KR102741526B1 - Guided weapon that detonates a thermo cell using a piezoelectric element and a method for induction thereof - Google Patents

Abstract

The present embodiments propose a guided weapon, which is equipped in a launcher and is launched toward a target, including a forward guidance assembly assembled at the front of the guided weapon and which generates current by drag when launched toward the target to guide the weapon to detect or track the target; and a propulsion unit assembled at the rear of the forward guidance assembly and which leaves the launcher by a detonation signal.

Description

Guided weapon that detonates a thermo cell using a piezoelectric element and a method for induction thereof {Guided weapon that detonates a thermo cell using a piezoelectric element and a method for induction thereof}

The present invention relates to a guided weapon and a guidance method therefor, and more particularly, to a guided weapon that detonates a thermal battery using a piezoelectric element and a guidance method therefor.

The material described in this section merely provides background information for the present embodiment and does not constitute prior art.

The Bigung is a guided weapon system that applies a thermal battery detonation signal through a device called a belly connector connected between the Smart Launcher and the guided rocket. The detonated thermal battery supplies power to the guided rocket and receives a detonation signal through a separate propulsion engine detonation line to combust the guided rocket's propulsion engine, allowing launch. The launched guided rocket hits the target through a mid-course guidance process using an inertial measurement device and a terminal homing guidance process using a seeker based on target information previously input through the belly connector. On the other hand, an unguided weapon is launched by receiving only the propulsion engine detonation signal from the dumb launcher and flies along a predetermined trajectory and trajectory to hit the target. Unguided weapons have the problem of low accuracy and are greatly affected by the pilot's ability.

Traditionally, it was used for shells, and a thermal cell activation device with an impact ignition was used. Unguided weapons using a dumb launcher only have a connecting line that detonates the propulsion system, so when a detonation signal is given to the propulsion system, the propulsion system detonates and launches it. Since it flies only along a set trajectory, there is a problem that the pilot's accurate aiming and the ability to aim at the target within the trajectory are required to accurately hit the target.

The main purpose of the embodiments of the present invention is to replace the forward warhead/fuse of an unguided weapon with a guided weapon guidance control unit to convert it into a guided weapon, thereby increasing the hit rate, and at the same time to generate power for the guidance control unit using a piezoelectric element.

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

According to one aspect of the present invention, a guided weapon is provided in a launcher and is launched toward a target, the guided weapon comprising: a forward guidance assembly assembled at the front of the guided weapon and generating current by drag when launched toward the target to guide the weapon to detect or track the target; and a propulsion unit assembled at the rear of the forward guidance assembly and detaching from the launcher by a detonation signal.

Preferably, the forward guidance assembly comprises: a guidance control unit that controls the guidance toward the direction in which the target is equipped by using the current generated by the resistance; and a warhead fuse unit provided at the rear end of the guidance control unit and connected to the propulsion unit.

Preferably, the guidance control unit includes: a piezoelectric element that generates current by deformation caused by external resistance after the guided weapon leaves the launcher; a seeker that searches for and selects the target and generates target information according to the target; a thermoelectric unit that receives current through the piezoelectric element to detonate and supply power; a driving unit that receives power from the thermoelectric unit and controls the weapon to fly toward the target; and an guidance control unit that receives power from the thermoelectric unit and controls the driving unit through the target information.

Preferably, the guidance control unit further includes at least two control blades connected to the driving unit and controlled by the driving unit to fly the guided weapon in a targeting direction, and the control blades are characterized in that they are deployed outwardly and controlled by the driving unit when power is supplied to the driving unit.

Preferably, the seeker transmits the generated target information to the guidance control unit, and the guidance control unit calculates the path of the guided weapon based on the target information and transmits a control command to the driving unit for controlling the control wing.

Preferably, the piezoelectric element is attached to the front step surface of the induction control unit formed in a dome shape to form a ring shape, and includes a wiring for transmitting current to the thermocouple unit, and the wiring is connected to the connector of the thermocouple unit, and is characterized in that it is formed to be attached so as to be in contact with the inner side of the dome-shaped induction control unit so as to deviate from the direction in which the optical window attached to the front step surface of the induction control unit transmits.

Preferably, the forward guidance assembly is implemented so as to be replaceable and assembled to the propulsion unit, and is characterized in that it is implemented so as to be partially exposed to the outside of the launcher.

Preferably, the guided weapon is characterized in that, as the propulsion unit detonates, the launcher is separated, and a rear wing formed at the rear of the propulsion unit is deployed, and power is supplied to the driving unit and the guidance control unit through the thermoelectric unit that is detonated by current generated as the piezoelectric element is compressed by drag, and the weapon is controlled toward the target through the control wing of the driving unit to which the power is supplied.

Preferably, the propulsion unit includes a rear wing that is deployed when the guided weapon receives a propulsion signal through the launcher and leaves the launcher, and the propulsion signal is transmitted through a detonation line connecting the launcher and the propulsion unit.

According to another embodiment of the present invention, the present invention proposes a guidance method using a guided weapon equipped in a launcher and launched toward a target, the guidance method including the steps of: launching the guided weapon toward the target by detonating a propulsion unit through a detonation line connected to the launcher; detonating a thermoelectric unit by current generated by deformation of a piezoelectric element due to resistance received by the launched guided weapon; applying power to a guidance control unit and a driving unit through the thermoelectric unit, and detecting and tracking the target; and guiding and hitting the detected and tracked target.

Preferably, the step of detonating the thermocouple unit is characterized in that the current is transmitted to the thermocouple unit through a wire attached to form a ring shape on the front step surface of the guidance control unit of the guided weapon, where the piezoelectric element is formed in a dome shape.

Preferably, the step of detecting and tracking the target is characterized in that when power is supplied to the guidance control unit, power is supplied to a seeker through the guidance control unit to search and select the target and detect and track the target through the seeker to generate target information according to the target, and when power is supplied to the drive unit, at least two control wings controlled by the drive unit are deployed to fly the guided weapon in the targeting direction.

Preferably, the step of detecting and tracking the target is characterized in that the step of transmitting the generated target information to the guidance control unit, and the step of guiding and hitting the detected and tracked target calculates the path of the guided weapon based on the target information and transmits a control command to the driving unit for controlling the control blades.

As described above, according to the embodiments of the present invention, the present invention has the effect of converting an unguided weapon launched from a dumb launcher into a guided weapon, and increasing the hit rate of hitting a target by controlling the guided weapon through a seeker.

Even if an effect is not explicitly mentioned herein, the effect and its provisional effect described in the following specification expected by the technical features of the present invention are treated as described in the specification of the present invention.

FIG. 1 is a drawing showing a guided weapon according to one embodiment of the present invention.
FIG. 2 is a drawing showing in detail a forward guidance assembly of a guided weapon according to one embodiment of the present invention.
FIGS. 3 and 4 are detailed drawings showing a forward guidance assembly of a guided weapon according to one embodiment of the present invention.
FIG. 5 is a drawing showing an operational sequence when launching a guided weapon according to one embodiment of the present invention.
Figure 6 is a flow chart showing a process of hitting a target using a guided weapon according to one embodiment of the present invention.
FIG. 7 is a drawing showing target hitting using a guided weapon according to one embodiment of the present invention.

Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings. The advantages and features of the present invention, and the methods for achieving them, will become apparent with reference to the embodiments described in detail below together with the accompanying drawings. However, the present invention is not limited to the embodiments disclosed below, but may be implemented in various different forms, and the embodiments are provided only to make the disclosure of the present invention complete and to fully inform those skilled in the art of the scope of the invention, and the present invention is defined only 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 a meaning that can be commonly understood by a person of ordinary skill in the art to which the present invention belongs. In addition, terms defined in commonly used dictionaries shall not be ideally or excessively interpreted unless explicitly specifically defined.

The terminology used in this application is only used to describe particular embodiments and is not intended to limit the present invention. The singular expression includes plural expression unless the context clearly indicates otherwise. In this application, it should be understood that the terms "comprises" or "has" and the like are intended to specify that a feature, number, step, operation, component, part or combination thereof described in the specification is present, but do not exclude in advance the possibility of the presence or addition of one or more other features, numbers, steps, operations, components, parts or combinations thereof.

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

The present invention relates to a guided weapon that supplies power to the projectile by detonating a thermal battery with a current generated by a piezoelectric element after ignition of a propulsion system and projectile departure.

FIG. 1 is a drawing showing a guided weapon according to one embodiment of the present invention.

Referring to Fig. 1, the guided weapon (1) includes a forward guidance assembly (10) and a propulsion unit (20). The guided weapon (1) may omit some of the various components exemplarily illustrated in Fig. 1 or may additionally include other components.

The guided weapon (1) is installed in the launcher (2) and can be launched toward a target.

The forward guidance assembly (10) is assembled at the front of the guided weapon (1), and when fired toward a target, current is generated by the drag force, which can guide the weapon to detect or track the target.

The forward guidance assembly (10) includes a guidance control unit (100) and a warhead fuse unit (200).

The induction control unit (100) can be controlled to guide toward the direction in which the target is equipped by using the current generated by the resistance.

The induction control unit (100) includes a piezoelectric element (110), a probe (120), a thermoelectric unit (130), a driving unit (140), and an induction control unit (150).

The piezoelectric element (110) can generate electric current by deformation caused by external resistance after the guided weapon (1) leaves the launcher (2).

The piezoelectric element (110) is attached to form a ring shape on the front step surface of the induction control unit (100) formed in a dome shape, and may include a wire (112) for transmitting current to the thermal unit (130).

The wiring (112) is connected to the connector of the thermal unit (130) and can be formed to be attached to the inside of the dome-shaped induction control unit (100) so as to be out of the direction in which the optical window (102) attached to the front step surface of the induction control unit (100) transmits.

The explorer (120) can search for and select a target and generate target information according to the target.

The explorer (120) can transmit the generated target information to the guidance control unit (150).

The thermocouple part (130) can receive current through the piezoelectric element (110) and detonate it to supply power.

The driving unit (140) receives power from the thermal battery unit (130) and can be controlled to fly toward a target.

The induction control unit (150) receives power from the thermal battery unit (130) and can control the driving unit (140) through target information.

The guidance control unit (150) can calculate the path of the guided weapon (1) based on target information and transmit a control command to the driving unit (140) to control the control wing (160).

The induction control unit (100) further includes a control vane (160).

The control wing (160) is connected to the driving unit (140) and can be controlled by the driving unit (140) to fly the guided weapon (1) in a target direction, and at least two of them can be formed to be connected to the driving unit (140).

The control wing (160) can be deployed outwardly and controlled by the driving unit (140) when power is supplied to the driving unit (140).

The warhead fuse (200) is provided at the rear end of the guidance control unit (100) and can be connected to the propulsion unit (20).

The forward guidance assembly (10) is implemented so that it can be replaced and assembled in the propulsion unit (20), and can be implemented so that a portion of it is exposed to the outside of the launcher (2).

The propulsion unit (20) is assembled at the rear of the forward guidance assembly (10) and can provide propulsion force to separate the launcher by a detonation signal.

The propulsion unit (20) may include a rear wing (22) that is deployed when the guided weapon (1) receives a propulsion signal through the launcher (2) and leaves the launcher (2). Here, the propulsion signal may be transmitted through a detonation line (24) connecting the launcher (2) and the propulsion unit (20).

The guided weapon (1) is separated from the launcher (2) as the propulsion unit (20) detonates, and the rear wing (22) formed at the rear of the propulsion unit (20) is deployed, and power is supplied to the drive unit (140) and the guidance control unit (150) through the thermal battery unit (130) that is detonated by the current generated as the piezoelectric element (110) is compressed by the drag force, and the weapon can be controlled toward the target through the control wing (160) of the drive unit (140) to which power is supplied.

The guided weapon (1) basically follows the target without performing navigation guidance using an inertial measurement device in the middle stage, so it can sufficiently track the target in the final terminal guidance stage. Therefore, there is no need to install an inertial measurement device. Here, the target indicates a gun that records various matters to be considered in gun firing. For example, the target may include, but is not necessarily limited to, elevation angle, range, and external environment.

A guidance method using a guided weapon equipped in a launcher and launched toward a target may include a step of launching the guided weapon toward the target by detonating a propulsion unit through a detonation line connected to the launcher; a step of detonating a thermal battery unit by current generated by deformation of a piezoelectric element due to resistance received by the launched guided weapon; a step of applying power to a guidance control unit and a driving unit through the thermal battery unit and detecting and tracking a target; and a step of guiding and hitting the detected and tracked target.

The step of detonating the thermocouple section can transmit current to the thermocouple section through wiring attached to form a ring shape on the front step surface of the guidance control section of the guided weapon where the piezoelectric element is formed in a dome shape.

The step of detecting and tracking a target includes: when power is supplied to the guidance control unit, power is supplied to the seeker through the guidance control unit to search and select the target, and the seeker detects and tracks the target by generating target information according to the target; and when power is supplied to the drive unit, at least two control wings controlled by the drive unit can be deployed to fly the guided weapon in the targeting direction.

The step of detecting and tracking a target can transmit the generated target information to the guidance control unit.

The step of guiding and hitting a detected and tracked target can calculate the path of the guided weapon based on target information and transmit a control command to the actuator to control the pilot wing.

FIG. 2 is a drawing showing in detail a forward guidance assembly of a guided weapon according to one embodiment of the present invention.

Conventional weapon systems consist of a warhead, a fuse, and a propulsion system, and can be implemented in an unguided manner that allows free flight with a set launch path.

In contrast, the guided weapon (1) of the present invention can be composed of a forward guidance assembly (10) and a propulsion unit (20) compared to a conventional weapon system. Here, the forward guidance assembly (10) includes a guidance control unit (100) and a warhead fuse unit (200).

According to one embodiment of the present invention, an unguided weapon can be converted into a guided weapon by replacing and assembling a forward guidance assembly (10), and can be implemented to have the same interface structure.

Referring to FIG. 2, the induction control unit (100) includes a piezoelectric element (110), a probe (120), a thermoelectric unit (130), a driving unit (140), and an induction control unit (150). The induction control unit (100) may omit some of the various components exemplarily illustrated in FIG. 2 or may additionally include other components.

The piezoelectric element (110) can generate electric current by being deformed by the drag force applied to the guided weapon (1) after the guided weapon (1) is detached. At this time, the piezoelectric element (110) can be made to operate above a certain pressure for safety.

The explorer (120) can search for and select an optimal target and provide target information to the guidance control unit (150).

By detonating the thermal battery unit (130), power can be supplied to the driving unit (140) and the induction control unit (150). At this time, the thermal battery unit (130) can be detonated by receiving current through the piezoelectric element (110).

The driving unit (140) can control the control wing (160) to fly to the target.

The guidance control unit (150) supplies power to the seeker (120) and controls the driving unit (140) using target information received from the seeker (120) to guide the guided weapon (1) to a desired target.

The induction control unit (100) further includes a control vane (160).

The control wing (160) can enable the guided weapon (1) to fly in a desired direction.

The guided weapon (1) can supply power within the guided weapon (1) by detonating the thermal battery unit (130) with the current generated by the piezoelectric element (110) after the propulsion unit (20) is ignited and separated from the launch tube (2).

The guided weapon (1) can fly to the target through the guidance/control technique of the guidance control unit based on the target information detected by the seeker after the guided weapon power is turned on. In addition, the guided weapon (1) generates current by deforming the piezoelectric element by the drag force received after the start of free flight in order to detonate the thermal battery. In addition, since the unguided weapon system freely flies along the target, there is no need for mid-term guidance using an inertial measurement device. Therefore, the guided weapon (1) of the present invention does not need to be equipped with an inertial measurement device, and instead can detect and guide the target by performing terminal homing guidance using a seeker.

FIG. 3 is a drawing showing in detail a forward guidance assembly of a guided weapon according to one embodiment of the present invention.

FIG. 3 is a drawing showing in detail a piezoelectric element part of a forward guidance assembly of a guided weapon according to one embodiment of the present invention.

Referring to FIG. 3, the piezoelectric element (110) may be implemented in a flat circular ring shape that at least partially surrounds the optical window (102), but is not necessarily limited thereto.

The forward guidance assembly (100) can have an optical window (102) and a piezoelectric element (110) assembled on the front.

The piezoelectric element (110) has a flat circular ring shape and can be attached by bonding to the front step surface of the dome structure (104). At this time, the optical window (102) can also be attached by bonding to the step surface of the dome structure.

The piezoelectric element (110) can be assembled by connecting the wiring (112) coming from the piezoelectric element (110) to the connector (132) of the thermocouple part (130). The wiring (112) can be attached to the dome so as not to cover the optical window (102).

The wiring (112) may be connected to at least one side of the piezoelectric element (110), but is not necessarily limited thereto.

FIG. 4 is a detailed drawing showing a seeker and a thermal battery section of a forward guidance assembly of a guided weapon according to one embodiment of the present invention.

Referring to Fig. 4, the probe (120) may be provided between the piezoelectric element (110) and the thermocouple unit (130). At this time, the wiring (112) connected to the piezoelectric element (110) may be attached along the inner side of the dome structure (104) and may pass through the probe (120) to be connected to the thermocouple unit (130).

The thermocouple unit (130) may include a connector (132) connected to the wiring (112) of the piezoelectric element (110) on the side where the probe (120) is provided.

The thermocouple unit (130) can receive current by being connected to the wiring (112) of the piezoelectric element (110) through the connector (132), and by using the received current to detonate, power can be supplied to the driving unit (140) and the induction control unit (150).

FIG. 5 is a drawing showing an operational sequence when launching a guided weapon according to one embodiment of the present invention.

Referring to Figure 5, the operation of the guidance control unit (100) and the interaction of the guidance control unit (100) configuration can be confirmed when launching a guided weapon.

When the propulsion unit (20) of the guided weapon (1) detonates and the guided weapon (1) leaves the launcher (2), the rear wing (22) formed in the propulsion unit (20) automatically unfolds and the piezoelectric element (110) is compressed by the drag force, which generates current and supplies current to the thermal battery unit (130) along the wiring (112).

The thermocouple part (130) can receive current through the piezoelectric element (110).

When the thermal battery unit (130) detonates, power can be supplied to the induction control unit (150) and the driving unit (140).

The induction control unit (150) can supply power to the probe (120) when power is supplied through the thermocouple unit (130).

The induction control unit (150) sends a wing unfolding command to the driving unit (140) so that the control wing (160) can unfold.

The driving unit (140) sends a feedback signal to the induction control unit (150) to determine whether the control blade (160) has been deployed. For example, the driving unit (140) may be implemented to be connected to the control blade (160), and may determine whether the control blade (160) has been deployed through a separate sensor attached to the control blade (160). For example, the driving unit (140) may measure the temperature through the sensor attached to the control blade (160) as the control blade (160) is deployed, and determine whether the control blade (160) has been deployed based on the change in temperature, or may measure the distance to objects located around the control blade (160) through the sensor attached to the control blade (160) and determine whether the control blade has been deployed based on a case where the distance is not measured or is measured to be greater than a certain distance, but is not necessarily limited thereto.

The explorer (120) can detect and track the optimal target.

The explorer (120) can transmit target information to the guidance control unit (150).

The guidance control unit (150) can calculate the optimal path of the guided weapon (1) and transmit a control command to the driving unit (140) to control the control wing (160).

Figure 6 is a flow chart showing a process of hitting a target using a guided weapon according to one embodiment of the present invention.

The target hitting process includes a step of starting the flight of the guided weapon by detonating the propulsion system (S610), a step of generating electric energy for piezoelectric element deformation (S620), a step of detonating the thermocouple (S630), a step of applying power to the guidance control unit (S640), a step of applying power to the seeker (S642), a step of detecting and tracking the target by the seeker (S644), a step of applying power to the drive unit (S650), a step of unfolding the control wings (S652), and a step of guiding/controlling the guided weapon and hitting the target (S660).

The stage (S610) where the propulsion system detonates and the guided weapon begins its flight can be launched by receiving a propulsion signal from the dumb launcher, and the rear wing of the propulsion system can be deployed.

The step (S620) of generating electric energy for piezoelectric element deformation is that the drag force received by the guided weapon when firing can deform the piezoelectric element, thereby generating electric current.

The step of detonating the thermocouple (S630) can detonate the thermocouple by using the current generated when the piezoelectric element is deformed.

The step of applying power to the induction control unit (S640) may be such that power may be applied to the induction control unit within the induction control unit.

The step of powering the explorer (S642) can have the induction control unit powering the explorer.

The step of applying power to the driving unit (S650) may apply power to the driving unit within the induction control unit.

The step of unfolding the control wings (S652) is such that the control wings can be unfolded and controlled by the driving unit.

The guided weapon guidance/control and targeting step (S660) can guide the guided weapon using target information received from the seeker by the guidance control unit, and control the guided weapon through an actuator control command.

FIG. 7 is a drawing showing target hitting using a guided weapon according to one embodiment of the present invention.

According to one embodiment of the present invention, the pilot can aim the target (3) by aligning the target with the target (3) and press the launch button to fire the guided weapon (1).

The propulsion unit is detonated and begins to burn when a detonation signal is applied, and the guided weapon (1) can be released from the launch tube. At this time, when the guided weapon (1) is released from the launch tube, the rear wings are spread and it can begin free flight toward the target.

In the guided weapon (1), if deformation occurs in the piezoelectric element above a certain pressure after detachment, a current is generated, and the generated current can detonate the thermal battery section.

The detonated thermocouple section can supply power to the drive section and the induction control section, and the induction control section supplies power to the seeker.

The guidance control unit transmits a command to deploy the control wings to the actuator unit, and the control wings of the actuator unit deploy.

The seeker searches for/selects a target (3) and provides target information to the guidance control unit. The guidance control unit starts tracking using the target information received from the seeker. At this time, the guided weapon (1) can start homing guidance by the seeker, thereby hitting the target (3).

Accordingly, the guided weapon of the present invention can transform an unguided weapon launched from a launcher into a guided weapon, and by replacing the forward warhead/fuse section of the unguided weapon with a guided control section, the thermal battery can be detonated by a piezoelectric element mounted on the front of the dome after launch, thereby supplying power to the components.

In addition, guided weapons can hit targets by controlling them through the seeker, and the hit rate can be increased by turning unguided weapons into guided weapons, and even if the pilot fires off-target, the target can be hit depending on the target detection performance of the seeker, so pin-point strikes can be possible.

Since guided weapons perform terminal guidance using a seeker, they are not affected by the external environment, and since they only use homing guidance in the terminal phase using the seeker, an inertial measurement device may not be needed.

The above description is merely an illustrative description of the technical idea of the present invention, and those skilled in the art will appreciate that various modifications, changes, and substitutions may be made without departing from the essential characteristics of the present invention. 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 to explain it, 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 interpreted by the following claims, and all technical ideas within a scope equivalent thereto should be interpreted as being included in the scope of the rights of the present invention.

1: Guided weapons
10: Forward guidance assembly
100: Induction Control Unit
110: Piezoelectric element
120: Explorer
130: Thermocouple section
140: Drive Unit
150: Guidance Control Unit
200: Warhead fuse
20: Propulsion Unit

Claims (13)

In a guided weapon equipped in a launcher and fired toward a target,
A forward guidance assembly assembled at the front of the guided weapon, which generates current by drag when fired toward the target and guides the target to detect or track the target; and
It is assembled at the rear of the above forward guidance assembly and includes a propulsion unit that provides propulsion force to separate the launcher by a detonation signal.
The above forward guidance assembly comprises a guidance control unit that controls the current generated by the resistance to guide the target toward the direction in which it is equipped; and a warhead fuse unit that is equipped at the rear end of the guidance control unit and is connected to the propulsion unit.
The guidance control unit includes a piezoelectric element that generates current by deformation caused by external resistance after the guided weapon leaves the launcher; a seeker that searches for and selects the target and generates target information according to the target; a thermoelectric unit that receives current through the piezoelectric element to detonate and supply power; a driving unit that receives power from the thermoelectric unit and controls the flight toward the target; and an guidance control unit that receives power from the thermoelectric unit and controls the driving unit through the target information.
The above piezoelectric element is attached to form a ring shape on the front step surface of the induction control unit formed in a dome shape, and includes a wiring for transmitting current to the thermocouple unit.
A guided weapon characterized in that the above wiring is connected to the connector of the above thermal unit and is formed to be attached to the inside of the dome-shaped induction control unit so as to be out of the direction in which the optical window attached to the front step surface of the induction control unit transmits. delete delete In the first paragraph,
The above induction control unit,
further comprising at least two control blades connected to the driving unit and controlled by the driving unit to fly the guided weapon in a targeting direction;
A guided weapon characterized in that the above control wings are deployed outwardly and controlled by the driving unit when power is supplied to the driving unit. In paragraph 4,
The above explorer,
The above generated target information is transmitted to the induction control unit,
A guided weapon characterized in that the guidance control unit calculates the path of the guided weapon based on the target information and transmits a control command to the driving unit to control the control wing. delete In paragraph 4,
The above forward guidance assembly is,
A guided weapon characterized in that the propulsion unit is implemented so as to be replaceable and assembled, and is implemented so as to be partially exposed on the outside of the launch tube. In the first paragraph,
The above guided weapon is,
A guided weapon characterized in that when the above propulsion unit detonates, the launch tube is separated, the rear wing formed at the rear of the propulsion unit is deployed, and power is supplied to the drive unit and the guidance control unit through the thermoelectric unit that is detonated by current generated as the piezoelectric element is compressed by drag, and the weapon is controlled toward the target through the control wing of the drive unit to which the power is supplied. In the first paragraph,
The above propulsion unit,
The above guided weapon includes a rear wing that is deployed when the weapon receives a propulsion signal through the launcher and leaves the launcher.
A guided weapon characterized in that the above propulsion signal is transmitted through a detonation line connecting the launch tube and the propulsion engine section. In a guidance method using a guided weapon equipped in a launcher and fired toward a target,
A step in which the propulsion unit is detonated through a detonation line connected to the launch tube, thereby launching the guided weapon toward the target;
A step in which a thermoelectric module is detonated by a current generated by deformation of a piezoelectric element due to the resistance received by the launched guided weapon;
A step of detecting and tracking the target by supplying power to the induction control unit and the driving unit through the above-mentioned thermal battery unit; and
Including a step of guiding and hitting the target detected and tracked above,
The step of detonating the thermal battery part is characterized in that the step of detonating the thermal battery part is characterized in that the piezoelectric element is attached to form a ring shape on the front step surface of the guidance control part of the guided weapon formed in a dome shape, is connected to the connector of the thermal battery part, and transmits current to the thermal battery part through a wiring formed to be attached so as to be in contact with the inside of the dome-shaped guidance control part so as to be out of the direction through which the optical window attached to the front step surface of the guidance control part transmits. delete In Article 10,
The steps of detecting and tracking the above target are:
When power is supplied to the above-mentioned induction control unit, power is supplied to the seeker through the induction control unit to search and select the target, and the target is detected and tracked through the seeker, which generates target information according to the target.
A guidance method characterized in that when power is supplied to the driving unit, at least two control blades controlled by the driving unit are deployed to fly the guided weapon in a target direction. In Article 12,
The steps of detecting and tracking the above target are:
The above generated target information is transmitted to the induction control unit,
A guidance method characterized in that the step of guiding and hitting the detected and tracked target calculates the path of the guided weapon based on the target information and transmits a control command to the driving unit to control the control wing.

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