Modular high-speed interceptor drone

Abstract

The utility model discloses a modularization high -speed intercepts unmanned plane, including modularization segmented fuselage, X type thin airfoil wing, power unit, core function subassembly and heat radiation structure, modularization segmented fuselage is constituted by nose, mid -fuselage and tail cover three sections, and X type thin airfoil wing is symmetrically set in the lower part of mid -fuselage two two, and X type thin airfoil wing end is equipped with wing tip fairing, power unit is constituted by four high KV value brushless motor and power paddle, and core function subassembly is constituted by radar seeker, combat unit, lithium battery, four in one electronic governor and flight control, wherein, radar seeker is installed in the inside of nose, combat unit is built -in mid -fuselage front position, and lithium battery is fixed in the rear end position of mid -fuselage, and the application is through the optimization aerodynamic layout, adopts high thrust -weight ratio power design and modularization structure, realizes the unity of high -speed response, high -efficient heat dissipation and convenient maintenance, fills the deficiency of existing intercept unmanned plane in speed and maneuverability.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, specifically a modular high-speed interception UAV. Background Technology

[0002] With the rapid popularization and application of drone technology, illegal flight targets such as "black flight" drones and maliciously intruding drones pose a serious threat to low-altitude security in key areas such as airports, military restricted areas, and important conference venues.

[0003] Using drones for counter-interception has many shortcomings: conventional multi-rotor drones generally have a flight speed of less than 140 km / h, resulting in a slow response and difficulty in quickly reaching the interception area; some fixed-wing interception drones have unreasonable aerodynamic layout designs, resulting in high aerodynamic drag at high speeds, and their onboard electronic equipment and power components are prone to overheating and failure due to insufficient heat dissipation; most interception drones adopt an integrated fuselage structure, making maintenance and repair inconvenient, and the replacement efficiency of core components such as warheads and batteries is low, which cannot meet the requirements of high-frequency interception missions. Utility Model Content

[0004] To achieve the above objectives, this application provides a modular high-speed interceptor unmanned aerial vehicle (UAV), comprising a modular segmented fuselage, X-shaped thin-winged wings, a power unit, core functional components, and a heat dissipation structure; the modular segmented fuselage consists of three sections: a nose, a mid-fuselage, and a tail fairing; the X-shaped thin-winged wings are symmetrically arranged in pairs on the lower part of the mid-fuselage, and wingtip fairings are provided at the tips of the X-shaped thin-winged wings; the power unit consists of four high-KV brushless motors and a propeller; The core functional components consist of a radar seeker, a warhead, a lithium battery, a four-in-one electronic speed controller (ESC), and a flight controller. The radar seeker is installed inside the nose, the warhead is built into the front of the mid-fuselage, the lithium battery is fixed at the rear of the mid-fuselage, and the four-in-one ESC and flight controller are integrated into the front of the tail cowl via an equipment mounting plate. The ESC is electrically connected to the high-KV brushless motor, and the flight controller maintains communication connections with both the radar seeker and the ESC. The heat dissipation structure includes four NACA air intakes symmetrically arranged at the front of the fuselage, and air vents on the tail cover.

[0005] Furthermore, the head, middle fuselage, and tail cover are connected in a detachable manner by threaded connections.

[0006] Furthermore, the high-KV brushless motor is partially embedded in the wingtip fairing, and its drive shaft is connected to the propeller, forming a tail-thrust power layout with a thrust-to-weight ratio greater than 6:1.

[0007] Furthermore, the modular segmented fuselage is made of either carbon fiber composite material or ABS material, and its shape is cylindrical like a rocket.

[0008] Furthermore, the air vents have multiple rectangular openings, and the NACA air intake duct penetrates the internal cavity of the fuselage and forms an airflow cooling channel between the air vents and the air outlets.

[0009] Furthermore, the X-shaped thin-wing adopts a delta-shaped thin-wing configuration, and the wingtip fairing is streamlined.

[0010] Furthermore, the warhead is cylindrical and has mounting plates on its sides, and the interior of the warhead is hollow.

[0011] Because of the adoption of the above technical solution, this utility model has the following beneficial effects: 1. Extremely fast speed response: The tail thrust power layout is equipped with a high KV value brushless motor, with a thrust-to-weight ratio of more than 6:1. The maximum flight speed can reach 320km / h, which is far higher than that of conventional multi-rotor drones. It can quickly respond to interception commands and effectively deal with incoming targets such as black-flying drones.

[0012] 2. Aerodynamics and heat dissipation are optimized in tandem. The combination of a small cylindrical rocket-like fuselage, X-shaped thin airfoil, and wingtip fairing significantly reduces aerodynamic drag and wingtip vortex interference during high-speed flight. The through-type heat dissipation channel formed by the NACA air intake and the tail exhaust port eliminates the need for additional active heat dissipation components, achieving zero-cost and high-efficiency heat dissipation and solving the heat dissipation problem of onboard equipment during high-speed flight.

[0013] 3. Modular segmented design: The fuselage is divided into three sections: nose, mid-fuselage, and tail fairing. Each section is fixed by a quick-connect structure and can be disassembled and separated, which facilitates the replacement of warheads, battery installation and removal, equipment maintenance and repair, and improves ease of use and combat sustainability.

[0014] 4. High interception accuracy: The radar seeker has long-range search and high-precision identification capabilities. Combined with the high-speed flight control algorithm of the flight control system, it can accurately lock onto and track moving targets, increasing the interception hit rate to over 90%. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the overall structure of the UAV of this utility model; Figure 2 This utility model Figure 1 Side view; Figure 3 This utility model Figure 1 The front view; Figure 4 This is a cross-sectional view of the modular segmented fuselage of this utility model; Figure 5 This is a schematic diagram showing the disassembled state of the modular segmented fuselage of this utility model; Figure 6This is a schematic diagram of the structure of the warhead of this utility model; Figure 7 This is a schematic diagram of the NACA air intake of this utility model.

[0016] In the diagram: 1. Modular segmented fuselage; 11. Nose; 12. Mid-fuselage; 13. Tail cowl; 2. Radar seeker; 3. X-shaped thin-wing; 31. Wingtip fairing; 4. Power unit; 41. High KV brushless motor; 42. Power propeller; 5. Warhead; 6. High energy density lithium battery; 7. Four-in-one ESC; 8. Flight control; 9. NACA air intake; 10. Exhaust vent. Detailed Implementation

[0017] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, not all embodiments. In addition, the terms "first," "second," "third," "upper," "lower," "left," and "right," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance. Based on the embodiments of the present utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present utility model.

[0018] Please see Figure 1-7 As shown, this application provides a modular high-speed interceptor drone, including a modular segmented fuselage 1, an X-shaped thin-wing wing 3, a power unit 4, core functional components, and a heat dissipation structure; the modular segmented fuselage consists of three sections: a nose 11, a mid-fuselage 12, and a tail cowl 13; the X-shaped thin-wing wing 3 is symmetrically arranged in pairs on the lower middle part of the mid-fuselage 12, and the ends of the X-shaped thin-wing wing 3 are provided with wingtip fairings 31; the power unit 4 consists of four high-KV brushless motors 41 and a propeller 42; The core functional components consist of a radar seeker 2, a warhead 5, a lithium battery 6, a four-in-one electronic speed controller (ESC) 7, and a flight controller 8. The radar seeker 2 is installed inside the nose 11, the warhead 5 is built into the front of the mid-fuselage 12, and the lithium battery 6 is fixed at the rear of the mid-fuselage 12. The four-in-one ESC 7 and the flight controller 8 are integrated into the front of the tail cowl via an equipment mounting plate. The ESC 7 is electrically connected to the high-KV brushless motor 41, and the flight controller 8 maintains communication connections with both the radar seeker 2 and the ESC 7. It can search for and identify targets in real time and output guidance signals. The detection window of the radar seeker 2 is aligned with the transparent protective cover at the front of the nose. The protective cover is made of high-strength polycarbonate material and does not affect radar signal transmission. The lithium battery 6 is a high-energy-density lithium battery with continuous high-current discharge capability, providing sufficient power for high-speed flight. It is connected to the four-in-one ESC 7 via a quick-connect connector, supporting rapid replacement. The ESC 7 is connected to four high-KV brushless motors 41 via wires. The flight controller 8 communicates with the radar seeker 2 and the ESC 7 via data wires, receiving target signals in real time and outputting control commands to achieve power adjustment and flight attitude control. The flight controller 8 integrates high-speed flight control algorithms to meet high maneuverability response requirements.

[0019] More specifically, the transmitter inside the radar seeker 2 first generates an electromagnetic wave of a specific waveform, which is then transmitted through the antenna into a predetermined airspace. As the electromagnetic wave propagates through the air, it is scattered upon encountering the target UAV. A portion of the energy returns along its original path and is captured by the receiving antenna of seeker 2. The system processes these returning signals, and by calculating the time difference between signal transmission and reception, the target's distance can be accurately determined. By measuring the phase difference between the signals received by multiple antennas, the target's azimuth and elevation angles can be determined. Objects of different sizes, shapes, and materials reflect radar waves differently. Some target signal characteristics are pre-programmed to avoid misidentification.

[0020] The heat dissipation structure includes four NACA air intakes 9 symmetrically arranged at the front of the fuselage 1, and an air outlet 10 opened on the tail cover 13.

[0021] Please refer to the following for details. Figure 5 As shown, the nose 11, mid-fuselage 12, and tail cowl 13 are detachably connected by threaded connections. The overall length is 300-700mm, and the maximum diameter is 40-90mm. Each section is easy to disassemble, and the fuselage is centrally symmetrical, effectively reducing air resistance during high-speed flight.

[0022] Furthermore, the modular segmented fuselage 1 is made of either carbon fiber composite material or ABS material, and its shape is cylindrical like a rocket.

[0023] Please refer to the following: Figure 1-2The high-KV brushless motor 41 is partially embedded within the wingtip fairing 31, and its drive shaft remains connected to the propeller 42, forming a tail-thrust power layout with a thrust-to-weight ratio greater than 6:1. The wingtip fairing 31 is used to reduce aerodynamic drag from the motor, while also weakening wingtip vortex intensity and improving flight stability. The motor 41 is externally mounted behind the fairing 31 with screws, and the propeller 42 is mounted on the motor's output shaft. This ensures tail-thrust power output from the propeller 42, while the fairing 31 facilitates direct contact between the motor 41 and the airflow for rapid heat dissipation. The four motors are symmetrically distributed along the wing center to ensure balanced power output.

[0024] like Figure 4-5 As shown in Figures 7 and 8, the air vent 10 has multiple rectangular openings, and the NACA air intake 9 penetrates the internal cavity of the fuselage, forming an airflow cooling channel between it and the air vent 10. The NACA air intake 9 has a trumpet-shaped opening. During high-speed flight, external cold air is compressed into the fuselage through the NACA air intake 9, flows through the high-energy-density lithium battery 6, the four-in-one ESC 7, the flight control 8, and other heat-generating components, and after heat exchange, the hot airflow is discharged from the air vent 10 of the tail cowl 13, forming an efficient circulation cooling system to ensure that the temperature of the airborne equipment remains stable during high-speed flight at 320 km / h, avoiding overheating failure.

[0025] like Figure 1-3 As shown, the X-shaped thin-wing 3 adopts a delta-shaped thin-wing configuration, and the wingtip fairing 31 is streamlined. The wingspan is 200-400mm, and the thin-wing design is used to optimize high-speed aerodynamic efficiency.

[0026] Please see Figure 6 As shown, the warhead 5 is cylindrical and has mounting plates on its side. The warhead 5 is hollow inside and contains 200~500g of micro-explosive, which can be used with proximity or contact fuses.

[0027] In practical applications, the operation process is as follows: First, a soldier carries the disassembled drone components and quickly assembles the modular fuselage, fixing the nose 11, mid-fuselage 12, and tail cowl 13. The warhead 5 and high-energy-density lithium battery 6 are then installed, completing deployment preparation in under 5 minutes. Next, the drone is activated via the ground control terminal. The radar seeker 2 begins searching for targets, covering low-altitude targets within a 5km radius, autonomously identifying and locking onto incoming drones. Subsequently, the flight control system 8, guided by the radar seeker 2, controls the power unit 4 to start, propelling the drone towards the target area at a maximum speed of 320km / h. The flight control system adjusts the flight attitude in real time to ensure accurate target tracking. Finally, upon reaching the interception position, the radar seeker 2 triggers the trigger fuse of the warhead 5, detonating the warhead to destroy the target. Furthermore, the disassembled fuselage can be recovered during routine training for equipment maintenance, battery replacement, or as a warhead dummy, improving reuse efficiency.

[0028] In summary, this application achieves a balance between high-speed response, efficient heat dissipation, and convenient maintenance by optimizing aerodynamic layout, adopting a high thrust-to-weight ratio power design, and modular structure, thus filling the gaps in speed and maneuverability of existing interceptor drones.

[0029] It will be apparent to those skilled in the art that this invention is not limited to the details of the exemplary embodiments described above, and that it can be implemented in other specific forms without departing from the spirit or essential characteristics of this invention. Therefore, the embodiments should be considered exemplary and non-limiting in all respects, and the scope of this invention is defined by the appended claims rather than the foregoing description. Thus, it is intended that all variations falling within the meaning and scope of equivalents of the claims be included within this invention.

Claims

1. A modular high-speed interceptor drone, characterized in that, It includes a modular segmented fuselage (1), an X-shaped thin-wing airfoil (3), a power unit (4), core functional components, and a heat dissipation structure; The modular segmented fuselage consists of three sections: the nose (11), the middle fuselage (12), and the tail fairing (13). The X-shaped thin-wing (3) is symmetrically arranged in pairs in the lower middle part of the middle fuselage (12), and the tip fairing (31) is provided at the end of the X-shaped thin-wing (3). The power unit (4) consists of four high-KV brushless motors (41) and a propeller (42). The core functional components consist of a radar seeker (2), a warhead (5), a lithium battery (6), a four-in-one ESC (7), and a flight controller (8). The radar seeker (2) is installed inside the nose (11). The warhead (5) is built into the front of the mid-fuselage (12). The lithium battery (6) is fixed at the rear of the mid-fuselage (12). The four-in-one ESC (7) and the flight controller (8) are integrated into the front of the tail cowl through an equipment mounting plate. The ESC (7) is electrically connected to a high-KV brushless motor (41). The flight controller (8) maintains a communication connection with the radar seeker (2) and the ESC (7). The heat dissipation structure includes four NACA air intakes (9) symmetrically arranged at the front end of the fuselage (1), and an air outlet (10) opened on the tail cover (13).

2. The modular high-speed interceptor drone according to claim 1, characterized in that, The head (11), middle body (12) and tail cover (13) are connected in a detachable manner by threaded connection.

3. The modular high-speed interceptor drone according to claim 1, characterized in that, The high KV brushless motor (41) is partially embedded in the wingtip fairing (31), and its drive shaft is connected to the propeller (42) to form a tail-thrust power layout.

4. The modular high-speed interceptor drone according to claim 1, characterized in that, The modular segmented fuselage (1) is made of either carbon fiber composite material or ABS material, and its shape is cylindrical like a rocket.

5. The modular high-speed interceptor drone according to claim 1, characterized in that, The air outlet (10) has multiple rectangular openings, and the NACA air intake (9) penetrates the internal cavity of the fuselage and forms an airflow heat dissipation channel between the air outlet (10).

6. The modular high-speed interceptor drone according to claim 1, characterized in that, The X-shaped thin wing (3) adopts a triangular thin wing configuration, and the wingtip fairing (31) is streamlined.

7. The modular high-speed interceptor drone according to claim 1, characterized in that, The warhead (5) is cylindrical and has mounting plates on its side, and the interior of the warhead (5) is hollow.

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