KR102618577B1 - Ejection apparatus provided in guided missile and ejection system having the same - Google Patents

Abstract

These embodiments are mounted inside the launch tube and the launch tube, and are fixed to the inside of the guided vehicle and the guided vehicle ejected from the launch tube to hit the target, and when the guided vehicle is ejected, the thermal cell is used as the driving wing of the guided vehicle is deployed. A guided vehicle ejection system including a detonator for detonating is provided.

Description

A detonator provided in a guided aircraft 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 injection system including the same. In particular, it relates to a detonator provided in a guided vehicle and an injection system including the same to deploy the folding drive wings of the guided vehicle through detonation of a thermocell. It's about.

The content described in this section simply provides background information for this embodiment and does not constitute prior art.

In the case of certain guided weapons, there are cases where a previously developed unguided missile is improved into a guided weapon by additionally attaching guided electronic devices and driving devices. In this case, it must be possible to detonate the thermocell without a connection line connecting it to a separate fire control device. Here, the thermocell refers to a battery for operating an inductive electronic device or driving device.

Conventionally, a method is used to detonate a thermocell by using a pestle to strike the detonator of the thermocell when an impact occurs. In this case, when a launch impact occurs, the pestle moves and strikes the detonator of the thermocell. The design may change depending on the amount of launch impulse. 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 mixing and combustion amount of the propulsion engine. In addition, the pestle must accurately hit the detonating part of the thermocell, and the thermocell must not be detonated in cases other than firing shock (e.g., vibration, environmental test shock, etc.). Therefore, in order to satisfy these conditions, there is a problem that each bullet must be redesigned according to the ammunition.

The main purpose of the embodiments of the present invention is to wirelessly detonate a thermocell using wings deployed during ejection of a guided aircraft, excluding the use of a ball.

Other unspecified objects of the present invention can be additionally considered within the scope that can be easily inferred from the following detailed description and its effects.

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

Preferably, the detonator includes a thermocell that supplies power to the guided vehicle after the guided vehicle is ejected from the launch tube; and a detonator that detonates the thermocell, wherein the thermocell and the detonator are connected to each other so that the detonator detonates the thermocell.

Preferably, the detonator includes a switch that is partially in contact with the driving blade and is turned on or off by the operation of the driving blade; an ignition control unit that controls the thermocell to ignite in order to detonate the thermocell according to the operation of the switch; an elastic assembly that connects the switch and the ignition control unit and helps turn the switch on or off; and a detonator housing surrounding the switch, the ignition control unit, and the elastic assembly to be located inside.

Preferably, the detonator is blocked in a state where the driving wing is turning on the switch before the guided aircraft is ejected from the launch tube, and when the guided aircraft is ejected from the launch tube, the driving wing is unfolded. The switch is turned off as the temperature decreases.

Preferably, the detonator further includes an ignition signal unit connected to the ignition control unit to transmit an ignition signal to the thermocell, and the ignition signal unit ignites the thermocell by the ignition signal when the switch is turned off. Preferably, the ignition signal generated by the ignition control unit is transmitted to the thermocell.

Preferably, the detonator further includes a fastening part fixed to the detonation housing and fastened to the inside of the guided aircraft, and the fastening part is characterized in that it is fixed to the inside of the guided aircraft by a fastening method through a screw.

Preferably, the elastic assembly includes: an elastic portion that moves up or down by the operation of the driving wing to turn the switch on or off; and an elastic housing provided with the elastic unit on the inside 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 drive blade is located. Do it as

Preferably, the detonator further includes a pin assembled to penetrate the elastic portion and the vertical direction of the switch, and the elastic portion moves up or down along the pin to turn the switch on or off. Do it as

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 prevent the switch from being turned off during assembly or inspection to control movement of the switch. It is characterized by:

Preferably, the ignition control unit includes a timing setting unit that matches the switch On or Off timing between the plurality of detonators provided in the guided aircraft; And it further includes an error checker that checks the operation of the switch of the plurality of detonators.

According to another embodiment of the present invention, the present invention provides a detonator provided within a guided vehicle, comprising: a thermocell for supplying power to the guided vehicle after the guided vehicle is ejected from the launch tube; and a detonator attached to the thermocell to detonate the thermocell.

Preferably, the detonator is connected to the driving wing of the guided aircraft, and includes a switch turned on or off by the operation of the driving wing; an ignition control unit that controls the thermocell to ignite in order to detonate the thermocell according to the operation of the switch; an elastic assembly that connects the switch and the ignition control unit and helps turn the switch on or off; and a detonator housing surrounding the switch, the ignition control unit, and the elastic assembly to be located inside.

Preferably, the detonator is blocked in a state where the driving wing is turning on the switch before the guided aircraft is ejected from the launch tube, and when the guided aircraft is ejected from the launch tube, the driving wing is unfolded. When the switch is turned off, the detonator further includes a thermocell ignition signal unit connected to the ignition control unit to transmit an ignition signal to the thermocell, and when the switch is turned off, the thermocell ignition signal unit is connected to the ignition control unit. It is characterized in that it receives the ignition signal generated from and ignites the thermocell by the ignition signal.

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

According to embodiments of the present invention, the present invention has the effect of blocking the thermal battery detonation at the source by using a latch when storing ammunition.

According to embodiments of the present invention, the present invention enables natural thermocouple detonation using wings that unfold during bullet ejection without creating a separate firing procedure, and has the effect of increasing reliability by utilizing a thermocell ignition circuit. there is.

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

Figure 1 is a diagram showing a guided aircraft ejection system according to an embodiment of the present invention.
Figure 2 is a diagram showing a detonator of a guided aircraft ejection system according to an embodiment of the present invention.
3 to 6 are diagrams showing the detonator of the detonator of the guided aircraft ejection system according to an embodiment of the present invention.
Figures 7 to 9 are diagrams for explaining the detonation of the detonator as the driving wings of the guided aircraft are deployed according to an embodiment of the present invention.

Hereinafter, embodiments of the present invention will be described in detail with reference to the attached drawings. The advantages and features of the present invention and methods for achieving them will become clear by referring to the embodiments described in detail below along with the accompanying drawings. However, the present invention is not limited to the embodiments disclosed below and may be implemented in various different forms. The present embodiments are merely intended to ensure that the disclosure of the present invention is complete and to provide common knowledge in the technical field to which the present invention pertains. It is provided to fully inform those who have the scope of the invention, and the present invention is only defined by the scope of the claims. Like reference numerals refer to like elements throughout the specification.

Unless otherwise defined, all terms (including technical and scientific terms) used in this specification may be used with meanings that can be commonly understood by those skilled in the art to which the present invention pertains. Additionally, terms defined in commonly used dictionaries are not interpreted ideally or excessively unless clearly specifically defined.

The terms used in this application are only used to describe specific embodiments and are not intended to limit the invention. The singular terms include plural expressions, unless the context clearly dictates otherwise. In this application, terms such as “comprise” or “have” are intended to designate the presence of features, numbers, steps, operations, components, parts, or combinations thereof described in the specification, but are not intended to indicate the presence of one or more other features. It should be understood that this does not exclude in advance the possibility of the existence or addition of elements, numbers, steps, operations, components, parts, or combinations thereof.

Terms containing ordinal numbers, such as second, first, etc., may be used to describe various components, but the components are not limited by the terms. The above terms are used only for the purpose of distinguishing one component from another. For example, the second component may be referred to as the first component without departing from the scope of the present invention, and similarly, the first component may also be referred to as the second component. The term and/or includes any of a plurality of related stated items or a combination of a plurality of related stated items.

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

Conventionally, a method was used to detonate a thermocell with a pestle using the impact generated during firing. When using this method, the detonation of the thermocell depends on the movement of the pestle, and there is a problem that a lot of know-how is required for design and production.

The injection system does not use a squib signal from the outside to detonate the thermal cell, but when the bullet is fired while separated from the outside of the bullet, it recognizes the firing situation from inside the bullet and detonates the thermal cell.

The guided aircraft ejection system (1) uses foldable wings and a small detonation circuit, so that the thermocell can be detonated by operating the detonation circuit when the foldable wing is deployed. Accordingly, the guided aircraft ejection system 1 may be designed efficiently by providing a wireless thermocell detonation method that excludes the use of a ball.

According to an embodiment of the present invention, the guided aircraft ejection system (1) is a device that improves a previously developed unguided projectile into a guided weapon by additionally attaching a guided electronic device, a driving device, etc., and has limitations in projectile size and belly wiring. Therefore, it can be applied to devices where a separate thermocell detonation signal wiring cannot be provided, but is not necessarily limited to this.

Figure 1 is a diagram showing a guided aircraft 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 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 to the inside of the guided vehicle 30, and can detonate the thermocell as the driving wings of the guided vehicle 30 are deployed when the guided vehicle 30 is ejected by an ejection signal.

The launch tube 20 is equipped with a guided vehicle 30 inside, and can eject the guided 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 the target.

According to one embodiment of the present invention, the guided vehicle 30 is a vehicle that strikes a target according to a command, and can 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 the driving wings may be deployed as the guided vehicle 30 is ejected. At this time, the guided vehicle ejection system 1 may detonate the thermal cell by turning off the switch for detonating the thermal cell as the driving wing is deployed.

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

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

In the guided vehicle ejection system 1, a type of guided vehicle 30 using a 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 unfolds, the switch 110 can be turned off. At this time, the guided vehicle ejection system 1 may be operated to detonate the thermocell when the switch 110 is turned off.

According to an embodiment of the present invention, the guided vehicle ejection system 1 can be designed with the same or similar shape and structure for various ammunition, and when storing ammunition, a latch (for example, a nut) is used to detonate the thermocell. It can be blocked at the source, and natural thermoelectric detonation can be possible by using the driving wings that unfold when the bullet is ejected, without creating a separate launch procedure. Additionally, the guided vehicle ejection system (1) can increase reliability by utilizing a thermocell ignition circuit.

Figure 2 is a diagram showing a detonator of a guided aircraft ejection system according to an embodiment of the present invention.

The detonator 10 includes a detonator 100 and a thermocell 200. The detonator 100 and the thermocell 200 are connected to each other, so that the thermocell 200 can be detonated by the detonator 100.

The detonator 100 may detonate the thermocell 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 blade 32 and can be turned on or off by the operation of the driving blade 32.

The elastic assembly 120 connects the switch 110 and the ignition control unit 130 and can help turn the switch 110 on or off.

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

The elastic housing 122 can be protected from the outside by having an elastic portion 124 on the inside.

The elastic portion 124 can 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 portion 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 of the center of the drive wing 32.

The ignition control unit 130 may control the thermocell 200 to ignite in order to detonate the thermocell 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 aircraft 30.

The error inspection 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 so that they are located on the inside.

The detonator 100 is blocked from operating in a state where the drive wing 32 turns 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. ), the drive wing 32 may unfold and the switch 110 may be turned off.

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 aircraft 30.

The fastening part 160 may be fixed on the inside of the guided aircraft 30 by fastening with a screw.

The detonator 100 may further include a pin 150.

The pin 150 may be assembled to penetrate the elastic portion 124 and the switch 110 in the vertical direction.

The detonator 100 has an elastic portion 124 that can move up or down to turn the switch 110 on or off along the pin 150.

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

The nut 152 can be assembled with the pin 150 at the top of the switch 110 to control the movement of the switch 110 so that the switch 110 does not turn off during assembly or inspection.

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

The ignition signal unit 300 is connected to the ignition control unit 130 and can transmit an ignition signal to the thermocell 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 thermocell ignition circuit, but is not necessarily limited thereto.

The thermocell 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 thermocell 200 supplies power to the guided vehicle 30 after the guided vehicle 30 leaves the launch tube 20. The switch 110 of the detonator 100 is used to detonate the thermocell 200, and is turned off when the driving wing 32 is unfolded. Before the guided aircraft 30 is launched, the drive wings 32 stand by in an unfolded state. The detonator 100 is a device attached to the thermocell 200, and before the guided aircraft 30 leaves the launch tube 20, the drive wing 32 turns on the switch 110, thereby detonating the detonator 100. blocks 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 in positions facing each other, but are not necessarily limited thereto.

When a plurality of detonators 100 are provided, timing matching or operation inspection of the switch 110 can be performed through the timing setting unit and the 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 sets the first detonator 100a and the second detonator 100b. It is possible to determine whether the timing between the devices is constant and, if the timing is off, to generate a timing misalignment signal to correct it. If the timing between the first detonator 100a and the second detonator 100b is misaligned, problems may occur in the timing of ignition of the thermocell 200 due to the ignition signal generated from each detonator, and it is necessary to prevent this. You can check the timing for this. At this time, a weight may be assigned to each timing of the operation of the switch 110 occurring in each of the first detonator 100a and the second detonator 100b so that an ignition signal may be generated accordingly.

Additionally, the error inspection unit may check the operation of the switch 110 of the first detonator 100a and the second detonator 100b to ensure that there are no errors in the operation of the switch 110. For example, the error checker may determine the error state by considering the timing of the operation of each switch 110 of the first detonator 100a and the second detonator 100b, the occurrence of an ignition signal, etc., and is necessarily limited to this. It doesn't work.

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

3 to 6 are diagrams showing the detonator of the detonator of the guided aircraft ejection system according to an embodiment of the present invention.

Figure 3 is a detailed diagram of a detonator 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 located at the bottom. For example, the ignition control unit 130 may be 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 to this.

According to one embodiment of the present invention, the switch 110 may be located at the top of the elastic assembly 120. Specifically, the switch 110 is formed in a block shape at the bottom center of the empty space inside the detonator housing 140, and is formed in a block shape at the top of the elastic assembly 120 provided on both sides of the block shape formed at the bottom center. 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 detonator housing 140, and may be fixed at the inner bottom of the detonator housing 140.

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

Accordingly, the elastic assembly 120 allows the On/Off button of the switch 110 to be pressed smoothly and is fastened to the detonator housing 140 with a screw.

The elastic assembly 120 may be provided with an elastic portion 124 within the elastic housing 122, and the upper and lower centers of the elastic housing 122 are open so that the pin 150 can pass through. At this time, the open shape at the top and bottom centers 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 where other components of the detonator 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 control unit 130 may generate an ignition signal for ignition of the thermocell 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 that the switch 110 is off and generates an ignition signal. can do.

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

According to one embodiment of the present invention, the pin 150 is assembled to penetrate the upper and lower sides of the elastic assembly 120 and the switch 110, and may be fixed to the inner bottom of the detonator housing 140. Specifically, the pin 150 may provide a guide for the switch 110 and the elastic portion 124 to move 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, and 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, the state in which the switch 110 is turned on may be implemented in a state in which the elastic portion 124 is compressed by the switch 110. At this time, when the switch 110 is on, the switch 110 and the elastic portion 124 move down along the pin 150 and are compressed, and the inner bottom of the detonator housing 140 and the switch 110 are aligned. It may be in contact.

Referring to (b) of FIG. 4, the state in which the switch 110 is turned off may be implemented in a state in which the elastic portion 124 is decompressed by the switch 110. At this time, when the switch 110 is off, the switch 110 and the elastic portion 124 move upward along the pin 150 and the compression is released, and the inner bottom of the detonator housing 140 and the switch 110 It can be formed to be spaced a certain distance apart.

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

Figure 5 is a diagram showing a detonator during assembly or inspection of a guided aircraft ejection system according to an embodiment of the present invention.

When assembling or inspecting the guided vehicle ejection system 1, the switch 110 must be maintained in the On state so that the ignition signal is not transmitted to the thermocell 200. Accordingly, the guided vehicle ejection system 1 can maintain the switch 110 in the On state by further including the nut 152.

Referring to FIG. 5, in order to maintain the on state of the switch 110, a nut 152 is assembled to the pin 150 to prevent movement of the switch 110 and the elastic portion 124.

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 the switch 110 and the elastic portion ( 124) can apply pressure.

A nut 152 was used as a device to apply pressure to the switch 110 and the elastic portion 124, but it is not necessarily limited thereto.

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

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

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

The fastening hole 162 of the fastening part 160 may be formed on the inside of the guided aircraft 30 to fasten the detonation housing 140 by a screw fastening method.

Accordingly, the fastening part 160 can attach the switch 110 to the inner skin of the guided vehicle 30 and fasten it to the guided vehicle 30.

Figures 7 to 9 are diagrams for explaining the detonation of the detonator as the driving wings of the guided aircraft are deployed according to an embodiment of the present invention.

Figure 7 shows a cross-sectional view of a guided aircraft ejection system equipped with a detonator according to an embodiment of the present invention as seen from the front.

Figure 7 shows a state in which the driving blade 32 is deployed, and at this time, the switch 110 of the detonator 10 is turned off.

The guided aircraft 30 includes a driving blade axis 34, and the driving blade 32 can be deployed based on the driving blade axis 34.

Referring to FIG. 7, the thermocell 200 is shown as being provided on either 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 opposing sides of the guided vehicle 30, but it is not necessarily limited thereto, and at least one detonator 100 may be provided within the guided vehicle 30. You can.

Figure 8 is a diagram showing the shape according to the On or Off state of the switch in the guided aircraft 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, and 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, when the switch 110 of the detonator 100 is turned on, the driving wing 32 is located within the guided aircraft 30. Specifically, when the switch 110 of the detonator 100 is turned on, the guided vehicle 30 is provided in the launch tube 20, and the driving wing 32 of the guided vehicle 30 is connected to the guided vehicle 30. It is located inside and indicates a state in which pressure is applied to the switch 110 by the drive vane 32.

Accordingly, when the switch 110 of the detonator 100 is turned on, the guided vehicle 30 is mounted on the launch tube 20, and the drive wing 32 is located within the guided vehicle 30, thereby turning the switch 110 on. The elastic assembly 120 is compressed by applying pressure, and the inner bottom of the switch 110 and the detonator housing 140 may come into contact with each other.

According to one embodiment of the present invention, the switch 110 and the elastic assembly 120 are compressed when the drive wing 32 is located within the guided aircraft 30. The switch 110 may be located within the detonator housing 140 so as to contact the inner bottom of the detonator 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, when the switch 110 of the detonator 100 is turned off, the driven wing located within the guided vehicle 30 is launched as the guided vehicle 30 is launched from the launch tube 20. (32) is deployed outside the guided aircraft (30). Specifically, when the switch 110 of the detonator 100 is turned off, the guided vehicle 30 is launched out of the launch tube 20, and the driving wing 32 of the guided vehicle 30 is launched from the guided vehicle 30. It expands from the inside to the outside, indicating a state in which no pressure is applied to the switch 110.

As the guided vehicle 30 is ejected, the pressure applied to the switch 110 by the drive blade 32 gradually decreases, and through this, the switch can be in an off state.

According to one embodiment of the present invention, the thermocell 200 is connected to the detonator 100. There is a switch 110 in the detonator 100, and it does not operate when the switch 110 is turned on. When the switch 110 is turned off, the detonator 100 can operate. Accordingly, as the guided vehicle 30 is separated from the launch tube 20 and the driving wing 32 is spread, the switch 110, which was in the on state, is turned in the off state. When the switch 110 is turned off, the thermocell 200 is ignited through the ignition signal unit 300.

Figure 9 is a diagram showing a shape in which a guided aircraft equipped with a detonator according to an embodiment of the present invention is ejected from a launch tube.

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

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

Referring to (b) of FIG. 9, the guided aircraft 30 has four drive wings 32 and can be deployed in four directions.

The drive blade shaft 34 fixes one side of the drive blade 32, is located in the front of the guided vehicle 30 in the launching direction of the guided vehicle 30, and is located on the drive blade shaft 34 of the drive blade 32. On the opposite side, when the drive wing 32 is located within the guided vehicle 30, it may be provided to contact the detonator 100.

The ignition signal unit 300 may connect the ignition control unit 130 provided at the bottom of the detonator 100 and the thermocell 200.

The thermocell 200 may be installed at a certain distance from the detonator 100 and may be located at the rear end of the guided vehicle 30.

Accordingly, the driving wings 32 can be unfolded after the guided vehicle 30 is launched. The thermocell 200 operates when the switch 110 of the detonator 100 is turned off, and when the guided aircraft 30 exits the launch tube 20, the driving wing 32 unfolds and the detonator 100 Switch 110 may be turned off. After the switch 100 is turned off, the detonator 100 operates and the thermocell 200 is detonated.

Even though all the components constituting the embodiments of the present invention described above are described as being combined or operated in combination, the present invention is not necessarily limited to these embodiments. That is, as long as it is within the scope of the purpose of the present invention, all of the components may be operated by selectively combining one or more of them.

The above description is merely an illustrative explanation of the technical idea of the present invention, and various modifications, changes, and substitutions can be made by those skilled in the art without departing from the essential characteristics of the present invention. will be. Accordingly, the embodiments disclosed in the present invention and the accompanying drawings are not intended to limit the technical idea of the present invention, but are for illustrative purposes, and the scope of the technical idea of the present invention is not limited by these embodiments and the attached drawings. . The scope of protection of the present invention should be interpreted in accordance with the claims below, and all technical ideas within the equivalent scope should be construed as being included in the scope of rights of the present invention.

1: Guided vehicle ejection system
10: Detonator
100: Detonator
200: thermocell
300: Ignition signal unit
20: launch tube
30: Guided aircraft

Claims (13)

launch tube;
A guided aircraft mounted inside the launch tube and ejected from the launch tube to hit the target; and
It is fixed to the inside of the guided vehicle and includes a detonator that detonates the thermal cell as the driving wings of the guided vehicle are deployed when the guided vehicle is ejected,
The detonator includes a thermocell that supplies power to the guided vehicle after the guided vehicle is ejected from the launch tube; And a detonator that detonates the thermocell,
The detonator includes a switch that is partially in contact with the driving blade and is turned on or off by the operation of the driving blade; an ignition control unit that controls the thermocell to ignite in order to detonate the thermocell according to the operation of the switch; an elastic assembly that connects the switch and the ignition control unit and helps turn the switch on or off; and a detonation housing surrounding the switch, the ignition control unit, and the elastic assembly to be located inside. According to paragraph 1,
A guided aircraft injection system, characterized in that the thermocell and the detonator are connected to each other and the thermocell is detonated by the detonator. delete According to paragraph 2,
The detonator,
Before the guided aircraft is ejected from the launch tube, the drive wing is blocked from operating with the switch turned on,
A guided vehicle ejection system, wherein when the guided vehicle leaves the launch tube, the switch is turned off while the drive wings are spread. According to paragraph 4,
The detonator is,
It further includes an ignition signal unit connected to the ignition control unit to transmit an ignition signal to the thermocell,
The ignition signal unit transmits the ignition signal generated by the ignition control unit to the thermocell so that the thermocell is ignited by the ignition signal when the switch is turned off. According to paragraph 2,
The detonator,
Further comprising a fastening part fixed to the detonation housing and fastened to the inside of the guided aircraft,
A guided aircraft injection system, characterized in that the fastening part is fixed on the inside of the guided aircraft by a fastening method through a screw. According to paragraph 2,
The elastic assembly is,
an elastic portion that moves up or down by the operation of the driving blade to turn the switch on or off; and
It includes an elastic housing provided with the elastic portion on the inside 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 of the drive wing. In clause 7,
The detonator,
Further comprising a pin assembled to penetrate the elastic portion and the switch in a vertical direction,
A guided aircraft ejection system, characterized in that the elastic part moves up or down to turn the switch on or off along the pin. According to clause 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 turn off during assembly or inspection. According to paragraph 2,
The ignition control unit,
a timing setting unit that matches the switch On or Off timing between the plurality of detonators provided in the guided aircraft; and
A guided aircraft ejection system further comprising an error checker that checks the operation of the switch of the plurality of detonators. In the detonator provided within the guided aircraft,
A thermocell that supplies power to the guided vehicle after the guided vehicle is ejected from the launch tube; and
It includes a detonator attached to the thermocell to detonate the thermocell,
The detonator is connected to the driving wing of the guided aircraft, and a switch that is turned on or off by the operation of the driving wing; an ignition control unit that controls the thermocell to ignite in order to detonate the thermocell according to the operation of the switch; an elastic assembly that connects the switch and the ignition control unit and helps turn the switch on or off; and a detonator housing surrounding the switch, the ignition control unit, and the elastic assembly to be located inside. delete According to clause 11,
The detonator,
Before the guided vehicle is ejected from the launch tube, the operation is blocked with the drive wing turning the switch on, and when the guided aircraft leaves the launch tube, the switch is turned off as the drive wing unfolds,
The detonator further includes a thermocell ignition signal unit connected to the ignition control unit to transmit an ignition signal to the thermocell,
The thermocell ignition signal unit receives the ignition signal generated by the ignition control unit when the switch is turned off, and ignites the thermocell by the ignition signal.

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