Portable high-speed patrol flight attack unmanned aerial vehicle and unmanned aerial vehicle system

Abstract

The invention relates to the technical field of unmanned aerial vehicles, in particular to a patrol flight attack unmanned aerial vehicle with high-speed cruise, rapid deployment and modular attack capabilities and an unmanned aerial vehicle system. The invention discloses a portable high-speed patrol flight attack unmanned aerial vehicle and an unmanned aerial vehicle system. The unmanned aerial vehicle comprises a main body fuselage module, a wing module, an empennage module, an undercarriage module and a task load module, the unmanned aerial vehicle system comprises an unmanned aerial vehicle and a ground control station, and the ground control station is used for performing remote control and task planning on the unmanned aerial vehicle, receiving data transmitted by the unmanned aerial vehicle and sending an instruction to the unmanned aerial vehicle. The method has the following advantages: the method has good universality and expansibility; battle requirements are quickly responded, and battle effectiveness is improved; reconnaissance and attack functions are integrated, and'detection and attack integration 'is realized. The disassembly and replacement modes are convenient; the same platform is supported to switch a reconnaissance-strike-electronic countermeasure mode in a single task; the unmanned aerial vehicle is made of light composite materials, the weight of the unmanned aerial vehicle is reduced, and fuel efficiency and flight performance are improved.

Description

Technical Field

[0001] The present invention relates to the field of UAV technology, and in particular to a patrol attack UAV and a UAV system with high-speed cruising, rapid deployment and modular attack capabilities, which are suitable for scenarios such as military reconnaissance, target strike and tactical support. Background Art

[0002] Current loitering attack drones face numerous limitations. Their rigid structure and highly integrated functional modules make it difficult to flexibly adjust their payloads to meet mission requirements, resulting in a single mission and high maintenance costs. Furthermore, their deployment efficiency is low, and the traditional assembly process is complex, making rapid disassembly and assembly on the battlefield difficult and prone to missed combat opportunities. Furthermore, their aerodynamic design fails to optimize high-speed flight and low-altitude penetration, resulting in insufficient speed and maneuverability. Their attack modes are also relatively limited, and their weapon system compatibility is poor, making them difficult to adapt to a variety of ammunition types.

[0003] These limitations are increasingly evident in modern military reconnaissance and attack missions. The relatively fixed functionality of drones makes them difficult to flexibly adjust to mission characteristics, limiting their adaptability to diverse operational requirements. The complex structure of some drones makes them difficult to carry and deploy quickly, potentially leading to delays. The low integration of payloads makes replacement cumbersome and time-consuming, severely impacting operational efficiency. Therefore, a modular design for a convenient, high-speed patrol attack drone is urgently needed to meet the multiple requirements of modern combat for drone flexibility, portability, and efficiency. Summary of the Invention

[0004] The purpose of the present invention is to provide a convenient high-speed patrol attack UAV and UAV system. By dividing the UAV into multiple modules that can be independently designed, manufactured and replaced, rapid switching and flexible combination of different mission payloads can be achieved, thereby improving the versatility and adaptability of the UAV, while facilitating maintenance, upgrading and reducing usage costs.

[0005] To achieve the above objectives, the present invention provides the following technical solution: a portable, high-speed patrol attack drone, comprised of multiple key modules: a main fuselage module, wings, tail module, landing gear module, and payload module. Each module utilizes four specialized quick-release mechanisms, enabling full field assembly in ≤5 minutes, achieving a 10-fold improvement in efficiency compared to traditional assembly methods.

[0006] The spline connection solves the axial precision problem of tail wing installation (error <0.1mm) and avoids aerodynamic interference. Four types of specialized standardized quick-release structures are used for connection, ensuring both stable connection and convenient and quick assembly and disassembly.

[0007] Main fuselage module: The main fuselage module mainly includes the fuselage frame, power module, flight control system and power module; The fuselage frame is constructed from a high-strength, lightweight carbon fiber composite and titanium alloy hybrid structure, providing the foundation for the spatial layout. Its design prioritizes the rational allocation of internal space, with reserved installation interfaces and channels for other modules to ensure the overall coordination and stability of the drone. Mechanical and electrical interfaces for connecting the wing module, tail module, and landing gear module are located on the sides, tail, and bottom of the drone. The power module is equipped with a high-performance turbojet engine, providing sufficient thrust to meet the high-speed flight requirements of the UAV. The connection between the engine and the fuselage module adopts a shock-absorbing design to reduce the impact of vibration on the UAV structure and equipment. At the same time, the power module is equipped with a fuel supply interface and an exhaust system interface to ensure efficient fuel supply and reasonable exhaust gas discharge. The flight control system precisely controls the UAV's flight attitude, heading, and speed through the flight control computer based on navigation information and preset mission instructions. It also maintains real-time communication with the ground control station through a data link system, transmitting flight data and information collected by the mission payload, and receiving ground instructions for real-time adjustments, ensuring the UAV's autonomous flight capability and mission execution accuracy in complex environments. The power module uses a high-energy-density lithium-ion battery pack as its primary power source, providing stable power to all modules of the drone. The battery pack adopts a modular design, allowing for flexible addition and subtraction of batteries based on mission duration. It is also equipped with a battery management system (BMS) that monitors battery status in real time, ensuring safe use and efficient power supply.

[0008] Wing Module: The wing module is detachably connected to the main fuselage module via a first disassembly structure. The upper surface of the wing features an efficient aerodynamic layout, while the lower surface provides mounting points for payload modules, enhancing the UAV's lift and maneuverability. The wing mounting points utilize a carbon fiber-Kevlar laminate, providing a load capacity of 200 kg while reducing weight by 30%.

[0009] Tail Module: Similar to the wing module, the tail module features a flexible and adjustable design, detachably connected to the main fuselage module via a second disassembly mechanism. The clearance between the spline slot and the external spline is ≤0.05mm, and preload is applied via locating bolts to ensure zero-displacement stability in high-speed airflow. The tail angle can be adjusted based on flight conditions and mission requirements, ensuring stable and flexible flight.

[0010] Landing gear module: The landing gear module is detachably connected to the main fuselage module through a third disassembly structure, and provides the UAV with stable, reliable support and cushioning functions that are adaptable to various take-off and landing environments, ensuring the safety and convenience of the UAV during take-off and landing.

[0011] Mission Payload Modules: Various payload modules can be designed based on mission requirements, including a reconnaissance payload module (including a high-resolution camera, infrared thermal imager, etc.), an attack payload module (carrying small precision-guided weapons), and an electronic countermeasures payload module (with electronic jamming and signal deception capabilities). The reconnaissance payload module is integrated into the UAV's nose, while the attack payload module is detachably connected to the main fuselage module via a fourth detachable structure. The mounting hook in this fourth detachable structure has a built-in spring-driven self-locking mechanism that automatically locks when mounted and requires manual release for removal. All mission payload submodules adhere to unified standard electrical interface specifications and can be quickly connected to the flight control system in the main fuselage module, achieving plug-and-play operation and enabling rapid switching of UAV functions in different mission scenarios.

[0012] The modular interface is the core of the convenient high-speed patrol attack drone to quickly connect and disconnect the various modules. The interface design is as follows: Mechanical Interface: Made from high-strength alloy, it offers excellent wear and fatigue resistance. The standardized plug-in design, coupled with precise positioning bolts and locking mechanisms, ensures precise alignment and a secure connection between modules. A buffering mechanism is also incorporated to mitigate the effects of vibration during takeoff, landing, and flight.

[0013] Electrical interface: The electrical interface follows a unified electrical standard and includes a power interface, a signal interface, and a data interface. The power interface adopts a gold-plated copper alloy multi-pin design and supports a peak current of 400A (meeting the instantaneous power consumption of the turbojet engine); the signal interface and data interface use high-speed communication protocols such as USB3.0 and Ethernet to ensure the fast and accurate transmission of control signals and data information. The electrical interface also has anti-misinsertion and anti-reverse insertion functions, and is designed with a positioning slot to avoid damage to the module due to human error. The signal interface has a built-in adaptive protocol converter that is compatible with the NATO STANAG 7085 standard payload.

[0014] Fuel port (between the power module and fuselage module): This fuel port features a quick-connect design, ensuring a reliable connection and excellent sealing, ensuring zero leakage during fuel transfer. A fuel filter is built into the port to prevent impurities from entering the engine fuel system and affecting engine performance.

[0015] Compared with traditional UAVs (such as the stackable modules of CN 205738041 U), the four dedicated quick-release interfaces of this design shorten the field assembly time from more than 30 minutes to less than 5 minutes, improving efficiency by 600%.

[0016] Compared with the prior art, the present invention has the following advantages: 1. The modular design gives the UAV good versatility and scalability, and allows for the rapid configuration and replacement of different mission payload modules based on mission requirements, improving the UAV's operational flexibility and adaptability. 2. High-speed flight capability enables drones to reach combat areas in a short period of time, quickly respond to combat needs, and improve combat effectiveness; 3. Integrate reconnaissance and attack functions to achieve "reconnaissance and attack integration." Targets can be attacked in real time during reconnaissance, shortening combat cycles and improving combat efficiency. 4. Convenient disassembly and replacement facilitates rapid adjustment of the drone's mission configuration in the field or in emergency situations. It also facilitates storage and transportation, reducing the difficulty of maintenance and support. 5. The ability to rapidly reconfigure in just 5 minutes allows the same platform to switch between reconnaissance, strike, and electronic warfare modes within a single mission, reducing mission response time by 70%. Through the flight control system's dynamic mission reconfiguration algorithm, the reconnaissance to strike mode switch can be completed within 5 seconds of receiving ground commands. 6. Made of lightweight composite materials, it reduces the weight of the drone, improves fuel efficiency and flight performance, while ensuring structural strength and durability. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a schematic diagram of the overall structure of Example 1 of the present invention; Figure 2 Schematic diagram of the cross-section of the main fuselage module structure in Example 1 of the present invention; Figure 3 This is a schematic diagram of the wing module structure in Example 1 of the present invention; Figure 4 This is a schematic structural diagram of the tail wing module in Example 1 of the present invention; Figure 5 This is a schematic diagram of the landing gear module structure design in Example 1 of the present invention; Figure 6 This is a schematic diagram of the structure of the mission payload module in Example 1 of the present invention; Figure 7 This is a schematic diagram of the connection of the first disassembly structure in Example 1 of the present invention; Figure 8 This is a schematic diagram of the connection of the second disassembly structure in Example 1 of the present invention; Figure 9 This is a schematic diagram of the connection of the third disassembly structure in Example 1 of the present invention; Figure 10 This is a schematic diagram of the fourth disassembly structure connection in Example 1 of the present invention; Figure 11 This is a schematic diagram of the landing gear module installation process in Example 2 of the present invention; Figure 12 Schematic diagram of the wing module installation process in Example 2 of the present invention; Figure 13 This is a schematic diagram of the installation process of the tail module in Example 2 of the present invention; Figure 14 This is a schematic diagram of the installation process of the mission payload module in Example 2 of the present invention; Figure 15 This is a logic block diagram of a portable high-speed patrol attack drone system according to embodiment 3 of the present invention; Figure 1 In the figure, 1, the main fuselage module; 2, the wing module; 3, the tail module; 4, the landing gear module; 5, the mission payload module; Figure 2 In the figure, 101, fuselage frame; 102, power system; 103, flight control system; 104, power module; 105, hatch; 106, antenna; 501, reconnaissance payload module; 10101, fixing bracket; 10102, bolt mounting hole; 10105, fixing slot; 10201, turbojet engine; 10202, tail nozzle; Figure 3 In the middle, 12, the fourth disassembly structure; 14, the signal interface; 201, the fixing screw; 202, the aileron; 203, the flap; Figure 4 In the middle, 13, power interface; 301, horizontal / vertical stabilizer; 302, rudder / elevator; 303, external spline; Figure 5 In the middle, 16, fixed plate; 17, tire; 18, support frame; 401, main landing gear; 402, front landing gear; Figure 6 In the middle, 15, data interface; 501, reconnaissance payload module; 502, attack payload module; 50101, high-resolution camera; 50102, infrared thermal imager; 50201, missile mounting device; 50202, air-to-ground missile; 1202, mounting hook; Figure 7 In the middle, 6, slotted nut; 7, cotter pin; 201, fixing screw; 10101, fixing bracket; Figure 8 In the middle, 8, positioning bolt; 10103, spline groove; 10104, positioning hole; Figure 9 Middle, 6, slotted nut; 10106, fixing screw; Figure 10 In the middle, 204, fixed frame; 1201, positioning slot; 1202, mounting hook; Figure 11In the middle, 11, the third disassembly structure; 401, main landing gear; 402, front landing gear; 10105, fixing slot; 10106, fixing screw; Figure 12 In the middle, 6, slotted nut; 9, first disassembly structure; 105, hatch; 201, fixing screw; 202, aileron; 203, flap; 10101, fixing bracket; 10102, bolt mounting hole; Figure 13 In the middle, 8, positioning bolt; 10, second disassembly structure; 301, horizontal / vertical stabilizer; 302, direction / elevator; 303, external spline; 10103, spline groove; 10104, positioning hole; Figure 14 Among them, 502, attack payload module; 50101, high-resolution camera; 50102, infrared thermal imager; 50201, missile mounting device; 1201, positioning slot; 1202, mounting hook. DETAILED DESCRIPTION

[0018] The present invention provides a convenient high-speed patrol attack UAV and UAV system. In order to make the technical means used in the present invention, the unique innovative features and the goals and effects achieved by the invention have a clearer and more intuitive understanding, the following is combined with Figures 1 to 14 The present invention is further described with reference to the structural diagram of FIG. Example 1

[0019] like Figure 1-6 As shown, a portable high-speed patrol attack UAV includes a main fuselage module 1, wing modules 2, tail module 3, landing gear module 4, and mission payload module 5. The main fuselage module 1 is the core part of the UAV and adopts a sturdy fuselage frame structure to connect various modules and integrated systems. The wing module 2 mainly provides lift for the UAV, and its lower wing surface is connected to the attack payload module 502 via a fourth detachable structure. The tail module 3 is installed at the tail of the main fuselage module 1 via a second detachable structure 10, which mainly provides the UAV with certain longitudinal and lateral maneuverability. The landing gear module 4 is connected to the main fuselage module 1 at the bottom via a third detachable structure 11, which mainly provides support and cushioning for the UAV during takeoff and landing. The mission payload module 5 mainly includes a reconnaissance payload module 501 and an attack payload module 502. The reconnaissance payload module 501 is integrated into the nose of the UAV, and the attack payload module 502 is installed on the lower wing surface of the wing module 2 via a fourth detachable structure 12. The payload module 502 mainly carries two small air-to-ground missiles 50202. The first disassembly structure 9 is a composite locking mechanism between the wing module 2 and the fuselage using multiple screws + slotted nuts + cotter pins, such as Figure 7As shown; the second disassembly structure 10 is the radial positioning connection between the tail module 3 and the fuselage using a spline groove + external spline + positioning bolts, such as Figure 8 The third disassembly structure 11 is a landing gear module 4 and the fuselage using a fixed plate + fixed slot + screw vertical plug structure, such as Figure 9 The fourth disassembly structure 12 is an attack payload module 502 and the wing using a positioning slot + mounting hook suspension quick-install structure, such as Figure 10 shown.

[0020] Specifically, such as Figure 2 As shown, the main fuselage module 1 includes a fuselage frame 101, a power system 102, a flight control system 103, a power module 104, a door 105, and an antenna 106. The fuselage frame 101 is carefully manufactured using high-strength, lightweight carbon fiber composite materials. During the design process, the first disassembly structure 9 for connecting to the wing module 2 is cleverly set on both sides of the fuselage frame 101. Figure 7 As shown, the first disassembly structure 9 includes multiple fixing screws 201 at the root of the wing module 2, a fixing bracket 10101 and bolt mounting holes 10102 on the fuselage frame 101, a slotted nut 6, and a cotter pin 7; the tail portion is carefully designed with a second disassembly structure 10 corresponding to the tail module 3, as shown in FIG. Figure 8 As shown, the second disassembly structure 10 adopts a spline-like connection method, including a spline groove 10103 and a positioning hole 10104 on the fuselage frame 101, an external spline 301 on the tail module 3, and a positioning bolt 8; the lower part is equipped with a third disassembly structure 11 adapted to the landing gear module 4, as shown in FIG. Figure 9 As shown, the third disassembly structure 11 includes a fixing plate 16 on the landing gear module 4, a fixing slot 10105 on the fuselage frame 101, a fixing screw 10106, a slotted nut 6, and a cotter pin 7; like Figure 2 As shown, the power system 102 mainly includes a turbojet engine 10201 and a tail nozzle 10202. The turbojet engine 10201 is installed in the fuselage frame, and the tail nozzle 10202 is set at the tail of the fuselage. The turbojet engine 10201 is connected to the flight control system to provide propulsion power for the UAV, so that the UAV has the ability to fly at high speed. The flight control system 103 includes multiple control surfaces, a flight control computer, and a sensor assembly. The control surfaces are installed on the wings and tail of the UAV. The flight control computer controls the deflection of the control surfaces based on the data collected by the sensor assembly to achieve attitude control and flight trajectory adjustment of the UAV. The sensor assembly includes an attitude sensor, an altitude sensor, and a speed sensor. The flight control computer adopts a redundant design to ensure the reliability of flight control. The power module 104 is a lithium battery pack installed inside the fuselage to provide power for various modules of the drone. The lithium battery pack has high energy density and fast charging capability, which can meet the power needs of the drone for long-term patrol and mission execution.

[0021] Specifically, such as Figure 3 As shown, the wing module 2 is installed on both sides of the main fuselage module 1 through a quick-release structure to provide lift and mount the attack payload module 502; it mainly includes a fixing screw 201, an aileron 202, a flap 203, and a fourth disassembly structure 12; the fixing screw 201, the slotted nut 6 and the cotter pin 7 are used to connect and fix the wing module 2 to the fuselage frame 101; the aileron 202 is installed on the outer side of the wing trailing edge and is the main lateral control surface on the wing, which can achieve rapid inclination changes and control the rolling movement of the drone, thereby changing the flight attitude of the drone; the flap 203 is installed on the trailing edge of the wing and is a common lift-enhancing device that can increase the curvature and area of ​​the wing, thereby increasing the maximum lift coefficient; the fourth disassembly structure 12 is located on the lower wing surface and is used to connect the attack payload module 502, as shown in FIG. Figure 10 As shown, the fourth disassembly structure 12 includes a fixing frame 204 , a positioning slot 1201 , and a mounting hook 1202 .

[0022] Specifically, such as Figure 4 As shown, the tail module 3 is removably mounted on the rear of the main fuselage module 1, providing the drone with a certain degree of longitudinal and lateral maneuverability and properly balancing the drone's center of gravity, ensuring a reasonable torque balance between various components during flight. It adopts a V-tail layout, combining the functions of the vertical and horizontal tail fins, reducing the number and weight of the tail fins and simplifying the structure. Its structure primarily includes a horizontal / vertical blended stabilizer 301, a blended rudder / elevator 302, an external spline 303, and a retaining bolt 8.

[0023] Further, such as Figure 5 As shown, the landing gear module 4 is mounted below the main fuselage module 1 and constructed from a lightweight, high-strength alloy. It primarily provides support and cushioning during takeoff and landing. It utilizes a tricycle landing gear system, providing stable, reliable support and cushioning suitable for various takeoff and landing environments, ensuring safety and convenience during takeoff and landing. It comprises a main landing gear 401 and a nose landing gear 402. The landing gear module 4 primarily includes a mounting plate 16, tires 17, and a support frame 18.

[0024] Specifically, such as Figure 6As shown, the mission payload module 5 can be detachably mounted on the wing module 2 or the main fuselage module 1; it includes a reconnaissance payload module 501 and an attack payload module 502; the reconnaissance payload module 501 is mounted on the main fuselage module 1, and includes a high-resolution camera 50101 and an infrared thermal imager 50102. The combined use of the two can achieve complementary advantages and meet the reconnaissance needs of the patrol UAV in different environments and missions; the attack payload module 502 is mounted on the wing module 2, and is used to perform different mission functions, including a missile mounting device 50201, a small air-to-ground missile 50202, including at least two small air-to-ground missiles 50202, which can achieve the combat needs of immediate detection and attack.

[0025] Furthermore, during actual combat, the various modules of the drone are transported to the designated take-off site. Through team collaboration, the landing gear module 4 is connected to the lower part of the main fuselage module 1 through the third disassembly structure 11, the wing module 2 is quickly connected to both sides of the main fuselage module 1 through the first disassembly structure 9, and the tail module 3 is quickly connected to the tail of the main fuselage module 1 through the second disassembly structure 10. Finally, the attack payload module 502 is quickly mounted on the wing module 2 through the fourth disassembly structure 12, thereby achieving the effect of rapid disassembly and assembly on the battlefield.

[0026] It should be noted that during the installation of each module, the electrical interfaces at the connection points of each module should be connected first, and then the mechanical interfaces of each disassembly structure should be connected. A plurality of quick connection interfaces are provided on the main fuselage module 1 and the wing module 2, and the mission payload module 5 is connected to the main fuselage module 1 and the wing module 2 through the quick connection interface. The quick connection interface includes a mechanical connection structure and an electrical connection structure. The mechanical connection structure is used to realize the fixed installation of the mission payload module 5, and the electrical connection structure is used to realize the electrical connection between the mission payload module 5 and the main fuselage module 1, so that the mission payload module 5 can obtain power and communicate data with the flight control system. The design of the quick connection interface enables the mission payload module 5 to be quickly disassembled and replaced. By Figure 7-10 As can be seen from the disassembled schematics, the electrical interfaces are all plug-in, including a power interface 13, a signal interface 14, and a data interface 15. These interfaces ensure stable transmission of electrical signals, enabling coordinated operation of the various drone components during flight, effectively improving the drone's overall performance and providing reliable structural support for efficient flight and stable operation.

[0027] The drone's main fuselage module 1 and payload module 2 are both manufactured from lightweight composite materials, such as carbon fiber composites. This effectively reduces the drone's weight while maintaining structural strength, improving fuel efficiency and flight performance. Composite materials also offer excellent corrosion and fatigue resistance, making them suitable for long-term use in complex environments.

[0028] As a preferred implementation of this embodiment, the fuselage frame 101 of the drone adopts a hybrid structure combining carbon fiber and titanium alloy. Compared with traditional aluminum alloy materials, this structure can significantly reduce the weight of the fuselage, with a weight reduction ratio of up to 40%. At the same time, by applying advanced topological optimization design methods, the local structure of the fuselage frame has been finely adjusted and optimized, so that the local impact strength has been greatly improved, with an improvement of 200%. This innovative material application and structural design not only effectively reduces the overall weight of the drone and enhances its impact resistance in complex environments, but also provides strong support for the drone's high-performance flight and long endurance, giving it significant advantages in terms of flight stability, load capacity and service life. Example 2

[0029] like Figure 11-14 As shown, this embodiment further illustrates how an operator team can quickly assemble an entire drone without tools in 5 minutes in a field environment according to the installation process. Example 2 uses all module and interface numbering from Example 1, with only additional details on the assembly sequence and precautions.

[0030] The installation process of landing gear module 4 is as follows Figure 11 As shown, Specifically, first remove the folded nose landing gear 402 and main landing gear 401 from the carrying case. After checking the tire pressure of the tire 17 and the support frame 18 for damage, lift the landing gear module 4 vertically from below the main fuselage module 1. Align the upper fixing plate 16 of the landing gear with the fixing slot 10105 at the bottom of the fuselage frame 101. Plug the landing gear electrical connector into place until a click is heard, confirming the lock. Next, push the landing gear vertically into the mounting slot, allowing the fixing screws 10106 on the fuselage frame to pass through the screw mounting holes in the mounting plate. Once the landing gear module is in place, screw the slotted nut 6 onto the end of the fixing screw and insert the cotter pin 7 to lock it. This completes the connection between the landing gear module 4 and the main fuselage module 1 via the third disassembly mechanism.

[0031] The installation process of wing module 2 is as follows Figure 12 As shown, Specifically, first open the hatch 105 at the bottom of the fuselage frame 101 to facilitate subsequent inspection of whether the wing module 2 is installed in place, and install the slotted nut 6 and cotter pin 7. Two operators lift the left and right wing modules 2 horizontally to both sides of the fuselage, aligning the fixing screws 201 at the wing root with the bolt installation holes 10102 of the fuselage frame 101, and then install the screws 201 at the wing root and the bolt installation holes 10102 of the fuselage frame 101. Figure 12Following the indicated disassembly and assembly directions, push the wing module horizontally until the wing root end face is flush with the fuselage, perfectly fitting onto mounting bracket 10101. Through hatch 105, screw in slotted nuts 6 and insert cotter pins 7 sequentially to complete the composite locking of the first disassembly structure 9. The wing electrical interface is located above the wing root. When plugging in, pay attention to the anti-misinsertion positioning slots to ensure that power, signals, and data are fully connected. The cables for the ailerons 202 and flaps 203 control surfaces are routed internally within the wing and automatically recognized and matched by the electrical connection structure with the flight control system.

[0032] The installation process of tail module 3 is as follows Figure 13 As shown, Specifically, first, move the V-tail tail module 3 horizontally to the rear fuselage, aligning the external splines 303 axially with the spline slots 10103 of the fuselage frame 101. Gently push it axially until the positioning holes 10104 align with the tail mounting holes. Insert the positioning bolts 8 and apply a preload of 8 N·m to complete the spline positioning connection of the second disassembly structure 10. The tail module 3 is then quickly connected to the fuselage module 1. The tail servo wiring harness is connected to the flight control system 103 via the tail electrical interface, and the system automatically completes the control surface neutral position calibration.

[0033] The installation process of mission payload module 5 is as follows Figure 14 As shown, Specifically, two small air-to-ground missiles 50202 are pre-installed on the missile mounting assembly 50201, forming the attack payload module 502. The mounting hook 1202 of the attack payload module 502 is vertically aligned with the positioning slot 1201 on the mounting bracket 204 of the fourth disassembly structure 12 below the wing. After being pushed in, it slides backward until the spring forces the mounting hook 1202 to automatically lock. A manual check is performed to ensure the safety pin is locked. The electrical connection structure simultaneously completes the weapon bus docking, and the flight control system 103 performs a self-check to identify the missile model and quantity. Example 3

[0034] like Figure 15 As shown, the portable high-speed patrol attack UAV system of the present invention includes the above UAV and a ground control station.

[0035] The ground control station is the command center of the UAV system and consists of a control terminal, data link equipment and display equipment.

[0036] The control terminal is equipped with a high-performance computer and professional flight control software. The operator can input control instructions and mission parameters through the control terminal to control the entire process of the UAV, including takeoff, cruising, reconnaissance, attack and return.

[0037] The data link equipment uses advanced encryption communication technology to ensure the security of control instructions and data information during transmission, prevent enemy theft and interference, and meet the needs of long-distance combat.

[0038] The display device uses a high-resolution display to display the drone's flight status parameters, reconnaissance images and video information, as well as battlefield situation maps in real time, providing operators with intuitive and comprehensive decision-making basis.

Claims

1. A portable high-speed patrol attack drone, comprising a main fuselage module, wing modules, tail module, landing gear module, and mission payload module, characterized by: The wing module, tail module, landing gear module and the main fuselage module can be detachably connected, and the mission payload module can be detachably connected to the main fuselage module and wing module; Among them, a fixing bolt is provided at the wing root of the wing module, and a fixing bracket and bolt mounting holes are provided on the fuselage frame of the main fuselage module. The bolt mounting holes are provided on the fixing bracket, and the fixing bolts correspond to and fit in the bolt mounting holes. The slotted nuts adapted to the fixing bolts are screwed in sequentially through the hatch and the cotter pins are inserted to achieve the locking of the wing module and the main fuselage module. An external spline and a tail mounting hole are provided at the wing root of the tail module, and a spline groove and a positioning hole are provided on the fuselage frame of the main fuselage module. The external spline is adapted to the spline groove. When the external spline is pushed axially into the spline groove, the tail mounting hole and the positioning hole coincide with each other, and the tail module and the main fuselage module are quickly connected by positioning bolts adapted to the two.

2. The portable high-speed patrol attack drone according to claim 1, characterized in that: The main fuselage module includes a fuselage frame, power system, flight control system and power module; mechanical interfaces and electrical interfaces connecting the wing module, tail module and landing gear module are set on both sides, tail and bottom of the fuselage frame; the power system, flight control system and power module are all set in the fuselage frame; a fuel interface is set between the power system and the main fuselage module to meet the high-speed flight requirements of the UAV; the flight control system is used to control the flight attitude, heading and speed of the UAV, and maintain real-time communication with the ground control station through the data link system; the power module provides stable power support for each module of the UAV.

3. The portable high-speed patrol attack drone according to claim 2, characterized in that: The power system includes an engine and a tail nozzle. The tail nozzle is set at the tail of the fuselage frame. The engine is installed inside the fuselage frame and connected to the flight control system. It is used to provide propulsion power for the UAV, enabling the UAV to have high-speed flight capability.

4. The portable high-speed patrol attack drone according to claim 2, characterized in that: The flight control system includes multiple control surfaces, a flight control computer and a sensor assembly; the control surfaces are set on the wings and tail of the UAV; the flight control computer controls the deflection of the control surfaces based on the data collected by the sensor assembly to achieve attitude control and flight trajectory adjustment of the UAV; the sensor assembly includes an attitude sensor, an altitude sensor and a speed sensor.

5. The portable high-speed patrol attack drone according to claim 1, characterized in that: An efficient aerodynamic layout is arranged on the upper surface of the wing module, and mounting points are set on the lower surface for installing mission payload modules; The hardpoints are made of carbon fiber-Kevlar laminate.

6. The portable high-speed patrol attack drone according to claim 1, characterized in that: The landing gear module includes an upper fixing plate, tires and a support frame; a fixing slot is provided at the lower part of the fuselage frame of the main fuselage module, the upper fixing plate of the landing gear is adapted to the fixing slot, and the upper fixing plate of the landing gear is connected and fixed to the fixing slot by fasteners to realize the connection between the landing gear module and the main fuselage module.

7. The portable high-speed patrol attack drone according to claim 1, characterized in that: The mission payload module includes a reconnaissance payload module and an attack payload module. The reconnaissance payload module is installed on the main fuselage module, and the attack payload module is mounted on the wing module. The attack payload module includes at least two small air-to-ground missiles.

8. The portable high-speed patrol attack drone according to claim 7, characterized in that: A fixing frame is provided under the wing of the wing module, and a positioning slot is provided on the fixing frame; a mounting hook is provided on the missile; the mounting hook is pushed into the positioning slot and then slid backward until the mounting hook is automatically locked under the spring drive.

9. A portable high-speed patrol attack drone system, characterized by: It comprises a portable high-speed patrol attack UAV as described in any one of claims 1 to 8, and a ground control station, which is used for remotely controlling and task planning the UAV, receiving data transmitted by the UAV, and sending instructions to the UAV.

10. The portable high-speed patrol attack drone system according to claim 9, characterized in that: The ground control station includes a control terminal, data link equipment and display equipment; the control terminal is used for operators to input control instructions and mission parameters; the data link equipment is used to wirelessly communicate with the UAV to transmit control instructions and data information; the display equipment is used to display the UAV's flight status and reconnaissance data.

Images