KR20230039257A - Ejection apparatus provided in guided missile and ejection system having the same - Google Patents

Abstract

The present embodiments of the present invention provide a guided flight ejection system including: a launch tube; a guided flight vehicle mounted inside the launch tube and ejected from the launch tube to hit a target; and a detonator fixed inside the guided flight vehicle and detonating a thermal cell as a driving wing of the guided flight vehicle is deployed when the guided flight vehicle is ejected.

Description

A detonator provided in a guided flight vehicle and an ejection system including the same {Ejection apparatus provided in guided missile and ejection system having the same}

The present invention relates to a detonator provided in a guided vehicle and an ejection system including the same, and more particularly, to a detonator provided in a guided vehicle and an ejection system including the same to deploy foldable drive wings of the guided vehicle through the detonation of a thermal battery. it's about

The contents described in this part merely provide background information on the present embodiment and do not constitute prior art.

In the case of a specific guided weapon, there are cases in which a previously developed unguided missile is improved into a guided weapon by additionally attaching a guidance electronic device, a driving device, and the like. In this case, it should be possible to detonate the thermal cell without the umbilical cord, which is a connecting line to a separate launch control device. Here, the thermal battery represents a battery for operating an induction electronic device and a driving device.

Conventionally, a method of detonating a thermal cell by hitting the detonator of the thermal cell when an impact occurs using a ball is in use, and at this time, when a firing impact occurs, the method of moving the ball to hit the detonator of the thermal cell may change the design according to the amount of the firing impact. there is. In the case of different types of ammunition, the design must be changed, and even in the case of the same type of ammunition, it must be changed according to conditions such as fuel mixture and combustion amount of the propulsion engine. In addition, the ball must accurately hit the detonator of the thermal cell, and the thermal cell must not detonate in cases other than launch impact (eg, vibration, environmental test impact, etc.). Therefore, in order to satisfy these conditions, there is a problem that each redesign must be made to suit the bullet.

Embodiments of the present invention exclude the use of the ball, and the main purpose of the invention is to detonate the thermal battery wirelessly using wings that are deployed when the guided flight vehicle is ejected.

Other non-specified objects of the present invention may be additionally considered within the scope that can be easily inferred from the following detailed description and effects thereof.

According to one aspect of this embodiment, the present invention is a launch tube; a guided flight vehicle mounted inside the launch tube and ejected from the launch tube to hit a target; and a detonator fixed inside the guided vehicle and detonating a thermal cell as the drive wings of the guided vehicle are deployed when the guided vehicle is ejected.

Preferably, the detonator may include: a thermal battery for supplying power to the guided vehicle after the guided vehicle is ejected from the launch tube; and an initiator for detonating the thermal cell, wherein the thermal cell and the initiator are connected to each other so that the thermal cell is detonated by the initiator.

Preferably, the detonator part is in contact with the driving wing, and the switch is turned on or off by the operation of the driving wing; an ignition control unit controlling to ignite the thermal cell in order to detonate the thermal cell according to the operation of the switch; an elastic assembly that connects the switch and the ignition control unit and assists an On or Off operation of the switch; and a detonation housing surrounding the switch, the ignition control unit, and the elastic assembly so as to be positioned inside.

Preferably, the detonator unit is blocked from operating before the guided vehicle is ejected from the launch tube with the drive wing turning on the switch, and when the guided vehicle is separated from the launch tube, the drive wing is unfolded. It is characterized in that the switch is turned off while being turned off.

Preferably, the detonator further includes an ignition signal unit connected to the ignition control unit and transmitting an ignition signal to the thermocell, and the ignition signal unit ignites the thermocell by the ignition signal when the switch is turned off. Characterized in that the ignition signal generated by the ignition control unit is transmitted to the thermal battery as much as possible

Preferably, the detonator unit further includes a fastening portion fixed to the detonator housing and fastened to the inside of the guided vehicle, and the fastening unit is fixed to the inside of the guided vehicle by a fastening method through a screw.

Preferably, the elastic assembly includes: an elastic part that moves up or down by the operation of the driving wing to turn on or off the switch; and an elastic housing provided inside the elastic part to protect it from the outside, wherein the elastic assembly is located between the switch and the ignition control unit, and is provided on both sides of the center where the driving wings are located. to be

Preferably, the detonator further includes a pin assembled to pass through the elastic part and the switch in a vertical direction, and the elastic part moves up or down to turn on or off the switch along the pin. to be

Preferably, the detonator further includes a nut assembled to the pin, and the nut is assembled with the pin at the top of the switch to control the movement of the switch so that the switch does not operate off during assembly or inspection. It is characterized by doing.

Preferably, the ignition control unit, a timing setting unit for matching the switch On or Off timing between the plurality of the detonator provided in the guided flight vehicle; and an error checking unit configured to check an operation of the switch of the plurality of detonators.

According to another embodiment of the present invention, the present invention is a detonator provided in a guided vehicle, after the guided vehicle is ejected from a launch tube, a thermal battery for supplying power to the guided vehicle; and a detonator attached to the thermal cell to detonate the thermal cell.

Preferably, the detonator unit is connected to the driving wing of the guided flight vehicle, and the switch is turned on or off by the operation of the driving wing; an ignition control unit controlling to ignite the thermal cell in order to detonate the thermal cell according to the operation of the switch; an elastic assembly that connects the switch and the ignition control unit and assists an On or Off operation of the switch; and a detonation housing surrounding the switch, the ignition control unit, and the elastic assembly so as to be positioned inside.

Preferably, the detonator unit is blocked from operating before the guided vehicle is ejected from the launch tube with the drive wing turning on the switch, and when the guided vehicle is separated from the launch tube, the drive wing is unfolded. While the switch is turned off, the detonator further includes a thermoelectric ignition signal unit connected to the ignition control unit and transmitting an ignition signal to the thermocell, wherein the thermocouple ignition signal unit is connected to the ignition control unit when the switch is turned off. It is characterized in that the ignition signal generated in is received and the thermocouple is ignited by the ignition signal.

As described above, according to the embodiments of the present invention, the present invention has the effect of being able to design the same or similar shape and structure to various bullets.

According to the embodiments of the present invention, the present invention has an effect of blocking the source of the thermal battery detonation by utilizing the clasp when storing the fuel.

According to the embodiments of the present invention, the present invention has the effect of enabling a natural thermal battery detonation using wings that are deployed during bullet ejection without making a separate firing procedure, and increasing reliability by utilizing a thermal battery ignition circuit. there is.

Even if the effects are not explicitly mentioned here, the effects described in the following specification expected by the technical features of the present invention and their provisional effects are treated as described in the specification of the present invention.

1 is a diagram showing a guided flight vehicle ejection system according to an embodiment of the present invention.
2 is a view showing a detonator of a guided flight ejection system according to an embodiment of the present invention.
3 to 6 are views showing the detonator of the detonator of the guided flight vehicle ejection system according to an embodiment of the present invention.
7 to 9 are views for explaining the detonation of the detonator as the drive wing of the guided vehicle according to an embodiment of the present invention is deployed.

Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings. Advantages and features of the present invention, and methods for achieving them, will become clear with reference to the embodiments described below in detail in conjunction with the accompanying drawings. However, the present invention is not limited to the embodiments disclosed below and may be implemented in various different forms, only the present embodiments make the disclosure of the present invention complete, and the common knowledge in the art to which the present invention belongs It is provided to fully inform the holder of the scope of the invention, and the present invention is only defined by the scope of the claims. Like reference numbers designate like elements throughout the specification.

Unless otherwise defined, all terms (including technical and scientific terms) used in this specification may be used in a meaning commonly understood by those of ordinary skill in the art to which the present invention belongs. In addition, terms defined in commonly used dictionaries are not interpreted ideally or excessively unless explicitly specifically defined.

Terms used in this application are only used to describe specific embodiments, and are not intended to limit the present invention, and singular expressions include plural expressions unless the context clearly dictates otherwise. In this application, the terms "include" or "have" are intended to designate that there is a feature, number, step, operation, component, part, or combination thereof described in the specification, but one or more other features It should be understood that the presence or addition of numbers, steps, operations, components, parts, or combinations thereof is not precluded.

Terms including ordinal numbers such as second and first may be used to describe various components, but the components are not limited by the terms. These terms are only used for the purpose of distinguishing one component from another. For example, a second element may be termed a first element, and similarly, a first element may be termed a second element, without departing from the scope of the present invention. The terms and/or include any combination of a plurality of related recited items or any of a plurality of related recited items.

The present invention relates to a detonator provided in a guided vehicle and an ejection system including the same.

Conventionally, a method of detonating a thermal cell with a ball using an impact generated during launch was used. When using this method, the detonation of the thermal cell depends on the movement of the ball, and there is a problem that requires a lot of know-how in design and manufacture.

The injection system does not detonate the thermal battery using a squib signal from the outside, and when the bullet is fired while being separated from the outside of the bullet, the thermal battery is detonated by recognizing the firing situation inside the bullet.

In the guided aircraft ejection system 1, the thermal battery can be detonated by operating the detonation circuit when the foldable wings are deployed using foldable wings and a small detonation circuit. Accordingly, the guided flight vehicle ejection system 1 may be designed efficiently by preparing a method for detonating a wireless thermal battery excluding the use of a ball.

According to one embodiment of the present invention, the guided flight vehicle ejection system 1 is a device for improving a guided weapon by additionally attaching a guidance electronic device, a driving device, etc. to a previously developed unguided missile, and there is no limitation in bullet size and belly button wiring. Therefore, it may be applied to a device in which a thermal cell initiation signal wire cannot be separately provided, but is not necessarily limited thereto.

1 is a diagram showing a guided vehicle launch system according to an embodiment of the present invention.

Referring to FIG. 1 , the guided vehicle ejection system 1 includes a detonator 10 , a launch tube 20 and a guided vehicle 30 . The guided air vehicle ejection system 1 may omit some of the various components exemplarily shown in FIG. 1 or may additionally include other components.

The detonator 10 is fixed inside the guided vehicle 30, and when the guided vehicle 30 is ejected by an ejection signal, the thermal battery can be detonated as the driving wings of the guided vehicle 30 are deployed.

The launch tube 20 is equipped with a guided flight vehicle 30 therein, and can eject the guided flight vehicle 30 to hit a target.

The guided vehicle 30 is mounted inside the launch tube 20 and can be ejected from the launch tube 20 to hit a target.

According to one embodiment of the present invention, the guided flight vehicle 30 is a flight vehicle that strikes a target by command, and may be mounted on the launch tube 20 and launched.

In the guided vehicle ejection system 1 , when the guided vehicle 30 is launched, the guided vehicle 30 is ejected from the launch tube 20 , and driving wings may be deployed while the guided vehicle 30 is ejected. At this time, the guided flight vehicle ejection system 1 may detonate the thermal cell by turning off a switch for detonating the thermal cell while the drive wing is deployed.

According to one embodiment of the present invention, the driving wing 32 of the guided vehicle 30 may be implemented as a foldable wing, but is not necessarily limited thereto.

The guided flight ejection system 1 can lock the switch with a pin latch during inspection or assembly. At this time, the pin clasp may be implemented with the pin 150 and the nut 152, but is not necessarily limited thereto.

In the guided vehicle ejection system 1, the guided vehicle 30 of the type using the launch tube 20 is ejected from the launch tube 20 according to a normal launch procedure, and the drive wings 32 are deployed, and the drive wings 32 are As it develops, the switch 110 can be turned off. At this time, the guided flight vehicle ejection system 1 may be operated to detonate the thermal battery while the switch 110 is turned off.

According to one embodiment of the present invention, the guided flight vehicle ejection system 1 can be designed with the same or similar shape and structure to various bullets, and the detonation of the thermal battery is detonated by utilizing a clasp (for example, a nut) when the bullet is stored. It is possible to block the source, and without making a separate firing procedure, natural thermal battery detonation may be possible using the drive wing that is deployed during bullet ejection. In addition, reliability of the guided flight vehicle ejection system 1 can be improved by utilizing a thermoelectric ignition circuit.

2 is a view showing a detonator of a guided flight ejection system according to an embodiment of the present invention.

The detonator 10 includes a detonator 100 and a thermal cell 200. Since the detonator 100 and the thermal battery 200 are connected to each other, the thermal battery 200 may be detonated by the detonator 100 .

The detonator 100 may detonate the thermal cell 200 .

The detonator 100 includes a switch 110, an elastic assembly 120, an ignition control unit 130, and a detonator housing 140.

The switch 110 is partially in contact with the driving wing 32, and can be turned on or off by the operation of the driving wing 32.

The elastic assembly 120 connects the switch 110 and the ignition control unit 130, and may help the On or Off operation of the switch 110.

The elastic assembly 120 includes an elastic housing 122 and an elastic part 124 .

The elastic housing 122 may have an elastic part 124 inside to protect it from the outside.

The elastic part 124 may move up or down by the operation of the driving wing 32 to turn the switch 110 on or off.

According to one embodiment of the present invention, the elastic part 124 may be implemented as a spring, but is not necessarily limited thereto.

The elastic assembly 120 is located between the switch 110 and the ignition control unit 130, and may be provided on both sides based on the center where the driving wings 32 are located.

The ignition control unit 130 may control the thermal cell 200 to be ignited in order to detonate the thermal cell 200 according to the operation of the switch 110 .

The ignition control unit 130 may include a timing setting unit and an error checking unit.

The timing setting unit may match the switch On or Off timing between the plurality of detonators 100 provided in the guided vehicle 30 .

The error checking unit may check the switch operation of the plurality of detonators 100 .

The detonation housing 140 may be implemented to surround the switch 110, the ignition control unit 130, and the elastic assembly 120 to be located inside.

The operation of the detonator 100 is blocked with the drive wing 32 turning on the switch 110 before the guided vehicle 30 is ejected from the launch tube 20, and the guided vehicle 30 is ejected from the launch tube 20. ) In the case of separation, the switch 110 may be turned off while the driving wings 32 are unfolded.

The detonator 100 may further include a fastening part 160 .

The fastening part 160 may be fixed to the detonation housing 140 and fastened to the inside of the guided flight vehicle 30 .

The fastening part 160 may be fixed on the inside of the guided flight vehicle 30 by a fastening method through a screw.

The detonator 100 may further include a pin 150.

The pin 150 may be assembled to pass through the elastic part 124 and the switch 110 in a vertical direction.

In the detonator 100, the elastic part 124 may move up or down to turn the switch 110 on or off along the pin 150.

In addition, the detonator 100 may further include a nut 152 assembled to the pin 150.

The nut 152 can control the movement of the switch 110 by being assembled with the pin 150 at the top of the switch 110 so that the switch 110 does not operate in the off state during assembly or inspection.

The detonator 10 may further include an ignition signal unit 300 .

The ignition signal unit 300 may be connected to the ignition control unit 130 to transmit an ignition signal to the thermal battery 200 .

When the switch 110 is turned off, the ignition signal unit 300 may transmit the ignition signal generated by the ignition control unit 130 to the thermocell 200 so that the thermocell 200 is ignited by the ignition signal.

According to one embodiment of the present invention, the ignition signal unit 300 may be implemented as a thermoelectric battery ignition circuit, but is not necessarily limited thereto.

The thermal battery 200 may supply power to the guided vehicle 30 after the guided vehicle 30 is ejected from the launch tube 20 .

According to one embodiment of the present invention, the thermal battery 200 supplies power to the guided vehicle 30 after the guided vehicle 30 is separated from the launch tube 20. The switch 110 of the detonator 100 is used to detonate the thermal cell 200, and is turned off when the driving wings 32 are unfolded. Before the guided flight vehicle 30 is launched, the driving wings 32 stand by in an unfolded state. The detonator 100 is a device attached to the thermal battery 200, and before the guided flight vehicle 30 leaves the launch tube 20, the detonator 100 is in a state in which the drive wing 32 turns on the switch 110 block the operation of

Referring to FIG. 2 , the detonator 100 includes a first detonator 100a and a second detonator 100b.

The first detonator 100a and the second detonator 100b may be provided at positions facing each other, but are not necessarily limited thereto.

When a plurality of initiators 100 are provided, timing matching or operation check of the switch 110 may be performed through a timing setting unit and an error checking unit of the ignition control unit 130 .

For example, the timing setting unit collects the timing by the operation of the switch 110 of the first detonator 100a and the second detonator 100b, and the first detonator 100a and the second detonator 100b It is possible to determine whether the timing between the intervals is constant, and if the timing is out of sync, a timing discrepancy signal can be generated to correct it. If the timing between the first detonator 100a and the second detonator 100b is out of sync, a problem may occur in the timing of ignition of the thermal cell 200 by the ignition signal generated from each detonator. You can check the timing for At this time, a weight may be given to each timing due to the operation of the switch 110 occurring in each of the first detonator 100a and the second detonator 100b so that an ignition signal is generated accordingly.

In addition, the error checking unit may check the operation of the switch 110 of the first detonator 100a and the second detonator 100b so that there is no error in the operation of the switch 110 . For example, the error checking unit may determine the error state in consideration of the timing of the switch 110 operation of each of the first detonator 100a and the second detonator 100b, generation of an ignition signal, and the like, and is necessarily limited thereto. it is not going to be

The ignition control unit 130 may further include a separate data storage unit to store data used in the timing setting unit and the error checking unit to generate a table and provide it to an inspector.

3 to 6 are views showing the detonator of the detonator of the guided flight vehicle ejection system according to an embodiment of the present invention.

3 is a view showing the detonator in detail according to an embodiment of the present invention.

The detonator 100 includes a switch 110, an elastic assembly 120, an ignition control unit 130, a detonator housing 140, and a pin 150.

Referring to FIG. 3 , the detonation housing 140 may be formed in a U shape, and the ignition control unit 130 may be positioned within the lower end. For example, the ignition control unit 130 is provided within the detonation housing 140, and the switch 110, the elastic assembly 120 and the pin 150 may be provided in an empty space inside the detonation housing 140, , but is not necessarily limited thereto.

According to one embodiment of the present invention, the switch 110 may be located on top of the elastic assembly (120). Specifically, the switch 110 is formed in a block shape at the center of the lower end of the empty space inside the detonator housing 140, and formed in a block shape at the top of the elastic assembly 120 provided on both sides of the block shape formed in the center of the lower end It can be. Here, the block shape formed at the bottom center and the block shape formed at the top of the elastic assembly 120 are connected to each other to form one block.

The elastic assembly 120 may be provided between the switch 110 and the ignition control unit 130 . Specifically, the elastic assembly 120 is surrounded by the switch 110 and the detonation housing 140, and may be fixed at the inner lower end of the detonation housing 140.

According to one embodiment of the present invention, the elastic assembly 120 may be fixed at the inner lower end of the detonator housing 140 in a screw fastening manner, but is not necessarily limited thereto.

Therefore, the elastic assembly 120 allows the On/Off button of the switch 110 to be smoothly pressed, and is fastened to the detonation housing 140 with screws.

In the elastic assembly 120 , an elastic part 124 may be provided in the elastic housing 122 , and the upper and lower centers of the elastic housing 122 are open so that the pin 150 may pass therethrough. At this time, the open shape of the center of the top and bottom of the elastic housing 122 may be the same as the shape of the pin 150, but is not necessarily limited thereto.

The ignition control unit 130 may be provided in the lower end located below the empty space in which the other components of the detonation housing 140 are provided.

The ignition control unit 130 may include a small capacitor 132 and a PCB 134, but is not necessarily limited thereto.

The ignition controller 130 may generate an ignition signal for ignition of the thermal cell 200 when the switch 110 is turned off.

For example, when the switch 110 is turned off, the ignition control unit 130 increases the distance between the switch 110 and the ignition control unit 130, and through this, determines whether the switch 110 is off to generate an ignition signal. can do.

The ignition control unit 130 may be connected to the thermal cell 200 through the ignition signal unit 300 and may transmit the generated ignition signal to the thermal cell 200 through the ignition signal unit 300 .

According to one embodiment of the present invention, the pin 150 is assembled to pass through the upper and lower portions of the elastic assembly 120 and the switch 110, and may be fixed to the inner lower end of the detonation housing 140. Specifically, the pin 150 may provide a guide for moving the switch 110 and the elastic part 124 up and down.

Figure 4 is a diagram showing the On or Off state of the switch of the detonator according to an embodiment of the present invention.

Figure 4 (a) is a diagram showing the On state of the switch of the detonator according to an embodiment of the present invention, Figure 4 (b) is a diagram showing the Off state of the switch of the detonator according to an embodiment of the present invention am.

Referring to (a) of FIG. 4 , a state in which the switch 110 is On may be implemented in a state in which the elastic part 124 is compressed by the switch 110 . At this time, when the switch 110 is On, the switch 110 and the elastic part 124 come down along the pin 150 and are compressed so that the inner lower end of the detonation housing 140 and the switch 110 meet. can be reached

Referring to (b) of FIG. 4 , a state in which the switch 110 is Off may be implemented in a state in which compression of the elastic part 124 is released by the switch 110 . At this time, in the state in which the switch 110 is Off, the switch 110 and the elastic part 124 go up along the pin 150, and the inner lower end of the detonation housing 140 and the switch 110 are in a state in which compression is released. It may be formed in a state spaced apart by a certain distance.

Therefore, when the switch 110 is On, pressure is applied to the switch 110, and as the switch 110 moves downward, the elastic part 124 is compressed, and when the switch 110 is Off, the switch 110 ) The switch 110 can be moved upward due to the property that the elastic part 124 returns to its original shape when the pressure applied to it is removed.

5 is a view showing a detonation part when assembling or inspecting a guided flight vehicle ejection system according to an embodiment of the present invention.

When assembling or inspecting the guided aircraft ejection system 1, the switch 110 must be kept in an On state so that an ignition signal is not transmitted to the thermal battery 200. Accordingly, the guided flight vehicle ejection system 1 may maintain the On state of the switch 110 as it further includes the nut 152 .

Referring to FIG. 5 , movement of the switch 110 and the elastic part 124 may be prevented by assembling the nut 152 to the pin 150 to maintain the On state of the switch 110 .

According to one embodiment of the present invention, the pin 150 may form a screw-shaped groove, and the nut 152 is assembled to the pin 150 along the screw-shaped groove to form a switch 110 and an elastic part ( 124) can be applied.

Although the nut 152 was used as a device for applying pressure to the switch 110 and the elastic part 124, it is not necessarily limited thereto.

Therefore, the detonator 100 operates when the switch 110 is turned off, and during assembly/inspection, use the nut 152 to fix the switch 110 so that it does not turn off.

6 is a view showing a form in which a fastening part is further included in the detonator according to an embodiment of the present invention.

The fastening part 160 may be formed on both sides of the top of the detonator housing 140 formed in a U shape. Specifically, the fastening part 160 may be formed to fix the detonation housing 140 to the guided flight vehicle 30 in a block shape, and may include a fastening hole 162.

The fastening hole 162 of the fastening part 160 may be formed to fix the detonation housing 140 by a screw fastening method inside the guided flight vehicle 30 .

Accordingly, the fastening part 160 may allow the switch 110 to be attached to the inner skin of the guided vehicle 30 and fastened with the guided vehicle 30 .

7 to 9 are views for explaining the detonation of the detonator as the drive wing of the guided vehicle according to an embodiment of the present invention is deployed.

7 is a cross-sectional view of a guided vehicle ejection system to which a detonator according to an embodiment of the present invention is applied, viewed from the front.

7 shows a state in which the drive wing 32 is deployed, and the switch 110 of the detonator 10 at this time shows an off state.

The guided vehicle 30 includes a driving wing axis 34, and the driving wing 32 may be deployed based on the driving wing axis 34.

Referring to FIG. 7 , the thermal battery 200 is illustrated as being provided on the left or right side of the guided vehicle 30, but is not necessarily limited thereto.

According to one embodiment of the present invention, the detonator 100 is shown as being provided on two facing sides within the guided vehicle 30, but is not necessarily limited thereto, and at least one may be provided within the guided vehicle 30. can

8 is a view showing the shape according to the On or Off state of the switch in the guided flight vehicle to which the detonator according to an embodiment of the present invention is applied.

Figure 8 (a) is a diagram showing the On state of the switch of the detonator according to an embodiment of the present invention, Figure 8 (b) is a diagram showing the Off state of the switch of the detonator according to an embodiment of the present invention am.

Referring to (a) of FIG. 8 , the state in which the switch 110 of the detonator 100 is On is a state in which the driving wings 32 are located within the guided vehicle 30 . Specifically, the state in which the switch 110 of the detonator 100 is On is that the guided vehicle 30 is provided in the launch tube 20, and the driving wing 32 of the guided vehicle 30 is It is located inside and shows a state in which pressure is applied to the switch 110 by the driving wing 32.

Therefore, in the state in which the switch 110 of the detonator 100 is On, the driving wing 32 is located within the guided vehicle 30 as the guided vehicle 30 is mounted on the launch tube 20, and the switch 110 The elastic assembly 120 is compressed by applying pressure, and the inner lower end of the switch 110 and the detonation housing 140 may come into contact.

According to one embodiment of the present invention, the switch 110 and the elastic assembly 120 are compressed as the switch 110 and the elastic assembly 120 are compressed when the driving wing 32 is located in the guided flight vehicle 30. The switch 110 may be located in the detonation housing 140 so as to come into contact with the inner lower end of the detonation housing 140. Specifically, the switch 110 and the elastic assembly 120 may be located at the bottom of the empty space inside the detonation housing 140, and the drive wing ( 32) may be located.

Referring to (b) of FIG. 8, the state in which the switch 110 of the detonator 100 is off is the driving wing located inside the guided vehicle 30 as the guided vehicle 30 is launched from the launch tube 20. (32) is a state that is deployed outside the guided flight vehicle (30). Specifically, the state in which the switch 110 of the detonator 100 is Off is that the guided flight vehicle 30 is launched out of the launch tube 20 so that the driving wing 32 of the guided flight vehicle 30 moves toward the guided flight vehicle 30 It is developed from the inside to the outside to indicate a state in which no pressure is applied to the switch 110.

As the guided flight vehicle 30 is ejected, the pressure applied to the switch 110 of the driving wing 32 gradually decreases, and through this, the switch can form an off state.

According to one embodiment of the present invention, the thermal cell 200 is connected to the detonator 100. There is a switch 110 in the detonator 100, and it does not operate while the switch 110 is turned on. When the switch 110 is Off, the detonator 100 may operate. Therefore, as the guided flight vehicle 30 is separated from the launch tube 20 and the drive wings 32 are spread, the switch 110, which was in an On state, becomes an Off state. When the switch 110 is turned off, the thermal battery 200 is detonated through the ignition signal unit 300 .

9 is a view showing a shape in which a guided flight vehicle to which a detonator according to an embodiment of the present invention is applied is ejected from a launch tube.

Figure 9 (a) is a view of the guided flight vehicle to which the detonator according to an embodiment of the present invention is applied and ejected from the launch tube, Figure 9 (b) is a guided flight vehicle to which the detonator according to an embodiment of the present invention is applied is a drawing of the injection completed in the launch tube.

Referring to (a) of FIG. 9 , the driving wings 32 of the guided vehicle 30 may be deployed in a clockwise direction based on the launch direction of the guided vehicle 30, but are not necessarily limited thereto.

Referring to (b) of FIG. 9 , four driving wings 32 of the guided vehicle 30 may be provided and deployed in four directions.

The driving wing shaft 34 fixes one side of the driving wing 32, is located in the front of the guided vehicle 30 in the launch direction of the guided vehicle 30, When the driving wing 32 is located in the guided flight vehicle 30 on the opposite side, it may be provided so as to come into contact with the detonator 100.

The ignition signal unit 300 may connect the ignition control unit 130 provided at the lower end of the detonator 100 and the thermal battery 200.

The thermal battery 200 may be provided at a location spaced apart from the detonator 100 by a predetermined distance, and may be located at the rear end of the guided vehicle 30.

Therefore, after the guided vehicle 30 is launched, the driving wings 32 can be unfolded. The thermal battery 200 operates when the switch 110 of the detonator 100 is turned off, and when the guided flight vehicle 30 exits the launch tube 20, the drive wings 32 are unfolded, and the Switch 110 may be off. After the switch 100 is turned off, the detonator 100 operates and the thermal cell 200 is detonated.

Even though all components constituting the embodiments of the present invention described above are described as being combined or operated as one, the present invention is not necessarily limited to these embodiments. That is, within the scope of the object of the present invention, all of the components may be selectively combined with one or more to operate.

The above description is merely an example of the technical idea of the present invention, and those skilled in the art can make various modifications, changes, and substitutions without departing from the essential characteristics of the present invention. will be. Therefore, the embodiments disclosed in the present invention and the accompanying drawings are not intended to limit the technical idea of the present invention, but to explain, and the scope of the technical idea of the present invention is not limited by these embodiments and the accompanying drawings. . The protection scope of the present invention should be construed according to the following claims, and all technical ideas within the equivalent range should be construed as being included in the scope of the present invention.

1: Guided flight ejection system
10: Detonator
100: detonator
200: thermal cell
300: ignition signal unit
20: launch tube
30: guided flight vehicle

Claims (13)

launch tube;
a guided flight vehicle mounted inside the launch tube and ejected from the launch tube to hit a target; and
A guided vehicle ejection system comprising a detonator fixed inside the guided vehicle and detonating a thermal battery as the drive wings of the guided vehicle are deployed when the guided vehicle is ejected. According to claim 1,
The detonator,
a thermal battery for supplying electric power to the guided vehicle after the guided vehicle is ejected from the launch tube; and
Including an initiator for detonating the thermal cell,
The guided flight ejection system, characterized in that the thermal battery and the detonator are connected to each other so that the thermal battery is detonated by the detonator. According to claim 2,
The detonator,
a switch that is partially in contact with the driving wing and turned on or off by the operation of the driving wing;
an ignition control unit controlling to ignite the thermal cell in order to detonate the thermal cell according to the operation of the switch;
an elastic assembly that connects the switch and the ignition control unit and assists an On or Off operation of the switch; and
A guided aircraft ejection system comprising an initiator housing surrounding the switch, the ignition control unit, and the elastic assembly so as to be located inside. According to claim 3,
The detonator,
Before the guided vehicle is ejected from the launch tube, the operation is blocked with the drive wing turning on the switch,
The guided vehicle ejection system, characterized in that the switch is turned off while the drive wings are unfolded when the guided vehicle is separated from the launch tube. According to claim 4,
The detonator,
Further comprising an ignition signal unit connected to the ignition control unit and transmitting an ignition signal to the thermal battery,
The ignition signal unit transmits the ignition signal generated by the ignition control unit to the thermocell so that the thermoelectric battery is ignited by the ignition signal when the switch is turned off. According to claim 3,
The detonator,
Further comprising a fastening portion fixed to the detonation housing and fastened to the inside of the guided vehicle,
The fastening unit is guided air vehicle ejection system, characterized in that fixed by a fastening method through a screw on the inside of the guided vehicle. According to claim 3,
The elastic assembly,
an elastic part that turns on or off the switch by moving up or down by the operation of the driving wing; and
An elastic housing provided inside the elastic part to protect it from the outside,
The elastic assembly is located between the switch and the ignition control unit, and is provided on both sides of the center where the driving wings are located. According to claim 7,
The detonator,
Further comprising a pin assembled to pass through the elastic portion and the upper and lower directions of the switch,
The guided flight ejection system, characterized in that the elastic part moves up or down to turn on or off the switch along the pin. According to claim 8,
The detonator,
Further comprising a nut assembled to the pin,
The nut is assembled with the pin at the top of the switch to control the movement of the switch so that the switch does not operate off during assembly or inspection. According to claim 3,
The ignition control unit,
A timing setting unit for matching the switch On or Off timing between the plurality of detonators provided in the guided flight vehicle; and
The guided flight ejection system further comprises an error checking unit for checking the operation of the switch of the plurality of detonators. In the detonator provided in the guided flight vehicle,
After the guided vehicle is ejected from the launch tube, a thermal battery that supplies power to the guided vehicle; and
A detonator comprising a detonator attached to the thermal cell to detonate the thermal cell. According to claim 11,
The detonator,
a switch connected to the drive wing of the guided vehicle and turned on or off by the operation of the drive wing;
an ignition control unit controlling to ignite the thermal cell in order to detonate the thermal cell according to the operation of the switch;
an elastic assembly that connects the switch and the ignition control unit and assists an On or Off operation of the switch; and
A detonator comprising a detonation housing surrounding the switch, the ignition control unit, and the elastic assembly so as to be located inside. According to claim 12,
The detonator,
Before the guided vehicle is ejected from the launch tube, the drive wing is blocked in a state where the switch is turned on, and when the guided vehicle is separated from the launch tube, the switch is turned off while the drive wing is unfolded,
The detonator further includes a thermoelectric battery ignition signal unit that is connected to the ignition control unit and transmits an ignition signal to the thermal battery,
The detonator, characterized in that, when the switch is turned off, the thermoelectric battery ignition signal unit receives the ignition signal generated by the ignition control unit and ignites the thermal battery by the ignition signal.

Images