Kite type laser anti-invasion security system

Abstract

The application discloses a kite type laser anti-no security system and relates to the technical field of unmanned aerial laser, which comprises an unmanned aerial load platform, a follow-sighting and launching subsystem, a ground light source and management subsystem and a comprehensive cable, the unmanned aerial load platform is provided with a plurality of butt joint ends for connecting loads; the follow-sighting and launching subsystem is arranged on the unmanned aerial load platform and is connected with the unmanned aerial load platform through the butt joint ends; the ground light source and management subsystem is used for controlling the unmanned aerial load platform and also supplies energy for the unmanned aerial load platform; one end of the comprehensive cable is connected with the unmanned aerial load platform, and the other end of the comprehensive cable is connected with the ground light source and management subsystem, and the comprehensive cable comprises an electric cable and an optical fiber. The kite type laser anti-no security system has the follow-sighting and launching subsystem carried on the unmanned aerial platform, the light source is arranged on the ground end, the detection visual field is wider, and the deployment is more flexible.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) laser technology, and in particular to a kite-shaped laser anti-security system. Background Technology

[0002] Currently, lasers possess advantages such as fast response speed, high aiming accuracy, and low cost of destroying targets, making them one of the ideal means of countering low, slow, and small targets, and demonstrating broad application prospects. A laser system typically consists of three parts: a laser source subsystem, a tracking and firing subsystem, and an integrated control subsystem. These three subsystems usually adopt a compact layout design and are integrated into various mounting platforms, representing the main form of laser system development and production at present.

[0003] However, the aforementioned laser countermeasures systems have limitations in practical applications. On the one hand, the system's "low-to-high" field of view is limited, resulting in insufficient ability to detect near-ground targets; on the other hand, high-energy laser systems are typically large and heavy, lacking flexibility in application, and are easily constrained by space in confined areas such as dense forests and buildings. Summary of the Invention

[0004] This invention aims to solve at least one of the technical problems existing in the prior art. To this end, this invention proposes a kite-style laser anti-grab security system. The tracking and firing subsystem is mounted on a drone platform, while the light source is located on the ground, resulting in a wider detection field of view and more flexible deployment. This system abandons the compact layout of traditional laser anti-grab systems, proposing a new structure with separate layouts for the light source and tracking / firing subsystems. The tracking and firing subsystem is mounted on the drone platform, while the light source and integrated control subsystems are deployed on the ground (portable, vehicle-mounted, etc.), connected to the drone platform by integrated cables. This configuration ensures a good detection field of view while significantly reducing the load on the drone platform, offering excellent portability and convenient deployment.

[0005] According to an embodiment of the present invention, a kite-type laser anti-security system includes a drone payload platform, wherein the drone payload platform has multiple docking ends for connecting payloads; The tracking and firing subsystem is installed on the UAV payload platform and is connected to the UAV payload platform through the docking terminal. A ground-based lighting and management subsystem is used to control the UAV payload platform and also supplies power to the UAV payload platform. The integrated cable includes a power cable and an optical fiber. One end of the integrated cable is connected to the UAV payload platform, and the other end of the integrated cable is connected to the ground light source and management subsystem.

[0006] The kite-type laser anti-security system according to embodiments of the present invention has at least the following beneficial effects: the UAV payload platform can connect to a payload, such as a tracking and firing subsystem, via a docking end; the tracking and firing subsystem is mounted on the UAV payload platform, utilizing the UAV to expand the detection field of view; the ground light source and management subsystem is connected to the UAV payload platform via a composite cable, and the ground light source and management subsystem can power the UAV payload platform to achieve kite-like tethering; the composite cable includes optical fiber, which can generate high-energy laser from the ground light source and management subsystem and transmit it to the UAV payload platform via the optical fiber, reducing the load on the UAV payload platform and reducing heat dissipation pressure.

[0007] According to some embodiments of the present invention, the tracking and firing subsystem includes a gimbal stabilization component and a laser tracking and firing component, the gimbal stabilization component being connected to the UAV payload platform, and the laser tracking and firing component being disposed on the gimbal stabilization component.

[0008] According to some embodiments of the present invention, the gimbal stabilization assembly includes a first connector and a second connector. The first connector has a first rotating shaft, which is connected to the UAV payload platform. The first connector is rotatable around the first rotating shaft and has a mounting groove. The second connector has a second rotating shaft, which is disposed in the mounting groove. The second rotating shaft is mounted between a set of opposing sidewalls of the mounting groove. The second connector is rotatable around the second rotating shaft, which is perpendicular to the first rotating shaft.

[0009] According to some embodiments of the present invention, the first connecting seat has a first cavity inside, and the second connecting seat has a second cavity inside. The laser tracking and emitting assembly includes a detection camera, a beam splitter, a first reflector, a second reflector, a third reflector, a concave mirror, and a convex mirror. The detection camera, the beam splitter, the first reflector, and the second reflector are all disposed in the first cavity. The beam splitter is disposed axially on the first rotating shaft. The detection camera and the first reflector are respectively disposed on both sides of the beam splitter. The second reflector is disposed axially on the second rotating shaft. The light reflected by the second reflector can pass through... After passing through the first reflector and the beam splitter, the light reaches the detection camera. The third reflector, the concave mirror, and the convex mirror are disposed in the second cavity. The third reflector is disposed on the axial direction of the second rotating shaft. The concave mirror and the convex mirror are respectively disposed on both sides of the third reflector, and the convex mirror is disposed on the opening side of the second cavity. The light from the outside of the second connector can pass through the concave mirror, the convex mirror, and the third reflector to reach the second reflector. The light outlet of the optical fiber is coaxial with the first rotating shaft, so that the laser emitted from the optical fiber passes through the beam splitter and reaches the first reflector.

[0010] According to some embodiments of the present invention, a vibration damping device is provided between the gimbal stabilization component and the UAV payload platform.

[0011] According to some embodiments of the present invention, the unmanned aerial vehicle (UAV) payload platform includes a frame and four rotor assemblies, the four rotor assemblies being centrally symmetrical about the midpoint of the frame.

[0012] According to some embodiments of the present invention, the airflow generated by the rotor assembly is parallel to the rotation axis of the rotor assembly, and the rotation axis of the rotor assembly forms an angle with the vertical direction, such that the airflow generated by the rotor assembly is directed towards the outside of the frame.

[0013] According to some embodiments of the present invention, the rotor assembly includes a rotating shaft seat, a blade holder, a blade clamp, and a blade mechanism. The rotating shaft seat is disposed on the frame, the blade holder is convexly connected to the rotating shaft seat, the blade holder has a U-shaped opening, the blade clamp is mounted between the openings of the blade holder, the blade clamp has a third rotating shaft, the third rotating shaft is perpendicular to the axial direction of the rotating shaft seat, the blade mechanism passes through the opening of the blade holder, and the blade mechanism is fixedly connected to the blade clamp. The rotating shaft seat can drive the blade mechanism to rotate, and the blade mechanism can oscillate around the third rotating shaft.

[0014] According to some embodiments of the present invention, the composite cable includes an outer sheath, a power cable transmission line, a signal cable transmission line, and a hollow optical fiber, wherein the power cable transmission line, the signal cable transmission line, and the hollow optical fiber are all disposed inside the outer sheath.

[0015] According to some embodiments of the present invention, a winch device is also included, on which the composite cable is wound, the winch device being capable of unwinding and rewinding the composite cable.

[0016] Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0017] The present invention will be further described below with reference to the accompanying drawings and embodiments, wherein: Figure 1 This is a schematic diagram of the structure of the kite-type laser anti-security system according to an embodiment of the present invention; Figure 2 This is a schematic diagram of the gimbal stabilization component according to an embodiment of the present invention; Figure 3 This is a schematic diagram of the tracking and firing subsystem according to an embodiment of the present invention; Figure 4This is a schematic diagram of the rotor assembly according to an embodiment of the present invention; Figure 5 This is a cross-sectional view of the integrated cable according to an embodiment of the present invention; Figure 6 This is a schematic diagram of the ground light source and management subsystem and winch device according to an embodiment of the present invention.

[0018] Icon labels: The unmanned aerial vehicle (UAV) payload platform 100, frame 110, rotor assembly 120, rotating shaft seat 121, propeller seat 122, propeller clip 123, propeller mechanism 124, tracking and firing subsystem 200, gimbal stabilization assembly 210, first connecting seat 211, second connecting seat 212, first rotating shaft 213, mounting slot 214, second rotating shaft 215, laser tracking and firing assembly 220, detection camera 221, beam splitter 222, first reflector 223, second reflector 224, third reflector 225, concave mirror 226, convex mirror 227, ground lighting and management subsystem 300, winch device 310, integrated cable 400, power cable transmission line 410, signal cable transmission line 420, and hollow optical fiber 430. Detailed Implementation

[0019] Embodiments of the present invention are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0020] In the description of this invention, it should be understood that the orientation descriptions, such as up, down, etc., are based on the orientation or positional relationship shown in the drawings and are only for the convenience of describing this invention and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0021] In the description of this invention, "multiple" refers to two or more. The use of "first" and "second" is for distinguishing technical features only and should not be construed as indicating or implying relative importance, or implicitly indicating the number of indicated technical features or their sequential relationship.

[0022] In the description of this invention, unless otherwise explicitly defined, terms such as "set up," "install," and "connect" should be interpreted broadly, and those skilled in the art can reasonably determine the specific meaning of the above terms in this invention in conjunction with the specific content of the technical solution.

[0023] Reference Figure 1As shown, an embodiment of the kite-type laser anti-drone security system of the present invention includes a drone payload platform 100, a tracking and firing subsystem 200, a ground light source and management subsystem 300, and an integrated cable 400. It should be understood that "anti-drone" in this application refers to countering drones.

[0024] The UAV payload platform 100 has multiple docking terminals for connecting payloads; the tracking and firing subsystem 200 is located on the UAV payload platform 100 and is connected to the UAV payload platform 100 through the docking terminals; the ground lighting and management subsystem 300 is used to control the UAV payload platform 100 and also supplies power to the UAV payload platform 100; one end of the integrated cable 400 is connected to the UAV payload platform 100, and the other end of the integrated cable 400 is connected to the ground lighting and management subsystem 300, the integrated cable 400 including electrical cable and optical fiber.

[0025] The UAV payload platform 100 can connect to a payload, such as the tracking and firing subsystem 200, via a docking terminal. In the embodiments of this application, the tracking and firing subsystem 200 can realize the functions of tracking, aiming, and firing high-energy lasers. The tracking and firing subsystem 200 is mounted on the UAV payload platform 100, which expands the detection field of view of the UAV and makes it more flexible when using lasers to illuminate targets. The ground light source and management subsystem 300 is a comprehensive platform with a power source and control system, and is connected to the UAV payload platform 100 via a comprehensive cable 400. The ground light source and management subsystem 300 can provide power to the UAV payload platform 100, enabling kite-like tethering, that is, the UAV payload platform 100 can stay in the air for a long time. The comprehensive cable 400 includes optical fibers, which can transmit the high-energy laser generated by the ground light source and management subsystem 300 to the UAV payload platform 100 through the optical fibers. Because generating lasers requires a large amount of energy and generates a significant amount of heat, moving the laser-generating components to the ground-based light source and management subsystem 300 (the ground end) reduces the load on the UAV payload platform 100 and lowers its heat dissipation pressure. It should be understood that the ground-based light source and management subsystem 300 includes at least a high-power laser light source and cooling module, as well as a data processing module, human-machine interface equipment, and external power supply equipment. The aforementioned kite-style laser anti-drone security system can be flexibly applied in confined areas such as dense forests and buildings to establish a defense system against attacks from enemy UAV swarms. Specifically, the tracking and firing subsystem 200, under the control of the ground-based light source and management subsystem 300, quickly identifies targets and responds with laser illumination.

[0026] It is important to understand that the kite-type laser anti-unidentified flying object (UFO) security system of this invention is mainly used for security measures, such as managing the airspace at some event venues to maintain clear airspace. When encountering uncontrolled or unidentified flying objects approaching, relying solely on ground personnel observation and radio countermeasures is insufficient for comprehensive protection. The kite-type laser anti-unidentified flying object security system proposed in this invention, however, uses a laser mounted on an unmanned aerial vehicle (UAV) platform, resulting in a wider detection field and greater operational flexibility.

[0027] It is understood that the tracking and firing subsystem 200 includes a gimbal stabilization component 210 and a laser tracking and firing component 220. The gimbal stabilization component 210 is connected to the UAV payload platform 100, and the laser tracking and firing component 220 is located on the gimbal stabilization component 210.

[0028] The gimbal stabilization component 210 can filter or reduce the minute displacements such as vibrations generated by the UAV payload platform 100, thereby improving the stability of the laser tracking and firing component 220. This makes it easier for the laser tracking and firing component 220 to detect and identify targets, and easier to adjust and control the irradiation point when irradiating a target with a laser.

[0029] Reference Figure 2 As shown, in some embodiments, it can be understood that the gimbal stabilization component 210 includes a first connecting seat 211 and a second connecting seat 212. The first connecting seat 211 has a first rotating shaft 213, which is connected to the UAV payload platform 100. The first connecting seat 211 is rotatable around the first rotating shaft 213. The first connecting seat 211 has a mounting groove 214. The second connecting seat 212 has a second rotating shaft 215. The second connecting seat 212 is disposed in the mounting groove 214. The second rotating shaft 215 is mounted between a set of opposing sidewalls of the mounting groove 214. The second connecting seat 212 is rotatable around the second rotating shaft 215. The second rotating shaft 215 is perpendicular to the first rotating shaft 213.

[0030] The gimbal stabilization component 210 often uses a more mature electronic gimbal. That is, both the first rotating axis 213 and the second rotating axis 215 are driven by motors, and the driving adjustment and control of the motors are managed by the ground light source and management subsystem 300.

[0031] Reference Figure 3As shown, it can be understood that the first connecting seat 211 has a first cavity inside, and the second connecting seat 212 has a second cavity inside. The laser tracking and aiming emission assembly 220 includes a detection camera 221, a beam splitter 222, a first reflector 223, a second reflector 224, a third reflector 225, a concave mirror 226, and a convex mirror 227. The detection camera 221, beam splitter 222, first reflector 223, and second reflector 224 are all disposed in the first cavity. The beam splitter 222 is disposed on the axial direction of the first rotating shaft 213. The detection camera 221 and the first reflector 223 are respectively disposed on both sides of the beam splitter 222. The second reflector 224 is disposed on the axial direction of the second rotating shaft 215. The reflected light from the second reflector 224 can reach the detector camera 221 after passing through the first reflector 223 and the beam splitter 222. The third reflector 225, the concave mirror 226, and the convex mirror 227 are disposed in the second cavity. The third reflector 225 is disposed on the axial direction of the second rotating shaft 215. The concave mirror 226 and the convex mirror 227 are respectively disposed on both sides of the third reflector 225, and the convex mirror 227 is disposed on the opening side of the second cavity. The light from the outside of the second connector 212 can reach the second reflector 224 after passing through the concave mirror 226, the convex mirror 227, and the third reflector 225. The light outlet of the optical fiber is coaxial with the first rotating shaft 213, so that the laser emitted from the optical fiber reaches the first reflector 223 after passing through the beam splitter 222.

[0032] The light from the target object enters the second cavity through the opening side, reaches the concave mirror 226, is reflected by the concave mirror 226, reaches the convex mirror 227, is reflected by the convex mirror 227, reaches the third mirror 225, is reflected by the third mirror 225, reaches the second mirror 224, is reflected by the second mirror 224, reaches the first mirror 223, is reflected by the first mirror 223, and after passing through the beam splitter 222, directly reaches the detection camera 221. The detection camera 221 acquires the image and sends the data to the ground light source and management subsystem 300 for processing, and controls the orientation of the opening side of the second cavity to track and aim at the target object. It is important to understand that the beam splitter 222, based on the reflection and transmission characteristics of light, uses coating or optical structure design to allow some light to be reflected and some light to be transmitted. Therefore, the laser light transmitted through the fiber optic cable can also illuminate the first mirror 223 after passing through the beam splitter 222. It is important to understand that the laser's emission path is opposite to the target's light path. The high-energy laser strikes the first reflecting mirror 223, is reflected to the second reflecting mirror 224, then to the third reflecting mirror 225, then to the convex mirror 227, then to the concave mirror 226, and finally, after reflection by the concave mirror 226, the laser exits from the opening of the second cavity and strikes the target, thus destroying it.

[0033] It is understandable that a vibration damping device is provided between the gimbal stabilization component 210 and the UAV payload platform 100.

[0034] The vibration damping device can further reduce the vibration generated by the UAV payload platform 100 and improve the stability of the gimbal stabilization component 210 itself. That is, the vibration damping device works in conjunction with the gimbal stabilization component 210; the vibration damping device provides passive vibration damping for the tracking and firing subsystem 200, while the gimbal stabilization component 210 provides active vibration damping for the tracking and firing subsystem 200. Preferably, the vibration damping device is a rubber-grease isolator, which provides passive vibration damping for the tracking and firing subsystem 200.

[0035] It is understood that the UAV payload platform 100 includes a frame 110 and four rotor assemblies 120, which are symmetrical about the midpoint of the frame 110.

[0036] Furthermore, it can be understood that the airflow generated by the rotor assembly 120 is parallel to the rotation axis of the rotor assembly 120, and the rotation axis of the rotor assembly 120 forms an angle with the vertical direction, so that the airflow generated by the rotor assembly 120 is directed towards the outside of the frame 110.

[0037] Through the above structural design, the downward airflow generated by the rotor assembly 120 does not overlap with the laser path emitted by the tracking and firing subsystem 200 in space, thereby minimizing the impact of airflow on the quality of the laser beam.

[0038] Reference Figure 4 As shown, it can be understood that the rotor assembly 120 includes a rotating shaft seat 121, a blade holder 122, a blade clamp 123, and a blade mechanism 124. The rotating shaft seat 121 is mounted on the frame 110. The blade holder 122 is connected to the rotating shaft seat 121 in a driving connection. The blade holder 122 has a U-shaped opening. The blade clamp 123 is mounted between the openings of the blade holder 122. The blade clamp 123 has a third rotating shaft, which is perpendicular to the axial direction of the rotating shaft seat 121. The blade mechanism 124 passes through the opening of the blade holder 122 and is fixedly connected to the blade clamp 123. The rotating shaft seat 121 can drive the blade mechanism 124 to rotate, and the blade mechanism 124 can swing around the third rotating shaft.

[0039] When the UAV payload platform 100 is in flight, the propeller mechanism 124 can swing around the third axis to achieve an effect similar to a flapping hinge, which can improve the flight performance of the UAV payload platform 100.

[0040] Reference Figure 5As shown, it can be understood that the composite cable 400 includes an outer sheath, a power cable transmission line 410, a signal cable transmission line 420, and a hollow optical fiber 430, with the power cable transmission line 410, the signal cable transmission line 420, and the hollow optical fiber 430 all located inside the outer sheath.

[0041] Power cable transmission line 410 provides power to the UAV payload platform 100, signal cable transmission line 420 provides various control signals to the UAV payload platform 100, and the ground light source and management subsystem 300 can receive various signals transmitted back from the UAV payload platform 100 via signal cable transmission line 420. Hollow-core optical fiber 430 is used to transmit high-energy laser to the UAV payload platform 100 and is emitted through the tracking and firing subsystem 200. Preferably, flexible hollow-core optical fiber 430 is used, which can carry higher energy laser beams. Specifically, the hollow-core optical fiber 430 can transmit a high-power laser with a power of not less than 5kW, a transmission efficiency of not less than 90%, and a beam quality M. 2 Not less than 1.5.

[0042] Reference Figure 1 and Figure 6 As shown, it can be understood that it also includes a winch device 310, on which the composite cable 400 is wound, and the winch device 310 is capable of winding and unwinding the composite cable 400.

[0043] Preferably, the radius of the winch device 310 is not less than 150mm. The winch device 310 is controlled by the ground light source and management subsystem 300 and can be linked with the UAV payload platform 100. It can wind and unwind the integrated cable 400 according to the flight altitude and flight distance of the UAV payload platform 100, and provide the UAV payload platform 100 with an integrated cable 400 of appropriate length.

[0044] The embodiments of the present invention have been described in detail above with reference to the accompanying drawings. However, the present invention is not limited to the above embodiments. Within the scope of knowledge possessed by those skilled in the art, various changes can be made without departing from the spirit of the present invention.

Claims

1. A kite-style laser anti-security system, characterized in that, include: A drone payload platform (100) having multiple docking ends for connecting payloads; A tracking and firing subsystem (200) is installed on the UAV payload platform (100) and is connected to the UAV payload platform (100) through the docking end; A ground-based lighting and management subsystem (300) is used to control the UAV payload platform (100) and also provides power to the UAV payload platform (100). The integrated cable (400) is connected at one end to the UAV payload platform (100) and at the other end to the ground light source and management subsystem (300). The integrated cable (400) includes a cable and an optical fiber.

2. The kite-type laser anti-security system according to claim 1, characterized in that, The tracking and firing subsystem (200) includes a gimbal stabilization component (210) and a laser tracking and firing component (220). The gimbal stabilization component (210) is connected to the UAV payload platform (100), and the laser tracking and firing component (220) is disposed on the gimbal stabilization component (210).

3. The kite-type laser anti-security system according to claim 2, characterized in that, The gimbal stabilization component (210) includes a first connector (211) and a second connector (212). The first connector (211) has a first pivot (213) connected to the UAV payload platform (100). The first connector (211) is rotatable around the first pivot (213). The first connector (211) has an installation groove (214). The second connector (212) has a second pivot (215). The second connector (212) is disposed in the installation groove (214). The second pivot (215) is mounted between a set of opposing sidewalls of the installation groove (214). The second connector (212) is rotatable around the second pivot (215). The second pivot (215) is perpendicular to the first pivot (213).

4. The kite-type laser anti-security system according to claim 3, characterized in that, The first connecting seat (211) has a first cavity inside, and the second connecting seat (212) has a second cavity inside. The laser tracking and firing assembly (220) includes a detection camera (221), a beam splitter (222), a first reflector (223), a second reflector (224), a third reflector (225), a concave mirror (226), and a convex mirror (227). The detection camera (221), the beam splitter (222), the first reflector (223), and the second reflector (224) are all disposed in the first cavity. The beam splitter (222) is disposed on the axial direction of the first rotating shaft (213). The detection camera (221) and the first reflector (223) are respectively disposed on both sides of the beam splitter (222). The second reflector (224) is disposed on the axial direction of the second rotating shaft (215). The light reflected by the second reflector (224) can pass through... The first reflector (223) and the beam splitter (222) reach the detection camera (221). The third reflector (225), the concave mirror (226), and the convex mirror (227) are disposed in the second cavity. The third reflector (225) is disposed on the axial direction of the second rotating shaft (215). The concave mirror (226) and the convex mirror (227) are respectively disposed on both sides of the third reflector (225), and the convex mirror (227) is disposed on the opening side of the second cavity. The light from the outside of the second connector (212) can reach the second reflector (224) after passing through the concave mirror (226), the convex mirror (227), and the third reflector (225). The light outlet of the optical fiber is coaxial with the first rotating shaft (213), so that the laser emitted from the optical fiber reaches the first reflector (223) after passing through the beam splitter (222).

5. The kite-type laser anti-security system according to claim 2, characterized in that, A vibration damping device is provided between the gimbal stabilization component (210) and the UAV payload platform (100).

6. The kite-type laser anti-security system according to claim 1, characterized in that, The unmanned aerial vehicle (UAV) payload platform (100) includes a frame (110) and four rotor assemblies (120), which are symmetrical about the midpoint of the frame (110).

7. The kite-type laser anti-security system according to claim 6, characterized in that, The airflow generated by the rotor assembly (120) is parallel to the rotation axis of the rotor assembly (120), and the rotation axis of the rotor assembly (120) forms an angle with the vertical direction, so that the airflow generated by the rotor assembly (120) is directed toward the outside of the frame (110).

8. The kite-type laser anti-security system according to claim 6, characterized in that, The rotor assembly (120) includes a rotating shaft seat (121), a propeller seat (122), a propeller clamp (123), and a blade mechanism (124). The rotating shaft seat (121) is disposed on the frame (110). The propeller seat (122) is connected to the rotating shaft seat (121) in a transmission manner. The propeller seat (122) has a U-shaped opening. The propeller clamp (123) is mounted between the openings of the propeller seat (122). The propeller clamp (123) has a third rotating shaft. The third rotating shaft is perpendicular to the axial direction of the rotating shaft seat (121). The blade mechanism (124) passes through the opening of the propeller seat (122) and is fixedly connected to the propeller clamp (123). The rotating shaft seat (121) can drive the blade mechanism (124) to rotate. The blade mechanism (124) can swing around the third rotating shaft.

9. The kite-type laser anti-security system according to claim 1, characterized in that, The composite cable (400) includes an outer sheath, a power cable transmission line (410), a signal cable transmission line (420), and a hollow optical fiber (430), wherein the power cable transmission line (410), the signal cable transmission line (420), and the hollow optical fiber (430) are all disposed inside the outer sheath.

10. The kite-type laser anti-security system according to claim 1, characterized in that, It also includes a winch device (310) on which the composite cable (400) is wound, the winch device (310) being capable of unwinding and rewinding the composite cable (400).

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