Vertical take-off and landing fixed-wing long-endurance unmanned aerial vehicle

Abstract

The invention discloses a vertical take-off and landing fixed-wing long-endurance unmanned aerial vehicle, which comprises a wing bracket which is used as a supporting framework of a wing of the unmanned aerial vehicle and adopts a hollow design; and the fuselage bracket is used as a supporting framework of the fuselage of the unmanned aerial vehicle, adopts a hollow design, is fixed below the wing bracket, and is perpendicular to the wing bracket. According to the angle-adjustable power mechanism, the adjusting motor drives the adjusting rod to rotate, so that the dynamic change of the angle of the rotor wing is realized, the rotor wing is smoothly switched between vertical take-off and landing and horizontal cruise, and the flight flexibility and the energy efficiency ratio are remarkably improved. The mechanism is not only suitable for attitude adjustment in different take-off and landing environments, but also capable of automatically adjusting the thrust direction, optimizing the aerodynamic performance, shortening the take-off and landing time and improving the loading capacity and endurance performance according to the flight stage, and is particularly suitable for executing multi-task flight operation under complex terrains.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and particularly to a vertical take-off and landing fixed-wing long-endurance unmanned aerial vehicle. Background Art

[0002] In recent years, unmanned aerial vehicle technology has developed rapidly. Fixed-wing unmanned aerial vehicles are widely used in fields such as aerial photography, mapping, and inspection due to their long endurance and high efficiency, while multi-rotor unmanned aerial vehicles are known for their flexibility in vertical take-off and landing. In the prior art, some unmanned aerial vehicles have attempted to combine the advantages of fixed wings and multi-rotors to develop vertical take-off and landing fixed-wing unmanned aerial vehicles (VTOLs), which provide take-off and landing capabilities through rotors and cruise efficiency through fixed wings. Such unmanned aerial vehicles usually adopt wing and fuselage support structures, and are equipped with power motors, flight control systems, and control mechanisms such as ailerons and rudders to meet diverse mission requirements. However, there is still room for improvement in the existing designs in terms of structure, control, and endurance, especially in terms of adaptability and intelligence level in complex environments.

[0003] Existing vertical take-off and landing fixed-wing unmanned aerial vehicles have some defects. First, traditional designs mostly adopt heavier fuselage structures, resulting in a relatively large overall weight, which limits the endurance and payload capacity. Second, the integration degree of the power system and the control system is insufficient, and the modular design is not perfect enough, making maintenance and upgrade inconvenient. In addition, the existing flight control systems are less autonomous in complex environments and lack efficient attitude adjustment and automatic return functions, which affect the stability and safety of mission execution. These defects limit the application of unmanned aerial vehicles in long-distance cruising, take-off and landing in urban environments, and high-precision missions, and there is an urgent need for improvement to enhance performance and adaptability. Summary of the Invention

[0004] The purpose of the present invention is to propose a vertical take-off and landing fixed-wing long-endurance unmanned aerial vehicle to solve the deficiencies existing in the prior art.

[0005] To achieve the above purpose, the present invention adopts the following technical solutions: Vertical takeoff and landing fixed-wing long-endurance unmanned aerial vehicle, including a wing support for serving as a support framework of the wing of the unmanned aerial vehicle, which adopts a hollowed-out design; a fuselage support for serving as a support framework of the fuselage of the unmanned aerial vehicle, which adopts a hollowed-out design, is fixed below the wing support, and is arranged perpendicular to the wing support; a power mechanism for the vertical takeoff and landing of the unmanned aerial vehicle, which is fixedly installed on the wing support, including an adjusting rod, two mounting blocks are fixedly arranged on the adjusting rod, a power motor is fixed on one side of the mounting block, a rotor is fixed at the output end of the power motor, and one end of the adjusting rod is fixed at the power output end of the adjusting motor; an integrated control mechanism is arranged in the fuselage support for power supply and control of electronic components; an aileron mechanism for assisting flight, which is installed on the wing support, including an aileron body rotatably arranged on the wing support, a first mounting seat is fixed below the aileron body, the first mounting seat is rotatably connected to one end of a first linkage rod, the other end of the first linkage rod is rotatably connected to the end of a first adjusting arm, the other end of the first adjusting arm is fixedly connected to the power output end of a first servo motor, and the first servo motor is fixedly arranged in the wing support; a landing gear is installed below the fuselage support for supporting the unmanned aerial vehicle; a rudder mechanism is installed behind the fuselage support for assisting in steering; an elevator mechanism is installed behind the fuselage support for assisting in takeoff and landing.

[0006] Preferably, the wing support includes a first support body, the first support body is integrally in a streamlined frame structure, aileron mounting positions matching the aileron mechanism and power mechanism mounting positions matching the power mechanism are arranged on the first support body, and a fuselage support mounting position for fixing with the fuselage support is further arranged below the first support body.

[0007] Preferably, the fuselage support includes a second support body, a wing support mounting position for fixing with the wing support is arranged above the second support body, a mounting cavity matching the integrated control mechanism is arranged in front of the second support body, and a rudder mechanism mounting position matching the rudder mechanism and an elevator mechanism mounting position matching the elevator mechanism are arranged behind the second support body.

[0008] Preferably, the rudder mechanism includes a vertical fin fixed on the fuselage support, the vertical fin is arranged vertically, a vertical adjustable fin is rotatably arranged at the rear side of the vertical fin, a second mounting seat is fixed on one side of the vertical adjustable fin, the second mounting seat is rotatably connected to one end of a second linkage rod, the other end of the second linkage rod is rotatably arranged at the end of a second adjusting arm, and one end of the second adjusting arm is fixed on the power output shaft of a second servo motor, and the second servo motor is fixed on the vertical fin.

[0009] Preferably, the elevator mechanism includes a horizontal stabilizer fixed to the fuselage bracket. The horizontal stabilizer is horizontally arranged. A horizontally adjustable stabilizer is rotatably arranged at the rear side of the horizontal stabilizer. A third mounting seat is fixed to the bottom of the horizontally adjustable stabilizer. One end of a third linkage rod is rotatably connected to the third mounting seat, and the other end of the third linkage rod is fixedly connected to the end of a third adjusting arm. The third adjusting arm is fixedly arranged on the power output shaft of a third servo motor, and the third servo motor is fixed below the horizontal stabilizer.

[0010] Preferably, it further includes a housing arranged on the surfaces of the wing bracket and the fuselage bracket. The surface of the housing is smooth. An adjustment opening is formed in the housing and is matched with the power motor to provide a certain moving space for the power motor.

[0011] Preferably, the integrated control mechanism includes a power system and a control system arranged in the fuselage bracket. The power system includes a battery module, a power distribution module, and a power supply line connected to each power motor, the first servo motor, the second servo motor, and the third servo motor. The control system includes a flight control main board, a GPS module, an attitude sensor, a video transmission module, and a remote control receiving module. The flight control main board is used to uniformly control the coordinated operation of flight components such as the power mechanism, the aileron mechanism, the rudder mechanism, and the elevator mechanism.

[0012] Preferably, the battery module adopts a detachable design and is fixedly installed in a battery slot at the inner bottom of the fuselage bracket. A quick-release lock structure is arranged on the surface of the battery slot to facilitate the quick replacement of the battery module. The power distribution module is fixedly connected between the battery module and each electrical component and is provided with an overcurrent protection device to ensure the safe operation of the system.

[0013] Preferably, the flight control main board is fixedly arranged in an installation cavity at the front of the fuselage bracket and is connected to the GPS module, the attitude sensor, the video transmission module, and the remote control receiving module through a cable. The flight control main board is provided with a central processing unit and multi-channel signal interfaces for processing flight attitude data and outputting control signals to the first servo motor, the second servo motor, the third servo motor, the power motor, and the adjustment motor.

[0014] Preferably, the GPS module is installed in the top housing of the wing bracket. The video transmission module is arranged at a front window in the front housing of the fuselage bracket. The remote control receiving module is wirelessly communicatively connected to the flight control main board and has an automatic return function in case of disconnection.

[0015] The present invention has the following beneficial effects: 1. By adopting a wing bracket and a fuselage bracket with a hollowed-out design, the present invention not only effectively reduces the overall weight of the drone, but also improves the structural strength and aerodynamic efficiency. The wing bracket and the fuselage bracket are vertically connected, enhancing the overall stability and wind resistance, suitable for flight missions in various complex environments. At the same time, it provides a reasonable installation position for each functional module, facilitating structural integration and assembly, and improving the systematicness and practicality of the overall design.

[0016] 2. By setting an adjustable power mechanism and flight control components such as ailerons, rudders, and elevators, and precisely controlling their action angles by servo motors, the present invention realizes multi-dimensional adjustment and control of the flight attitude, significantly improving the balance during vertical takeoff and landing and the stability during flight. Especially in the case of large wind speed changes or uneven loads, it can still maintain good flight performance and safety, enhancing the operation reliability.

[0017] 3. By integrating the control mechanism, the power system and the control system are modularly arranged inside the fuselage bracket, effectively shortening the line length, optimizing the electrical connection structure, and improving the system integration degree. The battery module is installed in a quick-release manner, facilitating replacement and maintenance; the control system uniformly schedules the power system and flight control components through the flight control main board to achieve precise response and autonomous control. At the same time, it has functions such as video transmission, GPS positioning, and return-to-home in case of loss of connection, improving the intelligent level and flight safety guarantee ability.

[0018] 4. The angle-adjustable power mechanism adopted by the present invention rotates the adjusting rod by adjusting the motor, thereby realizing the dynamic change of the rotor angle, enabling the rotor to smoothly switch between vertical takeoff and landing and horizontal cruising, significantly improving the flight flexibility and energy efficiency ratio. This mechanism is not only applicable to the attitude adjustment in different takeoff and landing environments, but also can automatically adjust the thrust direction according to the flight stage, optimize the aerodynamic performance, shorten the takeoff and landing time, improve the load capacity and flight time performance, and is especially suitable for performing multi-task flight operations in complex terrains. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 One of the schematic diagrams of the internal structure of the outer shell; Figure 2 The schematic diagram of the connection state of the wing bracket and the fuselage bracket; Figure 3 The schematic diagram of the wing bracket structure; Figure 4 The schematic diagram of the fuselage bracket structure; Figure 5 The schematic diagram of the power mechanism structure; Figure 6 The schematic diagram of the aileron mechanism structure; Figure 7 Another schematic diagram of the internal structure of the outer shell; Figure 8 It is the third schematic diagram of the internal structure of the housing; Figure 9 It is the schematic diagram of the rudder mechanism structure; Figure 10 It is the fourth schematic diagram of the internal structure of the housing; Figure 11 It is the schematic diagram of the elevator mechanism structure; Figure 12 It is the schematic diagram of the UAV structure; Figure 13 It is the schematic diagram of the UAV structure in the vertical takeoff and landing state.

[0020] In the figure: 1. Wing support; 101. Support body one; 102. Aileron installation position; 103. Power mechanism installation position; 104. Fuselage support installation position; 2. Fuselage support; 201. Support body two; 202. Wing support installation position; 203. Installation cavity; 204. Rudder mechanism installation position; 205. Elevator mechanism installation position; 3. Power mechanism; 301. Adjusting rod; 302. Installation block; 303. Power motor; 304. Rotor; 305. Adjusting motor; 4. Integrated control mechanism; 5. Aileron mechanism; 501. Aileron body; 502. First mounting seat; 503. First linkage rod; 504. First adjusting arm; 505. First servo motor; 6. Landing gear; 7. Rudder mechanism; 701. Vertical fin; 702. Vertical adjusting fin; 703. Second mounting seat; 704. Second linkage rod; 705. Second adjusting arm; 706. Second servo motor; 8. Elevator mechanism; 801. Horizontal fin; 802. Horizontal adjusting fin; 803. Third mounting seat; 804. Third linkage rod; 805. Third adjusting arm; 806. Third servo motor; 9. Housing; 901. Adjusting port. Specific implementation manners

[0021] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments.

[0022] Refer to Figures 1 - 13, a vertical takeoff and landing fixed-wing long-endurance unmanned aerial vehicle, comprising a wing support 1, which is used as a support framework for the wings of the unmanned aerial vehicle and is designed in a hollowed-out manner; a fuselage support 2, which is used as a support framework for the fuselage of the unmanned aerial vehicle and is designed in a hollowed-out manner, is fixed below the wing support 1 and is arranged perpendicular to the wing support 1; a power mechanism 3, which is used for the vertical takeoff and landing of the unmanned aerial vehicle, is fixedly installed on the wing support 1 and comprises an adjustment rod 301. Two mounting blocks 302 are fixedly arranged on the adjustment rod 301. A power motor 303 is fixed on one side of the mounting block 302. A rotor 304 is fixed at the output end of the power motor 303. One end of the adjustment rod 301 is fixed at the power output end of an adjustment motor 305; an integrated control mechanism 4 is arranged inside the fuselage support 2 and is used for power supply and control of electronic components; an aileron mechanism 5, which is used for assisting flight, is installed on the wing support 1 and comprises an aileron body 501 rotatably arranged on the wing support 1. A first mounting seat 502 is fixed below the aileron body 501. The first mounting seat 502 is rotatably connected to one end of a first linkage rod 503. The other end of the first linkage rod 503 is rotatably connected to the end of a first adjustment arm 504. The other end of the first adjustment arm 504 is fixedly connected to the power output end of a first servo motor 505. The first servo motor 505 is fixedly arranged inside the wing support 1; a landing gear 6 is installed below the fuselage support 2 and is used for supporting the unmanned aerial vehicle; a rudder mechanism 7 is installed behind the fuselage support 2 and is used for assisting steering; an elevator mechanism 8 is installed behind the fuselage support 2 and is used for assisting takeoff and landing.

[0023] In this embodiment, efficient flight and flexible takeoff and landing are achieved through optimized structural design. The wing support 1 and the fuselage support 2 are designed in a hollowed-out manner, reducing weight and providing stable support for the wings and the fuselage. The power mechanism 3 realizes the switching between vertical takeoff and landing and cruise modes through the adjustment rod 301, the mounting blocks 302, the power motor 303, the rotor 304 and the adjustment motor 305, improving the mission adaptability. The integrated control mechanism 4 is responsible for power supply and electronic control to ensure the coordinated operation of the system. The aileron mechanism 5 assists in adjusting the flight attitude through the aileron body 501, the first mounting seat 502, the first linkage rod 503, the first adjustment arm 504 and the first servo motor 505. The landing gear 6 supports takeoff and landing, and the rudder mechanism 7 and the elevator mechanism 8 assist in steering and takeoff and landing respectively, jointly enhancing the maneuverability and stability of the unmanned aerial vehicle and being suitable for long-endurance missions.

[0024] In the present invention, the wing support 1 comprises a first support body 101. The first support body 101 is in an overall streamline-shaped frame structure. An aileron mounting position 102 matching the aileron mechanism 5 and a power mechanism mounting position 103 matching the power mechanism 3 are arranged on the first support body 101. A fuselage support mounting position 104 for fixing to the fuselage support 2 is further arranged below the first support body 101.

[0025] In this embodiment, the support body 101 of the streamlined frame structure optimizes the aerodynamic performance, reduces the weight and enhances the flight efficiency. An aileron mounting position 102 is provided on the support body 101, which is matched with the aileron mechanism 5 to facilitate the installation and precise control of the flight attitude; the power mechanism mounting position 103 is matched with the power mechanism 3 to ensure the stable fixation of the rotor and the motor and support the vertical take-off and landing function; the fuselage support mounting position 104 is located below the support body 101 and is used to firmly connect with the fuselage support 2 to form a stable overall structure. This modular design facilitates assembly and maintenance. The streamlined frame reduces wind resistance, improves the endurance and mission adaptability of the long-endurance UAV, and is suitable for scenarios such as aerial photography and surveying.

[0026] In the present invention, the fuselage support 2 includes a support body 201 of the second part. An aileron support mounting position 202 for fixing with the aileron support 1 is provided above the support body 201 of the second part. An installation cavity 203 matched with the integrated control mechanism 4 is provided in front of the support body 201 of the second part. A rudder mechanism mounting position 204 matched with the rudder mechanism 7 and an elevator mechanism mounting position 205 matched with the elevator mechanism 8 are provided behind the support body 201 of the second part.

[0027] In this embodiment, the support body 201 of the second part provides the core support of the UAV, and a hollow design is adopted to reduce the weight and ensure the structural strength. An aileron support mounting position 202 is provided above the support body 201 of the second part, which is firmly connected with the aileron support 1 to form a stable frame. An installation cavity 203 is provided in front of the support body 201 of the second part, which is matched with the integrated control mechanism 4 to provide a protection space for the flight control main board and electronic components and ensure the coordinated operation of the system. A rudder mechanism mounting position 204 and an elevator mechanism mounting position 205 are provided behind the support body 201 of the second part, which are respectively matched with the rudder mechanism 7 and the elevator mechanism 8 to assist in steering and take-off and landing control. This modular layout optimizes the space utilization, improves the maintenance convenience, supports the stability and mobility of the UAV in complex tasks, and is suitable for applications such as inspection and surveying.

[0028] In the present invention, the rudder mechanism 7 includes a vertical tail 701 fixed on the fuselage support 2. The vertical tail 701 is vertically arranged. A vertical adjustable tail 702 is rotatably arranged at the rear side of the vertical tail 701. A second mounting seat 703 is fixed on one side of the vertical adjustable tail 702. One end of a second linkage rod 704 is rotatably connected to the second mounting seat 703. The other end of the second linkage rod 704 is rotatably arranged at the end of a second adjusting arm 705. One end of the second adjusting arm 705 is fixed on the power output shaft of a second servo motor 706. The second servo motor 706 is fixed on the vertical tail 701.

[0029] In this embodiment, the vertical stabilizer 701 is fixed to the fuselage bracket 2 to provide steering stability and control capabilities for the UAV. The vertical adjustment stabilizer 702 at the rear of the vertical stabilizer 701 is rotatably arranged and connected to the second servo motor 706 through the second mounting seat 703, the second linkage rod 704, and the second adjustment arm 705. The second servo motor 706 is fixed to the vertical stabilizer 701 to drive the vertical adjustment stabilizer 702 to achieve precise angle adjustment. This design ensures steering flexibility and response speed through servo motor control, enhancing the maneuverability of the UAV under complex flight routes or wind conditions. The modular connection structure facilitates installation and maintenance, enabling the UAV to achieve efficient steering during tasks such as inspection and mapping, significantly improving flight stability and control performance, and meeting the requirements of high-precision tasks.

[0030] In the present invention, the elevator mechanism 8 includes a horizontal stabilizer 801 fixed to the fuselage bracket 2. The horizontal stabilizer 801 is horizontally arranged, and a horizontal adjustment stabilizer 802 is rotatably arranged at the rear of the horizontal stabilizer 801. The bottom of the horizontal adjustment stabilizer 802 is fixed with a third mounting seat 803. One end of the third linkage rod 804 is rotatably connected to the third mounting seat 803, and the other end of the third linkage rod 804 is fixedly connected to the end of the third adjustment arm 805. The third adjustment arm 805 is fixedly arranged on the power output shaft of the third servo motor 806, and the third servo motor 806 is fixed below the horizontal stabilizer 801.

[0031] In this embodiment, by setting the horizontal stabilizer 801 and the horizontal adjustment stabilizer 802, precise control of the pitch attitude of the UAV is achieved, enhancing its stability and flexibility during takeoff, landing, and flight. The horizontal adjustment stabilizer 802 realizes rotational linkage control through the third mounting seat 803, the third linkage rod 804, and the third adjustment arm 805, and is driven by the third servo motor 806. It can quickly respond to adjustment commands according to the flight control system instructions, ensuring coordinated changes in lift and pitch angle, improving the overall control performance and flight safety of the aircraft, and being suitable for various flight attitude requirements.

[0032] In the present invention, it further includes a housing 9 provided on the surfaces of the wing bracket 1 and the fuselage bracket 2. The surface of the housing 9 is smooth, and an adjustment opening 901 is provided on the housing 9, which is matched with the power motor 303 to provide a certain moving space for the power motor 303.

[0033] In this embodiment, the housing 9 is arranged outside the wing bracket 1 and the fuselage bracket 2, and is a smooth structure as a whole, having good aerodynamic characteristics, which helps to reduce the wind resistance coefficient during flight and improve flight efficiency. The adjustment opening 901 provided thereon is matched with the position of the power motor 303, which can provide the necessary movement space for the angle adjustment of the power motor 303, ensuring a smooth switch between the vertical takeoff and landing mode and the horizontal cruise mode, and facilitating later maintenance and assembly operations, thereby improving the practicality and adaptability of the overall structure.

[0034] In the present invention, the integrated control mechanism 4 includes an electric power system and a control system arranged in the fuselage bracket 2, the electric power system includes a battery module, a power distribution module and a power supply line connected to each power motor 303 and the first servo motor 505, the second servo motor 706 and the third servo motor 806, the control system includes a flight control mainboard, a GPS module, an attitude sensor, an image transmission module and a remote control receiving module, and the flight control mainboard is used to uniformly control the coordinated operation of flight components such as the power mechanism 3, the aileron mechanism 5, the rudder mechanism 7 and the elevator mechanism 8.

[0035] In this embodiment, the integrated control mechanism 4 is located inside the fuselage bracket 2, and includes two major parts: the power system and the control system. The power system is composed of a battery module, a power distribution module, and a power supply line connecting each power motor 303 with the first servo motor 505, the second servo motor 706, and the third servo motor 806 to ensure the stable power supply of each driving component. The control system includes a flight control mainboard, a GPS module, an attitude sensor, an image transmission module, and a remote control receiving module. The flight control mainboard is responsible for coordinating the actions of the power mechanism 3, the aileron mechanism 5, the rudder mechanism 7, and the elevator mechanism 8 to achieve precise flight control and attitude adjustment, and enhance the autonomous flight capability and safety performance of the UAV.

[0036] In the present invention, the battery module adopts a detachable design and is fixedly installed in the battery slot at the bottom of the fuselage bracket 2. A quick-release lock structure is provided on the surface of the battery slot to facilitate rapid replacement of the battery module. The power distribution module is fixedly connected between the battery module and each power-consuming component, and a current overload protection device is provided to ensure the safe operation of the system.

[0037] In this embodiment, the battery module adopts a detachable design and is fixedly installed in the battery slot at the bottom of the fuselage bracket 2. The surface of the battery slot is provided with a quick-release lock structure to facilitate the rapid disassembly and replacement of the battery module, thereby improving maintenance efficiency and endurance flexibility. The power distribution module is fixedly connected between the battery module and each power-consuming component, and has a built-in current overload protection device to effectively prevent system failures caused by abnormal current, ensure the safe and stable operation of the entire power system, and improve the reliability and service life of the drone.

[0038] In the present invention, the flight control mainboard is fixedly arranged in the installation cavity 203 at the front part of the fuselage bracket 2, and is connected with the GPS module, attitude sensor, image transmission module and remote control receiving module through wiring. The flight control mainboard is provided with a central processing unit and a multi-channel signal interface for processing flight attitude data and outputting control signals to the first servo motor 505, the second servo motor 706, the third servo motor 806, the power motor 303 and the adjustment motor 305.

[0039] In this embodiment, the flight control main board is fixedly installed in the installation cavity 203 at the front of the fuselage bracket 2 and is connected to the GPS module, the attitude sensor, the video transmission module and the remote control receiving module through a wiring harness to realize real-time data transmission and processing. The flight control main board is internally provided with a central processing unit and multi-channel signal interfaces, which are responsible for processing flight attitude data and generating precise control signals, and respectively outputting them to the first servo motor 505, the second servo motor 706, the third servo motor 806, the power motor 303 and the adjustment motor 305 to coordinate the actions of each flight component and ensure the stability and response speed of the UAV flight.

[0040] In the present invention, the GPS module is installed in the top shell 9 of the wing bracket 1, the video transmission module is arranged at the front window in the front end shell 9 of the fuselage bracket 2, and the remote control receiving module is wirelessly communicatively connected to the flight control main board and has an automatic return function in case of signal loss.

[0041] In this embodiment, the GPS module is installed in the shell 9 at the top of the wing bracket (1) to ensure stable and reliable satellite signal reception; the video transmission module is arranged at the front window in the front end shell 9 of the fuselage bracket (2) to realize real-time transmission and monitoring of flight videos; the remote control receiving module is wirelessly communicatively connected to the flight control main board, supports remote control, and has an automatic return function in case of signal loss, effectively ensuring the safe return of the UAV when the signal is interrupted and improving the overall flight safety and the reliability of mission execution.

[0042] The above is only a preferred specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention, according to the technical solution of the present invention and its inventive concept, makes equivalent substitutions or changes, and all should be covered within the protection scope of the present invention.

Claims

1. A vertical takeoff and landing fixed-wing long-endurance unmanned aerial vehicle, characterized in that, Comprising: A wing support (1) for serving as a support framework for the wings of the drone, with a hollowed-out design; A fuselage support (2) for serving as a support framework for the fuselage of the drone, with a hollowed-out design, fixed below the wing support (1) and perpendicularly arranged with respect to the wing support (1); A power mechanism (3) for the vertical takeoff and landing of the drone, fixedly installed on the wing support (1), including an adjustment rod (301), on which two mounting blocks (302) are fixedly arranged. One side of the mounting block (302) is fixed with a power motor (303), and the output end of the power motor (303) is fixed with a rotor (304). One end of the adjustment rod (301) is fixed to the power output end of an adjustment motor (305); An integrated control mechanism (4) arranged inside the fuselage support (2) for power supply and control of electronic components; An aileron mechanism (5) for assisting flight, installed on the wing support (1), including an aileron body (501) rotatably arranged on the wing support (1). Below the aileron body (501) is fixed a first mounting seat (502). The first mounting seat (502) is rotatably connected to one end of a first linkage rod (503), and the other end of the first linkage rod (503) is rotatably connected to the end of a first adjustment arm (504). The other end of the first adjustment arm (504) is fixedly connected to the power output end of a first servo motor (505), and the first servo motor (505) is fixedly arranged inside the wing support (1); A landing gear (6) installed below the fuselage support (2) for supporting the drone; A rudder mechanism (7) installed behind the fuselage support (2) for assisting in steering; An elevator mechanism (8) installed behind the fuselage support (2) for assisting in takeoff and landing.

2. The vertical takeoff and landing fixed-wing long-endurance unmanned aerial vehicle according to claim 1, wherein The wing support (1) includes a support body one (101), the support body one (101) is a streamlined frame structure as a whole, and on the support body one (101) are provided an aileron mounting position (102) matching the aileron mechanism (5), a power mechanism mounting position (103) matching the power mechanism (3), and below the support body one (101) is also provided a fuselage support mounting position (104) for fixing to the fuselage support (2).

3. The vertical takeoff and landing fixed-wing long-endurance unmanned aerial vehicle according to claim 1, wherein The fuselage support (2) includes a support body two (201). Above the support body two (201) is provided a wing support mounting position (202) for fixing to the wing support (1). In front of the support body two (201) is provided a mounting cavity (203) matching the integrated control mechanism (4). Behind the support body two (201) are provided a rudder mechanism mounting position (204) matching the rudder mechanism (7) and an elevator mechanism mounting position (205) matching the elevator mechanism (8).

4. The vertical takeoff and landing fixed-wing long-endurance unmanned aerial vehicle according to claim 1, wherein The rudder mechanism (7) includes a vertical stabilizer (701) fixed to the fuselage bracket (2). The vertical stabilizer (701) is vertically arranged. A vertically adjustable fin (702) is rotatably arranged at the rear side of the vertical stabilizer (701). A second mounting seat (703) is fixed to one side of the vertically adjustable fin (702). One end of a second linkage rod (704) is rotatably connected to the second mounting seat (703). The other end of the second linkage rod (704) is rotatably arranged at the end of a second adjusting arm (705). One end of the second adjusting arm (705) is fixed to the power output shaft of a second servo motor (706). The second servo motor (706) is fixed to the vertical stabilizer (701).

5. The vertical takeoff and landing fixed-wing long-endurance unmanned aerial vehicle according to claim 1, wherein The elevator mechanism (8) includes a horizontal stabilizer (801) fixed to the fuselage bracket (2). The horizontal stabilizer (801) is horizontally arranged. A horizontally adjustable fin (802) is rotatably arranged at the rear side of the horizontal stabilizer (801). A third mounting seat (803) is fixed to the bottom of the horizontally adjustable fin (802). One end of a third linkage rod (804) is rotatably connected to the third mounting seat (803). The other end of the third linkage rod (804) is fixedly connected to the end of a third adjusting arm (805). The third adjusting arm (805) is fixedly arranged on the power output shaft of a third servo motor (806). The third servo motor (806) is fixed below the horizontal stabilizer (801).

6. The vertical takeoff and landing fixed-wing long-endurance unmanned aerial vehicle according to claim 1, wherein, It further includes a housing (9) arranged on the surfaces of the wing bracket (1) and the fuselage bracket (2). The surface of the housing (9) is smooth. An adjustment opening (901) is formed in the housing (9). The adjustment opening (901) is matched with the power motor (303) and is used to provide a certain moving space for the power motor (303).

7. The vertical takeoff and landing fixed-wing long-endurance unmanned aerial vehicle according to claim 1, characterized in that, The integrated control mechanism (4) includes a power system and a control system arranged in the fuselage bracket (2). The power system includes a battery module, a power distribution module, and a power supply line connected to each power motor (303), the first servo motor (505), the second servo motor (706), and the third servo motor (806). The control system includes a flight control main board, a GPS module, an attitude sensor, a video transmission module, and a remote control receiving module. The flight control main board is used to uniformly control the coordinated operation of flight components such as the power mechanism (3), the aileron mechanism (5), the rudder mechanism (7), and the elevator mechanism (8).

8. The vertical takeoff and landing fixed-wing long-endurance unmanned aerial vehicle according to claim 7, wherein The battery module adopts a detachable design and is fixedly installed in a battery slot at the inner bottom of the fuselage bracket (2). A quick-release lock structure is arranged on the surface of the battery slot, which is convenient for quickly replacing the battery module. The power distribution module is fixedly connected between the battery module and each electrical component and is provided with an overcurrent protection device to ensure the safe operation of the system.

9. The vertical takeoff and landing fixed-wing long-endurance unmanned aerial vehicle according to claim 1, characterized in that The flight control main board is fixedly arranged in the installation cavity (203) at the front of the fuselage bracket (2), and is connected to the GPS module, the attitude sensor, the video transmission module and the remote control receiving module through a flexible cable. The flight control main board is provided with a central processing unit and multi-channel signal interfaces, and is used for processing flight attitude data and outputting control signals to the first servo motor (505), the second servo motor (706), the third servo motor (806), the power motor (303) and the adjustment motor (305).

10. The vertical takeoff and landing fixed-wing long-endurance unmanned aerial vehicle according to claim 1, wherein The GPS module is installed in the top shell (9) of the wing bracket (1), the video transmission module is arranged at the front window in the front-end shell (9) of the fuselage bracket (2), and the remote control receiving module is wirelessly communicatively connected to the flight control main board and has an automatic return function in case of signal loss.

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