Anti-drone aircraft and method of operating the same

Abstract

An anti-drone aircraft according to one embodiment for detecting, tracking, and neutralizing a target drone may include: a seeker unit for collecting image signals of the target drone; a deployable main wing unit installed on the upper part of the fuselage, maintained in a folded state parallel to the longitudinal direction of the fuselage when loaded into a launch tube, and converted into a fixed-wing shape capable of flight by rotating in a vertical direction relative to the fuselage after launch; a deployable tail wing unit that deploys ahead of the deployable main wing unit after launch to stabilize the attitude of the aircraft; a deployment restraint unit that mechanically restrains the rotation of the deployable main wing unit; a propulsion unit that provides thrust to the aircraft; and a detonator unit capable of detonating under conditions of proximity to the target drone to neutralize the target drone.

Description

Technology Field

[0001] The following description relates to an anti-drone aircraft and its operation method. Background Technology

[0003] Conventionally, to counter enemy drones (target drones) infiltrating key national industrial complexes and military areas, operations to neutralize drones have been carried out by mobilizing armed helicopters or manned aircraft. However, this conventional method has drawbacks, such as high operating costs and the difficulty of immediate response due to the significant time required for countermeasures to reach the target location after detecting the target drone. Furthermore, a tactical vulnerability has been pointed out, as the cause of destruction could be exposed externally after the target drone is neutralized, allowing the enemy to analyze the cause and devise countermeasures.

[0004] Meanwhile, designing a missile-type anti-drone aircraft entails complex technical challenges, such as designing miniaturized and foldable wings for launch tube insertion, overcoming aerodynamic instability immediately after launch, real-time transmission of seeker images during high-speed flight, and safety management of the detonator.

[0005] The aforementioned background technology is one that the inventor possessed or acquired during the process of deriving the present invention, and it cannot be considered as publicly known technology disclosed to the general public prior to the filing of the present invention. The problem to be solved

[0007] The objective according to one embodiment is to provide an anti-drone aircraft and a method for operating the same. means of solving the problem

[0009] An anti-drone aircraft according to one embodiment for detecting, tracking, and neutralizing a target drone may include: a seeker unit for collecting image signals of the target drone; a deployable main wing unit installed on the upper part of the fuselage, maintained in a folded state parallel to the longitudinal direction of the fuselage when loaded into a launch tube, and converted into a fixed-wing shape capable of flight by rotating in a vertical direction relative to the fuselage after launch; a deployable tail wing unit that deploys ahead of the deployable main wing unit after launch to stabilize the attitude of the aircraft; a deployment restraint unit that mechanically restrains the rotation of the deployable main wing unit; a propulsion unit that provides thrust to the aircraft; and a detonator unit capable of detonating under conditions of proximity to the target drone to neutralize the target drone.

[0010] The above-described deployable main wing may include: a wing portion that provides lift necessary for flight; and a pivot portion having a hinge or axis structure that allows rotation of the wing portion and is equipped with an elastic restoring means so that the wing portion automatically rotates at a predetermined angle when the constraint of the deployable restraint is released.

[0011] The above-described deployable tail section includes four tail wings radially spaced around the fuselage and a slot-shaped opening that communicates so that each of the four tail wings rotates and is stored inside the fuselage along the longitudinal direction of the fuselage, and each of the four tail wings is folded inside when loaded into a launch tube through the slot-shaped opening and can be deployed to the outside after launch of the anti-drone aircraft.

[0012] An anti-drone aircraft according to one embodiment further includes an integrated control unit that drives the propulsion unit to perform flight and processes the image signal of the seeker unit to perform search and tracking of the target drone, and the integrated control unit can release the restraint of the deployable main wing unit by applying a release signal to the deployment restraint unit after the completion of deployment of the deployable tail unit is confirmed.

[0013] The above-described deployable tail section further includes a deployment switch that generates a deployment completion signal by physically interfering when the deployment of the four tail wings is completed, and the integrated control unit can perform the deployment of the above-described deployable main wing section by releasing the restraint of the deployment restraint when the deployment completion signal is input from the deployment switch.

[0014] The above deployment restraint further includes a sliding pin formed to protrude slidably toward the upper side of the fuselage and inserted into or interferes with the wing portion when the wing portion of the deployable main wing portion overlaps with the fuselage in an up-and-down direction in a folded state; and the integrated control unit can release the restraint on the wing portion by lowering the sliding pin when the deployment completion signal is input from the deployment switch.

[0015] The above propulsion unit is installed at the rear of the body and includes a plurality of variable blades that rotate at high speed by a motor and can pivot around a rotation axis perpendicular to the rotation axis, and the plurality of variable blades are pivoted forward so as to be close to the rotation axis when the anti-drone aircraft is loaded into the launch tube, but can be tilted backward under the acceleration load generated during launch after the launch of the anti-drone aircraft and aligned in a state horizontal to the rotation axis.

[0016] An anti-drone aircraft according to one embodiment further includes a transceiver that performs RF communication between the aircraft and a ground body, and the transceiver includes a TRX antenna that is installed on the upper side of the body to radiate and receive RF signals and is rotatable to be deployed to the outside of the body through elastic force while in a folded state stored inside the body, and the TRX antenna is constrained to be stored inside the body by interference from the upper side by the wing portion in the folded state when the anti-drone aircraft is loaded into a launch tube, but can be deployed to the outside of the body as the constraint by the wing portion is released as the deployment of the deployable main wing portion is performed after the launch of the anti-drone aircraft.

[0017] The above detonator includes a detonator that is ignited by a thermal battery; and a proximity detection unit that determines proximity to a target, and the integrated control unit can apply a loading signal to the detonator based on the proximity detection signal of the proximity detection unit.

[0018] The above integrated control unit is capable of collecting the operating frequency band of the target drone through the above transceiver, and

[0019] The above integrated control unit can transmit a disturbance signal to the frequency band of the target drone collected through the above transceiver when detonation is performed through the above detonator.

[0020] The integrated control unit further includes an image processing module that generates compressed image data by performing hardware-based encoding on an image signal collected from the explorer unit; and the compressed image data can be transmitted in real time to a ground body via the transceiver unit.

[0021] A method for operating an anti-drone aircraft according to one embodiment for detecting, tracking, and neutralizing a target drone may include: launching an anti-drone aircraft loaded into a launch tube; deploying wings sequentially after launch, in which a deployable tail section having four tail wings radially spaced around the body and constrained in a folded state along the longitudinal direction of the body, and a deployable main wing section having a wing section installed on the upper part of the body and aligned parallel to the longitudinal direction of the body and constrained in a folded state; performing navigation control of the anti-drone aircraft; tracking a target of the target drone through a seeker section; and performing detonation under conditions of proximity to the target drone to neutralize the target drone.

[0022] The step of deploying the wings may include: a step of deploying a deployable tail section by releasing the restraints of the four tail wings and rotating the four tail wings outward from the fuselage; and, after the deployment of the deployable tail section is completed, a step of deploying a deployable main wing section by releasing the physical restraints of the wing section and converting the wing section into a fixed wing shape capable of flying by rotating it vertically relative to the fuselage by elastic force.

[0023] The step of deploying the wing further includes a step of confirming the completion of deployment of the deployable tail section; wherein a deployment completion signal is generated by a deployment switch that is physically interfered with when the deployment of the deployable tail section is completed, and in the step of confirming the completion of deployment of the deployable tail section, a step of deploying the deployable main wing section may be performed after the completion of deployment of the deployable tail section is confirmed by the deployment completion signal.

[0024] The step of deploying the wing is performed prior to the step of deploying the deployable tail section, and further includes a step of checking whether the anti-drone aircraft and the ground connection device are separated; and in the step of checking whether the ground connection device is separated, if a separation signal of the ground connection device that was connected to the anti-drone aircraft prior to launch is applied, the step of deploying the deployable tail section may be performed.

[0025] The above anti-drone aircraft includes a TRX antenna that is rotatably installed on the upper side of the fuselage to radiate and receive RF signals, and is constrained to be housed inside the fuselage by interference from the upper side by the wing portion before the deployable main wing portion is deployed, and the step of deploying the wing may further include a step of deploying the TRX antenna, wherein, as the step of deploying the deployable main wing portion is performed, the physical constraint by the wing portion is released, and the TRX antenna rotates in the direction of the upper side of the fuselage by elastic force.

[0026] The step of performing the above detonation may include: a step of confirming proximity detection by detecting whether the target drone has entered a predetermined proximity range; and a step of applying a loading signal to the detonator based on the proximity detection signal of the proximity detection unit.

[0027] The above loading signal includes: a first loading signal applied when it is confirmed that the deployment of the deployable tail section and the deployable main wing section is mechanically completely completed; a second loading signal applied when it is confirmed that the anti-drone aircraft is separated from a safety zone where the launch base and operating personnel are located by a predetermined distance or more; and a third loading signal applied when it is confirmed that the target drone has entered within a predetermined proximity range; and in the step of applying the loading signal, the detonator of the detonator device can be ignited only when the first loading signal, the second loading signal, and the third loading signal are all applied sequentially.

[0028] The step of performing the above detonation may further include the step of collecting the operating frequency band of the target drone and, when performing the detonation, transmitting a disturbance signal for the collected frequency band to perform frequency disturbance. Effects of the invention

[0030] According to an anti-drone aircraft and a method of operation thereof according to one embodiment, by means of a sequential deployment structure in which the deployment restraint part releases the restraint of the deployable main wing part only after the completion of deployment of the deployable tail part is mechanically confirmed by a deployment switch, the main wing is prevented from deploying prematurely in an aerodynamically unstable state immediately after launch, and initial attitude stabilization by the tail part can be secured in advance.

[0031] According to an anti-drone aircraft and a method of operation thereof according to one embodiment, since the deployment of the main wing is constrained at a physical level by a mechanical interlock of the deployment restraint part, unintended deployment caused by electronic false signals can be prevented even in an environment of electronic noise and mechanical shock immediately after launch.

[0032] According to an anti-drone aircraft and a method of operation thereof according to one embodiment, detonation is permitted only when the confirmation of mechanical deployment completion, the confirmation of safe distance separation, and the confirmation of entry into the target proximity range are all sequentially satisfied by a three-stage safety loading system, so the possibility of false detonation due to a single condition misjudgment can be reduced.

[0033] According to an anti-drone aircraft and a method of operation thereof in one embodiment, when detonation is performed, a disturbance signal is simultaneously transmitted to the operating frequency band of the target drone collected by the frequency analysis unit, thereby blocking the communication link of the target drone and hindering the enemy's analysis of the cause of destruction. Brief explanation of the drawing

[0035] FIG. 1 is a side view of an anti-drone aircraft according to one embodiment. FIG. 2 is a block diagram of an anti-drone aircraft according to one embodiment. FIG. 3 is a side view showing an enlarged view of the deployable tail section and propulsion section of an anti-drone aircraft according to one embodiment. FIG. 4 is a bottom view of an anti-drone aircraft according to one embodiment. FIG. 5 is a flowchart of an operation method of an anti-drone aircraft according to one embodiment. FIG. 6 is a flowchart of the steps for unfolding a wing according to one embodiment. FIG. 7 is a flowchart of the steps for performing detonation according to one embodiment. Specific details for implementing the invention

[0036] Hereinafter, embodiments will be described in detail with reference to the attached drawings. The following description is one of several aspects of the embodiments, and the following description constitutes part of the detailed description of the embodiments.

[0037] However, in describing one embodiment, specific descriptions regarding known functions or configurations are omitted to clarify the gist of the present invention.

[0038] In addition, terms or words used in this specification and claims shall not be interpreted in their ordinary or dictionary senses, and based on the principle that the inventor may appropriately define the concepts of terms to best describe his invention, they shall be defined in a sense and concept consistent with the technical idea of ​​the anti-drone aircraft and the method of operation thereof according to one embodiment.

[0039] Therefore, the embodiments described in this specification and the configurations illustrated in the drawings are merely the most preferred embodiment of an anti-drone aircraft and its operation method according to one embodiment, and do not represent all technical concepts of the anti-drone aircraft and its operation method according to one embodiment; thus, it should be understood that various equivalents and modifications that can replace them may exist at the time of filing this application.

[0040] Referring to FIGS. 1 to 4, the anti-drone aircraft (1) according to one embodiment is an anti-drone system designed as a missile-type high-speed aircraft, and after being loaded into a launch tube and launched, it is converted into a flight shape using a deployable main wing (12) and a deployable tail wing (13), detects and tracks a target (target drone) with a seeker (11) and a sensor (18), and can track the target by driving a propulsion unit (14) under the control of an integrated control unit (15).

[0041] For example, the anti-drone aircraft (1) can be configured such that the tail and main wings are maintained in a folded shape while loaded into the launch tube, and after launch, the deployable tail section (13) is deployed first to stabilize the initial attitude of the aircraft, and then the deployable main wing section (12) is released and automatically deployed only after the completion of tail deployment is mechanically confirmed, thereby preventing the early deployment of the main wing in an aerodynamically unstable state at the beginning of launch.

[0042] For example, the anti-drone aircraft (1) can transmit and receive status, images, and commands to and from a ground entity through a transmitting and receiving unit (16), and is configured to neutralize the target through a detonating unit (17) when the distance and conditions to the target are met.

[0043] An anti-drone aircraft (1) according to one embodiment is a missile-type high-speed aircraft for detecting, tracking, and neutralizing a target drone (UAV), and includes a seeker section (11), a deployable main wing section (12), a deployable tail wing section (13), a propulsion section (14), an integrated control section (15), a transmission / reception section (16), a detonation section (17), a sensor section (18), and a deployment restraint section (19).

[0044] The seeker unit (11) is a surveillance sensor that collects image signals of a target and provides them to the integrated control unit (15), and is positioned at the front of the aircraft (1).

[0045] The seeker unit (11) may include, for example, an IR (infrared) camera, an EO (visible light) camera, a low-light sensor, a thermal sensor, or a combination of these sensors. The seeker unit (11) may be mounted on a gimbal structure as needed to stably track a target while compensating for vibrations during flight, or it may be configured as a fixed structure.

[0046] For example, the seeker (11) can activate the IR camera when it enters within a predetermined distance (e.g., about 4 km) from the target.

[0047] The image signal collected by the seeker unit (11) is input to the seeker signal processing module (152) of the integrated control unit (15) to perform processing such as target candidate extraction, ROI setting, and tracking stabilization. In addition, the image data of the seeker unit (11) can be compressed through the image processing module (154) of the integrated control unit (15) and then transmitted to a ground body via the transmission and reception unit (16).

[0048] According to the above structure, the seeker unit (11) can collect a video signal of a target in real time from the front of the aircraft (1) and provide visual information necessary for subsequent tracking and terminal guidance.

[0049] The deployable main wing (12) is a fixed-wing structure that provides lift and maneuverability to the aircraft (1). When loaded into the launch tube, it is maintained in a folded state parallel to the longitudinal direction of the fuselage at the top of the fuselage, and after launch, it is configured to rotate vertically relative to the fuselage to transform into a main wing shape capable of flight.

[0050] Even if the deployable main wing (12) has a mechanically deployable state, the rotation of the wing (121) is physically constrained by the deployment restraint (19) described later, and the restraint is released and the wing can be automatically deployed only after a predetermined condition, such as the completion of deployment of the deployable tail wing (13), is satisfied.

[0051] For example, the deployable main wing (12) may include a wing portion (121), a rotating portion (122), and a fixed portion (123).

[0052] In other words, since the deployment timing of the deployable main wing (12) is dependent on the mechanical confirmation event of the completion of tail wing deployment, the premature deployment of the main wing in an electronic noise environment immediately after launch is prevented at the mechanical level.

[0053] According to the above structure, the deployable main wing (12) ensures insertion into the launch tube while completing the fixed-wing flight shape through rapid and reliable deployment after launch, and unlike the conventional explosive bolt method, repetitive operation testing and mass production reliability are ensured by a non-destructive deployment mechanism.

[0054] The wing section (121) is a main wing structure that provides lift and stability necessary for flight, and forms a folded shape parallel to the longitudinal direction of the fuselage when loaded into the launch tube, and after launch, it can automatically unfold using an elastic spring structure and rotate vertically with the fuselage to switch to a flight shape.

[0055] For example, the wing portion (121) may have a symmetrical structure that extends in both directions along the longitudinal direction and may be rotatable relative to the fuselage through the pivot portion (122) at the center.

[0056] The pivoting part (122) is a hinge or shaft structure that allows rotation of the wing part (121) and may include an elastic restoring means such as a spring or a damper inside. For example, the pivoting part (122) may include a stopper structure that stops the wing part (121) at the completed deployment position.

[0057] The fixed portion (123) is positioned at the end of the wing portion (121) and is formed in a structure in which a pin or sliding member of the unfolding restraint portion (19) can be inserted or interfered with. The fixed portion (123) can be implemented, for example, as a groove, hole, stopper, slot, etc.

[0058] For example, as shown in FIG. 4, the wing portion (121) may be configured to automatically rotate at a predetermined angle (e.g., about 90 degrees) when released from restraint through the unfolding restraint portion (19) described later.

[0059] The deployment restraint (19) is a mechanical interlock that physically restrains the rotation of the wing portion (121) of the deployable main wing portion (12), and is configured to prevent the deployment of the main wing even after launch until a predetermined condition is satisfied.

[0060] For example, the unfolding restraint unit (19) can be implemented with a servo motor, a solenoid, a linear actuator, or a combination thereof, and can be controlled by an integrated control unit (15).

[0061] The deployment restraint (19) includes a slidingly drivable member to interfere with or be inserted into the fixed part (123) of the wing part (121), thereby forming a mechanical interlock that physically restrains the deployment of the main wing even after launch until a predetermined condition is satisfied.

[0062] The deployment restraint (19) may include, for example, a sliding pin (191), and the pin may restrict the rotation of the wing portion (121) by penetrating or interfering with the fixed portion (123) during the initial loading and firing phase, but after firing, when the signal indicating the completion of deployment of the deployable tail portion (13) is confirmed by the integrated control unit (15), an electrical signal (e.g., a PWM signal) is applied to the deployment restraint (19) so that the pin descends or retracts to release the restraint or interference on the wing portion (121), thereby allowing the wing portion (121) to be automatically deployed by the elastic force of the rotation portion (122).

[0063] In another embodiment, the deployment restraint (19) may be configured to additionally restrain the external deployment of the deployment tail section (13).

[0064] According to the above structure, the deployment restraint part (19) is formed with a reusable pin or slider structure instead of a single-use part such as a conventional explosive bolt, allowing for repeated testing and maintenance, and implements sequential deployment control by mechanical restraint and release, thereby preventing premature deployment of the main wing even in an environment of electronic noise and mechanical shock immediately after launch.

[0065] The deployable tail section (13) is positioned at the rear of the aircraft (1) and remains folded inside the fuselage when loaded into the launch tube, and deploys after launch to contribute to the attitude stabilization (pitch / yaw / roll) of the aircraft. The deployable tail section (13) is configured to deploy ahead of the deployable main wing section (12), so that the straightness and attitude stability of the aircraft can be quickly secured immediately after launch.

[0066] For example, the deployable tail section (13) may include four tail wings (131) that are radially spaced around the fuselage, a slot-shaped opening (132) that communicates so that each of the four tail wings (131) rotates into the interior of the fuselage along the longitudinal direction of the fuselage, and a deployment switch (133) that is physically interfered with when the external deployment of the four tail wings (131) is completed to generate a deployment completion signal.

[0067] For example, as illustrated in FIGS. 1 to 4, the deployable tail section (13) may include four tail wings (131), and each tail wing (131) may be radially spaced around the fuselage and maintained in a folded state inside when loaded into a launch tube through a slot-shaped opening (132) that communicates with the inside of the fuselage.

[0068] For example, each tail wing (131) can have its deflection angle controlled independently by a servo motor to control the pitch, yaw, and roll of the aircraft.

[0069] Each tail wing (131) is rotatably connected to the fuselage through a hinge or shaft structure and may be equipped with an elastic restoring means such as a spring or damper, and may be configured to automatically rotate and unfold outward from the fuselage by means of an elastic restoring force when the restraint is released. As another example, it should be noted that the deployable tail wing (13) may be deployed through a driving source such as a servo motor, a solenoid, or a linear actuator.

[0070] For example, the deployable tail section (13) may have a structure in which its deployment to the outside is restricted by being physically interfered with by the inner wall inside the launch tube. In another embodiment, the deployable tail section (13) may be restricted by a deployment restraining section (19).

[0071] For example, the deployment switch (133) may be configured to generate an electrical signal indicating the completion of deployment as an internal mechanical switch (e.g., limit switch, Hall sensor, micro switch) is pressed or activated when deployment is complete.

[0072] According to the above structure, the deployable tail section (13) is compactly stored inside the fuselage through the slot-type opening (132) when the launch tube is loaded, and automatically deploys by elastic restoring force after launch, thereby quickly securing the initial attitude stabilization of the aircraft. In addition, since the mechanical confirmation of deployment completion by the deployment switch (133) does not rely on electronic judgment, the completion of deployment can be reliably detected even in an electronic noise environment immediately after launch.

[0073] The propulsion unit (14) is a drive system installed at the rear end of the aircraft (1) to provide propulsion, and may include a plurality of variable blades (141) that rotate at high speed by a motor to form high-speed propulsion of the anti-drone aircraft (1).

[0074] For example, the propulsion unit (14) includes an electronic speed controller (ESC) that controls the rotational speed of the motor and can measure the motor's RPM in real time and provide it to the integrated control unit (15).

[0075] Multiple variable blades (141) can be designed so that the blade pitch or arrangement is self-aligned by centrifugal force when the motor rotates.

[0076] For example, when a plurality of variable blades (141) are loaded into a launch tube, as shown in FIG. 1, each of the plurality of variable blades (141) has a pivot axis perpendicular to the rotation axis, and each variable blade (141) can have a structure that can pivot forward relative to the body so as to be close to the rotation axis, so that as the anti-drone aircraft (1) is loaded into the launch tube, the plurality of variable blades (141) are folded so that they are adjacent to the body, thereby minimizing the space occupied outside the body.

[0077] Subsequently, when the anti-drone aircraft (1) is launched outward, the plurality of variable blades (141) are tilted backward under the acceleration load generated during launch, as shown in FIGS. 3 and 4, and can then self-align to an optimal horizontal state by centrifugal force when the motor is driven.

[0078] According to the above structure, the variable blade (141) of the propulsion unit (14) pivots forward when loaded into the launch tube to minimize the space occupied on the outside of the body, and after launch, it self-aligns by the acceleration load and the driving centrifugal force of the motor without a separate deployment actuator, so that the launch tube loading capability and propulsion efficiency can be secured simultaneously without additional parts.

[0079] The integrated control unit (15) is a control center that oversees the overall mission performance of the aircraft (1) and may include an integrated navigation module (151), a seeker signal processing module (152), a power module (153), an image processing module (154), a communication module (155), and a launch interlock unit (156).

[0080] The integrated control unit (15) can be implemented by stacking or integrating one or more boards or modules, and data exchange between internal modules can be configured, for example, as an Ethernet-based switching network. In addition, the integrated control unit (15) can ensure standardization and scalability of data transmission by applying a standardized communication protocol, for example, the Mavlink protocol.

[0081] The integrated navigation module (151) is a module that collects and fuses GPS / IMU / environment sensor information from the sensor unit (18) and estimates the position, velocity, and attitude (roll / pitch / yaw) of the aircraft (1). The integrated navigation module (151) can fuse GPS-based position and velocity, IMU-based angular velocity / acceleration, and environment sensor (183)-based airspeed / dynamic pressure information, for example, using a Kalman filter or a corresponding state estimation algorithm. In particular, by integrating the position coordinates received by two GPS antennas (181), it is possible to extract the heading (azimuth) of the aircraft even in hovering or low-speed flight states.

[0082] The output of the integrated navigation module (151) is used to control the propulsion unit (14) so ​​that the aircraft (1) tracks and flies toward the target direction, and can be combined with the output of the seeker signal processing module (152) for terminal guidance.

[0083] The seeker signal processing module (152) is a module that detects and tracks a target drone by analyzing a video signal input from the seeker unit (11). The seeker signal processing module (152) can perform, for example, inter-frame movement analysis, template matching, feature point tracking, thermal image-based spot detection, and calculate an azimuth / elevation angle based on the screen coordinates of the detected target and provide it to the integrated navigation module (151).

[0084] Additionally, the seeker signal processing module (152) can perform auxiliary logic (e.g., distance estimation based on image size) to determine the distance or proximity condition to the target, and may have a reinforcement structure that allows detonation to be performed together with the signal of the proximity detection unit (172).

[0085] The power module (153) is a module that includes or is connected to a battery (e.g., a lithium polymer battery) mounted on the aircraft (1) and distributes power to each component.

[0086] For example, the power module (153) can be configured to separate the high-power power path supplied to the propulsion unit (14) and the low-power power path supplied to the integrated control unit (15) and other electronic modules so that power fluctuations of the propulsion unit do not affect the control and sensor system.

[0087] For example, the power module (153) may be configured to receive ground power (via the belly connector) through the launch interlock unit (156) before launch, and to automatically switch to internal battery power when the belly connector is disconnected after launch. The power module (153) may be configured to apply power accompanied by a loading signal (ARM signal) to the detonator (17) only when the conditions of the safety control module (173) are met.

[0088] The image processing module (154) is a module that performs compression, frame rate adjustment, resolution scaling, and packetization on image data of the explorer unit (11). The image processing module (154) may include, for example, an H.264 series hardware encoder and can reduce image transmission delay compared to software-based compression methods.

[0089] In other words, the image processing module (154) can enable ultra-low latency real-time image transmission required in battlefield situations by performing image encoding at the hardware level.

[0090] The communication module (155) is a module that manages data exchange between each module inside the aircraft (1) and communication processing with an external ground unit. For example, the communication module (155) can support high-speed data transmission between internal modules by including an Ethernet-based hub switching structure, and can perform command and status data transmission and reception with the ground unit by applying a standardized communication protocol such as the Mavlink protocol.

[0091] According to the above structure, the communication module (155) can ensure communication compatibility with the ground body through a standardized protocol while simultaneously performing high-speed data transmission between internal modules.

[0092] For example, the communication module (155) can be logically separated into an aircraft inspection (AVTE) group and a ground unit RFP communication group based on an internal wired network. The inspection group is a data path used for pre-launch status inspection of the aircraft (1), module-specific self-diagnosis, and maintenance, and the ground unit communication group is a path for video, status, and command data exchanged with the ground unit via the transceiver (16) during mission execution. By logically separating the inspection group and the ground unit communication group in this way, mutual interference between inspection data and mission data is prevented, and communication delays caused by unnecessary inspection traffic during mission execution can be suppressed.

[0093] The launch interlock unit (156) is a structure connected to a ground connection device (umbilical connector) and is a safety mechanism to prevent the aircraft (1) from performing mission operations (deployment, propulsion, detonation) while in a ground restraint state.

[0094] The launch interlock unit (156) can receive mission information (target location, engagement zone, etc.), safety conditions, and initial settings from the ground unit via the ground connection device before launch. After launch, it detects whether the ground connection device is disconnected (e.g., electrical disconnection detection, disconnection switch, signal level change), and if disconnection is confirmed, it can switch the aircraft (1) from safety mode to mission mode.

[0095] In other words, the launch interlock unit (156) sets the physical separation of the ground connection device as an absolute prerequisite for the start of the flight sequence, thereby fundamentally suppressing malfunctions (main wing deployment, detonation power application, high-power propulsion, etc.) in the ground connection state. Accordingly, the launch interlock unit (156) performs the role of physically determining the starting point for the transition between the safety mode and mission mode of the aircraft (1).

[0096] According to the above structure, the integrated control unit (15) can integrally manage functions of navigation, target tracking, image transmission, power management, communication, and launch safety from a single control center, thereby ensuring information fusion between modules and consistency in mission execution.

[0097] The transceiver (16) is physical layer hardware for RF communication between the aircraft (1) and the ground unit, and is connected to the integrated control unit (15) to transmit and receive aircraft status data, image data, frequency information, and control commands.

[0098] The transceiver (16) may include an RF transceiver (161), an RF amplifier (162), and a TRX antenna (163).

[0099] The RF transceiver (161) can convert a data stream transmitted from the integrated control unit (15) into an RF signal and transmit it, and receive an RF signal from a ground unit and restore it into a data stream.

[0100] The RF amplifier (162) is configured to amplify the transmission output and improve reception sensitivity, and improves communication distance and link stability.

[0101] The TRX antenna (163) is an antenna that radiates and receives transmission and reception signals from the RF transceiver (161) and is rotatably installed on the upper side of the fuselage. The TRX antenna (163) has a folding or storage structure for loading into a launch tube, and when loaded into a launch tube, it is physically interfered with from the upper side by the wing portion (121) of the deployable main wing portion (12) in the folded state and is restrained in a stored state inside the fuselage.

[0102] After launch, as the deployment of the deployable main wing (12) is performed and the physical restraint by the wing (121) is released, the TRX antenna (163) rotates upward on the fuselage by the elastic force of the spring actuator (1631) and automatically deploys.

[0103] In other words, the deployment of the TRX antenna (163) does not require a separate release actuator and is performed by automatically removing physical interference through a preceding event of the deployment of the deployable main wing (12), so the deployment of the deployable tail (13) → deployable main wing (12) → TRX antenna (163) can be mechanically chained.

[0104] For example, it should be noted that the step of deploying the TRX antenna (163) may be performed by releasing a device that mechanically prevents the TRX antenna (163) from being deployed through a separate actuator.

[0105] The spring actuation part (1631) is an elastic driving means that automatically moves the TRX antenna (163) from the storage position to the deployment position.

[0106] For example, as shown in FIG. 4, an RF transceiver (161) and an RF amplifier (162) may be installed on the lower side of the body to increase the efficiency of transmission and reception with the ground.

[0107] The transceiver (16) is configured to analyze the received RF signal to identify and collect the operating frequency band of the target drone. The frequency band information collected by the frequency analysis unit (164) is provided to the integrated control unit (15) and can be used to transmit a jamming signal for the corresponding frequency band when detonation is performed, and the collected operating frequency band information of the target drone is transmitted to a ground entity via the transceiver (16) and can be used for subsequent anti-drone operations or electronic warfare response.

[0108] According to the above structure, the transceiver (16) provides RF communication between the aircraft and the ground vehicle, and the TRX antenna (163) automatically deploys without a separate driving source in conjunction with the deployment of the main wing, thereby reducing the number of parts, and the target frequency collection function is utilized for transmitting a jamming signal upon detonation, so that communication / deployment / electronic warfare functions can be performed integrally within a single transceiver (16).

[0109] The detonator (17) is configured to neutralize a target drone and includes a detonator (171) and a proximity detection unit (172), and can be positioned at the front of the aircraft (1) (behind the seeker unit (11)).

[0110] The detonator (17) may receive a detonation request signal or an ARM signal from the integrated control unit (15), but the safety control module (173) may be configured to independently verify conditions to prevent accidental detonation.

[0111] The detonator (171) may include a detonator (ignition tube), a detonation circuit, and an ignition element, and may generate detonation energy by applying an ignition signal to the thermal battery only when the final permission condition of the safety control module (173) is satisfied.

[0112] For example, the detonator (171) can neutralize the target drone through an explosion, fragmentation, impact, etc., under conditions of proximity to the target, and can perform detonation by igniting the thermal battery after receiving a loading signal.

[0113] According to a configuration in which the thermal battery is ignited at the terminal stage to charge the fuse power, the possibility of a false detonation can be physically eliminated by not storing energy during normal operation and charging it only immediately before the mission.

[0114] For example, the loading signal may include a first loading signal (ARM1) applied when it is confirmed that the deployment of the deployable tail section (13) and the deployable main wing section (12) is mechanically completely completed, a second loading signal (ARM2) applied when it is confirmed that the anti-drone aircraft (1) is separated from the safety zone where the launch base and operating personnel are located by a predetermined distance or more, and a third loading signal (ARM3) applied when it is confirmed that the target drone has entered within a predetermined proximity range.

[0115] For example, the integrated control unit (15) can ignite the detonator of the detonator (171) only when the first loading signal, the second loading signal, and the third loading signal are all applied sequentially, thereby preventing false detonation caused by a single sensor or a single condition misjudgment.

[0116] The proximity detection unit (172) is a sensor that determines proximity to a target drone and may include, for example, at least one of an RF proximity sensor, radar, ultrasonic sensor, laser distance sensor, or a proximity determination means based on specific signal strength.

[0117] For example, the proximity detection unit (172) may be a radar device (Target Detection Device, TDD) mounted on the upper and lower parts of the aircraft.

[0118] For example, the proximity detection unit (172) can generate a detection signal within a predetermined proximity range (e.g., about 3 m) from the target.

[0119] For example, the proximity detection unit (172) may be configured to include a plurality of radars positioned on the upper and lower sides of the aircraft (1), respectively, so as to enable three-dimensional proximity detection regardless of the approach direction of the target drone.

[0120] According to the above structure, the detonator (17) adopts an ignition method using a thermal battery so that the detonation energy source is kept in an inactive state in the pre-launch state and detonation is allowed only when all three safety loading conditions are sequentially satisfied, thus reducing the possibility of mis-detonation during pre-launch handling, the initial launch, and during flight.

[0121] The sensor unit (18) is a set of sensors for navigation and state estimation of the aircraft (1) and may include a GPS antenna (181), an IMU sensor (182), and an environment sensor (183). The output of the sensor unit (18) may be input to the integrated navigation module (151) of the integrated control unit (15).

[0122] The GPS antenna (181) receives GPS signals and provides information used to estimate the position and speed of the aircraft (1). The GPS antenna (181) may be configured, for example, to be arranged in two to improve position accuracy and enable heading extraction.

[0123] The IMU sensor (182) can measure the attitude, angular velocity, and acceleration of the aircraft (1), including an accelerometer and a gyroscope.

[0124] The environmental sensor (183) includes a sensor that measures atmospheric temperature, atmospheric pressure, and atmospheric speed, and may include, for example, a Pitot tube. The atmospheric speed and dynamic pressure information measured by the environmental sensor (183) can be used for speed control, stall prevention, and altitude estimation of the propulsion unit (14).

[0125] According to the above structure, the sensor unit (18) provides multiple sensor data from GPS, IMU, and environmental sensors to the integrated navigation module (151), thereby ensuring the accuracy and reliability of position, velocity, and attitude estimation based on multi-sensor fusion.

[0126] FIG. 5 is a flowchart of an operation method of an anti-drone aircraft according to one embodiment, FIG. 6 is a flowchart of a step of deploying wings according to one embodiment, and FIG. 7 is a flowchart of a step of performing detonation according to one embodiment.

[0127] The method of operating the anti-drone aircraft (2) is a method of operating the entire mission process in which the anti-drone aircraft launched from the ground is loaded into the launch tube, flies after launch to pursue the target drone, and finally neutralizes the target drone.

[0128] For example, the method of operating an anti-drone aircraft (2) includes the steps of launching the aircraft (21), deploying wings (22), performing navigation control (23), tracking a target (24), and performing detonation (25).

[0129] In the step (21) of launching the aircraft, the anti-drone aircraft (1) loaded into the launch tube is launched according to the launch command of the ground body. Before launch, the aircraft (1) can receive mission information and initial setting values ​​from the ground body through the ground connection device of the launch interlock unit (156).

[0130] In the wing deployment step (22), the tail wing and the main wing can be deployed sequentially so that the aircraft (1) is converted into a flight-capable shape after launch.

[0131] For example, the step of deploying the wings (22) may include a step of checking whether the ground connection device is separated (221), a step of deploying the tail wing (222), a step of checking whether the tail wing deployment is complete (223), a step of deploying the main wing (224), and a step of deploying the TRX antenna (225).

[0132] The step (221) of checking whether the ground connection device is separated is a step in which the integrated control unit (15) detects whether the ground connection device is separated according to the launch of the aircraft (1), and the integrated control unit (15) can perform the step (222) of deploying the subsequent tail fin only after the separation of the ground connection device is confirmed.

[0133] In the step (222) of deploying the tail, when the restraints on the four tail wings (131) of the deployable tail section (13) are released, each tail wing (131) can be automatically rotated outward from the fuselage by elastic restoring force and deployed. As shown in FIG. 3, the deployable tail section (13) can be deployed prior to the deployment of the deployable main wing section (12), i.e., the wing section (121), thereby enabling the attitude stabilization of the aircraft (1) to be secured quickly.

[0134] The step (223) of checking whether the tail fin deployment is complete is a step in which the integrated control unit (15) detects whether the deployment of the deployable tail fin unit (13) is complete, and the integrated control unit (15) can perform the step (224) of deploying the subsequent main wing only after it is confirmed that the tail fin deployment is complete.

[0135] For example, the integrated control unit (15) can check whether the tail fin has been fully deployed by the deployment switch (133) of the deployable tail fin unit (13).

[0136] In the step (224) of deploying the main wing, the integrated control unit (15) applies an electric signal to the deployment restraint unit (19) based on the tail wing deployment completion signal to release the sliding pin (191) that restrains the fixed part (123) of the wing part (121), so that as a result, the wing part (121) of the deployable main wing part (12) can be automatically deployed by the elastic restoring force of the rotation part (122).

[0137] In the step (225) of deploying the TRX antenna, as the deployment of the wing portion (121) is completed, the TRX antenna (163) provided on the upper or lower part of the fuselage of the anti-drone aircraft (1) can be deployed.

[0138] For example, in the step (225) of deploying the TRX antenna, the TRX antenna (163) located on the upper side can be deployed by automatically rotating upward through the elastic force of the spring actuation part (1631) as it is released from physical interference by the wing part (121).

[0139] For example, it should be noted that the step (225) of deploying the TRX antenna may be performed by releasing a device that mechanically prevents the TRX antenna (163) from being deployed through a separate actuator.

[0140] The step (23) of performing navigation control may be a step of estimating the position, speed, and attitude of the aircraft (1) by fusing GPS / IMU / environment sensor data of the sensor unit (18) through the integrated navigation module (151) of the integrated control unit (15), and controlling the propulsion unit (14) to maneuver the aircraft (1) toward the target direction.

[0141] The step of tracking a target (24) may be a step in which the seeker signal processing module (152) detects and tracks a target in the image of the seeker unit (11), and performs terminal guidance by reflecting the tracking result in navigation control.

[0142] The step (25) of performing the detonation is a step for neutralizing the target and may include a step of checking whether proximity detection is possible (251), a step of performing frequency interference (252), a step of checking the loading signal (253), and a step of igniting the detonator (254).

[0143] In the step (251) of checking for proximity detection, it can be determined whether the target drone has entered the detonation effect range by the signal of the proximity detection unit (172), and based on the proximity detection signal of the proximity detection unit (172), the integrated control unit (15) can confirm that the target drone is within the detonation-capable range.

[0144] For example, in the step (251) of checking whether proximity detection is present, the integrated control unit (15) may determine that proximity detection is present only when all of the following are satisfied: the proximity detection signal of the proximity detection unit (172), the image tracking (IR) signal and / or radar signal of the seeker unit (11).

[0145] In the step (252) of performing frequency disturbance, a disturbance signal through an RF amplifier (162) is transmitted to the operating frequency band of the target drone collected by the frequency analysis unit (164) of the transceiver (16), thereby inducing the weakening or blocking of the communication and control link of the target drone.

[0146] In the step (253) of checking the loading signal, the integrated control unit (15) can check whether all safety conditions for performing the detonation are satisfied.

[0147] In the step (253) of checking the loading signal, the integrated control unit (15) may perform the step (254) of finally igniting the detonator when the loading signal is finally confirmed, based on whether all three safety loading (ARM1 / ARM2 / ARM3) conditions are satisfied.

[0148] For example, in the step (253) of verifying the loading signal, the integrated control unit (15) may apply the final third loading signal (ARM3) only when all of the following are satisfied: the proximity detection signal of the proximity detection unit (172), the image tracking (IR) signal of the seeker unit (11), and / or the radar signal.

[0149] In the step (254) of igniting the detonator, when the integrated control unit (15) confirms that both the proximity detection condition and the loading condition are satisfied, an ignition signal is applied to the detonator (171) to perform ignition, thereby neutralizing the target drone.

[0150] For example, the integrated control unit (15) can apply a final ignition signal to the detonator (171) only under logical conditions where both image-based target confirmation by the seeker signal processing module (152) and physical proximity detection by the proximity detection unit (172) are satisfied.

[0151] According to an anti-drone aircraft and a method of operation therewith according to one embodiment, the deployment restraint part (19) releases the restraint of the deployable main wing part (12) only after the completion of deployment of the deployable tail wing part (13) is mechanically confirmed by the deployment switch (133), thereby preventing the main wing from deploying prematurely in an aerodynamically unstable state immediately after launch, and ensuring that initial attitude stabilization by the tail wing is secured in advance.

[0152] According to the anti-drone aircraft and the method of operation therewith according to one embodiment, since the deployment of the main wing is constrained at a physical level by the mechanical interlock of the deployment restraint part (19), unintended deployment caused by electronic false signals can be prevented even in an environment of electronic noise and mechanical impact immediately after launch.

[0153] According to an anti-drone aircraft and a method of operation thereof according to one embodiment, detonation is permitted only when the confirmation of mechanical deployment completion, the confirmation of safe distance separation, and the confirmation of entry into the target proximity range are all sequentially satisfied by a three-stage safety loading (ARM1 / ARM2 / ARM3) system, so the possibility of false detonation due to a single condition misjudgment can be reduced.

[0154] According to an anti-drone aircraft and a method of operation thereof according to one embodiment, when detonation is performed, a disturbance signal is simultaneously transmitted to the operating frequency band of the target drone collected by the frequency analysis unit (164), thereby blocking the communication link of the target drone and hindering the enemy's analysis of the cause of destruction.

[0155] Although embodiments have been described with reference to limited drawings as described above, those skilled in the art can make various modifications and variations from the description above. For example, appropriate results can be achieved even if the described techniques are performed in a different order than described, and / or components such as the described structure or device are combined or assembled in a form different from described, or replaced or substituted by other components or equivalents.

Claims

Claim 1 An anti-drone aircraft for detecting, tracking, and neutralizing a target drone comprises: a seeker unit for collecting image signals of the target drone; a deployable main wing unit installed on the upper part of a fuselage, maintained in a folded state parallel to the longitudinal direction of the fuselage when loaded into a launch tube, and converted into a fixed-wing shape capable of flight by rotating perpendicularly to the fuselage after launch to provide lift necessary for flight, and a pivot unit having a hinge or axis structure that allows rotation of the wing unit and equipped with an elastic restoring means to automatically rotate the wing unit to a predetermined angle through elastic force; a deployable tail wing unit that deploys ahead of the deployable main wing unit after launch to stabilize the attitude of the aircraft; a deployment restraint unit that mechanically restrains the rotation of the deployable main wing unit and is formed to protrude slidably toward the upper side of the fuselage when the wing unit is in a folded state and overlaps the fuselage in the vertical direction, and is equipped with a sliding pin that is inserted into or interferes with the wing unit; a propulsion unit that provides thrust to the aircraft; and a detonator unit capable of detonating under conditions of proximity to the target drone for neutralizing the target drone. The anti-drone aircraft comprises an integrated control unit that drives the propulsion unit to perform flight and processes the image signal of the seeker unit to perform search and tracking of the target drone, wherein the deployable tail section comprises four tail wings radially spaced around the fuselage, a slot-type opening communicating so that each of the four tail wings rotates and is stored inside the fuselage along the longitudinal direction of the fuselage, and a deployment switch that physically interferes when the deployment of the four tail wings is completed to generate a deployment completion signal, wherein each of the four tail wings is folded inside when loaded into a launch tube through the slot-type opening and deploys to the outside after launch of the anti-drone aircraft, and the integrated control unit, when the deployment completion signal is input from the deployment switch, lowers the sliding pin to release the restraint on the wing section to perform the deployment of the deployable main wing section. Claim 2 delete Claim 3 delete Claim 4 delete Claim 5 delete Claim 6 delete Claim 7 The anti-drone aircraft according to claim 1, wherein the propulsion unit is installed at the rear of the body and includes a plurality of variable blades that rotate at high speed by a motor and can pivot around a rotation axis perpendicular to the rotation axis, and wherein the plurality of variable blades are pivoted forward so as to be close to the rotation axis when the anti-drone aircraft is loaded into a launch tube, but are tilted backward under the acceleration load generated during launch after the launch of the anti-drone aircraft and aligned in a state horizontal to the rotation axis. Claim 8 An anti-drone aircraft for detecting, tracking, and neutralizing a target drone comprises: a seeker unit for collecting image signals of the target drone; a deployable main wing unit installed on the upper part of a fuselage, maintaining a folded state parallel to the longitudinal direction of the fuselage when loaded into a launch tube, and converting into a fixed-wing shape capable of flight by rotating perpendicularly to the fuselage after launch to provide lift necessary for flight, and a pivot unit having a hinge or axis structure that allows rotation of the wing unit and equipped with an elastic restoring means to automatically rotate the wing unit to a predetermined angle through elastic force; a deployable tail wing unit that deploys ahead of the deployable main wing unit after launch to stabilize the attitude of the aircraft; a deployment restraint unit that mechanically restrains the rotation of the deployable main wing unit; a propulsion unit that provides thrust to the aircraft; a detonator unit capable of detonating under conditions of proximity to the target drone for neutralizing the target drone; and an integrated control unit that drives the propulsion unit to perform flight and processes image signals from the seeker unit to search for and track the target drone.The apparatus includes a transceiver that performs RF communication between the aircraft and the ground vehicle, and the deployable tail section includes four tail wings radially spaced around the fuselage and a slot-shaped opening that communicates so that each of the four tail wings rotates and is stored inside the fuselage along the longitudinal direction of the fuselage, and the four tail wings are each folded inside when loaded into the launch tube through the slot-shaped opening, and then deploy outward after the launch of the anti-drone aircraft, and the integrated control unit applies a release signal to the deployment restraint unit to release the restraint of the deployable main wing section after confirming that the deployment of the deployable tail section is complete, and the transceiver includes a TRX antenna installed on the upper side of the fuselage to radiate and receive RF signals and is rotatable to deploy outward from the fuselage via elastic force while in a folded state stored inside the fuselage, and the TRX antenna is in a state where it is interfered from above by the wing section in the folded state when the anti-drone aircraft is loaded into the launch tube and is stored inside the fuselage. An anti-drone aircraft characterized by being restrained, but unfolding to the outside of the fuselage as the restraint by the wing portion is released as the deployment of the deployable main wing portion is performed after the launch of the anti-drone aircraft. Claim 9 In claim 8, the detonator comprises: a detonator ignited by a thermal battery; and a proximity detection unit that determines proximity to a target, and the integrated control unit applies a loading signal to the detonator based on the proximity detection signal of the proximity detection unit, an anti-drone aircraft. Claim 10 An anti-drone aircraft according to claim 9, wherein the integrated control unit is capable of collecting the operating frequency band of the target drone through the transceiver, and the integrated control unit transmits a disturbance signal to the frequency band of the target drone collected through the transceiver when detonation is performed through the detonator. Claim 11 In claim 10, the integrated control unit further comprises an image processing module that performs hardware-based encoding on an image signal collected from the explorer unit to generate compressed image data; and the compressed image data is transmitted in real time to a ground body via the transceiver unit, characterized in that the anti-drone aircraft. Claim 12 A method for operating an anti-drone aircraft for detecting, tracking, and neutralizing a target drone comprises: a step of launching an anti-drone aircraft loaded into a launch tube; a step of deploying wings, wherein, after launch, a deployable tail section having four tail wings radially spaced around a fuselage and constrained in a folded state along the longitudinal direction of the fuselage, and a deployable main wing section having a wing section installed on the upper part of the fuselage and aligned parallel to the longitudinal direction of the fuselage and constrained in a folded state; a step of performing navigation control of the anti-drone aircraft; a step of tracking a target drone through a seeker; and a step of performing detonation under conditions of proximity to the target drone to neutralize the target drone, wherein the step of deploying wings comprises: a step of checking whether the anti-drone aircraft and a ground connection device are separated; a step of deploying the deployable tail section by releasing the restraint of the four tail wings and rotating the four tail wings outside the fuselage; and a step of confirming the completion of deployment of the deployable tail section. A method for operating an anti-drone aircraft, comprising the step of deploying the deployable main wing by releasing the physical restraint of the wing portion, thereby allowing the wing portion to rotate vertically relative to the fuselage by elastic force and converting it into a fixed wing shape capable of flight, wherein the step of checking whether the ground connection device is separated is performed prior to the step of deploying the deployable tail wing, and when a separation signal of the ground connection device connected to the anti-drone aircraft prior to launch is applied, the step of deploying the deployable tail wing is performed, and when the deployment of the deployable tail wing is completed, a deployment completion signal is generated by a deployment switch that is physically interfered with, and in the step of checking the deployment completion of the deployable tail wing, the step of deploying the deployable main wing is performed after the deployment completion of the deployable tail wing is confirmed by the deployment completion signal. Claim 13 delete Claim 14 delete Claim 15 delete Claim 16 In claim 12, the anti-drone aircraft comprises a TRX antenna rotatably installed on the upper side of the fuselage to radiate and receive RF signals, and constrained to be housed inside the fuselage by interference from the upper side by the wing portion before the deployable main wing portion is deployed, and the step of deploying the wing further comprises a step of deploying the TRX antenna such that, as the step of deploying the deployable main wing portion is performed, the physical constraint by the wing portion is released, and the TRX antenna is rotated in the direction of the upper side of the fuselage by elastic force. Claim 17 A method for operating an anti-drone aircraft according to claim 12, wherein the step of performing the detonation comprises: a step of confirming proximity detection by detecting whether the target drone has entered a predetermined proximity range; and a step of applying a loading signal to a detonator based on a proximity detection signal from a proximity detection unit. Claim 18 In claim 17, the loading signal comprises: a first loading signal applied when it is confirmed that the deployment of the deployable tail section and the deployable main wing section is mechanically completely completed; a second loading signal applied when it is confirmed that the anti-drone aircraft is separated from a safety zone where a launch base and operating personnel are located by a predetermined distance or more; and a third loading signal applied when it is confirmed that the target drone has entered within a predetermined proximity range; and in the step of applying the loading signal, the detonator of the detonator is ignited only when the first loading signal, the second loading signal, and the third loading signal are all applied sequentially. Claim 19 In claim 17, the step of performing the detonation further comprises the step of collecting the operating frequency band of the target drone and, when performing the detonation, transmitting a disturbance signal to the collected frequency band to perform frequency disturbance; a method for operating an anti-drone aircraft.

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