric longitudinal axis.
  • Such imbalance can lead to disturbing transverse acceleration values of the sensor unit at high roll rates, which reduce the reliability of outputting a control signal for the purpose of arming.
  • the sensor unit has a roll sensor which is prepared to detect a roll of the projectile and to output a roll signal in the event of a rolling movement of the projectile, then the roll can be recognized and processed as additional information, e.g. from the process means for outputting the control signal for unlocking.
  • the process means is prepared to output the control signal for unlocking in dependence on the presence of the roll signal.
  • the rolling of the bullet is to be distinguished from a spin of bullets. While a twist is usually above 100 Hz, rolling is already below 100 Hz. In the following, a rotation between 1 Hz and 50 Hz, in particular between 2 Hz and 25 Hz, is defined as a roll and above 50 Hz as a twist.
  • the roll sensor detects a twist-free rolling of the projectile and outputs the roll signal even in a swirl-free state of the projectile.
  • the state "flight" can be clearly recognized from this.
  • the predetermined property is expediently chosen to be the condition "flight” with predetermined sufficient certainty characterized.
  • the process means is prepared to check both the enable signal and the roll signal on their presence and output in the presence of at least one of the two signals, the control signal for unlocking.
  • a logical OR circuit of the two signals can be used, which indicates whether one or the other signal is present.
  • the control signal can also be output if both signals are present simultaneously.
  • the sensor unit of the projectile may experience a lateral acceleration due to an imbalance of the projectile, however, the longitudinal acceleration is small in any case. It is only determined by the delay due to air resistance. It is therefore advantageous if the state "flight" detected by the roll signal is verified by a query of the longitudinal acceleration, that is to say the acceleration of the fuze in the direction of flight or in the direction of its longitudinal axis or in the axial direction. Conveniently, the process means is therefore prepared to check in the presence of the roll signal, whether the acceleration of the projectile in the axial direction is below a predetermined value and to output the control signal for unlocking only when the value is exceeded.
  • the roll sensor is expediently an acceleration sensor, which is arranged in particular outside the geometric longitudinal axis of the projectile. If this experiences a permanent acceleration, ie beyond a predetermined period of time, above the acceleration due to gravity, or more generally: above a predetermined value, this is an indication of the presence of the condition "flight".
  • the roll signal can be output to the process agent.
  • a magnetic field sensor is conceivable which senses the geomagnetic field and recognizes the roles and thus the state "flight” based on the relative rotation of the earth's magnetic field. Also advantageous is a gyroscope or a revolution counter.
  • the process means is prepared to distinguish on the basis of signals, in particular signals from the sensor unit, a free rolling of the projectile from a rolling of the projectile on a substrate.
  • signals in particular signals from the sensor unit
  • Such a distinction may be based on measurements of lateral acceleration over time. In a free-rolling these are constant, possibly even zero or near zero, whereas bottom roll is characterized by alternating lateral acceleration values in the orthogonal transverse directions.
  • the signals are therefore expediently signals which were obtained from the measurement of the lateral acceleration of the projectile or of the detonator.
  • a corresponding acceleration sensor is present, in particular as part of the sensor unit.
  • the sensor unit has a floor roll sensor which is prepared to detect a floor roll of the projectile on a substrate and to output a floor roll signal in the event of floor rolls.
  • the floor rolling may be a rolling movement with a lateral acceleration of the projectile which is in a predetermined relationship with the rolling movement.
  • the process means is prepared to suppress the output of the control signal for unlocking the interruption means in the presence of the ground roll signal. Underpressure is also understood to mean that the control signal will not output, regardless of whether it has already been generated in a signal pre-stage.
  • the bottom roll sensor may be part of the sensor unit or may be configured separately.
  • the invention is also directed to an igniter of a projectile having a safety device as described.
  • the invention relates to a method for releasing a fuse of a projectile, which comprises an ignition device with a detonator for igniting the igniter and a safety device with a fuse unit with a breaker for interrupting the ignition chain, which includes a process means for securing an ignition of the igniter.
  • an acceleration state in the igniter is detected by means of a sensor unit after the acceleration state has fallen below the acceleration due to gravity by at least one specified acceleration value
  • Release signal is output from the sensor unit and in response to the presence of the enable signal, a control signal for unlocking the interruption means is output by the process means.
  • Fig. 1 1 shows an operating scheme of a safety device 2 of a fuze 4 (FIG. Fig. 2 ) of a projectile.
  • a launch of the projectile is detected by a first securing means 6, for example a double-bolt system.
  • a timer set in motion, which ensures a Vorrohrschreib.
  • a third securing means 10 which may be a sensor unit for measuring an acceleration state, detects a low-acceleration flight condition and outputs a corresponding signal. This is given together with an action of the timer on an AND logic 12, which can be realized mechanically or electronically. An action can be done mechanically, z. B. by a mechanical release, or an electrical signal.
  • the operation of the AND logic 12 is switched to a further AND logic 14, which also acts on a third securing means 16, z. B. another time element.
  • the AND logic 14 acts on a means 18 for focusing the igniter 4, so that, for example, a force element is unlocked.
  • a fire signal 20 which must coincide with a sharp state of the igniter 4 by the means 18 - according to the further AND logic 22 - an ignition 24 of the igniter 4 is effected.
  • the safety device 2 off Fig. 1 is in Fig. 2 shown by a circuit diagram representation. It is housed in the igniter 4, which comprises a detonating chain with two ignition means 26, 28, wherein the ignition means 26 ignites the ignition means 28 with an ignition energy.
  • the igniter 4 may include an interrupting means 30, e.g. B. in the form of a movable barrier, which can be swung out by a mechanism 32 from the ignition chain, so that the ignition means 26 can ignite to the ignition means 28.
  • the mechanism 32 is controlled by a processing means 34 via a signal line 36, on which the processing means 34 sends a control signal for releasing the interruption means 30 to the mechanism 32, which converts the control signal into a mechanical movement for leading out of the interruption means 30 from the firing chain.
  • securing means 6, 8, 16 the ignition of the igniter and the fuse of the ignition process is described concretely in the illustrated embodiment, but the invention is not limited to these specific means. Rather, it is just as possible to use more or less and / or other securing means and to dispense with the ignition chain and in particular the interruption means and to use a different ignition and in particular interruption. In particular, an electronically controlled ignition and / or a purely electronic interruption of an ignition process is conceivable.
  • the process means 34 is connected to a sensor unit 38, which is an acceleration sensor unit. It is designed as a low-g sensor unit, which detects an acceleration state in which the amount of the total acceleration, z. B. in igniter 4, below the acceleration due to gravity, that is below the g-value of about 9.81 m / s 2 . Conveniently, it is therefore an acceleration sensor that responds to a total acceleration whose magnitude is below the acceleration due to gravity.
  • the sensor unit 38 comprises a sensor 40 with three outputs 42, 44, 46, each with a filter 48, three comparators 50, 52, 54, a time element 56 with an ohmic resistor 58 and a capacitor 60 and a comparator 62.
  • An output stage 64 which may be part of the processing means 34 is designed to output a release signal.
  • the securing device 2 comprises a self-test unit 66 with a controller 68.
  • the senor 40 which is a three-axis acceleration sensor, measures the acceleration in three orthogonal spatial directions, namely in the direction of flight of the projectile, ie parallel to its longitudinal axis, and in two transverse directions perpendicular to each other and perpendicular to the direction of flight. As a result of its measurement, it outputs an output signal for each spatial direction which is in a known relation to the acceleration of the sensor 40 in the corresponding spatial direction.
  • the three signals are output on the three outputs 42, 44, 46, wherein the sensor 40 is mounted in the fuse or igniter 4 so that on the output 42, the signal is applied, the acceleration of the igniter 4 and the securing device 2 indicates in the direction of flight of the projectile.
  • On the other two outputs 44, 46 are the two signals that correspond to the acceleration of the sensor 40 in the transverse directions.
  • the three signals are filtered by one of the filters 48, which is a low-pass filter.
  • This filter 48 filters the high-frequency component of the signal above z. B. 100 Hz out.
  • the filtered signals are applied to the three comparators 50, 52, 54. At their inputs is thus in each case the corresponding signal and in each case a comparison signal v 1 , v 2 , v 3 , wherein the comparators 50, 52, 54 compare the signals respectively.
  • the comparison signals v 1 , v 2 , v 3 in this case form threshold values.
  • the output signal of the comparator 50 is located on a z. B. negative or low voltage value in relation to ground or another reference potential value. Exceeds the signal from the filter 48, the comparison signal v 1 , the output signal of the comparator 50 z. B. a positive or higher voltage.
  • the signals from the outputs 42, 44, 46 correspond to the respective acceleration of the sensor 40 in a spatial direction, the sensor 40 outputs the signals inverted. The higher the acceleration in one direction, the lower the signal at the corresponding output 44, 44, 46.
  • the comparison signals v 1 , v 2 , v 3 thus form limit or threshold values, wherein when the signals exceed the above Comparison signals v 1 , v 2 , v 3 - ie at a decrease in the accelerations below the threshold values - the respective output signal of the comparators 50, 52, 54 from z. B. negative in a z. B. transferred positive potential.
  • the comparison signals v 1 , v 2 , v 3 form threshold values which correspond to acceleration limit values in each case in one spatial direction. If the acceleration in a spatial direction, for example in the direction of flight, falls below the limit, the signal on the output 42 rises above the comparison signal v 1 and the output voltage of the comparator 50 is positive.
  • the limit values are each below a specified value below the acceleration due to gravity, so that if the accelerations fall below their limit values in all three spatial directions, there will in any case be an acceleration state which is a specified further value below the acceleration due to gravity. If, for example, the limit value in the direction of flight is 0.14 m / s 2 and the limit value for the other two spatial directions is 0.1 m / s 2 , then the total acceleration is ⁇ 0.2 m / s 2 if the release signal is present.
  • an AND circuit is formed. If only one of the comparators 50, 52, 54 has a positive output signal, ie if only one acceleration value is below the limit value, then the signal on the output line 70 is negative, since it is held negative by the other two comparators 50, 52, 54. If the outputs of two comparators 50, 52, 54 are positive, a voltage source 72 ensures that the signal on the output line 70 is also negative or at a corresponding electrical potential. Only when all three outputs of the comparators 50, 52, 54 are positive, then the signal on the output line 70 is positive.
  • the positive signal reaches the time element 56, which is implemented by the resistor 58 and the capacitor 60 so that the positive signal on the output line 70 is blocked during a predetermined period of time, so that it does not reach the line 74.
  • the duration may, for example, be a few seconds, e.g. B. 1 - be 5 seconds. Only after this period of time is the capacitor 60 charged and the signal is present on the line 74. As a result, the potential on the line 74 is higher than the comparison signal v 4 at the comparator 62.
  • the output of the comparator 62 changes from z. B. negative to positive potential and thereby generates a release signal to the output stage 64, the release signal in the same or changed form to the process means 34 passes in two outputs, once as a positive signal and in addition to safety as a negative signal.
  • the processing means 34 In the presence of the enable signal, the processing means 34 generates the control signal for driving the mechanism 32 and releasing the interruption means 30 or the ignition chain.
  • the release signal is passed on directly to the mechanism 32 or the interruption means 30 for releasing the ignition chain.
  • the output stage 64 already outputs the control signal without the process means 34 being necessary for this purpose.
  • the output stage 64 can be understood here as a process agent itself.
  • the process means 34 is also connected directly to the output 42 of the sensor 40 and thereby monitors the acceleration value of the sensor 40 in the direction of flight.
  • the monitoring is directed to an absolute minimum in the course of this acceleration value, expediently only the frequency part z.
  • B a Fourier spectrum of the signal on the output 42 with a frequency in the range greater than one second for evaluation to the absolute minimum.
  • the flying through of the vertex of the trajectory is detected, and in another embodiment, the presence of this minimum is used as a further safety criterion for generating the control signal on the signal line 36.
  • the enable signal from the output stage 64 is present and the minimum has not yet been detected, then no control signal is given to the mechanism 32. Only when the minimum has been detected and at the same time the release signal from the output stage 64 over a period which is greater than a predetermined limit, in the range of 1-5 seconds, the process means 34 was present, the control signal is switched to the signal line 36.
  • the fuse unit 2 can be checked.
  • a switch 76 is closed by the controller 68 and the potential on the line 74 permanently z. B. held negative potential.
  • the command for such a self-test is generated by the processing means 34, which responds, for example, to a command from an operator.
  • the controller 68 outputs a corresponding signal to the sensor 40 due to which the potentials on the outputs 42, 44, 46 are increased by a predetermined value, corresponding to a very low acceleration.
  • the corresponding values are used by the self-test unit 66 for Control tapped, evaluated and the result is communicated to the controller 68. Although this generates the positive signal on the output line 70 and optionally propagates it via the time element 56, the closed switch 76 ensures that the comparator 62 does not generate an enable signal.
  • the controller 68 outputs an additional blocking signal to the output stage 64.
  • Fig. 3 shows a further embodiment in which the in Fig. 2 shown sensor unit 38 is extended by a roll sensor 78 and bottom roll sensor 80.
  • the representation of the self-test unit 66 and the controller 68 of the sensor unit 38 has been dispensed with, it being understood that both units can be present. All components shown are part of the fuze 4, which is also in Fig. 3 is indicated.
  • the sensor unit 38 as shown in FIG Fig. 3 includes a roll sensor 78, a bottom roll sensor 80 and a low-g sensor 82, which is already closed Fig. 2 has been described and is the same, how to Fig. 2 is described.
  • the low-g sensor 82 is opposed by the roll sensor 78. Both sensors 82, 78 generate their signal independently and deliver it to output stage 64, with both the low-g signal that low-g sensor 82 supplies to output stage 64 and the roll signal, that of roll sensor 78 to the output stage 64 which can trigger the control signal to enable the interruption means 30.
  • the roll sensor 78 comprises a sensor 84, in this embodiment a single-axis gyroscope, which detects a rolling movement of the igniter 4 about its roll axis. Equally well an acceleration sensor is possible, which is arranged outside the longitudinal axis of the projectile.
  • the signal from the sensor 84 is filtered by a filter 86, which is a low-pass filter for filtering noise, and given to a comparator 88.
  • the resulting signal is applied to a comparator 92 via a time element 90, which has the same structure as the time element 56 given, which outputs the roll signal.
  • the time element 90 and the comparator 92 are used by the bottom roll sensor 80 and are shown as part of the bottom roll sensor 80, they can just as well be components of the roll sensor 78.
  • the sensor 84 When the projectile or the igniter 4 rolls, the sensor 84 generates a signal which corresponds to the rolling rate, that is to say the rotational speed of the igniter 4 about the rolling or longitudinal axis of the igniter 4 or projectile. The signal grows with increasing roll rate.
  • the signal is compared by the comparator 88 with a comparison signal v 5 .
  • the comparator 88 When the signal rises above the comparison signal v 5 , the comparator 88 outputs a positive signal, or the signal of the comparator 88 changes from a negative or a low value to a positive or higher value.
  • the comparison signal v 5 is chosen so that the roll signal only becomes positive at a fixed roll rate, for example 2 Hz.
  • the transverse acceleration acting as an interference acceleration which the sensor 40 experiences as a result of an unbalance of the projectile, is so small that a failure of the low-g signal caused by the imbalance can be ruled out for reasons of fixed production tolerances of the projectile.
  • the time element 90 checks whether the roll signal is present for a longer period of time, which can be in the range of 1 to 5 seconds, for example, without interruption. Only when this is the case, the roll signal penetrates to the comparator 92 is there - released analogously to the comparator 62 and given to the output stage 64.
  • the low g signal of the low g sensor 82 and the roll signal of the roll sensor 78 are treated equivalently in the output stage 64. If one of the two signals is present, the output stage 64 and the processing means 34 react as if Fig. 2 described and the control signal for unlocking the interruption means 30 is output.
  • the low-g signal and the roll signal are therefore interconnected in an OR operation, so that the presence of one of the two signals is checked. The control signal can thus be triggered simultaneously even when both signals are present, which is usually the case, that is to say with a small imbalance of the projectile.
  • a triggering of the control signal for unlocking the interruption means 30 is to be avoided at all costs, when the projectile is rolled on the ground and not in "flight" state, so not flying freely.
  • the roll sensor 78 can not distinguish whether the rolling motion is due to a uniform roll on the ground or a free-flying roll. He therefore outputs the roll signal even when rolling on the ground.
  • the sensor unit 38 is equipped with the bottom roll sensor 80, which detects a rolling of the projectile on the ground.
  • the ground roll sensor 80 uses an input signal from an output of the sensor unit 20, namely a signal of the output 44 or 46 or both outputs 44, 46, which represent the lateral acceleration.
  • the two sensors of the sensor unit 40 which measure the transverse accelerations, output an alternating signal, since they measure the gravitational acceleration downward. Since the sensor unit 40, at least its two sensors which measure the lateral acceleration, is arranged in the geometric axis of the projectile, the speed of the rolling does not affect the amplitude of the alternating signal as well, since the sensor unit 40 does not measure any centrifugal force.
  • the alternating signal is filtered by a filter 94, which is a high-pass filter, so that only high-frequency components of the alternating signal above a predetermined frequency, for example 2 Hz, pass through the filter. In this way, only a bottom roll above the predetermined frequency is detected.
  • the alternating signal is converted into a simply smoothed DC voltage signal, which is now applied to the comparator 98.
  • Rolling of the projectile on a ground causes at the entrance of the filter 94 an alternating signal with the roll frequency and the amplitude, which corresponds to approximately 1 g.
  • the rectification ripple 95 the frequency information is at least substantially eliminated because the AC signal is converted into a DC voltage.
  • the magnitude of the DC signal corresponds to the total acceleration value of approximately 1 g and is therefore independent of the type of rolling.
  • the roll sensor 78 When the projectile rolls over a ground, the roll sensor 78 outputs a positive roll signal. At the same time, the comparator 98 outputs a ground roll signal indicative of ground roll.
  • the ground roll signal is a negative signal, which dubles the roll signal of the roll sensor 78, so that no sufficiently positive signal can be present at the comparator 92. The release of the roll sensor 78 is thus blocked by the bottom roll sensor 80.
  • the output signal of the comparator 50 which indicates an acceleration in the direction of flight, is applied to the roll signal. This signal also plays over the roll signal. If, for example, a roll signal, that is to say a positive signal, is output, the longitudinal acceleration of the fuze 4 is not below the limit, this is a sign that the projectile is not in free flight. Accordingly, the signal of the comparator 50 is zero or negative and dubbing the positive roll signal so that it can not trigger the control signal for unlocking the interruption means.
  • the combination of roll sensor 78 and bottom roll sensor 80 may also undergo a self-test, such as Fig. 1 is described.
  • the switch 96 is closed and the sensor 84 is controlled by the processing means 34 or the controller 68, so that the roll sensor outputs the roll signal and at the same time and / or offset in time, the bottom roll sensor 80, the ground roll signal.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Air Bags (AREA)
  • Percussive Tools And Related Accessories (AREA)
  • Automotive Seat Belt Assembly (AREA)
  • Toys (AREA)

Claims (14)

  1. Dispositif de sûreté (2) pour un détonateur (4) d'un projectile, lequel possède un dispositif d'amorçage destiné à amorcer le détonateur (4), comprenant une unité de sûreté avec
    a) un moyen de traitement (34) destiné à appliquer une sûreté à une opération d'amorçage du dispositif d'amorçage, le moyen de traitement (34) étant préparé pour délivrer un signal de commande destiné à annuler la sûreté de l'unité de sûreté en fonction de la présence d'un signal de libération, et
    b) une unité de détection (38) qui est préparée pour délivrer le signal de libération en présence d'un état d'accélération défini qui est inférieur à l'accélération dûe à la pesanteur, l'unité de détection (38) étant préparée pour mesurer trois accélérations directionnelles dans trois directions spatiales mutuellement orthogonales et la délivrance du signal de libération ayant lieu à un instant auquel chacune des trois accélérations directionnelles est inférieure à l'accélération dûe à la pesanteur à chaque fois d'au moins une valeur d'accélération définie.
  2. Dispositif de sûreté (2) selon la revendication 1, la valeur d'accélération définie étant différente dans la direction du vol du projectile de la valeur d'accélération définie dans les deux autres directions.
  3. Dispositif de sûreté (2) selon l'une des revendications précédentes, l'état d'accélération défini étant, inférieur à l'accélération dûe à la pesanteur d'au moins une valeur d'accélération définie et l'unité de détection (38) comprenant au moins un comparateur (50, 52, 54) avec lequel la valeur d'accélération peut être réglée.
  4. Dispositif de sûreté (2) selon l'une des revendications précédentes, comprenant un élément de temps (56) destiné à prédéfinir un intervalle de temps, le moyen de traitement (34) ne délivrant le signal de commande que lorsque le signal de libération a été présent de manière ininterrompue pendant la totalité de l'intervalle de temps.
  5. Dispositif de sûreté (2) selon l'une des revendications précédentes, l'unité de détection (38) possédant un capteur de roulis (78) qui est préparé pour reconnaître un roulis du projectile et délivrer un signal de roulis en présence d'un mouvement de roulis.
  6. Dispositif de sûreté (2) selon la revendication 5, le moyen de traitement (34) étant préparé pour vérifier la présence à la fois du signal de libération et du signal de roulis et, en présence d'au moins l'un des deux signaux, délivrer le signal de commande destiné à annuler la sûreté de l'unité de sûreté.
  7. Dispositif de sûreté (2) selon la revendication 5 ou 6, le moyen de traitement (34) étant préparé pour, en présence du signal de roulis, vérifier si l'accélération du projectile dans la direction axiale est inférieure à une valeur prédéfinie et ne délivrer le signal de commande destiné à annuler la sûreté que lorsqu'elle est inférieure à la valeur.
  8. Dispositif de sûreté (2) selon l'une des revendications 5 à 7, le capteur de roulis (78) étant un capteur d'accélération.
  9. Dispositif de sûreté (2) selon l'une des revendications précédentes, le moyen de traitement (34) étant préparé pour différencier le roulis de vol libre du projectile d'un roulis du projectile sur un support.
  10. Dispositif de sûreté (2) selon l'une des revendications précédentes, l'unité de détection (38) possédant un capteur de roulis au sol (82) qui est préparé pour reconnaître un roulis au sol du projectile sur un support et délivrer un signal de roulis au sol en présence d'un roulis au sol.
  11. Dispositif de sûreté (2) selon la revendication 10, le moyen de traitement (34) étant préparé pour inhiber la délivrance du signal de commande destiné à annuler la sûreté en présence du signal de roulis au sol.
  12. Dispositif de sûreté (2) selon l'une des revendications précédentes, l'unité de détection (38)
    - possédant en plus un capteur de roulis (78) qui est préparé pour reconnaître un roulis du projectile et délivrer un signal de roulis en présence d'un mouvement de roulis, et
    - possédant en outre un capteur de roulis au sol (82) qui est préparé pour reconnaître un roulis au sol du projectile sur un support et délivrer un signal de roulis au sol en présence d'un roulis au sol,
    et le moyen de traitement (34) étant préparé pour les étapes suivantes :
    - vérifier la présence à la fois du signal de libération et du signal de roulis et, en présence d'au moins l'un des deux signaux, délivrer le signal de commande destiné à annuler la sûreté de l'unité de sûreté, cependant
    - en présence du signal de roulis, vérifier en plus si l'accélération du projectile dans la direction axiale est inférieure à une valeur prédéfinie et ne délivrer le signal de commande destiné à annuler la sûreté que lorsqu'elle est inférieure à la valeur, et
    - différencier un roulis de vol libre du projectile d'un roulis au sol du projectile sur un support et inhiber la délivrance du signal de commande destiné à annuler la sûreté en présence du signal de roulis au sol.
  13. Dispositif de sûreté (2) selon l'une des revendications précédentes, le dispositif d'amorçage possédant une chaîne d'amorçage comportant une charge d'amorçage destinée à amorcer le détonateur (4) et l'unité de sûreté possédant un moyen d'interruption (30) destiné à interrompre la chaîne d'amorçage.
  14. Procédé pour annuler la sûreté d'un détonateur (4) d'un projectile, lequel possède un dispositif d'amorçage avec une chaîne d'amorçage destiné à amorcer le détonateur (4) et un dispositif de sûreté (2) selon l'une des revendications 1 à 13, comprenant une unité de sûreté munie d'un moyen d'interruption (30) destiné à interrompre la chaîne d'amorçage, laquelle contient un moyen de traitement (34) destiné à appliquer une sûreté à une opération d'amorçage du dispositif d'amorçage,
    - un état d'accélération dans le détonateur étant détecté au moyen d'une unité de détection (38),
    - un signal de libération étant délivré par l'unité de détection (38) après que l'état d'accélération soit devenu inférieur à l'accélération dûe à la pesanteur d'au moins une valeur d'accélération définie, et
    - un signal de commande destiné à annuler la sûreté du moyen d'interruption de l'unité de sûreté étant délivré par le moyen de traitement (34) en fonction de la présence du signal de libération.
EP10784255.1A 2009-12-17 2010-11-05 Dispositif de sécurité pour une amorce de projectile Active EP2513594B1 (fr)

Applications Claiming Priority (2)

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DE102009058718A DE102009058718B4 (de) 2009-12-17 2009-12-17 Sicherungseinrichtung für einen Zünder eines Geschosses
PCT/EP2010/006743 WO2011072774A1 (fr) 2009-12-17 2010-11-05 Dispositif de sécurité pour une amorce de projectile

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EP (1) EP2513594B1 (fr)
KR (1) KR20120103643A (fr)
AU (1) AU2010333399B2 (fr)
CA (1) CA2779026C (fr)
DE (1) DE102009058718B4 (fr)
ES (1) ES2620179T3 (fr)
IL (1) IL219389A (fr)
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DE102012001219B4 (de) 2012-01-21 2014-07-31 Junghans Microtec Gmbh Geschosszünder, hierzu ausgebildetes Waffenrohr und Verfahren
US8939083B1 (en) * 2012-07-03 2015-01-27 L3 Fuzing and Ordnance Systems Fuze safing system
DE102013000050B3 (de) * 2013-01-07 2014-01-30 Rheinmetall Waffe Munition Gmbh Selbstzerlegungsmechanimus für einen Zünder
US9500458B2 (en) * 2014-04-10 2016-11-22 Scicast International, Inc. Electronically activated hand grenade
IL249976B (en) 2017-01-08 2022-02-01 Israel Aerospace Ind Ltd Safety device
DE102017109627B4 (de) 2017-05-04 2022-08-04 Rheinmetall Waffe Munition Gmbh Elektronische Sicherungsvorrichtung
GB2575989B (en) * 2018-07-30 2021-02-24 Thales Holdings Uk Plc A safety and arming unit for a munition
DE102018123935A1 (de) * 2018-09-27 2020-04-02 Rheinmetall Waffe Munition Gmbh Aufschlagzünder
US11073369B2 (en) * 2019-01-02 2021-07-27 Advanced Acoustic Concepts, LLC Electronic safe arm and fire device and method
SG11202112645YA (en) * 2019-06-01 2021-12-30 St Engineering Advanced Mat Engineering Pte Ltd Safe-and-arm fuzing method for a projectile
CN111457797A (zh) * 2020-02-26 2020-07-28 北京理工大学重庆创新中心 一种基于事件驱动架构的微引信安全控制系统及其方法

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ES2620179T3 (es) 2017-06-27
DE102009058718A1 (de) 2011-06-22
US8820241B2 (en) 2014-09-02
EP2513594A1 (fr) 2012-10-24
CA2779026A1 (fr) 2011-06-23
US20120240805A1 (en) 2012-09-27
AU2010333399A1 (en) 2012-06-07
KR20120103643A (ko) 2012-09-19
AU2010333399B2 (en) 2014-04-03
DE102009058718B4 (de) 2011-12-08
SG180714A1 (en) 2012-07-30
IL219389A (en) 2016-06-30
IL219389A0 (en) 2012-06-28
WO2011072774A1 (fr) 2011-06-23
ZA201205215B (en) 2013-03-27
CA2779026C (fr) 2015-03-17

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