JP5121064B2 - Detonation system - Google Patents

Description

  The present invention relates to a detonation system for detonating explosives mounted on a flying object such as a missile launched from a launching device.

Conventionally, as this type of detonation system, there is one disclosed in Patent Document 1 under the name of pyrotechnics ignition circuit for spacecraft-equipped equipment.
A pyrotechnics ignition circuit for a spacecraft-mounted device described in Patent Document 1 obtains ignition power to be applied to a pyrotechnic from a battery assembly formed by connecting a plurality of batteries in series. The ignition power supplied to the product is selectively extracted from among a plurality of batteries constituting the battery assembly.
JP 2001-260999 A

  However, as described in the cited document 1, as shown in FIGS. 1 and 2 attached thereto, since a plurality of batteries are mounted, weight increase cannot be avoided.

  Moreover, in order to operate the ignition relay, an ignition command signal is input. However, a connection for outputting the ignition command signal to the ignition relay must be made, and therefore, the degree of freedom of the outfitting is reduced. It is causing a decline.

  Furthermore, the pyrotechnics, the battery that is the energy source, and the ignition circuit are closely arranged, and storage in this arrangement is not always preferable from the viewpoint of safety.

  SUMMARY OF THE INVENTION Accordingly, an object of the present invention is to provide a detonation system that can be reduced in size and weight, increase the degree of freedom of fitting, and further improve safety.

  The detonation system for solving the above problems is for detonating explosives loaded on a projectile launched from a launcher, and the projectile side for power feeding using induced electromotive force is applied to the projectile A coil unit, a power storage unit for accumulating power for initiation fed from the flying body side coil unit, an initiator for detonating explosives, and an initiation signal for detonating explosives at a predetermined timing after the launch. An ignition circuit that wirelessly transmits to the ignition circuit, and an ignition circuit that ignites by connecting the power storage unit to the initiator by an explosion signal wirelessly transmitted from the explosion circuit, Is paired with a power source, a converter that modulates power output from the power source in accordance with a frequency corresponding to the type of the power storage unit, and the flying body side coil unit, A power supply unit having a launching device side coil unit for performing power feeding utilized, and immediately before launching the flying object, the feeding device side coil unit and the flying object side coil feed power from the power supply unit to the power storage unit mounted on the flying object. And a power feeding circuit to be performed through the section.

  The detonation system for solving the above-mentioned problem is for detonating explosives loaded on the projectile launched from the launcher, and the projectile is used for power feeding using induced electromotive force. The body side coil part, the power storage body for storing the power for initiation fed from the flying body side coil part, the initiator for detonating the explosive, and the initiation signal wirelessly transmitted from the outside are wirelessly received and received. An explosion circuit that wirelessly transmits an initiation signal toward the ignition circuit, and an ignition circuit that ignites by connecting the power storage unit to the initiator by the initiation signal wirelessly transmitted from the initiation circuit, The launching device is paired with a power source, a converter that modulates the power output from the power source in accordance with the frequency according to the type of the power storage unit, and the flying body side coil unit, and is guided to the power storage unit. A power source unit having a launcher side coil unit for performing power feeding using electric power, and a launcher side wireless transmission for wirelessly transmitting an initiation signal for initiating explosives toward a flying object at a predetermined timing after launching And a power feeding circuit that feeds power from the power supply unit to the power storage unit mounted on the flying body via the launching device side coil section and the flying body side coil section immediately before launching the flying body.

  The detonation system for solving the above-mentioned problem is for detonating the explosive loaded on the N-stage type flying object launched from the launching device. A flying object side coil part for performing power feeding using induced electromotive force, a power storage body for storing electric power for detonation fed from the flying object side coil part, an initiator for detonating explosives, and a predetermined after launching And an ignition circuit that wirelessly transmits an initiation signal for initiating explosives toward the ignition circuit, and an ignition circuit that connects the power storage unit to the initiator and ignites with the initiation signal wirelessly transmitted from the initiation circuit. On the other hand, the N-1 stage flying body has a power supply, a converter that modulates the power output from the power supply in accordance with the frequency according to the type of the storage body, and the Nth stage flying body. Body side coil A power supply unit having a pair of N-1th stage flying body side coil units for supplying power using induced electromotive force to the N-th stage flying body power storage unit, and an Nth stage flying body Immediately before disconnection, a power supply circuit for supplying power from the power supply unit to the power storage unit is provided.

  According to the present invention, the power unit is disposed on the launching device side, and the power storage unit that is charged with power by the power unit on the launching device side is disposed on the flying body side, and the initiation between the initiation circuit and the ignition circuit is performed. Since signal transmission / reception is performed wirelessly, the weight can be reduced, the size can be reduced, and the degree of freedom of fitting can be increased, and the safety can be improved.

In addition, since the electric power output from the power source is modulated by the converter in accordance with the frequency corresponding to the type of the power storage unit, the frequency corresponding to the type of the power storage unit can be supported.
Furthermore, since the feeding device side coil unit arranged in the launching device and the flying object side coil unit arranged in the flying object are performing power feeding using the induced electromotive force, there is no need to perform connection for feeding, Contactless power feeding can be performed. Thereby, preparation for launch can be simplified.
Furthermore, an explosion signal output unit that wirelessly outputs an initiation signal for initiating explosives at a predetermined timing after launching is arranged in the launching device, and the initiation signal wirelessly transmitted from the outside is wirelessly received and received. When an explosion circuit that wirelessly transmits an initiation signal to the ignition circuit is mounted on the flying object, it is not necessary to set timing for each missile.

  The best mode for carrying out the present invention will be described below with reference to the drawings. FIG. 1 is a block diagram showing a circuit configuration of an initiation system according to the first embodiment of the present invention.

  In the initiation system A1 according to the first embodiment of the present invention, the power supply unit 10 and the power feeding circuit 20 are arranged in the launching device B, and the initiation circuit 30, the ignition circuit 40, and the initiator 50 are arranged on the flying object C side such as a missile. doing.

First, the launcher B will be described.
The launcher B can launch a single or multiple projectiles (hereinafter simply referred to as “missiles”) C mounted on the launcher B, and is illustrated through a communication link terminal (DLT) by VHF radio or optical fiber. It is designed to be connected to the fire control device.

  The power supply unit 10 is for supplying power for initiation to a power storage unit 45 (described later) disposed on a missile C mounted on the launching device B. The power supply unit 10 includes a DC power supply 11, a DC-AC converter 12, and A launcher-side coil unit 13 for power feeding using induced electromotive force is disposed.

The DC-AC converter 12 shown in the present embodiment employs a pulse width modulation circuit (PWM) that modulates by changing the duty ratio of the pulse wave. Thereby, although it can respond to the frequency according to the kind of electrical storage body 45, another modulation system may be sufficient.
In addition, the power supply unit is not limited to the one using the DC power supply described above, and may be configured using an AC power supply.

The power supply circuit 20 supplies power from the power supply unit 10 to the missile C immediately before launching the missile C, and is turned on / off provided in the wiring between the DC power supply 11 and the DC-AC converter 12 described above. A switch 21 and a switch switching circuit 22 for turning on the on / off switch 21 are provided. By turning on the on / off switch 21, power for initiation is supplied from the power supply unit 10 to the power storage unit 45. It is designed to supply power.
Note that “power feeding” in this embodiment is synonymous with “charging”, and “power storage unit” can also be referred to as “charging unit”.
“Initiation power” is necessary and sufficient to ignite the squib 52 of the initiator 50 to be described later. Therefore, the capacity of the power storage unit 45 is sufficient to store the power.

In the present embodiment, the on / off switch 21 is turned on by the input of a power feeding start signal transmitted from the shooting control device (not shown).
“Just before launching the missile C” is assumed to be, for example, several tens of seconds before launch in consideration of the discharge characteristics when the power storage unit 45 is a super capacitor, for example.
That is, when the missile C is stored, the power storage unit 45 is not stored.

Next, the missile C will be described.
The initiation circuit 30 shown in this embodiment includes a DC power supply 31, a sequence circuit 32, and a wireless transmission unit 33.

The initiation circuit 30 has a function of outputting an initiation signal for initiating the explosive 51 of the initiator 50 at a predetermined timing after the launch.
“Predetermined timing after launch” is when a predetermined time has elapsed since launch, for example, by a timer circuit (not shown).

The wireless transmission unit 33 has a function of wirelessly transmitting the initiation signal output from the sequence circuit 32 toward the wireless reception unit 41 of the ignition circuit 40.
In this embodiment, Bluetooth technology is used, and reliability is enhanced by using a technically mature commercial product.
Further, by using the Bluetooth technology, communication can be performed even if there is an obstacle between the initiation circuit 30 and the ignition circuit 40, so that the internal equipment is not limited. In other words, the degree of freedom of outfitting can be improved.

The ignition circuit 40 includes a wireless receiver 41, an accelerometer 42, ignition switches 43 and 43, safety switches 44 and 44, a power storage unit 45, and a flying object side coil unit 46.
The ignition switches 43 and 43 and the safety switches 44 and 44 are disposed between the wires of the power storage unit 45 and the initiator 50.

  The wireless reception unit 41 receives an initiation signal wirelessly transmitted from the wireless transmission unit 33, and includes a switch operation circuit (illustrated) for turning on the ignition switches 43 and 43 upon reception of the initiation signal. Not incorporated).

  The accelerometer 42 detects the acceleration generated with the flight of the missile C, and adopts a MEMS (Micro Electro Mechanical Systems) type. A MEMS is a device in which circuits are integrated on a single silicon substrate, glass substrate, organic material, etc., and is advantageous in reducing size and weight.

Further, the accelerometer 42 incorporates a switch operation circuit (not shown) for turning on the safety switches 44 and 44.
That is, the safety switches 44 and 44 are turned on by detecting the acceleration after the launch.
In the present embodiment, the accelerometer 42 and the safety switches 44 and 44 constitute a malfunction prevention circuit 47 for preventing malfunction. Thereby, for example, even when the ignition switches 43 and 43 are erroneously turned on when mounted on the launcher B, it is possible to prevent accidental explosion.

The power storage unit 45 shown in the present embodiment is a so-called supercapacitor, and by adopting this supercapacitor, it is possible to perform rapid charging and to reduce the size and weight.
The power storage unit is not limited to the super capacitor, and a general secondary battery may be employed.

The operation of the detonation system having the above configuration will be described.
When the missile C is fired, the on / off switch 21 is turned on by the switch switching circuit 22 immediately before launching according to the power supply start signal transmitted from the shooting control device side to the launching device B prior to the launch signal.
Thereby, the direct current of the direct current power source 11 is converted into an alternating current by the DC-AC converter 12, and power is supplied to the power storage unit 45 via the launcher side coil unit 13 and the flying body side coil unit 46.

When the missile C is fired by the launch signal transmitted thereafter and the acceleration accompanying the flight is detected by the accelerometer 42, the safety switches 44, 44 are turned on.
When a predetermined time elapses, an initiation signal is output from the sequence circuit 32. The initiation signal is wirelessly transmitted to the wireless reception unit 41 of the ignition circuit 40 via the wireless transmission unit 33.

  When the wireless reception unit 41 of the ignition circuit 40 receives the initiation signal, the ignition switches 43 and 43 are turned on, and the power for initiation of the power storage unit 45 is supplied to the squib 52 of the initiator 50 to initiate explosion.

According to the first embodiment of the present invention described above, the following effects can be obtained.
・ A power unit is placed on the launcher side, and a power storage unit powered by the launcher side power unit is placed on the projectile side, and transmission and reception of initiation signals between the initiation circuit and ignition circuit are performed wirelessly. As a result, it is possible to reduce the weight, reduce the size, increase the degree of freedom of the outfitting, and improve the safety.

・ Because charging using the induced electromotive force is performed by the launcher side coil section arranged in the launcher and the flying body side coil section arranged in the flying body, it is not necessary to perform connection for power feeding, Power can be supplied by contact. Thereby, preparation for launch can be simplified.

-Since a super capacitor is used as the battery, rapid charging can be performed, and the size and weight can be reduced. Thereby, the time required for launch preparation can be shortened.
-Since the wireless transmitter and wireless receiver placed on the flying object transmit and receive the initiation signal using Bluetooth technology, they can communicate even if there is an obstacle between the initiation circuit and the ignition circuit. There is no restriction on the internal outfitting.
-Since a malfunction prevention circuit is provided on the flying object, it is possible to prevent accidental explosion.
Since the power supply unit is configured by including a DC power supply and a pulse width modulation circuit, it is inexpensive.

  Next, an initiation system according to the second embodiment of the present invention will be described with reference to FIG. FIG. 2 is a block diagram showing a circuit configuration of an initiation system according to the second embodiment of the present invention. In addition, about the thing equivalent to what was demonstrated in embodiment mentioned above, the code | symbol same as them is attached | subjected and description is abbreviate | omitted.

  In the initiation system A2 according to the second embodiment of the present invention, an explosion circuit 30A, an ignition circuit 40, and an initiator 50 having configurations different from those of the above-described embodiment are arranged in the flying object C, while The signal output unit 60, the launcher-side radio transmission unit 70, the power supply unit 10, and the power feeding circuit 20 are arranged.

The initiation signal output unit 60 disposed in the launching device B has a function of outputting an initiation signal for initiating explosives at a predetermined timing after launch, and corresponds to the sequence circuit 32 described above.
The launcher-side wireless transmission unit 70 has a function of wirelessly transmitting the initiation signal output from the initiation signal output unit 60 toward the initiation circuit 30A.

  The initiation circuit 30 </ b> A includes an initiation signal wireless reception unit 80 having a function of wirelessly receiving the initiation signal wirelessly transmitted from the launching device side wireless transmission unit 70 and a wireless transmission unit 33.

The operation of the detonation system having the above configuration will be described.
When the missile C is fired, the on / off switch 21 is turned on by the switch switching circuit 22 immediately before launching according to a power supply start signal transmitted from the shooting control device side to the launching device C prior to the launch signal.
Thereby, the direct current of the direct current power source 11 is converted into an alternating current by the DC-AC converter 12, and power is supplied to the power storage unit 45 via the launcher side coil unit 13 and the flying body side coil unit 46.

Thereafter, when the missile C is launched by the launch signal and the acceleration accompanying the flight is detected by the accelerometer 42, the safety switches 44, 44 are turned on.
When a predetermined time elapses, an initiation signal is output from the initiation signal output unit 60. This initiation signal is wirelessly transmitted toward the missile C via the launcher-side wireless transmission unit 70.

  When the initiation signal wireless reception unit 80 of the missile C receives the initiation signal wirelessly transmitted from the launcher B, the initiation signal is wirelessly transmitted to the wireless reception unit 41 of the ignition circuit 40 via the wireless transmission unit 33. To do.

  When the wireless reception unit 41 of the ignition circuit 40 receives the initiation signal, the ignition switches 43 and 43 are turned on, and the initiation power stored in the power storage unit 45 is supplied to the squib 52 of the initiator 50 to initiate the initiation. To do.

  According to the above-described invention, in addition to the effects obtained in the first embodiment of the present invention, an initiation signal output unit that wirelessly outputs an initiation signal for initiating explosives at a predetermined timing after the launch is arranged in the launching device. Therefore, there is no need to set timing for each missile.

  In the above-described embodiment, the detonation system for detonating the explosive loaded on the flying object launched from the launching device has been described as an example. However, the detonation system for detonating the explosive loaded on the N-stage flying object. Can be applied to.

  That is, an N-stage flying object loaded with explosives is wirelessly transmitted to the ignition circuit with an initiator for initiating explosives and an initiation signal for initiating explosives at a predetermined timing after being separated. The N-1 stage has an initiation circuit and an ignition circuit that has an electrical storage body that stores electrical power for initiation, and that ignites by connecting the electrical storage body to the initiator by an initiation signal wirelessly transmitted from the initiation circuit. A power supply unit for supplying power to the power storage unit of the Nth stage flying object and a power supply circuit for supplying power from the power supply unit to the power storage unit immediately before disconnecting the Nth stage flying object are arranged on the flying object of the eye. Specifically, the configuration is as follows.

  FIG. 3 is a block diagram showing a circuit configuration of an initiation system according to the third embodiment of the present invention. In addition, about the thing equivalent to what was demonstrated in embodiment mentioned above, the code | symbol same as them is attached | subjected and description is abbreviate | omitted.

  A detonation system A3 according to the third embodiment of the present invention includes a power supply unit 10 and a power supply circuit 20 in a rocket D that is a first stage flying body, and a detonation circuit 30 in a rocket E that is a second stage flying body. The ignition circuit 40 and the initiator 50 are arranged.

The power feeding circuit 20 feeds power from the power supply unit 10 to the second stage rocket E immediately before the second stage rocket E is disconnected, and is connected between the DC power source 11 and the DC-AC converter 12 described above. An on / off switch 21 provided in the wiring and a switch switching circuit 22 for turning on the on / off switch 21 are provided. By turning on the on / off switch 21, the power storage unit 10 45 is supplied with power for detonation.
In the present embodiment, the on / off switch 21 is turned on by the input of a power supply start signal transmitted prior to the disconnection signal.

The present invention is not limited to the above-described embodiments, and the following modifications can be made.
-In above-mentioned embodiment, although the example which employ | adopted the super capacitor as an electrical storage body was demonstrated, it replaces with this and a secondary battery etc. are employable.
In FIG. 3, the configuration described in FIG. 1 is applied to the two-stage rocket. However, the configuration described in FIG. 2 may be applied.

It is a block diagram which shows the circuit structure of the detonation system which concerns on 1st embodiment of this invention. It is a block diagram which shows the circuit structure of the initiation system which concerns on 2nd embodiment of this invention. It is a block diagram which shows the circuit structure of the initiation system which concerns on 3rd embodiment of this invention.

Explanation of symbols

DESCRIPTION OF SYMBOLS 10 Power supply part 11 DC power supply 12 DC-AC converter 13 Launcher side coil part 20 Feeding circuit 30, 30A Explosion circuit 33 Wireless transmission part 45 Power storage unit 40 Ignition circuit 41 Wireless reception part 42 Accelerometer 46 Flying body side coil part 47 Prevention of malfunction Circuit 50 Initiator 51 Explosive 60 Explosive signal output unit 70 Launcher side wireless transmitter 80 Explosion signal radio receivers A1 to A3 Explosion system B Launcher C Flying object D First stage rocket (flying object)
E Second stage rocket (aircraft)

Claims (8)

In the detonation system for detonating the gunpowder loaded on the projectile launched from the launcher,
The flying body includes a flying body side coil unit for feeding power using induced electromotive force, a storage body for storing power for initiation fed from the flying body side coil unit, and an initiator for detonating explosives. If, at a predetermined timing after the firing, a detonator circuit for wirelessly transmits a detonation signal to detonate the explosive ignition circuit, wirelessly transmitted detonated signals from the detonation circuit, to connect the power storage bodies to the initiator while it is distributing an ignition circuit for igniting Te,
The launcher includes a power source, a converter that modulates the power output from the power source in accordance with a frequency corresponding to the type of the power storage unit, and the flying body side coil unit, and the power storage unit using the induced electromotive force. A power supply unit having a launcher side coil unit for supplying power to
Immediately before launching the flying object, a power supply circuit is provided that feeds power from the power source to the power storage unit mounted on the flying object via the launcher side coil part and the flying object side coil part. Detonation system.   2. The initiation system according to claim 1, wherein the initiation circuit includes a signal output unit that outputs an initiation signal at a predetermined timing after the launch, and a wireless transmission unit that wirelessly transmits the initiation signal toward the ignition circuit. In the detonation system for detonating the gunpowder loaded on the projectile launched from the launcher,
The flying body includes a flying body side coil unit for feeding power using induced electromotive force, a storage body for storing power for initiation fed from the flying body side coil unit, and an initiator for detonating explosives. If, wirelessly receives an initiation signal wirelessly transmitted from the outside, and a detonator circuit for wirelessly transmits the detonation signal the received ignition circuit, wirelessly transmitted detonated signals from the detonator circuit, the power storage body initiator while an ignition circuit for igniting connect to you are distribution,
The launching device is paired with a power source, a converter that modulates the power output from the power source in accordance with the frequency according to the type of the power storage unit, and the flying body side coil unit. A power supply unit having a launcher side coil unit for performing power feeding utilized, and a launcher side wireless transmission unit for wirelessly transmitting an initiation signal for initiating explosives toward a flying object at a predetermined timing after launching; , characterized in that immediately prior to firing the projectile, and arranged a feeding circuit to perform through the launcher side coil portion power supply to the equipped with the power storage unit to the projectile and flight side coil unit from the power supply unit Detonation system. The ignition circuit includes a wireless reception unit that receives an initiation signal wirelessly transmitted from the wireless transmission unit, and a connection circuit that electrically connects the power storage unit to the initiator by the initiation signal received by the wireless reception unit . The detonation system according to claim 3. The detonation system according to any one of claims 1 to 4 , wherein the power storage unit is a super capacitor . The initiation system according to any one of claims 1 to 5, wherein the wireless transmission unit and the wireless reception unit arranged in the flying body transmit and receive an initiation signal by Bluetooth technology . 7. The flying object according to claim 1 , further comprising an accelerometer that detects acceleration associated with the flying of the flying object, and a malfunction prevention circuit that prevents malfunction by detecting the acceleration . Detonation system. In the detonation system for detonating the gunpowder loaded on the N-stage projectile launched from the launcher,
The N-stage flying body loaded with explosives has a flying body side coil portion for performing power feeding using induced electromotive force, a power storage body for storing power for initiation fed from the flying body side coil portion, With an initiator for detonating explosives, an explosion circuit for wirelessly transmitting an explosion signal for detonating explosives toward the ignition circuit at a predetermined timing after launch, and an explosion signal wirelessly transmitted from this explosion circuit, While arranging an ignition circuit that ignites by connecting the power storage unit to the initiator,
The N-1th stage flying object is paired with a power supply, a converter that modulates the power output from the power supply in accordance with the frequency according to the type of the power storage body, and the Nth stage flying object side coil section. The power supply unit having the N-1th stage flying body side coil unit for supplying power using the induced electromotive force to the N-stage flying body power storage unit and immediately before separating the Nth stage flying body And a power supply circuit for supplying power from the power supply unit to the power storage unit .

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