KR101600990B1 - The shock-sensing and unlocking circuits of the safety and arming device for the missile fuze - Google Patents

Abstract

The present invention relates to a shock detection circuit and a lock release circuit of a safety device for a safety device for a new missile for a missile, and more particularly, to a safety device for a safety device for a missile gun capable of sufficiently transmitting an explosive energy to an explosion tube And more particularly, to a lock releasing circuit for a safety device for a safety device for a new bobbin for a shotgun, which can increase the safety of the safety device for new bobbin with a small impact consumption and a small amount of power consumption.
In order to accomplish the above object, an embodiment of an embodiment of a shock detection circuit of a safety device for a lead-in-fuse bobbin according to the present invention includes: a first resistor used for charging a capacitor; A second resistor used to discharge the capacitor; A capacitor charging voltage is supplied to the base end of the transistor by charging the voltage when the power source is applied and discharging the capacitor charging voltage when an impact signal is input to cut off the capacitor charging voltage supply to the base end of the transistor A capacitor for cutting off; And a transistor for generating an excitation trigger signal that extends the pulse width of the impact signal by a time when the capacitor charge voltage supply is cut off. . ≪ / RTI >
According to another aspect of the present invention, there is provided a lock releasing circuit for a safety device for a lead-in fuel for a touring car, wherein when the charging switch is turned off after power is applied, A first transistor for blocking the voltage at the base end of the second transistor when the charging switch is turned on after the power source is applied; A gate terminal of the MOSFET is supplied with a voltage when the voltage is supplied to the base end of the second transistor and a gate terminal of the MOSFET is turned off when the voltage is cut off at the base end of the second transistor 2 transistor; And a MOSFET for applying the power to a locking device when the voltage is supplied to the gate terminal of the MOSFET and for blocking the power applied to the locking device when the voltage is blocked at a gate terminal of the MOSFET; . ≪ / RTI >

Description

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a shock detection circuit and a lock release circuit of a safety device for a safety device for a lead-

The present invention relates to a shock detection circuit and a lock release circuit of a safety device for a safety device for a new missile for a missile, and more particularly, to a safety device for a safety device for a missile gun capable of sufficiently transmitting an explosive energy to an explosion tube And more particularly, to a lock releasing circuit for a safety device for a safety device for a new bobbin for a shotgun, which can increase the safety of the safety device for new bobbin with a small impact consumption and a small amount of power consumption.

FIG. 1 is a block diagram showing a configuration of a safety charging apparatus for a guide pipe according to the prior art, FIG. 2 is a detailed circuit diagram showing an impact sensing circuit in a safety charging apparatus for a guide pipe according to the prior art, FIG. 3 is a diagram showing a change in an ignition trigger signal and an ignition capacitor after an impact detection. FIG.

Referring to FIG. 1, the safety device (0) of the fuse protects the safety of the bullet when storing, transporting and handling the bullet, and igniting the bullet or ammunition at a point outside the safety distance after the fire.

Hereinafter, the operation principle of the fuse safety loading apparatus 0 will be described in more detail.

First, when the missile safety load device 0 is supplied with the missile power source 1 and the missile is fired, the safety device 100 starts to detect the launch condition or the launch environment of the missile. Thereafter, when the missile comes out of the safe distance, the primary safety device 121 and the secondary safety device 122 of the safety device 100 operate to align the explosive series part 400 in a straight line , And mechanically turns the charging switch 220 on. When the recharging switch 220 is turned on, the urging energy supply circuit 230 is supplied with the discharge charger 1. Thereafter, the aeronautical energy charging circuit 230 delays the aeronautical energy charging time in consideration of the time when the guided char is out of the safety distance, and then charges the aeronautic energy 5 into the aeronautic capacitor 262 in the detonator circuit 260 . When the charging of the ignition capacitor 262 is completed, the impact switch 240 is turned on and charged into the ignition capacitor 262 in the detonating circuit 260 The collision energy 5 is transmitted to the detonating pipe 300 through the impact switch 240. When the explosion-related part 400 is operated by the explosion-proof pipe 300 having received the explosion energy 5, the bullet explodes and destroys the target. However, when the turn-on time of the impact switch 240 is very short, which is less than several microseconds, in the event of a target collision of the missile, the aerodynamic energy 5 is not sufficiently transmitted to the explosion pipe 300, 300 may not operate. Accordingly, the explosion sequence unit 400 can not operate.

Referring to FIG. 2, when the spark plug collides with the target and the impact switch 240 is turned on, the aerodynamic energy 5 stored in the ignition capacitor 262 in the detonator circuit 260 is applied to the impact switch 240 to discharge the aerodynamic energy 5 to the aerating tube 300. If the turn-on time of the impact switch 240 is several microseconds or less, the pulse width of the impact signal 2 is also short as less than several microseconds, It may not be enough to deliver.

Referring to FIG. 3, the aerodynamic capacitor 262 is charged with the aerodynamic energy 5 as the missile power source 1 is applied. When the missile collides with the target in the state where the aerodynamic energy 5 is charged, the impact switch 240 is turned on and turned on, and the explosive energy 5 is transmitted through the impact switch 240 And is transmitted to the explosion pipe (300). If the pulse width of the impact signal 2 is very short, such as about several microseconds, the aerodynamic energy 5 charged in the aerobic capacitor is not sufficiently transferred to the aerobic tube 300, ) Can not be ignited.

The present invention has been proposed in order to solve the above problems. In the case where the missile collides with the target, the pulse signal having the pulse width expanded is transmitted to the detonation circuit, so that the detonation energy in the detonation circuit can be sufficiently transmitted to the detonator And an object of the present invention is to provide an impact detection circuit for a safety load device for a new pipe for a missile.

It is another object of the present invention to provide a lock releasing circuit for a safety load device for a newbuilding canister which can reduce the power consumption and increase the safety of the safety device.

In order to accomplish the above object, an embodiment of an embodiment of a shock detection circuit of a safety device for a lead-in-fuse bobbin according to the present invention includes: a first resistor used for charging a capacitor; A second resistor used to discharge the capacitor; A capacitor charging voltage is supplied to the base end of the transistor by charging the voltage when the power source is applied and discharging the capacitor charging voltage when an impact signal is input to cut off the capacitor charging voltage supply to the base end of the transistor A capacitor for cutting off; And a transistor for generating an excitation trigger signal that extends the pulse width of the impact signal by a time when the capacitor charge voltage supply is cut off. . ≪ / RTI >

According to another aspect of the present invention, there is provided a lock releasing circuit for a safety device for a lead-in fuel for a touring car, wherein when the charging switch is turned off after power is applied, A first transistor for blocking the voltage at the base end of the second transistor when the charging switch is turned on after the power source is applied; A gate terminal of the MOSFET is supplied with a voltage when the voltage is supplied to the base end of the second transistor and a gate terminal of the MOSFET is turned off when the voltage is cut off at the base end of the second transistor 2 transistor; And a MOSFET for applying the power to a locking device when the voltage is supplied to the gate terminal of the MOSFET and for blocking the power applied to the locking device when the voltage is blocked at a gate terminal of the MOSFET; . ≪ / RTI >

According to the shock detection circuit of the safeguarding device for a missile in accordance with the present invention, when the missile collides with the target, the impact signal with the extended pulse width is transmitted to the detonation circuit, thereby sufficiently transmitting the detonation energy in the detonation circuit to the detonation tube So that the reliability of the ignition tube ignition can be improved.

In addition, according to the lock releasing circuit of the safing device for a newbuilding can according to the present invention, it is possible to increase the safety of the safety device for the safety of the new building while consuming a small amount of power.

FIG. 1 is a block diagram showing a configuration of a safety load device for a fuse for shotgun according to the prior art; FIG.
FIG. 2 is a detailed circuit diagram showing a shock detection circuit in a safety load device for a fuse for a missile in accordance with the prior art; FIG.
FIG. 3 is a diagram showing a change in an ignition trigger signal and an ignition capacitor after a shock detection according to the related art; FIG.
FIG. 4 is a block diagram showing a first embodiment of a safing device for a fire fighting cannon according to the present invention. FIG.
FIG. 5 is a block diagram showing a second embodiment of a safe loading device for a guide pipe for a token according to the present invention. FIG.
FIG. 6 is a block diagram showing a third embodiment of the safing device for a fuse for shotgun according to the present invention. FIG.
FIG. 7 is a detailed circuit diagram showing a shock detection circuit in a safing device for a firearm for a missile in accordance with the present invention. FIG.
FIG. 8 is a diagram showing a change in an ignition trigger signal and an ignition capacitor after a shock detection according to the present invention. FIG.
FIG. 9 is a detailed circuit diagram showing a lock releasing circuit in a safety load device for a fuse for a missile in accordance with the present invention. FIG.
10 is a diagram showing a change in driving force of a lock device in an embodiment of a lock releasing circuit in a safety load device for a lead-in-fog car for a lead in accordance with the present invention.

While the invention is susceptible to various modifications and alternative forms, specific embodiments thereof are shown by way of example in the drawings and will herein be described in detail.

It is noted that the technical terms used herein are used only to describe specific embodiments and are not intended to limit the invention. Also, the technical terms used herein should be interpreted in a sense that is generally understood by those skilled in the art to which the present disclosure relates, unless otherwise specifically defined in the present specification, Or shall not be construed to mean excessively reduced. It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory and are intended to provide further explanation of the invention as claimed. But is to be understood as including all modifications, equivalents, and alternatives falling within the scope of the appended claims.

Hereinafter, a first embodiment of a safety load device for a lead-in-gun using a shock detection circuit and a lock release circuit according to the present invention will be described in detail with reference to the accompanying drawings.

FIG. 4 is a block diagram showing a first embodiment of a safe loading device for a guide pipe according to the present invention.

Referring to FIG. 4, the safety load device for a lead-in vehicle using a shock detection circuit and a lock release circuit according to the present invention includes a safety device 100, an ignition circuit part 200, And an explosion series portion 400.

The safety device unit 100 receives the power source 1 from the lock release circuit 270 and senses a firing condition or a firing environment of the missile, And turns the charging switch 220 on. Here, the predetermined condition may be a condition generated by an internal module of the safety device 100, and may be a condition transmitted from the outside of the safety device 100. [ Particularly, the predetermined condition may be a condition for judging whether or not the missile is out of the safe distance in terms of the launch condition or the launch environment of the missile. When the predetermined condition is satisfied, for example, when the missile is out of the safe distance, the safety device 100 senses the launch condition or the launch environment of the missile, . More particularly, the safety device 100 includes a locking device 110 and a safety device 120.

The locking device 110 receives the driving force source 1 from the unlocking circuit 270 and operates the safety device 120 installed in the safety device 100. That is, the locking device 110 maintains the locked state to prevent the safety device 120 mounted inside the safety device 100 from operating until receiving the driving force source 1. Thereafter, when the power source 1 is applied to the locking device 110, the locking device 110 releases the locking state so that the safety device 120 operates. Here, the locking device 110 may be an electrical or mechanical device for enhancing the safety of the bullet during storage, transportation, or handling of the bullet, and may serve as a safety pin for the safety device 120. In particular, the locking device 110 may be a solenoid valve assembly 111. That is, the solenoid valve assembly 111 can operate the safety device 120. Here, the power source 1 of the missile charger applied to the locking device 110 may be referred to as a locking device driving power source 6.

The safety device 120 senses the firing condition or the firing environment of the missile, and turns on the recharge switch 220 of the detonating circuit unit 200 when the predetermined condition is satisfied. When the charging switch 220 is turned on, the magazine energy source 1 is applied to the aeronautical energy charging circuit 230, and the aeronautical energy charging circuit 230 charges the aeronautic capacitor 262 So that it can be charged. Here, the safety device 120 may mechanically and electrically turn on the recharging switch 220. In addition, the safety device 120 senses the firing condition or the firing environment of the missile, and when the predetermined condition is satisfied, for example, when the missile is out of the safety distance, the explosion series part 400 is straight . Thus, the explosion-proof part 400 can ignite the warhead by the explosion-proof pipe 300. Here, the fact that the explosion series part 400 is aligned means that a circuit for moving the warhead-detonating devices to an explosive state or igniting the warhead is constituted. More particularly, the safety device 120 may include a first safety device 121 and a second safety device 122.

The first safety device 121 and the second safety device 122 sense the firing condition or the firing environment of the missile and if the predetermined condition is satisfied, the recharging switch 220 is turned on, . Here, the first safety device 121 and the second safety device 122 may mechanically and electrically turn on the recharging switch 220. In addition, the first safety device 121 and the second safety device 122 may align the explosion series part 400 by sensing the launch condition or the launch environment of the missile.

When the missile collides with the target in the loaded state, the detonation circuit unit 200 transmits the explosion energy 5 to the detonation tube 300. Here, the loading state is a state in which the safety device 100 operates to turn on the charging switch 220, so that an ignition energy 5 is generated in the ignition capacitor 262 in the detonating circuit It may mean a charged state. More specifically, the detonating circuit unit 200 includes a power supply filter 210, a charging switch 220, an ignition energy charging circuit 230, an impact switch 240, an impact sensing circuit 250, an explosion circuit 260, And a lock release circuit 270.

The power supply filter 210 removes noise or the like from the power source for the guidance gun.

The charging switch 220 is turned on by the safety device 100 and applies the driving force source 1 to the explosive energy charging circuit 230.

 The aeronautical energy charging circuit 230 charges the aeronautical energy 5 into the aeronautic capacitor 262 in the aeronautical circuit 260 when the charging switch 220 applies the guide discharge power source 1 thereto. At this time, the aeronautical energy charging circuit 230 may charge the aeronautic energy 5 to the aeronautic capacitor 262 after delaying the charging time by a necessary delay time. In addition, the aeronautical energy charging circuit 230 may delay the time by considering the time when the missile is out of the safety distance, thereby charging the aeronautical energy 26 to the aeronautical energy 5.

The impact switch (240) generates an impact signal (2) in the event of a collision between the missile and the target.

The shock sensing circuit 250 receives the impact signal 2 and generates an excitation trigger signal 4 that extends the pulse width 7 of the impact signal. Therefore, the pulse width 9 of the trigger signal generated by the shock sensing circuit 250 is the pulse width 7 of the impact signal.

The detonating circuit 260 receives the detonating trigger signal 4 and transmits the detonating energy 5 charged in the detonating capacitor 262 to the detonating tube 300. More specifically, the detonating circuit 260 receives the ignition trigger signal 4 whose pulse width is adjusted at the gate terminal of the detonating circuit MOSFET 261, and turns on the detonating circuit MOSFET 261 Turn-on. When the detonating circuit MOSFET 261 is turned on, the detonation energy 5 stored in the detonating capacitor 262 is transferred to the detonating tube 300 to operate the detonating tube 300.

The lock releasing circuit 270 applies or disconnects the poWer charger power source 1 to the locking device 110. [ More specifically, the lock releasing circuit 270 releases the lock device 110 by applying a guide discharge power source 1 to the lock device 110. In addition, the lock release circuit 270 may automatically shut off the automatic guided vehicle power source 1 applied to the locking device 110 at the same time that the loading switch 220 is turned on. As a result, the fuse safety loading apparatus 0 can reduce the consumption amount of the discharge charger 1. For example, the lock releasing circuit 270 releases the solenoid valve assembly 111 by applying a guide discharge power source 1 to the solenoid valve assembly 111, which is one type of the lock device 110. [ In addition, the lock release circuit 270 may be configured such that when the recharging switch 220 is turned on by the safety device 120 and simultaneously the stimulus current power source 1 applied to the solenoid valve assembly 111 ) Can be automatically blocked. Therefore, the solenoid valve assembly 111 having a large amount of power consumption does not consume the power source for the missile charger 1, thereby reducing the power consumption of the safety device for the fuse-safe 0. Here, the power source of the missile charger 1 applied to the locking device 110 may be referred to as a locking device driving power source 6.

The detonating tube (300) senses the explosion energy (5) and detonates the explosion sequence part (400).

The detonation sequence unit 400 detonates the warhead by the detonation of the detonator 300. Here, the explosion sequence unit 400 may mean a set of detonators except for the detonation pipe 300.

Hereinafter, a second embodiment of a safing device for a fire fighting vehicle using a shock detection circuit according to the present invention will be described in detail with reference to the accompanying drawings.

FIG. 5 is a block diagram showing a second embodiment of a safing device for a fire fighting cannon according to the present invention. Among the configurations of this embodiment, the same reference numerals as those of the first embodiment of the present invention are used for the same reference numerals in FIG. 4, and a detailed description thereof will be omitted.

Referring to FIG. 5, a safety device for a lead-in-bail (0) according to the present invention includes a safety device unit 100, an ignition circuit unit 200, an explosion-proof pipe 300 and an explosion- 400).

More particularly, the safety device 100 includes a safety device 120. [ That is, this embodiment is different from the safety device 100 of the first embodiment in that the above-described shock sensing circuit and lock releasing circuit according to the present invention are used. will be. The detonating circuit unit 200 includes a power supply filter 210, a charging switch 220, an ignition energy charging circuit 230, an impact switch 240, an impact sensing circuit 250 and an detonating circuit 260 . That is, this embodiment is different from the ignition circuit unit 200 of the first embodiment in that the lock releasing circuit 270 is installed in the safety lock apparatus for a lead-in fuel using the shock detection circuit and the lock releasing circuit according to the present invention .

Therefore, according to the present embodiment, when the missile charger 1 is applied and the missile is fired, the safety device 100 starts to detect the launch condition or the launch environment of the missile. Thereafter, when the shooting condition of the missile or the shooting environment satisfies a predetermined condition, for example, when the missile is out of the safety distance, the loading switch 220 of the detonating circuit unit 200 is turned- and the explosion circuit part 200 is turned into a loaded state and the explosion series part 400 is aligned in a straight line.

The components other than the lock device 110 and the lock release circuit 270 are substantially the same as the first embodiment of the safety fuse device for a fire fighting vehicle using the shock detection circuit and the lock release circuit according to the present invention described above, The detailed description is omitted.

Hereinafter, a third embodiment of the safety load device for a guide pipe for a toddler in which the lock releasing circuit according to the present invention is used will be described in detail with reference to the accompanying drawings.

FIG. 6 is a block diagram showing a third embodiment of the safing device for a fire fighting cannon according to the present invention. Among the configurations of this embodiment, the same reference numerals as those of the first embodiment of the present invention are used for the same reference numerals in FIG. 4, and a detailed description thereof will be omitted.

Referring to FIG. 6, the safety device for a lead-in-bail for a toddler using a lock releasing circuit according to the present invention includes a safety device unit 100, an ignition circuit unit 200, a detonating pipe 300, (400).

More specifically, the detonating circuit unit 200 includes a power supply filter 210, a charging switch 220, an explosion energy charging circuit 230, an impact switch 240, an explosion circuit 260, and a lock releasing circuit 270 ). That is, the shock sensing circuit 250 of the present embodiment is different from the ignition circuit portion 200 of the embodiment of the safing device for a lead-in fuel using the shock sensing circuit and the lock releasing circuit according to the present invention.

Therefore, in the present embodiment, the detonating circuit unit 200 receives the impact signal 2 and does not expand the pulse width 7 of the impact signal. More specifically, the impact switch 240 in the detonating circuit portion 200 generates the impact signal 2 when the target and the missile collide. Therefore, the ignition trigger signal 4 having the same pulse width as the impact signal 2 is transmitted to the detonating circuit 260. Accordingly, the detonating circuit 260 receives the detonating trigger signal 4, that is, the shock signal 2, and outputs the detonating energy 5 charged in the detonating capacitor 262 to the detonating tube 300 ).

Components other than the impact sensing circuit 250 are substantially the same as those of the first embodiment of the safety device for the safety device for a new missile in which the shock detection circuit and the lock releasing circuit according to the present invention are used. do.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, an embodiment of a shock detection circuit of a safety device for a lead-in-fuse bobbin according to the present invention will be described in detail with reference to the accompanying drawings.

FIG. 7 is a detailed circuit diagram showing a shock detection circuit in a safing device for a fire fighting cannon according to the present invention, and FIG. 8 is a diagram showing a change in an ignition trigger signal and an ignition capacitor after an impact detection according to the present invention.

Referring to FIG. 7, the impact sensing circuit 250 of the fuse fuse safety charging device for a toddler can include a first resistor 251, a second resistor 252, a capacitor 253, and a transistor 254.

The first resistor 251 is used to charge the capacitor. Here, the first resistor 251 may be a variable resistor to extend the pulse width 9 of the trigger signal. In addition, the first resistor 251 may include a resistance of a conductor.

The second resistor 252 is used to discharge the capacitor. Here, the second resistor 252 may include a resistance of a conductor.

The capacitor 253 charges the voltage when the power source 1 is applied and supplies the capacitor charging voltage 3 to the base end of the transistor 254. When the impulse signal 2 is input, Discharges the capacitor charging voltage 3 and cuts off the supply of the capacitor charging voltage 3 to the base end of the transistor 254. That is, the capacitor 253 charges the voltage and turns on the transistor 254 for a time period in which the capacitor charging voltage 3 maintains the predetermined voltage or higher, ). The capacitor 253 also discharges the capacitor charging voltage 3 to turn off the transistor 254 for a time that the capacitor charging voltage 3 remains below a predetermined voltage, .

Here, the predetermined voltage may be 0.7 V, and the capacitor charging voltage 3 may be 0.7 V or more. The time 8 during which the capacitor discharges may be determined by the second resistor 252 and the capacitor 253 and the discharge time 8 may be determined by the minimum turn-on time of the impact switch 240, Is equal to or smaller than the time corresponding to the pulse width (7) of the signal. This is because, if the discharge time 8 is not less than the pulse width 7 of the impact signal, the start time of the ignition trigger signal 4 may be delayed or it may not generate a valid ignition trigger signal 4 .

The transistor 254 generates an excitation trigger signal 4 that extends the pulse width 7 of the impulse signal by the time the supply of the capacitor charge voltage 3 is cut off. That is, while the capacitor charging voltage 3 is supplied to the base end of the transistor 254, the transistor 254 is turned on to generate the excitation trigger signal 4 can not do. At this time, the collector voltage of the transistor 254 becomes 0 v. However, when the supply of the capacitor charging voltage 3 to the base end of the transistor 254 is interrupted, the transistor 254 is turned off to generate the trigger signal 4. At this time, the collector short-circuit voltage of the transistor 254 becomes the voltage of the discharge charger 1.

Here, the ignition trigger signal 4 has a role of turning on the ignition circuit MOSFET 261 in the detonating circuit 260 with the pulse width extended signal from the impact signal 2 . The pulse width 9 of the excitation trigger signal means the time when the capacitor 253 is charged to the voltage of 0.7 v and can be determined by the first resistor 251 and the capacitor 253. However, when the value of the capacitor 253 is increased to expand the pulse width 7 of the impact signal to generate the trigger signal 4, the discharge time 8 becomes longer and the pulse width of the trigger signal (9) can be reduced. This is because the discharge time 8 is determined by the second resistor 252 and the capacitor 253. Therefore, in order to extend the pulse width 7 of the impact signal, the value of the first resistor 251 can be largely selected. In order to adjust the pulse width of the impact signal, the first resistor 251 is a variable resistor .

Referring to FIG. 8, the aerodynamic energy 5 is charged into the aerodynamic capacitor 262 with a time lag from the power source 1 of the guide discharge charger 1 as the aerodynamic force source 1 is applied. When the warhead is in collision with the target in the state where the aerodynamic energy 5 is charged, when the impact switch 240 is turned on to generate the impact signal 2, the impact sensing circuit 250 operates do. That is, when the contact terminal of the impact switch 240 is short-circuited, the capacitor charging voltage 3 charged in the capacitor 253 is discharged to 0.7 V or less through the second resistor 252 and the impact switch 240, The transistor 254 is turned off. Thereafter, when the target collision is completed, the contact of the impact switch 240 is opened, and the capacitor 253 is again charged with the aeronautical energy 5. The charging time may vary depending on the value of the first resistor 251 and the value of the capacitor 253 and the capacitor 253 may be charged to 0.7 v or less immediately after the capacitor 253 is discharged to 0.7 v or less. The time until the voltage is charged to the above voltage can be the pulse width 9 of the trigger signal. That is, even if the short circuit time of the impact switch 240 is short by several microseconds when the missile collides with the target, the magnitude of the value of the first resistor 251 and the capacitor 253 is adjusted to adjust the pulse width 9 of the ignition trigger signal. Can be adjusted. Thus, according to the present invention, the ignition trigger signal 4 having a pulse width of several tens usec or more is stably supplied to the gate terminal of the igniter circuit MOSFET 261 in the detonator circuit 260, 5 to the awakening tube 300.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, an embodiment of a lock releasing circuit of a safety load device for a lead-in fuel can according to the present invention will be described in detail with reference to the accompanying drawings.

FIG. 9 is a detailed circuit diagram showing a lock releasing circuit in the safing device for a lead-in-purpose car according to the present invention. FIG. 10 is a circuit diagram of a locking device driving power source This diagram shows the change.

Referring to FIG. 9, the lock releasing circuit 270 of the safety fuse for lead charger for a toddler can apply or shut off the poWer charger power source 1 to the lock device 110. More specifically, the lock release circuit 270 may include a first transistor 271, a second transistor 272, and a MOSFET 273.

The first transistor 271 supplies a voltage to the base end of the second transistor 272 when the charging switch 220 is turned off after the discharge current source 1 is applied, The voltage is cut off at the base end of the second transistor 272 when the charging switch 220 is turned on after the discharge current source 1 is applied. Here, the recharging switch 220 may be turned on by the safety device 100 that senses the firing condition of the missile or the firing environment. That is, the recharging switch 220 can be turned-on or turned-on depending on the firing condition of the missile and the firing environment.

The second transistor 272 supplies a voltage to the gate terminal of the MOSFET 273 when the voltage is supplied to the base end of the second transistor 272, When the voltage is cut off, the gate of the MOSFET 273 is cut off.

The MOSFET 273 applies the driving force source 1, i.e., the lock driving power supply 6, to the locking device 110 when the voltage is supplied to the gate terminal of the MOSFET 273, When the voltage is cut off at the gate terminal of the locking device driving power source (273), the locking device (110) cuts off the driving force source power source (1), i.e., the locking device driving power source (6). More specifically, until the charging switch 220 is turned on after the charging device 1 is applied, the MOSFET 273 supplies the locking device 110 with the driving force source 1 May be applied to release the locking device 110. However, at the same time that the charging switch 220 is turned on, the MOSFET 273 can automatically shut off the poWer charger power source 1 applied to the locking device 110.

On the other hand, the lock release circuit 270 may include a first protection circuit 274 mounted on the gate terminal of the P-channel MOSFET 273 to protect the gate terminal of the MOSFET 273. More specifically, the first protection circuit 274 may include a capacitor 276 and a diode 277.

In addition, the lock release circuit 270 may include a second protection circuit 275 mounted on the drain terminal of the P-channel MOSFET to prevent damage to the MOSFET. The second protection circuit 275 prevents damage to the P-channel MOSFET 273 from counter electromotive force generated when the missile power source 1 is cut off. More specifically, the second protection circuit 275 may include a resistor 278 and a diode 279.

Referring to FIG. 10, when the missile charger 1 is applied to the fuse safety deposit device 0 before the missile is fired, the lock release circuit 270 is connected to the lock device 110, for example, the solenoid valve assembly 111 ), That is, the locking device driving power source 6 is applied. Accordingly, the locking device 110 is released and the safety device 120 can be operated. When the ignition charger is fired and the mechanical charging is completed, that is, when the charging switch circuit 220 is short-circuited and the malfunctioning circuit part 200 is switched to the charging state, the lock releasing circuit 270 turns on the lead- The locking device driving power source 6 is cut off to reduce the consumption amount of the driving force source 1.

Hereinafter, the operation principle of the lock releasing circuit 270 of the safing device for the lead-in fuel for a touring car according to the present invention will be described by way of example.

First, before the guided missile is fired, the fuse safety loading apparatus 0 is in a non-spooling state, that is, the charging switch 220 is in a turn-off state. The first transistor 271 is then turned off when the missile charger 1 is applied to the safety device 220 for shooting the missile and the second transistor 272 ) Is turned on. When the second transistor 272 is turned on, a reverse voltage is applied to the gate-source terminal of the P-channel MOSFET 273 so that the MOSFET 273 is turned on . This causes the locking device drive power source 6 to be applied to the locking device 110 so that the solenoid pins of the locking device 110, for example the solenoid valve assembly 111, The safety device 120 is operated.

After the guided missile is fired, the safety device 120 starts to detect the guided vehicle firing environment (retrace force and acceleration magnitude). When the missile is out of the safe distance, the safety device 120 turns on the recharging switch 220. When the charging switch 220 is turned on, the first transistor 271 is turned on and the second transistor 272 is turned off. Turn-off state. When the second transistor 272 is turned off, the P-channel MOSFET 273 is also turned off so that the lock device driving power source (not shown) applied to the lock device 110 6) The car is broken. Accordingly, the power of the lock device 110, for example, the solenoid valve assembly 111, which can consume a large amount of energy, can be cut off, and the consumption amount of the missile charger 1 during the missile flying can be reduced.

0: Safe loading device for new gun for missile
1: the missile power source 2: the impact signal
3: Capacitor charging / discharging signal (capacitor charging voltage)
4: Activation trigger signal
5: Aperture Capacitor Charge Voltage (Aperture Energy)
6: Lock drive power source 7: Pulse width of impact signal
8: Discharge time of the capacitor 9: Pulse width of the excitation trigger signal
100: Safety device
110: Locking device 111: Solenoid valve assembly
120: Safety device 121: Primary safety device
122: Secondary safety device
200: an igniter circuit part 210: a power filter
220: recharge switch 230: explosion energy charging circuit
240: Shock switch
250: shock detection circuit 251: first resistance
252: second resistor 253: capacitor
254: transistor
260: Explosion circuit 261: Explosion circuit MOSFET
262: Aperture Capacitor
270: lock release circuit 271: first transistor
272: second transistor 273: MOSFET
274: first protection circuit 275: second protection circuit
276: Capacitor (for gate protection) 277: Diode (for gate protection)
278: Resistor 279: Diode (for MOSFET protection)
300: Explosive tube 400: Explosion series part

Claims (12)

1. A shock detection circuit for a safing device for a lead-in ballast for a missile,
A first resistor used to charge a capacitor;
A second resistor used to discharge the capacitor;
A capacitor charging voltage is supplied to the base end of the transistor by charging the voltage when the power source is applied and discharging the capacitor charging voltage when an impact signal is inputted in case of a target collision with the touring charger, A capacitor that cuts off the charging voltage supply; And
A transistor for generating an excitation trigger signal that extends the pulse width of the impulse signal by a time when the supply of the capacitor charge voltage is cut off and transmits an excitation energy to the detonation circuit;
And a shock detection circuit for a safety load device for a new missile.
The method according to claim 1,
Wherein the discharge time of the capacitor is less than the minimum turn-on time of the impact switch.
1. A lock releasing circuit for a safing device for a lead-in fuel for a missile,
When the charging switch is turned off after the power is applied, a voltage is supplied to the base end of the second transistor, and when the charging switch is turned on after the power is applied A first transistor for blocking the voltage at a base end of the second transistor;
A gate terminal of the MOSFET is supplied with a voltage when the voltage is supplied to the base end of the second transistor and a gate terminal of the MOSFET is turned off when the voltage is cut off at the base end of the second transistor 2 transistor; And
When the voltage is supplied to the gate terminal of the MOSFET in the pre-spark discharge state of the missile propulsion, a driving voltage is applied to the solenoid valve assembly to release the lock device, and the voltage is shut off at the gate terminal of the MOSFET after the missile is fired A MOSFET which cuts off a driving voltage applied to the solenoid valve assembly to cut off the power applied to the locking device to reduce power consumption during flight;
Wherein the lock releasing circuit of the safing device for the missile fuse for a missile is provided.
The method of claim 3,
A first protection circuit mounted on a gate terminal of the MOSFET and protecting the gate terminal of the MOSFET; Wherein the lock releasing circuit of the safety load device for a firing cannon is further provided.
The method of claim 3,
A second protection circuit mounted on a drain terminal of the MOSFET to prevent damage to the MOSFET; Wherein the lock releasing circuit of the safety load device for a firing cannon for a missile is provided.
In an ignition circuit portion of a safety device for a new pipe for a missile gun,
A power filter to remove noise from the power supply;
A charging switch which is turned on by the safety device and applies the power to the explosion energy charging circuit;
An ignition energy charging circuit for charging the ignition capacitor in the ignition circuit when the power is applied by the charging switch;
An impact switch for generating an impact signal;
The shock detection circuit of claim 1, wherein the shock detection circuit receives the shock signal and generates an ignition trigger signal that extends the pulse width of the shock signal.
An ignition circuit for receiving the ignition trigger signal and transmitting the ignition energy charged in the ignition capacitor to the ignition tube; And
The lock release circuit of claim 3, wherein the lock release device applies or cuts off the power supply;
A malfunctioning circuit part of a safe loading device for a missile gun including a missile. delete In an ignition circuit portion of a safety device for a new pipe for a missile gun,
A power filter to remove noise from the power supply;
A charging switch which is turned on by the safety device and applies the power to the explosion energy charging circuit;
An ignition energy charging circuit for charging the ignition capacitor in the ignition circuit when the power is applied by the charging switch;
An impact switch for generating an impact signal;
An explosion circuit for receiving the impulse signal and delivering the aeronautical energy charged in the aeronautic capacitor to the explosion pipe; And
The lock release circuit according to any one of claims 3 to 5, wherein the lock release device applies or cuts off the power supply;
A malfunctioning circuit part of a safe loading device for a missile gun including a missile.
A safety device for a safety device for a safety device for a lead-in fuel for a missile gun using the lock releasing circuit according to any one of claims 3 to 5,
A locking device that receives the power from the lock release circuit and operates an internal safety device; And
A safing device for turning on the charging switch of the detonating circuit part and aligning the detonating part when the firing condition of the guided car is sensed and the firing condition is satisfied;
Safety devices for safe loading and unloading equipment for guided missiles, including.
A safety load device for a new gun for a guided vehicle using the ignition circuit of claim 6,
Wherein when the power is supplied from the lock releasing circuit and the firing condition of the missile is sensed and the firing condition is satisfied, the charging switch of the firing circuit portion is turned on and the explosion fringing portion is aligned, A safety device for switching the circuit part into a charged state;
An explosion pipe for detecting the explosion energy to detonate the explosion series portion; And
And an explosion-proof portion for detonating the warhead by the ignition of the explosion-proof pipe,
Wherein the ignition circuit unit transmits the ignition energy to the ignition tube when the missile collides with the target in the loaded state.
A safety load device for a new gun for a guided vehicle using the ignition circuit of claim 6,
A safing unit for turning on the charging switch of the detonating circuit unit and aligning the detonating unit so as to switch the detonating circuit unit into a charged state when the firing condition of the missile is detected and the firing condition is satisfied;
An ignition circuit unit that transmits the ignition energy to the ignition tube when the missile collides with the target in the charged state;
An explosion pipe for detecting the explosion energy to detonate the explosion series portion; And
An explosion-based part for detonating the warhead by the ignition of the detonating tube;
A safety device for a fuse for a missile.
A safety device for a safety device for a lead-in fuel using the safety device of claim 9,
The safety device receives the power from the lock release circuit and senses the firing condition of the missile, and when the firing condition is satisfied, the safety device turns on the charging switch of the ignition circuit section, An ignition circuit unit for transmitting an ignition energy to the ignition tube when the ignition charger collides with the target in the charged state in which the ignition circuit unit is arranged to be aligned;
An explosion pipe for detecting the explosion energy to detonate the explosion series portion; And
An explosion-based part for detonating the warhead by the ignition of the detonating tube;
A safety device for a fuse for a missile.

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