Vertical fixed-wing unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a vertical fixed wing unmanned aerial vehicle which comprises an unmanned aerial vehicle body, fixed wings are fixedly arranged on the two sides of the unmanned aerial vehicle body, winglets are fixedly arranged at the tail ends of the fixed wings, a fixing frame is fixedly arranged at the lower ends of the fixed wings, and motors are fixedly arranged at the upper ends of the two sides of the fixing frame. A vertical take-off and landing rotor wing is arranged at the output end of the motor in a transmission mode, a double-tail-boom inverted-V-shaped tail is fixedly arranged at the tail end of the fixed wing, a piston gasoline engine is fixedly arranged at the tail end of the unmanned aerial vehicle body, and a push-back type propeller is arranged at the output end of the piston gasoline engine in a transmission mode. The problems that in the prior art, the voyage is short, the loading capacity is limited, and the plateau adaptability is poor are solved, efficient vertical take-off and landing, long-endurance flight, large-load adaptation and complex environment operation capacity are achieved, a dual-redundancy flight control system is adopted, and flight safety is ensured.

Description

TECHNICAL FIELD

[0001] The utility model relates to unmanned plane technical field, concretely is a kind of vertical take-off fixed wing unmanned plane. BACKGROUND

[0002] The existing vertical take-off unmanned plane (such as multi-rotor type) generally has the problems of short range, low load capacity and poor adaptability on plateau;Traditional fixed-wing unmanned plane needs to rely on runway to take off and land, which limits its application in emergency, surveying and mapping and other scenarios. Some vertical take-off fixed-wing unmanned planes can take into account vertical take-off and long flight time, but their aerodynamic efficiency, load expansion and extreme environment adaptability are still insufficient. For example:

[0003] Aerodynamic layout defects: conventional layout leads to large cruising resistance, and limited endurance;

[0004] Single power system: unable to realize efficient switching between rotor and cruising mode, low energy utilization rate;

[0005] Therefore, a vertical take-off fixed-wing unmanned plane is needed to improve the above problems. INVENTION CONTENTS

[0006] The utility model aims at providing a vertical take-off fixed-wing unmanned plane to solve the problems raised in the background.

[0007] To achieve the above object, the utility model provides the following technical scheme:

[0008] A vertical take-off fixed-wing unmanned plane, comprising an unmanned plane body, fixed wings are fixed on both sides of the unmanned plane body, wing tip strakes are fixed at the ends of the fixed wings, fixed frames are fixed at the lower ends of the fixed wings, motors are fixed at the upper ends of both sides of the fixed frames, vertical take-off rotors are driven by the output ends of the motors, double-tail strut inverted V tails are fixed at the ends of the fixed wings, piston gasoline engines are fixed at the ends of the unmanned plane body, and rear push type propellers are driven by the output ends of the piston gasoline engines.

[0009] Further, direction elevators adjusting mechanisms and aileron adjusting mechanisms are respectively installed on the lower sides of the fixed wings and the double-tail strut inverted V tails.

[0010] Further, the direction elevators adjusting mechanisms comprise rudders, hinge rods and ailerons, and the direction elevators adjusting mechanisms and the aileron adjusting mechanisms have the same structure.

[0011] Further, mounting grooves are arranged on the surfaces of the fixed wings and the double-tail strut inverted V tails, and the ailerons are rotatably arranged in the mounting grooves.

[0012] Further, rudders are fixed on the lower surfaces of the fixed wings and the double-tail strut inverted V tails, hinge rods are rotatably connected to the output ends of the rudders, and the other ends of the hinge rods are rotatably connected to the ailerons.

[0013] Furthermore, the lower end of the UAV body is fixedly equipped with a three-light pod and several fixed buffer landing gears, and the front end of the UAV body is fixedly equipped with a pitot tube.

[0014] Furthermore, an electronic speed controller is fixedly installed on the surface of the mounting frame, and the speed of the UAV body is adjusted by the electronic speed controller.

[0015] Compared with the prior art, the beneficial effects of this utility model are:

[0016] 1. Composite aerodynamic layout:

[0017] It adopts a high aspect ratio high-wing monoplane design with winglets to reduce induced drag and improve lift-to-drag ratio; the twin-boom inverted V-tail layout enhances flight stability and pitch control efficiency.

[0018] 2. Intelligent power system:

[0019] The combination of a rear-push propeller and a vertical take-off and landing rotor enables intelligent switching between rotor and cruise modes, improving endurance; the interchangeable pods are adaptable to various tasks such as surveying, inspection, and emergency communication.

[0020] 3. Redundant control system:

[0021] By employing a composite aerodynamic layout, intelligent power system, and modular design, this technology addresses issues such as short range, limited payload capacity, and poor adaptability to high altitudes, enabling efficient vertical takeoff and landing, long-endurance flight, high-payload adaptability, and operation in complex environments. A dual-redundant flight control system ensures flight safety. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the overall three-dimensional top view of the present invention;

[0023] Figure 2 This is a schematic diagram of the overall three-dimensional bottom view of the present invention;

[0024] Figure 3 This is a schematic diagram of the steering elevator adjustment mechanism of this utility model;

[0025] Figure 4 This is a schematic diagram of the overall side structure of this utility model;

[0026] Figure 5 This is a schematic diagram of the overall front structure of this utility model.

[0027] In the diagram: 1. UAV body; 2. Vertical takeoff and landing rotor; 3. Fixed wing; 4. Winglet; 5. Motor; 6. Mount; 7. Twin-boom inverted V-tail; 8. Pusher propeller; 9. Piston gasoline engine; 10. Elevator adjustment mechanism; 11. Fixed buffer landing gear; 12. Aileron adjustment mechanism; 13. Electronic speed controller; 14. Tri-light pod; 15. Piston tube; 16. Servo; 17. Hinge rod; 18. Aileron. Detailed Implementation

[0028] The technical solutions of the present invention will be clearly and completely described below with reference to the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0029] To facilitate understanding of the present invention, a more complete description will be given below with reference to relevant descriptions. Several embodiments of the invention are provided. However, the invention can be implemented in many different forms and is not limited to the embodiments described herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete.

[0030] It should be noted that when a component is said to be "fixed to" another component, it can be directly on the other component or there may be an intervening component. When a component is said to be "connected to" another component, it can be directly connected to the other component or there may be an intervening component. The terms "vertical," "horizontal," "left," "right," and similar expressions used in this document are for illustrative purposes only.

[0031] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. The terminology used herein in the description of the invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0032] like Figures 1-5As shown, this utility model provides a technical solution: a vertical takeoff and landing (VTOL) fixed-wing unmanned aerial vehicle (UAV), including a UAV body 1, fixed wings 3 fixed on both sides of the UAV body 1, winglets 4 fixed at the ends of the fixed wings 3, a fixed frame 6 fixed at the lower end of the fixed wings 3, motors 5 fixed at the upper ends of both sides of the fixed frame 6, VTOL rotors 2 driven by the output ends of the motors 5, a double-boom inverted V-tail 7 fixed at the ends of the fixed wings 3, and a piston gasoline engine 9 fixed at the ends of the UAV body 1, with a pusher propeller 8 driven by the output end of the piston gasoline engine 9. Vertical takeoff and landing (VTOL) is achieved by the motors 5 driving the VTOL rotors 2, and forward propulsion is provided by the piston gasoline engine 9 driving the pusher propeller 8. The design of the fixed wings 3 and the double-boom inverted V-tail 7 improves flight stability and controllability, while the winglets 4 reduce wingtip vortices and improve flight efficiency.

[0033] As an example of this utility model, a directional elevator adjustment mechanism 10 and an aileron adjustment mechanism 12 are respectively installed on the lower sides of the fixed wing 3 and the twin-tailed V-tail 7. The directional elevator adjustment mechanism 10 and the aileron adjustment mechanism 12 can automatically adjust the angle of the aileron 18 according to the flight status, optimize lift and drag, and improve flight performance.

[0034] As an example of this utility model, the elevator adjustment mechanism 10 includes a servo motor 16, a hinge rod 17, and an aileron 18. The elevator adjustment mechanism 10 and the aileron adjustment mechanism 12 have the same structure. The servo motor 16 drives the aileron 18 to rotate through the hinge rod 17, thereby adjusting the aileron angle and improving flight flexibility and adaptability.

[0035] As an example of this utility model, both the fixed wing 3 and the double-tailed V-tail 7 have mounting grooves on their surfaces, and the aileron 18 is rotatably mounted inside the mounting groove. The design of the mounting groove provides a stable mounting position for the aileron 18, ensuring that the aileron 18 can rotate smoothly during adjustment.

[0036] As an example of this utility model, a servo motor 16 is fixedly mounted on the lower surface of both the fixed wing 3 and the twin-tailed V-tail 7. A hinge rod 17 is rotatably connected to the output end of the servo motor 16, and the other end of the hinge rod 17 is rotatably connected to the aileron 18. The servo motor 16 achieves precise control of the angle of the aileron 18 through the rotation of the hinge rod 17, thereby improving flight stability and maneuverability.

[0037] As an example of this utility model, the lower end of the UAV body 1 is fixedly equipped with a three-light pod 14 and several fixed buffer landing gears 11, and the front end of the UAV body 1 is fixedly equipped with a pitot tube 15. The three-light pod 14 can provide a variety of optical sensor functions for monitoring and data acquisition, the fixed buffer landing gears 11 ensure the stability and safety of the UAV during takeoff and landing, and the pitot tube 15 is used to measure flight speed and provide accurate flight data.

[0038] As an example of this utility model, an electronic speed controller 13 is fixedly provided on the surface of the mounting bracket 6, and the speed of the UAV body 1 is adjusted by the electronic speed controller 13.

[0039] Working principle: During use, the vertical take-off and landing phase:

[0040] During takeoff and landing, motor 5 drives the vertical takeoff and landing rotor 2 to rotate at high speed, generating sufficient lift to enable the drone to take off or land vertically. This design is similar to the takeoff and landing method of multi-rotor drones, enabling takeoff and landing in limited spaces, making it suitable for use in complex terrain or narrow spaces.

[0041] During vertical takeoff and landing, the aileron adjustment structures (elevator adjustment mechanism 10 and aileron adjustment mechanism 12) on the fixed wing 3 and the twin tail boom V-tail 7 control the angle of the aileron 18 through the servo motor 16, increasing the lift of the wings and tail, and further improving the stability and safety of vertical takeoff and landing.

[0042] Fixed-wing flight phase:

[0043] Once the drone reaches a certain altitude, it switches to fixed-wing flight mode. At this time, the piston gasoline engine 9 drives the rear-mounted propeller 8 to rotate, providing forward thrust to the drone and enabling it to enter cruise flight mode.

[0044] In fixed-wing flight mode, the aerodynamic design of the fixed wing 3 and the twin-tailed inverted V-tail 7 provides good lift and stability. At the same time, by adjusting the angle of the aileron 18, the flight attitude can be finely adjusted to optimize flight performance.

[0045] Flight control and data transmission

[0046] Flight attitude control:

[0047] The directional elevator adjustment mechanism 10 and the aileron adjustment mechanism 12 control the rotation angle of the aileron 18 through the servo motor 16 and the hinge rod 17, thereby changing the aerodynamic characteristics of the fixed wing 3 and the twin-tailed inverted V-tail 7, and achieving precise control of the UAV's flight attitude.

[0048] For example, during climb or descent, the angle of the aileron 18 can be adjusted to increase or decrease lift; during turns, the angle of the aileron 18 can also be fine-tuned to achieve smoother turns.

[0049] Data transmission and monitoring:

[0050] The UAV body 1 is wirelessly connected to the ground terminal via a wireless transceiver on the mounting bracket 6, enabling data transmission and remote control. Ground operators can receive flight data (such as speed, altitude, attitude, etc.) from the UAV through the terminal equipment and send control commands to achieve real-time monitoring and operation of the UAV.

[0051] The pitot tube 15 at the front of the drone is used to measure flight speed, providing accurate speed data to the flight control system to ensure flight safety and stability.

[0052] Landing and Buffer

[0053] Landing phase:

[0054] During landing, the vertical takeoff and landing rotor 2 restarts, and the electronic speed controller 13 adjusts the speed to provide sufficient lift, enabling the UAV to land smoothly.

[0055] The fixed buffer landing gear 11 at the lower end of the UAV body 1 can absorb the impact force during landing, protect the UAV body and key components, and ensure a safe landing.

[0056] Task payloads and applications:

[0057] The three-light pod 14 at the lower end of the UAV body 1 can be used to carry a variety of mission payloads, such as optical cameras and infrared thermal imagers, for tasks such as reconnaissance, mapping, and environmental monitoring.

[0058] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A vertical take-off and landing fixed-wing unmanned aerial vehicle (UAV), comprising a UAV body (1), characterized in that: The UAV body (1) is fixed with fixed wings (3) on both sides, and winglets (4) are fixed at the ends of the fixed wings (3). A fixed frame (6) is fixed at the lower end of the fixed wings (3). Motors (5) are fixed at the upper ends of both sides of the fixed frame (6). A vertical take-off and landing rotor (2) is driven at the output end of the motor (5). A double tail boom inverted V tail (7) is fixed at the end of the fixed wings (3). A piston gasoline engine (9) is fixed at the end of the UAV body (1). A pusher propeller (8) is driven at the output end of the piston gasoline engine (9).

2. The vertical take-off and landing fixed-wing unmanned aerial vehicle according to claim 1, characterized in that: The fixed wing (3) and the twin-tailed inverted V-tail (7) are respectively equipped with a directional elevator adjustment mechanism (10) and an aileron adjustment mechanism (12).

3. A vertical take-off and landing fixed-wing unmanned aerial vehicle according to claim 2, characterized in that: The directional elevator adjustment mechanism (10) includes a servo motor (16), a hinge rod (17), and an aileron (18). The directional elevator adjustment mechanism (10) and the aileron adjustment mechanism (12) have the same structure.

4. A vertical take-off and landing fixed-wing unmanned aerial vehicle according to claim 3, characterized in that: The fixed wing (3) and the double tail boom inverted V tail (7) are both provided with mounting grooves, and the aileron (18) is rotatably mounted inside the mounting groove.

5. A vertical take-off and landing fixed-wing unmanned aerial vehicle according to claim 4, characterized in that: Servo motors (16) are fixedly installed on the lower surfaces of the fixed wing (3) and the double-tailed inverted V-tail (7). A hinge rod (17) is rotatably connected to the output end of the servo motor (16), and the other end of the hinge rod (17) is rotatably connected to the aileron (18).

6. A vertical take-off and landing fixed-wing unmanned aerial vehicle according to claim 5, characterized in that: The lower end of the UAV body (1) is fixedly equipped with a three-light pod (14) and several fixed buffer landing gears (11), and the front end of the UAV body (1) is fixedly equipped with an airspeed tube (15).

7. A vertical take-off and landing fixed-wing unmanned aerial vehicle according to claim 6, characterized in that: An electronic speed controller (13) is fixedly mounted on the surface of the mounting frame (6), and the speed of the UAV body (1) is adjusted by the electronic speed controller (13).

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