KR100927223B1 - Contactless explosive bridgewire detonator for satellite cover removal - Google Patents

Abstract

According to the present invention, the flyback transformer comprises a primary side circuit portion and a secondary side circuit portion separated from the primary side circuit portion, the primary side circuit portion is provided with a semiconductor switch, the flyback converts the input battery DC voltage into an AC voltage to transfer A conversion unit; A trigger circuit unit for converting an input external command signal into a trigger signal; A pulse converter configured to include a primary pulse part of the pulse transformer and a secondary pulse part separated from the primary pulse part to transmit a trigger signal of the trigger circuit part to the outside; A booster comprising a plurality of diodes and capacitors and boosting an AC voltage received from a flyback converter to a DC output voltage; An explosion capacitor unit for charging the boosted output voltage of the boost unit; And a switch unit for supplying and cutting off the output voltage charged in the initiator capacitor unit using the trigger signal received from the pulse conversion unit, wherein the primary circuit unit, the trigger circuit unit and the primary pulse unit are provided in the projectile, the secondary circuit unit, The booster, the detonation capacitor part, the secondary side pulse part, and the switch part are provided with a non-contact explosive bridgewire detonator for satellite cover separation, which is installed in the satellite cover part coupled to the projectile and separated from the projectile when detonating.

Satellite cover, separation, explosive bridgewire, detonation, EBW

Description

Contactless explosive bridgewire detonator for satellite cover separation {Contactless EBW firing device for fairing separation of satellite launch vehicle}

The present invention relates to a non-contact explosive bridge wire detonator for satellite cover separation, more specifically, a satellite cover for detonating explosive bridge wire explosives, which is an igniter used for the separation of a satellite cover (pairing) of a satellite projectile. A noncontact explosive bridgewire detonator for separation.

The present invention relates to an apparatus for detonating an exploding bridgewire (EBW) in a satellite cover separating apparatus of a satellite launch vehicle.

Conventional explosive bridgewire detonator used for the same purpose is composed of a single structure, the power of about 28V is applied and loaded state, and the high voltage energy of about 2kV or more charged inside is output by external command It has a way to detonate the bridgewire.

1 is an invention of patent registration No. 0763558 registered by the present applicant, wherein the generation of a high voltage in the detonator 8 causes the input 28V DC battery voltage to be converted into an AC voltage through a semiconductor switch in the flyback converter 1. After the conversion, the flyback transformer of the flyback converter 1 is boosted to about 600V, and then the booster 2 finally reaches a high voltage of about 2kV or more.

In addition, the power source used in the satellite launch vehicle is a battery having a nominal voltage of 28 V, and monotonically decreases to about 33 to 24 V depending on the use of the load. Feedback circuits 3 and 5 are used.

The high voltage energy for detonating the explosive bridgewire 10 is formed by storing the generated 2 kV or more voltage in the detonation capacitor 4 of 0.2 to 1 uF, and the interruption of energy for delivering to the explosive bridgewire 10 is Spark-gap switches have been commonly used.

However, since most of the military and space spark gap switches rely on imports, and the producing countries have designated export licensed items to restrict exports, the invention to replace them with thyristors (6) has been filed.

Since the conventional spark gap switch is controlled by a high voltage pulse of several kV, the external command signal of several V is converted to a high voltage of several kV using a pulse transformer, and then the spark gap switch is reached, whereas the thyristor 6 Like the conventional power semiconductor switch can be controlled by a signal of several tens of V, there is an advantage that can simplify the trigger circuit (7).

In the satellite cover separation device of the satellite launch vehicle, the detonator 8 is generally located together with the battery in the bay (fixed part) of the satellite launch vehicle, and the explosive bridge wire 10 is gunpowdered through a detonation cord. It is located in the satellite cover (separation part) because it must be connected with.

Here, the detonator 8 and the explosive bridgewire 10 are connected to each other by an electric wire, and in order to prevent the satellite cover from being constrained by the electric wire when the satellite cover is separated, the separating connector 9 is provided with the detonator 8. And is installed between the explosive bridge wire 10 to be removed by the separation acceleration.

As a problem of this method, the satellite cover is constrained by the detachment failure of the separation connector 9 when the satellite cover is removed, which may cause the satellite cover and the projectile to collide.

In addition, since the high voltage energy of the detonator 8 is maintained until the capacity of the battery which is the input power is exhausted even after the completion of the mission of the projectile, there is a possibility of explosion due to external factors, and of course, if an actual explosion occurs. There is a problem that can leave the universe debris by this.

The present invention has been made to solve the above-described problems, by physically separating the primary circuit portion and the secondary circuit portion of the flyback transformer in the detonator, the primary circuit portion and the secondary circuit portion to the projectile and the satellite cover portion, respectively It provides a contactless explosive bridgewire detonator for satellite cover separation that ensures system stability by dissipating the energy stored in the capacitors in the detonator in a short time, as well as ensuring complete freedom of the satellite cover when the satellite cover is removed. There is a purpose.

In order to achieve the above object, a non-contact explosive bridgewire detonator for satellite cover separation of the present invention comprises a primary circuit portion and a secondary circuit portion separated from the primary circuit portion of a flyback transformer, A switch provided with a flyback converting unit converting the input battery DC voltage into an AC voltage and transmitting the AC voltage; A trigger circuit unit for converting an input external command signal into a trigger signal; A pulse converter configured to include a primary pulse part of a pulse transformer and a secondary pulse part separated from the primary pulse part to transmit a trigger signal of the trigger circuit part to the outside; A booster comprising a plurality of diodes and capacitors and boosting an AC voltage received from the flyback converter to a DC output voltage; An initiator capacitor unit for charging the boosted output voltage of the boost unit; And a switch unit configured to supply and cut an output voltage charged in the initiator capacitor unit by using the trigger signal received from the pulse converter, wherein the primary circuit unit, the trigger circuit unit, and the primary pulse unit are provided in the projectile. The secondary circuit portion, the boosting portion, the detonation capacitor portion, the secondary pulse portion and the switch portion is coupled to the projectile, characterized in that installed in the satellite cover portion separated from the projectile when detonating.

According to the present invention, the projectile is provided in the projectile to generate a pulse width control signal and to control the turn-on time of the semiconductor switch, but with a predetermined turn-on time to enable detonation at a minimum battery DC voltage. It may further include a PWM controller for controlling.

According to the present invention, the non-contact explosive bridgewire detonator for satellite cover separation provides the following effects.

First, since a separate connector for removing the satellite cover is not necessary, the restraint phenomenon of the satellite cover due to the failure of the detachment operation of the connector is completely eliminated, thereby ensuring complete freedom of the satellite cover.

Second, the primary side and secondary side of the detonator are separately provided on the projectile and satellite cover side, and when the primary side and secondary side are completely separated during separation, the remaining energy source is removed within a short time after separation, so that the system is stable. Allows you to complete your flight mission.

Third, the stability of the system due to the reduction of the number of parts due to the removal of the feedback function and the stability of the system can be improved by the effect of the open-loop control method.

Fourth, since the secondary module of the transformer is removed at the same time as the separation of the satellite cover portion, it is possible to reduce the weight ratio of the projectile compared to the conventional method.

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 present specification and claims should not be construed as being limited to the common or dictionary meanings, and the inventors should properly explain the concept of terms in order to best explain their own invention. Based on the principle that it can be defined, it should be interpreted as meaning and concept corresponding to the technical idea of the present invention.

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.

2 is a block diagram of a non-contact explosive bridge wire detonator for removing the satellite cover according to an embodiment of the present invention, Figure 3 is a circuit diagram of FIG.

The present invention is an electric detonator 100 required to safely detonate an explosive bridge wire (EBW; 10) explosive, which is an igniter used to separate the satellite cover portion 30 coupled to the satellite projectile 20 as shown in FIG. It is about the components of and their connections.

The present invention physically separates the primary side circuit portion 111 and the secondary side circuit portion 112 of the flyback transformer inherent in the detonator 100 in order to solve some of the problems expected in the conventional method, the primary side circuit portion ( 111 is mounted on the upper end of the projectile 20, and the secondary circuit portion 112 is mounted on the satellite cover portion 30, respectively, and the gap between the primary circuit portion 111 and the secondary circuit portion 112 for electric energy transfer. It has a configuration that generates induction electromotive force on the secondary side by magnetizing (Air gap).

Hereinafter, the present invention will be described in more detail with reference to FIGS. 2 to 3.

According to the present invention, the flyback converter 110, the trigger circuit 120, the pulse converter 130, the boosting unit 140, the explosion capacitor unit 150 and the switch unit 160.

The flyback converter 110 may include a flyback transformer and a semiconductor switch as shown in FIG. 3 to convert the input battery DC voltage into an AC voltage.

More specifically, the flyback converter 110 includes a primary side circuit portion 111 and a secondary side circuit portion 112 physically separated from the primary side circuit portion 111 of a flyback transformer including a semiconductor switch. The battery DC voltage input to the circuit unit 111 is converted into an AC voltage through the semiconductor switch and transferred to the secondary circuit unit 112.

Although the primary side circuit portion 111 and the secondary side circuit portion 112 are separated from each other, the magnetized air gap between the primary side circuit portion 111 and the secondary side circuit portion 112 is magnetized according to the characteristics of the transformer. Induced electromotive force is generated in the vehicle side circuit part 112 to transmit electric energy.

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.

Meanwhile, the semiconductor switch located in the primary side circuit unit 111 may be formed of a semiconductor device such as a field-effect transistor (FET) or a bipolar junction transistor (BJT) as shown in FIG. 3. have.

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.

Meanwhile, the trigger circuit unit 120 converts an input external command signal into a trigger signal.

The pulse converting unit 130 has a configuration of a pulse transformer, and is composed of a primary side pulse unit 131 and a secondary side pulse unit 132 physically separated from the primary side pulse unit 131, and the trigger circuit unit 120. The trigger signal transmitted from the primary pulse unit 131 is transmitted to the switch unit 160 through the secondary pulse unit 132.

Here too, of course, the induced gap is generated in the secondary side pulse unit 132 by magnetizing a separate air gap between the primary side pulse unit 131 and the secondary side pulse unit 132 to transfer electrical energy.

As shown in FIG. 2 or FIG. 3, the primary side circuit unit 111 of the flyback converter 110, the trigger circuit unit 120, and the primary side pulse unit 131 of the pulse converter 130 as described above are projectiles. 20 is installed. In addition, the secondary circuit unit 112 of the flyback converter 110 and the secondary pulse unit 132 of the pulse converter 130 are installed in the satellite cover unit 30.

That is, since the primary side and the secondary side of the transformer are configured to be separated from each other on the basis of the separation surface 40 of FIG. 3, the separation connector as shown in FIG. 9) is not necessary at all, and thus there is no advantage in that the satellite cover portion 30 is not restrained due to the detachment failure of the separation connector 9, thereby ensuring complete freedom of the satellite cover portion 30. .

Meanwhile, in order to maximize energy transfer efficiency of the flyback transformer or the pulse transformer, the primary side and the secondary side of each transformer (that is, the primary side circuit unit 111 of the flyback conversion unit 110) with respect to the separation plane 40. Preferably, the secondary circuit unit 112 and the secondary circuit unit 112 and the primary pulse unit 131 and the secondary pulse unit 132 of the pulse conversion unit 130 are disposed close to each other so as to contact each other as much as possible.

The booster unit 140, the detonation capacitor unit 150, and the switch unit 160, which will be described later, are provided in the satellite cover unit 30, and are located at the rear end of the secondary circuit unit 112 of the flyback converter 110. Is installed on.

The booster 140 includes a plurality of diodes and capacitors as shown in FIG. 3, and boosts the AC voltage received from the secondary circuit unit 112 to a DC output voltage.

That is, it is possible to convert the AC into direct current by using the rectifier action of the diode using the capacitor, and the boosted direct current output voltage becomes an energy source for the detonation of the EBW.

For example, the booster 140 boosts an AC voltage in the range of about 500 V to 600 V peak output from the secondary circuit unit 112 to a DC voltage of 2.0 kV to 2.4 kV, which is an output voltage sufficient to detonate the EBW 10. It is possible. In this case, as shown in FIG. 3, it may have a form of a quadruple booster composed of four capacitors and four diodes.

The detonation capacitor unit 150 is a portion for charging the boosted output voltage of the boosting unit 140, and the charged output voltage is used as a voltage for detonation of the EBW 10.

The switch unit 160 is installed at the rear end of the secondary pulse unit 132 of the pulse converter 130 and is operated on / off in accordance with a trigger signal received from the secondary pulse unit 132, whereby an initiator capacitor unit ( The output voltage charged in 150 is supplied and cut off to the EBW 10 side.

For example, when a trigger signal of a predetermined magnitude or more generated from the trigger circuit unit 120 is input to the switch unit 160 by an external command signal, the switch is turned on and at the same time, the charge capacitor unit 150 is charged. The output voltage can be discharged and supplied.

The switch unit 160 may be a thyristor switch that operates semi-permanently and stably.

The trigger circuit unit 120 may control an on / off switch unit 160 by receiving an external command signal of 28V and converting the trigger signal into a trigger signal of about 3V.

The present invention as described above is as follows.

Primary side of the flyback converter 110, the battery DC power input 110, the trigger circuit unit 120 for converting the external command signal to the trigger signal, the primary side of the pulse converter 130, the trigger signal is input The pulse part 131 is all located at the upper end of the projectile 20.

In addition, in the satellite cover portion 30 coupled to the upper end of the projectile 20, the secondary circuit portion 112 and the secondary pulse portion 132 is disposed, but the primary circuit portion 111 on the projectile 20 side and Arranged so as to be as close as possible to the secondary side circuit portion 112, and the boosting unit 140, the detonation capacitor unit 150, and the switch unit 160 is arranged at the rear end of the secondary side circuit unit 112.

Here, when the switch unit 160 is turned on in response to the trigger signal and the output voltage charged in the detonation capacitor unit 150 is supplied to the EBW 10 to become the detonator, the projectile 20 and the satellite cover unit 30 are released. ) Is completely separated to ensure complete freedom of the satellite cover (30).

In addition, as the primary side and the secondary side are completely separated during the separation, the remaining energy source stored in the detonation capacitor unit 150 is exhausted within a short time, so that the system can terminate the flight mission in a stable state.

Here, in the case of the conventional FIG. 1 in which the primary side and the secondary side are not separated, since high voltage energy is maintained until the capacity of the battery is exhausted, there is a possibility of explosion due to external factors.

On the other hand, by eliminating the conventional feedback circuit as shown in Figure 1, the number of parts is reduced, the reliability is improved and the stability of the system according to the open-loop control method is guaranteed.

Meanwhile, the present invention may include a PWM controller 170 as shown in FIGS. 1 and 2.

The PWM controller 170 is a part provided in the projectile 20. The PWM controller 170 generates a pulse width modulation signal (PWM), inputs it to the gate of the semiconductor switch, and turns on the turn-on time of the semiconductor switch. This is the part to control.

Here, the PWM controller 170 may control the semiconductor switch with a turn-on time of a predetermined value to enable the detonation at a minimum battery DC voltage.

The EBW 10 can be detonated within a certain range above the minimum voltage.

Therefore, in the present invention, the semiconductor switch is controlled to a specific turn-on time capable of detonation at the minimum battery DC voltage. This is considered that the output voltage of the high voltage charged in the capacitor capacitor unit 150 is adjusted according to the input battery DC voltage, and the battery DC voltage is monotonically reduced according to the use of the load.

As described above, although the present invention has been described by way of limited embodiments and drawings, the present invention is not limited thereto and is intended by those skilled in the art to which the present invention pertains. Of course, various modifications and variations are possible within the scope of equivalents of the claims to be described.

1 is a circuit diagram of a conventional explosive bridge wire detonator for a satellite launch vehicle;

2 is a block diagram of a non-contact explosive bridge wire detonator for satellite cover separation according to an embodiment of the present invention,

3 is a circuit diagram of FIG. 2.

<Description of the symbols for the main parts of the drawings>

10 ... EBW 20 ... projectile

30.Satellite cover

100 ... Non-contact explosive bridgewire detonator for satellite cover removal

110 Flyback converter 111 Primary circuit

112 ... Secondary circuit section 120 ... Trigger circuit section

130 ... Pulse converter 131 ... Primary pulse part

132 ... 2nd pulse side 140 ... Booster

150 ... Detonation capacitor section 160 ... Switch section

170 ... PWM controller

Claims (2)

It consists of a primary side circuit portion 111 and a secondary side circuit portion 112 separated from the primary side circuit portion 111 of the flyback transformer, the semiconductor circuit is provided in the primary side circuit portion 111, the input battery DC voltage A flyback converter 110 converting and transferring the AC voltage; A trigger circuit unit 120 for converting an input external command signal into a trigger signal; Pulse transformer 130 for transmitting the trigger signal of the trigger circuit 120 to the outside consisting of a primary pulse unit 131 of the pulse transformer and a secondary pulse unit 132 separated from the primary pulse unit 131. ); A booster 140 formed of a plurality of diodes and capacitors and boosting an AC voltage received from the flyback converter 110 to an output voltage of DC; An explosion capacitor unit 150 for charging the boosted output voltage of the boosting unit 140; And And a switch unit 160 for supplying and blocking an output voltage charged in the initiator capacitor unit 150 by using the trigger signal received from the pulse converting unit 130, The primary side circuit unit 111, the trigger circuit unit 120, and the primary side pulse unit 131 are provided in the projectile 20, and the secondary side circuit unit 112, the boosting unit 140, and the initiator capacitor unit 150 are provided. The secondary pulse part 132 and the switch part 160 are separated from the satellite cover which is coupled to the projectile 20 but is installed in the satellite cover part 30 which is separated from the projectile 20 when detonated. Non-contact explosive bridgewire detonator. The method of claim 1, The PWM controller is provided in the projectile 20 to generate a pulse width control signal and to control the turn-on time of the semiconductor switch, but to control the turn-on time of a predetermined value to enable detonation at the minimum battery DC voltage. Non-contact explosive bridgewire detonator for satellite cover separation, characterized in that it further comprises (170).

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