KR20240032487A - Apparatus and systems for launching to reduce launch shock - Google Patents

Abstract

The present embodiments provide a launch device applied to at least one projectile fired toward a target, is connected to at least one projectile on one side, generates a launch signal to remove the target at a certain location, and generates a magnetic field by the launch signal. A launch device is provided that blocks and separates and launches at least one projectile.

Description

Launching device and system for reducing launch shock {Apparatus and systems for launching to reduce launch shock}

The present invention relates to a launch device and system for reducing launch shock, and particularly to a launch device and system for reducing launch shock of a projectile applied to an unmanned flying vehicle.

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

Unmanned aerial vehicle-launched guided weapons have a hovering function in which the unmanned aerial vehicle maintains its posture in the direction of the target so that the guided weapon's seeker can aim at the target. Afterwards, during the launch of the guided weapon, the reaction of the thrust of the guided weapon's propulsion engine affects the attitude of the unmanned aircraft, causing an unstable situation in the directionality of the guided weapon and the attitude stability of the unmanned aircraft.

In addition, cold-launch (two-stage propulsion) methods and methods of launching with aerodynamic launch or thrust from launch tube detonation and methods of dropping guided weapons can be used, but the directivity of guided weapons and unmanned aerial vehicles are still limited. There is a problem that affects flight attitude stability.

Another solution is a launch method that mechanically releases restraint, which can provide stability in flight attitude, but has the problem of increasing the weight and manufacturing cost of the mechanical device.

The main purpose of the embodiments of the present invention is to secure the attitude stability of the unmanned aircraft by reducing the impact of firing a guided weapon mounted on the unmanned aircraft.

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.

In order to achieve the above-described object, the present invention provides a launch device applied to at least one projectile fired toward a target, connected to the at least one projectile on one side, and providing a launch signal to remove the target at a certain position. A launch device is proposed, wherein the launch signal blocks magnetism to separate and launch the at least one projectile.

Preferably, the launch device includes: an electromagnet unit that magnetically fixes the at least one launch vehicle; and a control unit connected to the electromagnet unit and generating the firing signal to control a current flowing into the electromagnet unit.

Preferably, the control unit is connected to at least one electromagnet unit corresponding to the projectile, and controls the electromagnet unit to form magnetism and be fixed to the projectile by magnetic force by controlling the current flowing through the electromagnet unit. do.

Preferably, the control unit generates the firing signal when the firing point of the projectile is reached, and blocks the current flowing in the electromagnet unit by the firing signal to block the magnetic force between the projectile and the electromagnet unit. It is characterized by firing a projectile.

Preferably, the projectile is formed on a side connected to the launch device and includes a fixing part that is fixed or unfastened to the electromagnet part, and the fixing part is magnetic and is formed at a position corresponding to the electromagnet part. It is characterized by being

Preferably, the electromagnet part includes a first electromagnet part and a second electromagnet part formed to correspond to the first electromagnet part, and the fixing part includes a first fixing part fixed to correspond to the first electromagnet part and the second electromagnet part. It includes a second fixing part fixed to correspond to the electromagnet part, and the control part is characterized in that it controls the current flowing in the first electromagnet part and the second electromagnet part to control the posture of the projectile and launch it.

Preferably, the control unit generates a first firing signal so that the first electromagnet part and the first fixing part connected to the front of the projectile are preferentially separated when the target is located below a certain height than the projectile. This blocks the current flowing in the first electromagnet unit, and after the connection with the first electromagnet unit is released, when the projectile forms a preset angle to aim at the target, a second launch signal is generated to generate the second electron. It is characterized in that the projectile is fired by blocking the current flowing through the stone part.

Preferably, the control unit adjusts the angle between the projectile and the launch device so that the projectile is aimed at the target by adjusting the intensity of the current flowing in the first electromagnet unit, and the angle is adjusted to the position of the target. , The launch device is attached to a separate device and is adjusted by the intensity of the current flowing in the first electromagnet unit in consideration of movement information including the moving coordinates, speed and direction, and the weather of the area where the launch device is provided. It is characterized by

Preferably, it further includes a performance analysis unit that analyzes launch performance according to the current value controlled by the electromagnet unit through the control unit, and the performance analysis unit includes the weight of the projectile, the area where the projectile is fixed to the launch device, the Receiving launch information including at least one current value and the location of the target, comparing the launch information value according to the launch information with a predefined reference value to calculate a performance evaluation index indicating launch performance according to the current value, The performance evaluation index is characterized in that similarity is formed through the difference between the current value and the reference value, and accuracy is formed through the average value in the total measurement period according to the difference between the current value and the reference value.

In addition, according to another aspect of this embodiment, the present invention provides an unmanned flying vehicle; At least one guided weapon assembled at the bottom of the unmanned aircraft and fired toward a target; and a launch device connected to the at least one guided weapon on one side, generating a launch signal to remove the target at a predetermined position, and blocking magnetism by the launch signal to separate and launch the at least one guided weapon. We propose a launch system that includes.

Preferably, the launch device includes: an electromagnet unit that magnetically fixes the at least one launch vehicle; And a control unit connected to the electromagnet unit and generating the firing signal to control a current flowing into the electromagnet unit, wherein the guided weapon includes a fixing part formed on a side connected to the launching device, and the fixing part A launch system characterized in that it is magnetic and is formed to correspond to the electromagnet part.

Preferably, the control unit is connected to at least one electromagnet unit corresponding to the projectile, and controls the electromagnet unit to form magnetism and be fixed to the projectile by magnetic force by controlling the current flowing through the electromagnet unit, and controls the projectile to be fixed to the projectile by magnetic force. When the firing point is reached, the firing signal is generated, and the firing signal blocks the current flowing through the electromagnet unit to block the magnetic force between the projectile and the electromagnet unit to launch the projectile.

Preferably, the electromagnet part includes a first electromagnet part and a second electromagnet part formed to correspond to the first electromagnet part, and the fixing part includes a first fixing part fixed to correspond to the first electromagnet part and the second electromagnet part. It includes a second fixing part fixed to correspond to the electromagnet part, and the control part is characterized in that it controls the current flowing in the first electromagnet part and the second electromagnet part to control the posture of the projectile and launch it.

As described above, according to the embodiments of the present invention, the present invention has the effect of securing the attitude stability of the unmanned flying vehicle by reducing the launch shock of the unmanned flying vehicle-launched guided weapon.

In addition, the present invention allows the guided weapon to be launched after aiming at the target, which has the effect of maintaining the accuracy of the guided weapon and enabling multiple launches of the unmanned flying vehicle-launched guided weapon.

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 illustrating a launch system for reducing launch shock according to an embodiment of the present invention.
Figure 2 is a diagram showing a launch device for reducing launch shock according to an embodiment of the present invention.
Figure 3 is a diagram showing the installation of a projectile in a launch device according to an embodiment of the present invention.
Figure 4 is a diagram showing separation of a projectile from a launch device according to an embodiment of the present invention.
Figure 5 is a diagram showing temporal separation of projectiles of a launch device 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 launch device and system for reducing launch shock.

In the case of drone-launched guided weapons, the drone has a hovering function that maintains its posture in the direction of the target in order for the guided weapon's seeker to aim at the target. Afterwards, during the launch of the guided weapon, the reaction of the thrust of the guided weapon's propulsion engine affects the attitude of the drone, creating an unstable situation in the directionality of the guided weapon and the stability of the drone's attitude. To solve this, the method of cold-launch (two-stage propulsion) can be used, but it still affects the directivity of the guided weapon and the stability of the drone's flight attitude. Another solution is a launch method that mechanically releases restraint, which can provide stability in flight posture, but is expected to increase weight and cost.

Specifically, in the case of existing drone-launched guided/unguided weapons, there is a technology for continuous firing by attaching a grenade launcher (unguided) to the drone. In this technology, the drone must be pointed in the direction of the target so that the grenade launcher is aimed at the target, and the drone's hovering technology is key for continuous launch. Drone attitude control (hovering) technology based on the launch impact of a grenade launcher is the key, and the launch of guided/unguided weapons is limited during the time the drone returns to an attitude that can aim at the target, and the drone does not aim at the target. If not, there is a problem that it directly affects the accuracy of guided and unguided weapons.

Additionally, there is technology for Cold-Launch (two-stage propulsion), and in the case of Cold-Launch, there may be a method of launching with aerodynamic launch or thrust from the launch tube detonation, and in the case of guided weapons, there may be a method of dropping the guided weapon. And there is a method of mechanically releasing the restraint and firing it. In the case of cold-launch, even in the case of launch by aerodynamic force or detonation, the reaction caused by thrust affects the attitude of the drone, and in the case of dropping the guided weapon, the guided weapon falls depending on the surrounding environment (wind, etc.) There is a problem that may make it difficult to maintain the target orientation of guided weapons. The method of mechanically releasing restraints has the problem of increasing the cost compared to the method of attaching a simple electromagnet (the proposed method) due to the increase in the weight and manufacturing cost of the mechanical device that releases the restraints.

Therefore, the launch system 1 for reducing launch shock includes a launch device to which an electromagnet is applied, which can maintain the directivity of the guided weapon and minimize the influence of thrust reaction on the drone.

The launch system (1) for reducing launch shock is a launch device ( 10) Includes.

According to an embodiment of the present invention, the launch system 1 for reducing launch shock can be used for an unmanned aerial vehicle launch vehicle, but is not necessarily limited thereto.

Figure 1 is a diagram illustrating a launch system for reducing launch shock according to an embodiment of the present invention.

As shown in FIG. 1, the launch system 1 for reducing launch shock includes a launch device 10, an unmanned flying vehicle 20, and a launch vehicle 30. The launch system 1 may omit some of the various components exemplarily shown in FIG. 1 or may additionally include other components.

The launch device 10 is attached to the unmanned flying vehicle 20 and can launch the projectile 30 toward the target.

The launch device 10 may be applied to at least one projectile 30 fired toward a target.

The launch device 10 is connected to at least one projectile 30 on one side, generates a launch signal to remove a target at a certain location, and blocks magnetism by the launch signal to separate and launch at least one projectile. You can.

Referring to FIG. 1, the launch device 10 includes a control unit 12 and an electromagnet unit 14. The launch device 10 may omit some of the various components exemplarily shown in FIG. 1 or may additionally include other components.

The control unit 12 is connected to the electromagnet unit 14 and can control the current flowing into the electromagnet unit 14 by generating a firing signal.

The control unit 12 is connected to at least one electromagnet unit 14 corresponding to the projectile 30, and by controlling the current flowing into the electromagnet unit 14, the electromagnet unit 14 forms magnetism to produce a projectile ( 30) and can be controlled to be fixed.

The control unit 12 generates a launch signal when the launch point of the projectile 30 is reached, and blocks the current flowing in the electromagnet unit 14 by the launch signal to maintain the magnetic force between the projectile 30 and the electromagnet unit 14. By blocking, the projectile 30 can be fired.

The electromagnet unit 14 can magnetically secure at least one projectile 30.

The unmanned air vehicle 20 may be implemented as a drone airplane, etc., but is not necessarily limited thereto.

The projectile 30 may include guided weapons, unguided weapons, etc., but is not necessarily limited thereto.

The projectile 30 is formed on a side connected to the launch device 10 and may include an electromagnet portion 14 and a fixing portion 32 that is fixed or unfastened.

The fixing part 32 is magnetic and may be formed to correspond to the electromagnet part 14.

The electromagnet unit 14 may include a first electromagnet unit 14a and a second electromagnet unit 14b. The second electromagnet portion 14b may be formed to correspond to the first electromagnet portion 14a.

The fixing part 32 may include a first fixing part 32a and a second fixing part 32b. The first fixing part 32a may be fixed to correspond to the first electromagnet part 14a, and the second fixing part 32b may be fixed to correspond to the second electromagnet part 14b.

The control unit 12 can control the current flowing through the first electromagnet unit 14a and the second electromagnet unit 14b to control the attitude of the projectile 30 and launch it.

When the target is located below a certain height than the projectile 30, the control unit 12 is configured to preferentially separate the first electromagnet part 14a and the first fixing part 32a connected to the front of the projectile 30. 1 By generating a firing signal, the current flowing in the first electromagnet unit 14a can be blocked. The control unit 12 generates a second launch signal when the projectile 30 forms a preset angle to aim at the target after the connection with the first electromagnet unit 14a is released, thereby generating a current flowing in the second electromagnet unit 14b. The projectile 30 can be launched by blocking.

The control unit 12 may adjust the angle between the projectile 30 and the launch device 10 so that the projectile 30 is aimed at the target by adjusting the intensity of the current flowing through the first electromagnet unit 14a. At this time, the angle is calculated by taking into account the location of the target, movement information including the coordinates, speed, and direction in which the launch device 10 moves while attached to a separate device, and the weather in the area where the launch device 10 is installed. It can be adjusted by the intensity of the current flowing through the stone part 14a.

The launch device 10 may further include a performance analysis unit that analyzes launch performance according to the current value controlled by the electromagnet unit 14 through the control unit 12. The performance analysis unit receives launch information including at least one of the weight of the projectile 30, the area where the projectile 30 is fixed to the launch device 10, the current value, and the location of the target, and a launch information value according to the launch information By comparing predefined reference values, a performance evaluation index indicating launch performance according to the current value can be calculated. The performance evaluation index can form similarity through the difference between the current value and the reference value, and form accuracy through the average value in the total measurement cycle according to the difference between the current value and the reference value.

Therefore, the launch device 10 can be applied to the launch vehicle 30 that can be operated on the unmanned air vehicle 20, and the reaction caused by the propulsion thrust of the projectile 30 received by the unmanned air vehicle 20 is minimized. (20) Flight stability can be secured.

Figure 2 is a diagram showing a launch device for reducing launch shock according to an embodiment of the present invention.

According to one embodiment of the present invention, the launch device 10 may be attached to the unmanned flying vehicle 20 for launching the projectile 30. For example, the launch system 1 may be equipped with a launch device 10 to enable continuous launch of the projectile 30 from the small unmanned flying vehicle 20.

The launch device 10 includes an electromagnet unit 14 capable of fixing the projectile 30 and a control unit 12 capable of controlling the magnetism of the electromagnet unit 14. The control unit 12 can control the current in the direction a, but is not necessarily limited to this.

According to one embodiment of the present invention, the electromagnet unit 14 may be implemented as a coil, but is not necessarily limited thereto.

The projectile 30 may include a fixing part 32 that can be magnetically fixed to the electromagnet part 14 of the launch device 10.

Accordingly, the launch device 10 can ensure the attitude stability of the unmanned aircraft 20 by preventing the unmanned aircraft 20 from receiving the thrust of the launch vehicle 30.

The launch device 10 can reduce the launch shock of the unmanned aerial vehicle launch type projectile, secure the attitude stability of the unmanned aerial vehicle 20, and enable launch after aiming the projectile 30 at the target, thereby improving the accuracy of the projectile 30 and It is possible to enable multiple launches of the projectile 30.

Figure 3 is a diagram showing the installation of a projectile in a launch device according to an embodiment of the present invention.

The launch device 10 sends electric current to the electromagnet unit 14 through the control unit 12 in the flight section of the unmanned aircraft 20 to create magnetism in the electromagnet unit 14, thereby forming the fixing unit 32 of the launch vehicle 30. and the electromagnet part 14 can be fixed by magnetic force. At this time, when fixed, the electromagnet unit 14 may be implemented to move in the a direction and the projectile 30 may be implemented to move in the b direction.

Figure 4 is a diagram showing separation of a projectile from a launch device according to an embodiment of the present invention.

After the flight of the unmanned aircraft 20, when the launch vehicle 30 is launched, the launch device 10 blocks the current flowing through the electromagnet unit 14 through the control unit 12 to separate the electromagnet unit 14 and the projectile 30. ) can block the magnetic force between the fixing parts 32. Afterwards, the projectile 30 can be launched by igniting the propulsion engine.

Figure 5 is a diagram showing temporal separation of projectiles of a launch device according to an embodiment of the present invention.

If a projectile is dropped with only one electromagnet part installed in the launch device, it may be difficult to estimate the attitude of the projectile when it is dropped. Specifically, since projectiles generally have a sensor attached to the front, if they are released in an incorrect posture, it may be difficult for the sensor to recognize the target or problems may arise in initial control.

Accordingly, the launch device 10 may be implemented by installing a plurality of electromagnet units 14 and controlling each electromagnet unit 14 to set the throwing posture of the projectile 30. For example, in the case of air-to-ground guided weapons, the target is on the ground, so the front part of the guided weapon must be pointed downward and released to easily recognize the target. The release sequence can be implemented as follows.

Figure 5(a) is a view showing the side of the projectile mounted on the launch device according to an embodiment of the present invention, and Figure 5(b) is a view showing the front of the projectile mounted on the launch device according to an embodiment of the present invention. This is a diagram showing the side from which the projectile is separated, and Figure 5 (c) is a diagram showing the side from which the projectile is separated from the launch device according to an embodiment of the present invention.

Referring to (a) of FIG. 5, the lateral state of the projectile 30 mounted on the launch device 10 before being dropped can be shown. At this time, the launch device 1 can load the projectile 30 by passing current through the two first electromagnet parts 14a and the second electromagnet part 14b, respectively.

The first electromagnet unit 14a may be connected to and fixed to the first fixing part 32a, and the second electromagnet part 14b may be connected to and fixed to the second fixing part 32b.

Referring to (b) of FIG. 5, the first electron connected to the first fixing part 32a formed on the front of the projectile 30 to drop it from the front of the projectile 30 mounted on the launch device 10. By controlling the current of the stone portion 14a, the front of the projectile 30 can be dropped.

The control unit 12 of the launch device 10 may control the strength of the current provided to the first electromagnet unit 14a to adjust the angle of the launch vehicle 30. For example, the control unit 12 stores the current for forming an angle for the projectile 30 to maintain a preset angle in data and performs angle adjustment of the projectile 30 according to the location of the target based on this. You can.

Referring to (c) of FIG. 5, the posture of the projectile 30 can be maintained through the launch device 10, and the second electronic device is connected to the second fixing part 32b formed at the rear end of the projectile 30. The projectile 30 can be dropped by controlling the current of the stone part 14b.

Specifically, when the projectile 30 forms a certain angle as shown in (b) of FIG. 5, the launch device 10 maintains the posture of the projectile 30 and controls the current flowing in the second electromagnet unit 14b. It is possible to control the projectile 30 so that it can be completely dropped in a stable position.

According to one embodiment of the present invention, the launch device 10 may include a plurality of electromagnet parts 14, and a fixing part 32 is formed on the projectile 30 to correspond to the plurality of electromagnet parts 14. It can be. Specifically, the launch device 10 may further include an electromagnet unit provided on the front and rear sides to adjust the launch angle of the projectile 30, as well as an electromagnet unit for fixing the projectile 30. The electromagnet part for fixing the projectile 30 is located in a straight line with the electromagnet part provided at the front and rear to adjust the launch angle, and can be implemented to allow or block current along with the electromagnet part for angle adjustment. . Through this, the launch device 10 can be implemented to support the launch vehicle through the electromagnet units located on the same straight line when a problem occurs in some of the plurality of electromagnet units during operation of the unmanned flying vehicle 20, and a plurality of electromagnet units. If a problem occurs at a rate exceeding the threshold during stone installation, the unmanned air vehicle 20 can be controlled to stop flying and return.

According to one embodiment of the present invention, the launch device 10 may further include a performance analysis unit (not shown) that analyzes launch performance according to the current value controlled by the electromagnet unit through the control unit. The performance analysis unit may receive launch information of the launch device 10, compare the launch information value according to the launch information with a predefined reference value, and calculate a performance evaluation index indicating launch performance according to the current value. Here, the launch information includes the weight of the projectile 30, the area where the projectile 30 is fixed to the launch device 10, the current value provided by the control unit 12 of the launch device 10, the location of the target, and the unmanned flying vehicle ( 20), and the launch information value can be calculated based on this. The performance evaluation index can form similarity through the difference between the current value and the reference value, and form accuracy through the average value in the total measurement cycle according to the difference between the current value and the reference value. At this time, the measurement period may represent the interval from the moment the controller 12 blocks the current of the projectile 30 attached to the launch device 10 to the moment the projectile 30 is separated. Therefore, the performance of the operating launch device 10 can be evaluated based on the performance evaluation index, through which the launch device 10 can be replaced or the intensity of the current provided through the control unit 12 of the launch device 10 Accurate adjustment values, etc. can be derived.

According to one embodiment of the present invention, the launch device 10 includes a plurality of electromagnet units and can be operated while attached to the unmanned flying vehicle 20. When operating the unmanned flying vehicle 20, magnetic objects other than the projectile 30 may be attached to the launch device 10, which may interfere with operation. Therefore, magnetic objects other than the projectile 30 may be attached to the launch device 10. If it is determined that the magnetic object is attached more than the threshold value, the control unit 12 may separate the magnetic object by blocking the current in the electromagnet unit 14 that is attached more than the threshold value. At this time, if it is determined that a magnetic object exceeding the threshold value is attached to a plurality of electromagnet units, the current to the electromagnet units may be blocked sequentially, and the projectile 30 connected to the launch device 10 may be prevented from being separated. can do.

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: Launch system
10: launcher
12: control unit
14: Electromagnet part
20: Unmanned aerial vehicle
30: projectile
32: fixing part

Claims (13)

In a launch device applied to at least one projectile fired toward a target,
It is connected to the at least one projectile on one side, generates a firing signal to remove the target at a certain location, and blocks magnetism by the firing signal to separate and launch the at least one projectile. Device. According to paragraph 1,
The launch device is,
an electromagnet unit that magnetically fixes the at least one projectile; and
A launch device connected to the electromagnet unit and including a control unit that generates the launch signal and controls a current flowing to the electromagnet unit. According to paragraph 2,
The control unit,
A launch device that is connected to at least one electromagnet unit corresponding to the projectile, and controls the electromagnet unit to form magnetism and be fixed to the projectile by magnetic force by controlling the current flowing through the electromagnet unit. According to paragraph 3,
The control unit,
When the firing point of the projectile is reached, the launch signal is generated, and the current flowing through the electromagnet unit is blocked by the launch signal, thereby blocking the magnetic force between the projectile and the electromagnet unit to launch the projectile. Launch device. According to paragraph 2,
The projectile is,
It is formed on a side connected to the launch device and includes a fixing part that is fixed or unfastened to the electromagnet part,
A launch device, characterized in that the fixing part is magnetic and is formed at a position corresponding to the electromagnet part. According to clause 5,
The electromagnet portion includes a first electromagnet portion and a second electromagnet portion formed to correspond to the first electromagnet portion,
The fixing part includes a first fixing part fixed to correspond to the first electromagnet part and a second fixing part fixed to correspond to the second electromagnet part,
The launch device is characterized in that the control unit controls the current flowing in the first electromagnet unit and the second electromagnet unit to control the posture of the projectile and launch it. According to clause 6,
The control unit,
When the target is located below a certain height than the projectile, a first firing signal is generated so that the first electromagnet portion and the first fixing portion connected to the front of the projectile are preferentially separated, and the first firing signal is generated so that the first electromagnet portion flows into the first electromagnet portion. blocks the current,
After the connection with the first electromagnet unit is released, when the projectile forms a preset angle to aim at the target, a second launch signal is generated to block the current flowing in the second electromagnet unit to launch the projectile. Characterized by a launch device. In clause 7,
The control unit,
By adjusting the intensity of the current flowing in the first electromagnet unit, the angle between the projectile and the launch device is adjusted so that the projectile is aimed at the target,
The angle is determined by taking into account the location of the target, movement information including the coordinates, speed, and direction in which the launch device is attached to a separate device, and the weather of the area where the launch device is installed. A launch device characterized in that it is controlled by the intensity of electric current. According to paragraph 2,
It further includes a performance analysis unit that analyzes launch performance according to the current value controlled by the electromagnet unit through the control unit,
The performance analysis unit receives launch information including at least one of the weight of the projectile, the area where the projectile is fixed to the launch device, the current value, and the location of the target, and predefines a launch information value according to the launch information. By comparing the reference value, a performance evaluation index indicating launch performance according to the current value is calculated,
The performance evaluation index is a launch device characterized in that similarity is formed through the difference between the current value and the reference value, and accuracy is formed through an average value in the total measurement cycle according to the difference between the current value and the reference value. unmanned aerial vehicle;
At least one guided weapon assembled at the bottom of the unmanned aircraft and fired toward a target; and
A launch device that is connected to the at least one guided weapon on one side, generates a launch signal to remove the target at a certain location, and blocks magnetism by the launch signal to separate and launch the at least one guided weapon. Launch system including: According to clause 10,
The launch device is,
an electromagnet unit that magnetically fixes the at least one projectile; and
A control unit connected to the electromagnet unit and generating the firing signal to control a current flowing into the electromagnet unit,
The guided weapon includes a fixing part formed on a side connected to the launch device,
A launch system, wherein the fixing part is magnetic and is formed to correspond to the electromagnet part. According to clause 11,
The control unit,
It is connected to at least one electromagnet unit corresponding to the projectile, and controls the electromagnet unit to form magnetism and be fixed to the projectile by magnetic force by controlling the current flowing through the electromagnet unit,
When the firing point of the projectile is reached, the launch signal is generated, and the current flowing through the electromagnet unit is blocked by the launch signal, thereby blocking the magnetic force between the projectile and the electromagnet unit to launch the projectile. launch system. According to clause 12,
The electromagnet portion includes a first electromagnet portion and a second electromagnet portion formed to correspond to the first electromagnet portion,
The fixing part includes a first fixing part fixed to correspond to the first electromagnet part and a second fixing part fixed to correspond to the second electromagnet part,
The launch system is characterized in that the control unit controls the current flowing in the first electromagnet unit and the second electromagnet unit to control the posture of the projectile and launch it.

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