KR100763558B1 - Ebw triggering device for satellite launch vehicle - Google Patents

Abstract

An EBW(Exploding BridgeWire) triggering device for a satellite launch vehicle is provided to prevent excessive design of a system and reduce the manufacturing cost by charging a triggering capacitor by using constant voltage. An EBW(Exploding BridgeWire) triggering device for a satellite launch vehicle comprises a flyback conversion section(110) including a flyback transformer and a semiconductor switch to convert input DC into AC. A boosting section(120) comprises a plurality of diodes and capacitors to boost the AC converted by the flyback conversion section to DC output voltage. A triggering capacitor section(130) charges the output voltage boosted by the boosting section. A switch section(150) comprises a trigger circuit unit(152) to supply or block the output voltage charged by the triggering capacitor section.

Description

Explosive bridgewire detonator for satellite launch vehicles {EBW triggering device for satellite launch vehicle}

1 is a block diagram of an explosive bridge wire detonator for a satellite launch vehicle according to an embodiment of the present invention,

FIG. 2 is a circuit diagram of FIG. 1.

<Explanation of symbols for main parts of the drawings>

100 ... Explosive Bridgewire Detonators for Satellite Launchers

110 Flyback converter 120 Booster

130 ... Detonation capacitor section 140 ... Charging monitor section

150 Switch section 151 Switch

152 ... trigger circuit section 160 ... feedback circuit section

161 ... Comparators 162 ... Photocouplers

163 ... PWM controller

The present invention relates to an explosive bridgewire (EBW) detonator for satellite launchers, and more particularly to an explosive bridgewire detonator for detonating EBW explosives contained in the satellite launch vehicle safely during high-air flight.

In general, operations such as single separation, pairing separation, satellite separation, and suspension of flight, which are major events occurring in the satellite launch vehicle, are caused by the explosion of a hot bridgewire (HWB) or explosive bridgewire (EBW) powder. It may be initiated by.

Among them, the EBW gunpowder is a device insensitive to external noise since it is ignited by a high current of about 600 A or more, and the EBW gunpowder is an explosive gun suitable for an inorganic system such as an expensive satellite projectile or a ballistic / guided missile.

The basic configuration of the electric EBW detonator reported up to now at home and abroad is using a push-pull type voltage converter and a multi-stage voltage booster to receive 24V to 34V battery voltage and convert it to high voltage of 2kV or higher Charge and discharge the high-pressure energy charged in the detonation capacitor to the EBW by activating the spark-gap switch of the vacuum method by an external command.

Here, in the push-pull voltage converter, an open loop control method in which an output voltage is controlled only by an input voltage without using output voltage detection is generally used, and the input battery voltage is reduced. If the output voltage is reduced in proportion to this, it is designed to obtain an output of 2kV or more near about 24V which is normally expected minimum input voltage.

However, as in the satellite launch vehicle, when a pyro detonator, a valve driving device for attitude control, and the like, which are discontinuously sudden load fluctuations are connected to the same battery voltage, while the load elements are operated, As a sudden load change occurs, the battery voltage is also likely to fluctuate below the minimum operating voltage, and sufficient energy (E = 0.5CV ² ) may be expressed according to the fluctuation of the battery voltage to explode the EBW powder. There is no problem.

In addition, in the conventional detonation method, a high voltage of 3 kV or more is output at the time of initial driving at which the battery voltage becomes maximum (for example, about 34 V), and by increasing the withstand voltage ratio of various circuit components and printed circuit boards in consideration of this, In a vacuum environment, the projectile can be safely protected from the corona discharge generated during flight, in which case the size and weight of the detonator increases and manufacturing cost increases.

On the other hand, the spark gap switch of the vacuum method to control the high-voltage energy charged in the detonation capacitor in the conventional detonation method may be limited in life due to characteristics such as corrosion of the electrode and exhaustion of the built-in gas, In order to operate the spark gap switch, a high-voltage pulse of 3 kV or more must be applied to the trigger portion of the switch, which causes a disadvantage in that the driving circuit becomes complicated.

The present invention has been made to solve the above-mentioned problems, in order to safely detonate the EBW explosive included in the satellite launch vehicle during high-air flight, regardless of the wide input change caused by sudden power fluctuations of loads connected to the same battery power source The aim is to provide an explosive bridgewire detonator for satellite launchers that can be used to charge detonation capacitors with voltage, preventing overdesign of the system and reducing manufacturing costs.

Other objects and advantages of the invention will be described below and will be appreciated by the embodiments of the invention. Furthermore, the objects and advantages of the present invention can be realized by means and combinations indicated in the claims.

An explosive bridge wire detonator for a satellite launch vehicle according to the present invention for achieving the above object comprises a flyback transformer and a semiconductor switch, a flyback converter for converting an input battery DC voltage into an AC voltage; A booster including a plurality of diodes and capacitors, and boosting an AC voltage converted by the flyback converter to an output voltage of DC; An initiator capacitor unit for charging the boosted output voltage of the boost unit; And a trigger circuit unit for converting an input external command signal into a trigger signal, and using the trigger signal, a switch unit for supplying and interrupting the output voltage charged in the initiator capacitor unit.

In addition, the present invention includes a charge monitor unit for sensing the output voltage charged in the detonation capacitor unit; And a feedback circuit unit configured to compare the output voltage sensed by the charging monitor unit with a pre-stored reference voltage and generate a pulse width control signal that is differently adjusted according to the compared value and input the same to the semiconductor switch of the flyback converter. Can be.

The feedback circuit unit may include: a comparator configured to generate a difference signal about a compared value by comparing an output voltage sensed by the charge monitor unit with a pre-stored reference voltage; And a PWM controller generating a pulse width control signal proportional to the magnitude of the difference signal generated by the comparator and inputting the pulse width control signal to the semiconductor switch of the flyback converter.

The PWM controller may sense an input side current of a flyback transformer provided in the flyback converter, and apply a blocking signal to the semiconductor switch when the detected current value is greater than or equal to a preset reference value.

Here, the charge monitor unit may be a voltage distribution circuit having two resistors connected in parallel with the detonation capacitor unit.

In addition, the switch provided in the switch unit may be a thyristor switch.

Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings. Prior to this, terms or words used in the specification and claims should not be construed as having a conventional or dictionary meaning, and the inventors should properly explain the concept of terms in order to best explain their own invention. It should be interpreted as meanings and concepts corresponding to the technical idea of the present invention based on the principle of definition.

Therefore, the embodiments described in the specification and the drawings shown in the drawings are only the most preferred embodiment of the present invention and do not represent all of the technical idea of the present invention, various modifications that can be replaced at the time of the present application It should be understood that there may be equivalents and variations.

The present invention relates to an explosive bridgewire detonator for safely detonating EBW (Explosive Bridgewire) explosives contained in a satellite launch vehicle during high-air flight.

1 is a configuration diagram of an explosive bridge wire detonator for a satellite launch vehicle according to an embodiment of the present invention, Figure 2 is a circuit configuration diagram of FIG.

1 to 2, the explosive bridge wire detonator 100 for a satellite projectile according to an embodiment of the present invention is a flyback converter 110, boosting unit 120, detonation capacitor unit 130 And a switch unit 150.

The flyback converter 110 includes a flyback transformer and a semiconductor switch as shown in FIG. 2 and converts the input battery DC voltage into an AC voltage.

The flyback converter 110 may increase the input DC voltage according to the winding ratio (N value of 1: N) of the flyback transformer.

For example, the battery DC voltage of 28V may be converted into an AC voltage in the range of about 500Vpeak to 600Vpeak (peak voltage) by the flyback transformer provided in the flyback converter 110.

Here, the battery DC voltage is ideally always supplied at a constant value, but may substantially fluctuate within a predetermined range according to the operation of the load connected to the battery, so the range of 500V to 600V is also within the range in consideration of the fluctuating range. It corresponds to an example.

Meanwhile, the semiconductor switch of the flyback converter 110 may be formed of a semiconductor device such as a field-effect transistor (FET) or a bipolar junction transistor (BJT) as shown in FIG. 2. Can be.

That is, the flyback converter 110 as described above may convert the input DC battery voltage into an amplified AC voltage by the interaction between the switching operation of the semiconductor switch and the voltage increasing operation of the flyback transformer.

In addition, the flyback switching unit 110 of the flyback switching method including the flyback transformer can reduce the number of parts and the manufacturing cost compared to the conventional push-pull switching type converter, which pursues small size and light weight. There is an advantage suitable for space launch applications.

The boosting unit 120 includes a plurality of diodes and capacitors, and the AC voltage converted by the flyback converter 110 boosts and outputs a DC output voltage, that is, a rectifying action of the diode using the capacitor. By converting the AC to a direct current using the DC output voltage, such a boosted DC output voltage can be used as an energy source for detonating the EBW.

For example, the boosting unit 120 may convert an AC voltage in the range of 500 V to 600 V peak output from the flyback converter 110 to a DC voltage of 2.0 kV to 2.4 kV, which is an output voltage sufficient to detonate the EBW powder. In this case, the booster 120 may be a quadruple booster composed of four capacitors and four diodes as shown in FIG. 2.

The detonation capacitor unit 130 is connected to the booster unit 120 in parallel to charge the boosted output voltage of the booster unit 120, and is driven for the EBW detonation by driving the switch unit 150. It can be used as an initiator voltage.

The switch unit 150 is a portion for performing the on / off operation of the switch in accordance with an external command signal to supply and cut off the output voltage charged in the initiator capacitor 130.

The switch unit 150 may include a trigger circuit unit 152 for converting an external command signal input from the outside into a trigger signal, and a switch 151 that is turned on / off according to the trigger signal.

That is, the switch 151 is turned on when a trigger signal of a predetermined magnitude or more generated by the trigger circuit unit 152 is input by an external command signal, and at the same time, an output voltage charged in the detonation capacitor unit 130. Can be supplied after being discharged.

Here, the trigger circuit unit 152 may receive an external command signal of 28V and convert it into a trigger signal of about 3V to control the switch 151 on / off, but the voltage value is not limited thereto.

On the other hand, the switch 151 provided in the switch unit 150 is preferably a thyristor switch consisting of three terminals as shown in FIG.

That is, referring to FIG. 2 in detail, the detonation capacitor unit 130 is interconnected with both terminals (+) of the thyristor switch 151, and also the charged output voltage of the detonation capacitor unit 130. Is input to both terminals (+) of the thyristor switch 151 and then output to the negative terminal (−). At this time, the output voltage interruption of the switch 151 may be determined by input to the trigger signal of the trigger circuit unit 152 as described above.

The thyristor switch as the switch 151 provided in the switch unit 150, unlike the spark gap switch of a limited lifetime used in the conventional detonator can ensure the semi-permanent life and the reliability of the operation accordingly Therefore, there is an advantage that the driving circuit can be simplified.

On the other hand, the explosive bridgewire detonator 100 for the satellite projectile of the present invention, in order to constantly adjust the output voltage to a predetermined voltage, that is, of the battery voltage that can be generated according to the operation of the load connected to the battery The charging monitor unit 140 and the feedback circuit unit 160 may be further included so that a constant output voltage is output even with the variation.

The charge monitor unit 140 is a part for detecting the output voltage value charged in the detonation capacitor unit 130, and comprises a voltage distribution circuit having two resistors connected in parallel with the detonation capacitor unit 130. Can be.

That is, the charge monitor unit 140 may detect the charged output voltage of the detonation capacitor unit 130 using the voltage of the voltage distribution point, which is the contact portion where the two resistors contact each other. Here, the output voltage sensed by the charge monitor unit 140 is oscillated together when the magnitude of the battery voltage input to the flyback converter 110 is fluctuated as described above.

Meanwhile, the feedback circuit unit 160 compares the output voltage sensed by the charging monitor unit 140 with a pre-stored reference voltage, and then generates a pulse width control signal that is differently adjusted according to the compared value to generate the flyback conversion. A part input to the semiconductor switch terminal of the unit 110 may include a comparator 161 and a PWM controller 163.

That is, the comparator 161 may generate a difference signal regarding the compared value by comparing the output voltage sensed by the charging monitor unit 140 with a pre-stored reference voltage.

In addition, the PWM controller 163 generates a pulse width modulation (PWM) signal having a pulse width proportional to the magnitude of the difference signal generated by the comparator 161 to generate the flyback converter 110. As the input of the semiconductor switch to the gate of the output voltage can be adjusted to a predetermined output voltage range.

In addition, the flyback converter 110 senses a current flowing through an input side of the flyback transformer, that is, a primary side circuit, and cuts off the gate of the semiconductor switch when an overcurrent whose detected current value is greater than a preset reference value is detected. A signal can be applied to protect the circuit at the same time.

On the other hand, the feedback circuit unit 160 may further include a photo coupler 162.

The grounds of the primary and secondary power sources, which are the input and output terminals of the flyback transformer provided in the flyback transformer 110, are independently driven without interference. The photocoupler 162 may convert the secondary side power to be suitable for the primary side power during the feedback operation.

As shown in FIG. 2, the comparator 161 may be driven using the voltage of the secondary circuit of the flyback transformer, and the secondary circuit voltage output from the comparator 161 may be input to the photocoupler 162 again. The photocoupler 162 may convert the voltage of the secondary circuit to suit the voltage of the primary circuit without an electrical connection through a photo signal. That is, the ground of the secondary power can be converted to match the ground of the primary power.

Using the converted voltage of the primary circuit, the PWM controller 163 may generate a pulse width control signal corresponding to the difference signal transmitted from the comparator 161 and input the pulse width control signal to the semiconductor switch of the primary circuit.

On the other hand, with respect to the operation of the flyback converter 110 as described above, for example, when the output voltage is less than the predetermined reference voltage, the difference signal for this is the semiconductor switch of the flyback converter 110 The output voltage of the booster unit 120 may be adjusted to be increased to a reference voltage by inputting the input signal to the input signal and adding the difference signal to the battery voltage by the flyback transformer.

 On the contrary, when the output voltage exceeds the reference voltage, the difference signal between the output voltage and the reference voltage is input to the semiconductor switch of the flyback converter 110, and the input difference signal is input by the flyback transformer. By subtracting the battery voltage to the output voltage can be adjusted so that the output voltage of the boosting unit 120 is lowered to the reference voltage.

That is, according to the charge monitor unit 140 and the feedback circuit unit 160 as described above, by comparing the sensed output voltage with a predetermined output voltage, ultimately, the semiconductor provided in the flyback converter 110 By adjusting the switch conduction time of the switch 151, the output voltage can be adjusted to be constant regardless of the fluctuation of the input battery voltage.

As described above, the present invention provides feedback control of the battery input voltage using the EBW detonation output voltage which is constantly monitored, so that the input voltage fluctuates or fluctuates due to the fluctuation of the load elements connected to the same battery voltage. Its output voltage ensures product reliability and contributes to the compactness, weight savings and cost savings that are especially required in satellite launch applications.

As described above, the present invention has been described by means of limited embodiments and drawings, but the present invention is not limited thereto and is described below by the person skilled in the art and the following description of the present invention. Various modifications and variations are possible without departing from the scope of the appended claims.

The explosive bridgewire detonator for a satellite launch vehicle according to the present invention provides the following effects.

First, as the feedback control of the battery input voltage using the EBW detonation output voltage that is constantly monitored, it is possible to maintain a certain range of output voltage even if the input voltage fluctuates or fluctuates due to the fluctuations of the load devices connected to the same battery voltage. have.

Second, as the flyback switching method is applied, the number of parts can be reduced compared to the conventional push-pull switching method and contribute to the compactness and light weight of the space launch vehicle.

Third, as the thyristor switch is used, unlike the conventional spark gap switch of the limited lifetime, it is possible to guarantee the semi-permanent life and the reliability of the operation thereof, and to simplify the driving circuit.

Claims (6)

A flyback converter having a flyback transformer and a semiconductor switch and converting an input battery DC voltage into an AC voltage; A booster including a plurality of diodes and capacitors, and boosting an AC voltage converted by the flyback converter to an output voltage of DC; An initiator capacitor unit for charging the boosted output voltage of the boost unit; And And a trigger circuit unit for converting an input external command signal into a trigger signal, and using the trigger signal, the explosive bridge wire detonator for a satellite projectile including a switch unit for supplying and blocking the output voltage charged in the detonation capacitor unit. . The method of claim 1, A charge monitor unit configured to sense the output voltage charged in the initiator capacitor unit; And And a feedback circuit unit configured to compare the output voltage sensed by the charging monitor unit with a pre-stored reference voltage and generate a pulse width control signal that is differently adjusted according to the compared value and input the same to the semiconductor switch of the flyback converter. An explosive bridgewire detonator for a satellite launch vehicle. The method of claim 2, wherein the feedback circuit unit, A comparator for comparing the output voltage sensed by the charging monitor unit with a pre-stored reference voltage to generate a difference signal regarding the compared value; And And a PWM controller for generating a pulse width control signal proportional to the magnitude of the difference signal generated by the comparator and inputting the pulse width control signal to the semiconductor switch of the flyback converter. The method of claim 3, wherein the PWM controller, And an input signal of a flyback transformer provided in the flyback converter to detect an input side current and apply a blocking signal to the semiconductor switch when the detected current value is greater than or equal to a preset reference value. The method of claim 2, wherein the charge monitor unit, An explosive bridgewire detonator for a satellite launch vehicle, characterized in that the voltage distribution circuit having two resistors connected in parallel with the detonation capacitor unit. The method of claim 1, The switch provided in the switch unit is an explosive bridge wire detonator for a satellite projectile, characterized in that the thyristor switch.

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