Large unmanned aerial vehicle capable of flying stably

Abstract

The invention relates to the technical field of unmanned aerial vehicles, in particular to a stable-flight large unmanned aerial vehicle which comprises a fuselage, a power storage device, an undercarriage device and propellers, the power storage device is arranged at the upper end of the fuselage, the undercarriage device is located at the lower end of the fuselage, and the propellers are located on the periphery of the fuselage. Hydraulic rods are arranged at the top ends of the hydraulic rod supporting rods, the output ends of the hydraulic rods are fixed to the four corners of the bottom of the solar panel, a storage battery supporting rod is arranged in the middle of the hydraulic rods, and a storage battery is fixedly connected to the upper end of the storage battery supporting rod and electrically connected with a conversion port of the solar panel; according to the scheme, a fuel-electric hybrid mode combining the fuel tank and the storage battery is adopted, the fuel tank is arranged at the middle section of the bottom of the fuselage, the solar panel is arranged at the top, the angle of the solar panel is adjusted through the hydraulic rod, wind resistance and fuselage stabilization are achieved, light tracking and energy storage are achieved, flight performance is improved in cooperation with the vortex generator, and endurance is remarkably prolonged.

Description

Technical Field

[0001] The invention relates to the technical field of unmanned aerial vehicles, and in particular to a large unmanned aerial vehicle with stable flight. Background Art

[0002] In today's complex and ever-changing operating environment, existing drones have exposed many shortcomings. The flight stability is poor. When flying through complex areas such as cities with tall buildings and valleys, the airflow is turbulent and complex, and drones are easily affected. For example, in urban canyons, due to the obstruction and guidance of buildings, the airflow forms irregular vortices, and the flight posture of the drone is instantly out of control, causing the shooting picture to shake and blur, seriously affecting the execution of tasks such as aerial photography and surveying. In terms of endurance, its limited power or fuel reserves make it difficult to support long-term continuous operation. When performing large-area inspection tasks, it is often necessary to return to replenish energy before the entire process is completed, which greatly reduces work efficiency and cannot meet the needs of long-term operation scenarios such as power inspection and agricultural plant protection. In order to break through these bottlenecks, it is urgent to deeply improve and innovate the flight stability mechanism and energy supply system of drones to adapt to increasingly stringent application requirements.

[0003] Therefore, the present invention proposes to provide multiple groups of propellers working in coordination, and the propellers and spare propellers use different connection lines to ensure that when the main propeller fails, the spare propeller can quickly take over the flight control and maintain the stable flight of the fuselage; the power reserve device includes a fuel tank and a battery, and the electric energy converted by the solar panel is stored in the battery. The dual energy supply of electric energy and fuel prolongs the flight time and can ensure the flight stability of the UAV; the four corners of the solar panel are fixedly connected with hydraulic rods, and the height of the hydraulic rods is adjusted to adjust the inclination angle of the solar panel, which can be used to resist the wind direction when the UAV is flying and to chase the light, thereby improving the efficiency of the solar panel; the landing gear device is equipped with shock-absorbing springs and shock-absorbing plates to effectively absorb landing impact, reduce fuselage vibration, and improve flight safety and stability. At the same time, the cooperation of the gear group realizes the horizontal and vertical adjustment of the landing gear, so that it can both support the landing of the UAV and balance the flight of the UAV, and has both functionality and practicality. Summary of the invention

[0004] Technical problems solved: insufficient stability and easily affected by airflow.

[0005] In view of the deficiencies in the prior art, the present invention provides a large unmanned aerial vehicle with stable flight, thereby solving the technical problems mentioned in the background technology.

[0006] To achieve the above objectives, the present invention is implemented through the following technical solutions:

[0007] A large unmanned aerial vehicle with stable flight, comprising a fuselage, a power reserve device, a landing gear device, and a propeller; characterized in that the power reserve device is arranged at the upper end of the fuselage, the landing gear device is arranged at the lower end of the fuselage, and the propeller is arranged around the fuselage;

[0008] The power reserve device includes a fuel tank arranged at the middle section of the bottom of the fuselage at the upper end, a solar panel arranged on the top of the fuselage, a hydraulic rod support rod arranged at the upper end of the interior of the fuselage, a hydraulic rod arranged at the top of the hydraulic rod support rod, the output end of the hydraulic rod is fixed at the four corners of the bottom of the solar panel, a battery support rod is arranged in the middle of the hydraulic rod, a battery is fixedly connected to the upper end of the battery support rod, and the battery is electrically connected to the conversion port of the solar panel.

[0009] In a possible implementation, a single propeller group is provided at a symmetrical position on each of the left and right sides of the fuselage, and the propeller group consists of two propellers located at the same height of the fuselage. A group of spare propellers is provided at each of the front and rear ends of the fuselage.

[0010] In a possible implementation, vortex generators are provided on the surface of the solar panel and the fuselage.

[0011] In a possible implementation, a visible light camera is disposed at the front end of the fuselage.

[0012] In a possible implementation, a stepper motor is fixed at the middle position of the bottom of the fuselage, and an active bevel gear is fixedly connected to the output end of the stepper motor. The bevel gear ends of a gear rod are meshed on both sides of the active bevel gear, and the other end of the gear rod is a gear end. The relative position of the active bevel gear and the gear rod is in a vertical state, and the active bevel gear is located between the two gear rods.

[0013] In a possible implementation, a landing gear is provided at the bottom of the side of the fuselage, and the landing gear is in a flat plate shape.

[0014] In a possible implementation, the upper end of the fuselage landing gear is fixedly connected to a rotating rod via a connecting rod, and a driven gear is fixed to the middle of the fuselage rotating rod.

[0015] In a possible implementation, the gear rod is connected by a connecting plate, which is in the shape of a gate with a horizontal opening, and has openings at both ends of the connecting plate. The gear rod body passes through the opening of the connecting plate, and the length of the connecting plate is consistent with the length of the connecting block of the meshing part of the active bevel gear and the gear rod.

[0016] In a possible implementation, the gear at the other end of the gear rod is meshed with a driven gear fixed on the outside of the rotating rod at the upper end of the landing gear through a rack.

[0017] In a possible implementation, a support rod is provided at a position corresponding to the gear rod at the bottom of the fuselage, a hole is opened at the top of the support rod, and the gear rod passes through the opening.

[0018] Beneficial effects compared with the prior art:

[0019] 1. In this scheme, the left and right sides are precisely symmetrically arranged, each equipped with a propeller group consisting of two propellers at the same height. When the drone soars in the sky, its flight control system can flexibly adjust the rotation speed and angle of each propeller group very accurately according to the real-time flight direction. This ingenious design allows the drone to cleverly balance the aerodynamic force during flight. Whether it is flying in a stable straight line or turning, hovering and other operations in a complex environment, it can maintain excellent stability, greatly improving the smoothness and controllability of the flight. In order to cope with possible emergencies, spare propellers are specially set at the front and rear ends of the fuselage. During normal flight, these spare propellers are in a stationary standby state. However, once the main propeller fails for various reasons, such as blade damage, motor failure, etc., the spare propeller will start quickly in a very short time. They can immediately replace the failed main propeller, continue to provide stable lift and propulsion for the drone, ensure the continuity and safety of the drone flight, avoid flight accidents caused by propeller failure, and ensure the flight reliability of the drone.

[0020] 2. In this scheme, the power reserve device is carefully placed at the top of the fuselage, and an innovative hybrid power supply mode combining a fuel tank and a battery is adopted. The fuel tank is cleverly set in the middle of the bottom of the fuselage to provide reliable traditional fuel power support for the flight of the drone. At the same time, a large solar panel is reasonably installed on the top of the fuselage. The solar panel is connected to the fuselage through a hydraulic rod, and the tilt angle can be flexibly adjusted. During the flight, on the one hand, this design can effectively resist the strong wind during the flight, stabilize the fuselage by adjusting the angle of the solar panel, and reduce the interference of wind on the flight posture; on the other hand, it can keenly capture the sun, achieve efficient light chasing, and efficiently convert solar energy into electrical energy and store it in the battery. In addition, the fuselage and the surface of the solar panel are equipped with vortex generators, which can make the boundary layer airflow on the surface of the fuselage interact with each other, introduce the external airflow with higher energy into the boundary layer, increase the kinetic energy of the boundary layer airflow, and effectively delay the separation of the airflow. This series of designs work together to significantly improve the flight performance of the drone, greatly extend its endurance, and enable the drone to perform longer-range and more durable flight missions.

[0021] 3. In this solution, the front end of the drone is equipped with an advanced visible light camera, which can clearly and smoothly transmit the real-time images of the drone during flight to the terminal device. Through these real-time images, the operator can accurately grasp the flight environment and status of the drone, so as to accurately control the drone, whether it is shuttling in a complex urban environment or performing tasks in the field, to ensure the stable flight of the drone. The landing gear at the lower end of the fuselage is in a unique flat plate shape. It uses a stepper motor to drive a complex gear set to achieve free switching between horizontal and vertical directions. When the drone is ready to land, the landing gear is in a vertical state, and the shock absorbing device it is equipped with can effectively absorb the huge impact force generated during landing, ensuring the safe and smooth landing of the drone. When the drone takes off and reaches a certain height, the landing gear can be switched to a horizontal state, at which time it will transform into an auxiliary wing, which can increase the lift of the drone, optimize the flight posture, and further improve the endurance. This ingenious multi-functional conversion design greatly improves the practicality and adaptability of the drone. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] The above description is only an overview of the technical solution of the present invention. In order to more clearly understand the technical means of the present invention and implement it according to the contents of the specification, the following is a detailed description of the preferred embodiments of the present invention in conjunction with the accompanying drawings.

[0023] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0024] Figure 2 It is a schematic diagram of the overall structure of the present invention from another angle;

[0025] Figure 3 It is a schematic structural diagram of a solar panel and an angle adjustment assembly thereof of the present invention;

[0026] Figure 4 It is a schematic diagram of the structure of a gear set consisting of an active bevel gear and a gear rod of the present invention;

[0027] Figure 5 It is a schematic diagram of the gear and rack structure of the present invention;

[0028] Figure 6 It is a schematic diagram of the landing gear structure of the present invention.

[0029] Legend: 1. Fuselage; 2. Propeller; 3. Spare propeller; 4. Fuel tank; 5. Solar panel; 6. Hydraulic rod; 7. Battery; 8. Hydraulic rod support rod; 9. Battery support rod; 10. Vortex generator; 11. Visible light camera; 12. Shock-absorbing spring; 13. Landing gear; 14. Shock-absorbing plate; 15. Connecting rod; 16. Rotating rod; 17. Stepping motor; 18. Active bevel gear; 19. Gear rod; 20. Connecting plate; 21. Support rod; 22. Rack; 23. Driven gear. DETAILED DESCRIPTION

[0030] The preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. However, the present invention can be implemented in various forms, so the present invention is not limited to the embodiments described below. In addition, in order to more clearly describe the present invention, components that are not connected with the invention will be omitted from the drawings.

[0031] The technical solution in the embodiment of the present application is to solve the problems of the above-mentioned background technology, and the overall idea is as follows:

[0032] Embodiment 1:

[0033] Please refer to Figure 1-Figure 6 As shown, this embodiment introduces a specific structure of a large UAV with stable flight, including a fuselage 1, a power reserve device, a landing gear 13 device, and a propeller 2. The power reserve device is arranged at the upper end of the fuselage 1, the landing gear 13 device is located at the lower end of the fuselage 1, and the propeller 2 is located around the fuselage 1;

[0034] The present invention is provided with multiple groups of propellers 2 working in coordination, and the propellers 2 and the backup propellers 3 use different connection lines to ensure that when the main propellers 2 fail, the backup propellers 3 can quickly take over the flight control and maintain the stable flight of the aircraft body; the power reserve device includes a fuel tank 4 and a battery 7, and the electric energy converted by the solar panel 5 is stored in the battery 7. The dual energy supply of electric energy and fuel prolongs the flight time and can ensure the flight stability of the UAV; the four corners of the solar panel 5 are fixedly connected with hydraulic rods 6, and the height of the hydraulic rods 6 is adjusted to adjust the inclination angle of the solar panel 5, which can be used to resist the wind direction when the UAV is flying and can be used to chase light, thereby improving the efficiency of the solar panel 5; the landing gear 13 device is equipped with shock-absorbing springs 12 and shock-absorbing sheets 14, which can effectively absorb the landing impact, reduce the vibration of the fuselage 1, and improve the flight safety and stability. At the same time, the cooperation of the gear set realizes the horizontal and vertical adjustment of the landing gear 13, so that it has the functions of supporting the landing of the UAV and balancing the flight of the UAV, and has both functionality and practicality;

[0035] Specifically, the fuselage 1 of the UAV is symmetrically provided with a single propeller group 2 on both sides, each propeller group 2 is composed of two propellers 2, and the propellers 2 are located at the same height of the fuselage 1. When the UAV is flying normally, the rotation speed and angle of each propeller group 2 are adjusted according to the flight direction to complete the adjustment of the flight direction to achieve the best aerodynamic balance. In addition, a group of spare propellers 3 are respectively provided at the front and rear ends. Under normal conditions, the spare propellers 3 are in a stationary state and do not participate in providing power. When any one of the propeller groups 2 fails, the propeller groups 2 all stop working, and the spare propellers 3 are immediately started to ensure the continuity and safety of the flight, so as to replace the failed propellers 2 and maintain the flight of the UAV. The design layout of the spare propellers 3 enables them to be quickly switched to a working state, which greatly improves the reliability of the UAV.

[0036] At the same time, the UAV is also equipped with an efficient energy management system. A fuel tank 4 is arranged in the middle section of the bottom of the fuselage 1. The fuel in the fuel tank can be used as the power source for the UAV flight. Electric energy is also arranged as the power source. The hybrid energy supply mode of oil and electricity greatly improves the endurance and flight reliability of the UAV. The main source of electric energy is solar energy conversion. The solar panel 5 is located at the top of the fuselage 1. A hydraulic rod support rod 8 is arranged at the upper end of the fuselage 1. A hydraulic rod 6 is arranged at the top of the hydraulic rod support rod 8. The output end of the hydraulic rod 6 is fixed at the four corners of the bottom of the solar panel 5. A battery support rod 9 is arranged between the two groups of hydraulic rod support rods 8. A battery 7 is fixedly connected to the upper end of the battery support rod 9. The battery 7 is electrically connected to the conversion port of the solar panel 5. The solar panel 5 absorbs solar energy and converts it into electric energy, which is stored in the battery 7. The electric energy is provided to the UAV for operation as energy. The connected hydraulic rod 6 can adjust the height. During flight, the height of each corner of the solar panel 5 can be adjusted to offset the influence of wind force, making the fuselage 1 more stable. At the same time, it can also absorb light energy and convert it into electrical energy. When the UAV is in a non-flying state, the hydraulic rod 6 can adjust the height to change the inclination angle of the solar panel 5 for light chasing, so that the solar panel 5 can more effectively capture solar energy and convert it into electrical energy, providing additional power support for the UAV. Vortex generators 10 are provided on the surface of the solar panel 5 and the fuselage 1. The vortex generators 10 can make the boundary layer airflow on the surface of the fuselage 1 interact with each other, introduce the external airflow with higher energy into the boundary layer, increase the kinetic energy of the boundary layer airflow, thereby delaying the separation of the airflow, so that the wing maintains good lift characteristics in a larger angle of attack range, improve the stall angle of attack and lift coefficient of the UAV, and improve the take-off, landing and maneuverability of the UAV;

[0037] A visible light camera 11 is provided at the front end of the drone, which can transmit the flight status to the terminal device in real time. The operator can adjust the flight status of the drone according to the real-time picture to ensure the stable flight of the drone. In a complex flight environment, the operator can accurately control the drone through the images captured by the camera. The high-definition video stream of the visible light camera 11 not only ensures the accuracy of mission execution, but also makes the drone more flexible and adaptable when performing reconnaissance, rescue and other tasks.

[0038] The landing gear 13 of the drone is in the shape of a flat plate. The upper end of the landing gear 13 is fixedly connected to a rotating rod 16 through a connecting rod 15. The rotating rod 16 passes through the front and rear sides of the fuselage 1. A driven gear 23 is fixed in the middle of the rotating rod 16. A stepper motor 17 is fixed at the middle position of the bottom of the fuselage 1. The output end of the stepper motor 17 is fixedly connected to an active bevel gear 18. The bevel gear ends of the gear rod 19 are meshed on both sides of the active bevel gear 18. The other end of the bevel gear rod 19 is a gear end. The two gear rods 19 are connected by the connecting rod 15. The connecting piece 20 is in the shape of a door with a horizontal opening. There are openings at both ends of the connecting piece 20. The gear rod 19 passes through the opening of the connecting piece 20. The length of the connecting piece 20 is the same as the meshing part of the active bevel gear 18 and the gear rod 19. The lengths of the connecting blocks are consistent, which can ensure that the bevel gears are in a meshing state. At the same time, the connecting piece 20 with an opening does not limit the rotation of the gear rod 19. The active bevel gear 18 and the relative position gear rod 19 are in a vertical state. The active bevel gear 18 is located between the two gear rods 19. When the active bevel gear 18 rotates, the two gear rods 19 rotate in opposite directions. A support rod 21 is provided at the corresponding position of the gear rod 19 at the bottom of the fuselage 1. The top of the support rod 21 has a hole, and the gear rod 19 passes through the opening. The support rod 21 can ensure that the gear rod 19 remains stable during the rotation process to avoid mechanical failures caused by vibration. The gear at the other end of the gear rod 19 is meshed with a driven gear 23 fixed on the outside of the rotating rod 16 at the upper end of the landing gear 13 through a rack 22.

[0039] The rotation range of the stepper motor 17 is 90°. When the UAV is ready to descend, the motor output end rotates to drive the active bevel gear 18 to rotate, driving the gear rods 19 on both sides to move in the opposite direction, thereby driving the rotating rod 16 of the landing gear 13 from a horizontal state to a vertical state, thereby realizing the retraction and extension of the landing gear 13, ensuring the adaptability of the UAV on different terrains, and improving flight safety. The landing gear 13 can be retracted and extended freely, and a shock-absorbing plate 14 is provided at the bottom to absorb the impact force generated during landing, thereby ensuring a smooth landing of the UAV, reducing structural damage, and extending the service life. After the fuselage 1 takes off, the motor output end rotates 90° in the opposite direction, driving the active bevel gear 18 to rotate, driving the gear rods 19 on both sides to move in the opposite direction, thereby driving the rotation of the landing gear 13. The rod 16 changes from a vertical state to a horizontal state, and can be used as an auxiliary wing of the UAV, which increases lift, optimizes flight attitude, and improves endurance. The horizontal and vertical positions of the landing gear 13 are switched. The vertical state as the landing gear 13 is cleverly designed, taking into account shock absorption and support functions, ensuring that the UAV can provide stable support and reduce landing impact in various complex environments, ensuring safe, stable take-off and landing, and flexible response, which greatly improves the reliability and efficiency of mission execution. The horizontal state is used as an auxiliary wing to enhance lift, optimize flight attitude, make the UAV flight more stable, and improve endurance. The design cleverly uses the principle of mechanical structure to realize the functional conversion of the landing gear 13 and the auxiliary wing, which not only ensures take-off and landing safety, but also improves flight performance.

[0040] In summary, it should be noted that the drone of the present invention is equipped with multiple sets of propeller 2 systems that work in coordination. Among them, the propeller 2 and the spare propeller 3 respectively use independent connection lines. When the main propeller 2 fails, the spare propeller 3 can respond quickly and seamlessly take over the flight control, thereby ensuring the stability of the body during flight. In terms of power reserve, the drone adopts a dual energy supply mode combining a fuel tank 4 and a battery 7. The electric energy converted by the solar panel 5 will be stored in the battery 7. The fuel and the electric energy work together to significantly extend the endurance of the drone and effectively ensure the stability of the flight. The solar panel 5 can flexibly adjust the height through the hydraulic rods 6 fixedly connected at its four corners, and then accurately adjust the inclination angle of the solar panel 5. This design can not only effectively resist the wind direction interference during the flight of the drone, but also realize the light chasing function, greatly improving the energy conversion efficiency of the solar panel 5. The landing gear 13 device is carefully equipped with a shock-absorbing spring 12 and a shock-absorbing sheet 14, which can efficiently absorb the impact generated when the drone lands, greatly reduce the vibration of the fuselage 1, and add protection for flight safety and stability. At the same time, with the help of the coordinated cooperation of the gear set, the landing gear 13 can achieve flexible adjustment in the horizontal and vertical directions, which can not only stably support the landing of the drone, but also assist in balancing the body during flight, fully demonstrating its excellent functionality and practicality.

[0041] Finally, it should be noted that: Obviously, the above embodiments are only examples for clearly explaining the present invention, and are not intended to limit the implementation methods. For ordinary technicians in the relevant field, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all the implementation methods here. The obvious changes or modifications derived from this are still within the scope of protection of the present invention.

Claims

1. A large unmanned aerial vehicle with stable flight, comprising a fuselage (1), a power reserve device, a landing gear (13) device, and a propeller (2); characterized in that: The power reserve device is arranged at the upper end of the fuselage (1), the landing gear (13) device is located at the lower end of the fuselage (1), and the propeller (2) is located around the fuselage (1); The power reserve device comprises a fuel tank (4) arranged at the middle section of the bottom of the fuselage (1) at the upper end of the fuselage (1), a solar panel (5) arranged at the top of the fuselage (1), a hydraulic rod (6) support rod arranged at the upper end of the interior of the fuselage (1), a hydraulic rod (6) arranged at the top end of the hydraulic rod support rod (8), an output end of the hydraulic rod (6) fixed at the four corners of the bottom of the solar panel (5), a battery support rod (9) arranged in the middle of the hydraulic rod (6), a battery (7) fixedly connected to the upper end of the battery (7) support rod, and the battery (7) is electrically connected to the conversion port of the solar panel (5).

2. A large unmanned aerial vehicle with stable flight as claimed in claim 1, characterized in that: A single propeller (2) group is provided at a symmetrical position on both sides of the fuselage (1); the propeller (2) group consists of two propellers (2); the propellers (2) are located at the same height of the fuselage (1); and a group of spare propellers (3) is provided at the front and rear ends of the fuselage (1).

3. A large unmanned aerial vehicle with stable flight as claimed in claim 1, characterized in that: Vortex generators (10) are provided on the surface of the solar panel (5) and the fuselage (1).

4. A large unmanned aerial vehicle with stable flight as claimed in claim 2, characterized in that: A visible light camera (11) is arranged at the front end of the fuselage (1).

5. A large unmanned aerial vehicle with stable flight as claimed in claim 1, characterized in that: A stepper motor (17) is fixed at the middle of the bottom of the body (1), the output end of the stepper motor (17) is fixedly connected to an active bevel gear (18), both sides of the active bevel gear (18) are meshed with bevel gear ends of a gear rod (19), the other end of the gear rod (19) is a gear end, the active bevel gear (18) and the gear rod (19) are in a vertical state relative to each other, and the active bevel gear (18) is located between the two gear rods (19).

6. A large unmanned aerial vehicle with stable flight as claimed in claim 1, characterized in that: A landing gear (13) is arranged at the bottom of the side of the fuselage (1), and the landing gear (13) is in the shape of a flat plate.

7. A large unmanned aerial vehicle with stable flight as claimed in claim 1, characterized in that: The upper end of the landing gear (13) of the fuselage (1) is fixedly connected to a rotating rod (16) via a connecting rod (15), and a driven gear (22) is fixed to the middle of the rotating rod (16) of the fuselage (1).

8. A large unmanned aerial vehicle with stable flight as claimed in claim 7, characterized in that: The gear rod (19) is connected via a connecting piece (20), the connecting piece (20) is in the shape of a horizontally opened gate, both ends of the connecting piece (20) are opened, the gear rod (19) body passes through the opening of the connecting rod (15), and the length of the connecting piece (20) is consistent with the length of the connecting block of the meshing part of the active bevel gear (18) and the gear rod (19).

9. A large unmanned aerial vehicle with stable flight as claimed in claim 7, characterized in that: The gear at the other end of the gear rod (19) is meshed with a driven gear (23) fixed on the outside of a rotating rod (16) at the upper end of the landing gear (13) through a rack (22).

10. A large unmanned aerial vehicle with stable flight as claimed in claim 7, characterized in that: A support rod (21) is arranged at a corresponding position of the gear rod (19) at the bottom of the fuselage (1), a hole is opened at the top of the support rod (21), and the gear rod (19) passes through the opening.

Images