Drone with obstacle avoidance warning function

Abstract

The present invention discloses a drone with obstacle avoidance and early warning function, comprising a fuselage and wings, wherein the fuselage and wings are correspondingly connected through a connecting structure, and rotors are arranged on the top surfaces of both ends of the wings. The present invention first contacts the ground through the bottom end of an inner rod, and the inner rod moves upward inside an inner groove under the action of impact force, and the inner rod drives a top frame to move upward synchronously on the surface of a bracket, and the top frame squeezes an elastic plate during the upward movement, and the impact force between the bracket and the ground is further reduced by the elastic plate, so as to avoid the impact force of the landing of the drone directly acting on the wings and the fuselage, and when the top frame moves upward, the top frame pulls the ring through a pull rope, and when the ring moves upward, the buffer frame is driven to move upward, and the buffer frame moves upward and then pushes the bottom ends of two rotating plates to move upward, and the two rotating plates rotate so that the top ends of the two rotating plates drive two slide plates to gradually move away, and the two slide plates drive two connecting rods to gradually move away, thereby improving the connection buckle effect between the connecting rod and the fuselage.

Description

Technical Field

[0001] The invention belongs to the technical field of obstacle avoidance and early warning UAVs, and in particular relates to a UAV with obstacle avoidance and early warning functions. Background Art

[0002] Drones are unmanned aerial vehicles that are controlled by radio remote control equipment or self-contained program control devices. Currently, drones are widely used in aerial photography, agriculture, plant protection, micro selfies, express delivery, disaster relief, wildlife observation, infectious disease monitoring, surveying and mapping, news reporting, power inspections, disaster relief, film and television shooting, creating romance and many other fields.

[0003] The drone needs to land on the ground after flying. If the drone descends too quickly, the impact force between the drone and the ground will cause damage to the drone, making it unable to continue flying.

[0004] Therefore, it is necessary to invent a drone with obstacle avoidance and warning function to solve the above problems. Summary of the invention

[0005] In view of the above problems, the present invention provides a drone with obstacle avoidance and warning functions to solve the problems raised in the above background technology.

[0006] To achieve the above object, the present invention provides the following technical solutions:

[0007] A drone with obstacle avoidance and warning function comprises a fuselage and wings, wherein the fuselage and wings are correspondingly connected via a connecting structure;

[0008] Both ends of the wing are provided with brackets, and the brackets penetrate the wing; the first end of the bracket is connected to the rotor, and a buffer frame is connected between the second ends of the brackets located at the two ends of the wing, and the two ends of the buffer frame are movably sleeved on the surfaces of the two brackets respectively;

[0009] The buffer frame is connected to the wing through two rotating plates, and the two rotating plates are arranged at the center of the top surface of the buffer frame; the surface of the bracket is provided with a buffer structure for buffering the fuselage, and the buffer frame is connected to the buffer structure;

[0010] The buffer structure comprises an inner rod, an inner groove which is slidably matched with the inner rod is arranged inside the bracket, a plurality of limiting grooves are arranged on the circumferential outer side of the bracket, and the limiting grooves are equidistantly distributed along the circumference of the bracket; a top frame is fixedly connected to the top of the inner rod, the top surface of the top frame is fixedly connected to the bottom surface of the wing through an elastic plate, and the top frame is slidably sleeved on the surface of the bracket through the limiting groove;

[0011] Both ends of the buffer frame are fixedly connected with a ring, the ring is movably sleeved on the surface of the bracket, and the top surface of the ring is fixedly connected to the bottom surface of the top frame through a plurality of pull ropes; the bottom surface of the ring is fixedly connected with a spring, and the end of the spring away from the ring is fixedly connected to the bottom of the bracket.

[0012] Optionally, the connection structure includes a connecting rod, the connecting rod is configured as a square rod, the inner end of the connecting rod is provided with a waist-round plate, both sides of the fuselage are provided with a slide groove corresponding to the inner end of the connecting rod, the inner end of the slide groove is provided with a slot corresponding to the waist-round plate, and the inner end of the connecting rod is slidably matched with the slot inside the slide groove through the waist-round plate;

[0013] The width of the slide groove is smaller than the width of the waist round plate. A first through groove corresponding to and matching the waist round plate is arranged at the center of the slide groove. The waist round plate enters into the slot through the first through groove.

[0014] Optionally, the connection structure further comprises a rotating sleeve, the rotating sleeve is rotatably sleeved on the surface of the connecting rod, a spacer is provided at the center of the connecting rod, and a clamping ring at the center of the rotating sleeve is rotatably matched with two side surfaces of the spacer;

[0015] Pressure rings are arranged on both sides of the spacer, and square grooves corresponding to the square rods are arranged on the inner sides of the two pressure rings. The two sides of the rotating sleeve are respectively spirally sleeved on the inner ends of the two pressure rings, and the outer ends of the two pressure rings are respectively fitted with the fuselage and the wings.

[0016] Optionally, a movable groove is provided at the center of the top surface of the wing, a slide is fixedly connected to the outer end of the connecting rod, a second through groove corresponding to the movable groove is provided at the center of the inner side surface of the wing, the outer end of the connecting rod passes through the second through groove, and the outer end of the connecting rod is slidably matched with the movable groove through the slide;

[0017] The top and bottom of the slide plate are both provided with limiting plates, and the two limiting plates correspond to and cooperate with the top surface and the bottom surface of the wing respectively.

[0018] Optionally, a connecting frame is connected to the bottom of the limiting plate at the bottom of the skateboard, connecting frames are arranged on both sides of the center of the top surface of the buffer frame, and the top and bottom ends of the rotating plate are rotatably connected to the connecting frame of the limiting plate at the bottom of the skateboard and the connecting frame of the buffer frame respectively, and the wings, the buffer frame and the two rotating plates form an inverted isosceles trapezoidal structure.

[0019] Optionally, the bottom end of the inner rod passes through the bracket.

[0020] Optionally, the ferrule is located below the top frame.

[0021] Optionally, the inner rod is made of rubber material, and the circumferential side surface of the inner rod is correspondingly fitted with the inner side surface of the inner groove.

[0022] Technical effects and advantages of the present invention:

[0023] The bottom end of the inner rod first contacts the ground, and the inner rod moves upward inside the inner groove under the action of the impact force, and the inner rod drives the top frame to move upward on the surface of the bracket synchronously, and the top frame squeezes the elastic plate during the upward movement, and the elastic plate further reduces the impact force between the bracket and the ground, so as to avoid the impact force of the landing of the drone directly acting on the wings and the fuselage. When the top frame moves upward, the top frame pulls the ring through the pull rope, and when the ring moves upward, it drives the buffer frame upward, and the upward movement of the buffer frame pushes the bottom ends of the two rotating plates upward. The two rotating plates rotate, so that the top ends of the two rotating plates drive the two slide plates to gradually move away, and the two slide plates drive the two connecting rods to gradually move away, thereby improving the connection buckle effect between the connecting rod and the fuselage.

[0024] Other features and advantages of the present invention will be described in the following description, and partly become obvious from the description, or be understood by implementing the present invention. The purpose and other advantages of the present invention can be realized and obtained by the structures pointed out in the description and the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0026] Figure 1 A schematic diagram of the overall structure of a drone with obstacle avoidance and warning functions according to an embodiment of the present invention is shown;

[0027] Figure 2 A schematic cross-sectional view of a connection structure according to an embodiment of the present invention is shown;

[0028] In the figure: 1, fuselage; 2, wing; 3, rotor; 4, bracket; 5, buffer frame; 501, rotating plate; 6, connecting rod; 7, waist round plate; 8, slide groove; 9, card slot; 10, first through slot; 11, rotating sleeve; 12, spacer block; 13, pressure ring; 14, movable slot; 15, slide plate; 16, second through slot; 17, limiting plate; 18, inner rod; 19, limiting slot; 20, top frame; 21, elastic plate; 22, ring; 23, pull rope; 24, spring. DETAILED DESCRIPTION

[0029] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0030] The present invention provides a drone with obstacle avoidance and early warning functions, such as Figure 1-2 As shown, it includes a fuselage 1 and wings 2, and the fuselage 1 and wings 2 are correspondingly connected through a connecting structure.

[0031] Wherein, both ends of the wing 2 are provided with a bracket 4, and the bracket 4 passes through the wing 2; the first end of the bracket 4 is connected to the rotor 3, and a buffer frame 5 is connected between the second ends of the bracket 4 located at both ends of the wing 2, and the two ends of the buffer frame 5 are movably sleeved on the surfaces of the two brackets 4 respectively;

[0032] The buffer frame 5 is connected to the wing 2 via two rotating plates 501 , and the two rotating plates 501 are arranged at the center of the top surface of the buffer frame 5 ; a buffer structure for buffering the fuselage 1 is provided on the surface of the bracket 4 , and the buffer frame 5 is connected to the buffer structure.

[0033] The two wings 2 are respectively connected to the two sides of the fuselage 1 through a connecting structure, and the entire drone is supported by a bracket 4 at the bottom of the wing 2. When the drone falls from a high altitude, the collision impact force between the drone and the ground is reduced through the cooperation of the buffer frame 5 and the buffer structure, thereby reducing the impact force causing serious impact damage to the drone itself, thereby increasing the service life of the entire drone.

[0034] The fuselage 1 has a built-in millimeter-wave anti-collision radar sensor, which can collect the relative speed, relative distance and azimuth between the drone and the obstacle; the fuselage 1 also has a built-in ultrasonic radar sensor, which is used to collect the relative distance to the obstacle; when the fuselage 1 determines through the main controller that the data obtained by each sensor exceeds the threshold, the drone is controlled to fly left, right, hover and then return to avoid obstacles. Obstacles can be detected in real time, and the operator can adjust the flight status of the drone to avoid the drone colliding with obstacles and causing losses.

[0035] The airborne end and the control console end, the airborne end includes a distance sensor, the distance sensor is connected to the controller, and the controller is connected to the airborne wireless communication module; the control console end includes a local wireless communication module, the local wireless communication module is connected to the early warning controller, and the early warning controller is connected to the early warning prompt module, which mainly detects the distance to the obstacle ahead to prevent the drone from colliding with the obstacle and causing losses.

[0036] The drone with obstacle avoidance warning function can control the distance between the drone and the obstacle in real time, and control the drone to stop moving toward the obstacle when it is at a safe distance from the obstacle. It does not need to make too many adjustments to the drone flight control system, nor does it need to add additional hardware equipment such as auxiliary distance measuring devices. It only needs information to calibrate the distance. It avoids the drone from hitting obstacles or falling directly to the ground, which greatly reduces the damage to the drone.

[0037] exist Figure 1 and Figure 2 In the figure, the connecting structure includes a connecting rod 6, which is set as a square rod, and a waist-round plate 7 is set at the inner end of the connecting rod 6. Both sides of the fuselage 1 are provided with a slide groove 8 corresponding to the inner end of the connecting rod 6, and the inner end of the slide groove 8 is provided with a clamping groove 9 corresponding to the waist-round plate 7. The inner end of the connecting rod 6 slides with the clamping groove 9 inside the slide groove 8 through the waist-round plate 7. The width of the slide groove 8 is smaller than the width of the waist-round plate 7. A first through groove 10 corresponding to the waist-round plate 7 is set at the center of the slide groove 8, and the waist-round plate 7 enters into the clamping groove 9 through the first through groove 10. When the connecting structure needs to be connected to the fuselage 1, the waist-round plate 7 at the inner end of the connecting rod 6 is inserted into the sliding groove 8 through the first through groove 10 until the waist-round plate 7 and the slot 9 are matched, and then the two connecting rods 6 are pushed to separate from each other. At this time, the two connecting rods 6 drive the two waist-round plates 7 to gradually separate inside the slot 9. Through the buckle limitation of the waist-round plate 7 and the slot 9, the connecting rod 6 cannot be pulled out from the slide groove 8 of the fuselage 1, which is convenient for the initial connection and limitation of the connecting structure to the fuselage 1.

[0038] exist Figure 1 and Figure 2 In the figure, the connection structure also includes a rotating sleeve 11, which is rotatably sleeved on the surface of the connecting rod 6, a spacer 12 is arranged at the center of the connecting rod 6, and a clamping ring is rotatably matched with the two side surfaces of the spacer 12 at the center of the rotating sleeve 11, and pressure rings 13 are arranged on both sides of the spacer 12. The inner sides of the two pressure rings 13 are provided with square and round grooves corresponding to the square and round rods, and the two sides of the rotating sleeve 11 are respectively spirally sleeved on the inner ends of the two pressure rings 13, and the outer ends of the two pressure rings 13 are respectively fitted with the fuselage 1 and the wing 2.

[0039] When limiting the wing 2 and the fuselage 1, the rotating sleeve 11 is rotated, and the waist circular plate 7 is limited by the clamping groove 9. At this time, the connecting rod 6 cannot rotate with the rotating sleeve 11, and the square rod of the connecting rod 6 and the square groove of the pressure ring 13 are limited, and at this time, the two pressure rings 13 cannot rotate on the surface of the connecting rod 6. Since the two ends of the rotating sleeve 11 are respectively spirally matched with the inner end surfaces of the two pressure rings 13, and the spiral lines of the circumferential sides of the two pressure rings 13 are in opposite directions, the connecting rod 6 limits the position of the rotating sleeve 11 through the rotational cooperation of the spacer 12 and the clamping ring, so as to prevent the rotating sleeve 11 from sliding on the surface of the connecting rod 6; when the rotating sleeve 11 rotates, the two ends of the rotating sleeve 11 are respectively spirally matched with the inner ends of the two pressure rings 13, so that the two pressure rings 13 gradually approach or move away; when the two pressure rings 13 gradually move away, the outer ends of the two pressure rings 13 are respectively corresponding to the side of the fuselage 1 and the inner side of the wing 2, and the wing 2 can be stably fixed on the side of the fuselage 1 through the extrusion limitation of the two pressure rings 13.

[0040] exist Figure 1 In the embodiment, a movable groove 14 is provided at the center of the top surface of the wing 2, a slide plate 15 is fixedly connected to the outer end of the connecting rod 6, a second through groove 16 corresponding to and connected to the movable groove 14 is provided at the center of the inner side surface of the wing 2, the outer end of the connecting rod 6 passes through the second through groove 16, and the outer end of the connecting rod 6 slides with the movable groove 14 through the slide plate 15, and a limiting plate 17 is provided at the top and bottom of the slide plate 15, and the two limiting plates 17 correspond to and match with the top and bottom surfaces of the wing 2 respectively. When the two connecting rods 6 gradually approach or move away, at this time, the outer ends of the two connecting rods 6 gradually approach or move away inside the second through groove 16, and the two slide plates 15 fixedly connected to the outer ends of the two connecting rods 6 gradually approach or move away inside the movable groove 14, through the sliding cooperation between the movable groove 14 and the slide plate 15, at this time, it is convenient for the waist round plate 7 at the inner end of the connecting rod 6 to slide with the card slot 9, so that the wing 2 can be connected to different fuselages 1 through the connection structure, thereby improving the adaptability of the fuselage 1 to different wings 2.

[0041] exist Figure 1 In the figure, the bottom of the limiting plate 17 at the bottom of the slide 15 is connected with a connecting frame, and connecting frames are arranged on both sides of the center of the top surface of the buffer frame 5, and the top and bottom of the rotating plate 501 are respectively connected with the connecting frame of the limiting plate 17 at the bottom of the slide 15 and the connecting frame of the buffer frame 5, and the wing 2, the buffer frame 5 and the two rotating plates 501 form an inverted isosceles trapezoidal structure. When the slide 15 moves inside the movable groove 14, the limiting plate 17 at the bottom of the slide 15 drives the top of the rotating plate 501 to move, and the tops of the two rotating plates 501 gradually approach or move away under the movement of the two slides 15, and the two rotating plates 501 and the connecting frame at the top of the buffer frame 5 are rotated as the axis. When the two slides 15 are closest to each other, the two rotating plates 501 are in a vertical state, and when the two slides 15 gradually move away from each other, the two rotating plates 501 rotate, and the buffer frame 5 gradually approaches the wing 2.

[0042] exist Figure 1 In the figure, the buffer structure includes an inner rod 18, an inner groove slidably matched with the inner rod 18 is arranged inside the bracket 4, and a plurality of limiting grooves 19 are arranged on the circumferential outer side of the bracket 4, and the limiting grooves 19 are equidistantly distributed along the circumference of the bracket 4; the top end of the inner rod 18 is fixedly connected with a top frame 20, and the top surface of the top frame 20 is fixedly connected to the bottom surface of the wing 2 through an elastic plate 21, and the top frame 20 is slidably sleeved on the surface of the bracket 4 through the limiting grooves 19.

[0043] The inner rod 18 is made of rubber material, and the circumferential side of the inner rod 18 is correspondingly fitted with the inner side of the inner groove. When the entire drone needs to land on the ground through the bracket 4, the bottom end of the inner rod 18 contacts the ground first. The rubber inner rod 18 can reduce a part of the impact force between the bracket 4 and the ground. The inner rod 18 moves up inside the inner groove under the impact force, and the inner rod 18 drives the top frame 20 to move up synchronously on the surface of the bracket 4. The top frame 20 squeezes the elastic plate 21 during the upward movement, and the elastic plate 21 further reduces the impact force between the bracket 4 and the ground, so as to prevent the impact force of the drone landing from directly acting on the wing 2 and the fuselage 1.

[0044] exist Figure 1 In the figure, both ends of the buffer frame 5 are fixedly connected with a ring 22, the ring 22 is movably sleeved on the surface of the bracket 4, and the top surface of the ring 22 is fixedly connected to the bottom surface of the top frame 20 through multiple pull ropes 23; the bottom surface of the ring 22 is fixedly connected with a spring 24, and the end of the spring 24 away from the ring 22 is fixedly connected to the bottom of the bracket 4.

[0045] When the top frame 20 moves upward, the top frame 20 pulls the ring 22 through the pull rope 23, and the ring 22 moves upward, driving the buffer frame 5 upward, and the buffer frame 5 moves upward and pushes the bottom ends of the two rotating plates 501 upward, and the two rotating plates 501 rotate so that the top ends of the two rotating plates 501 drive the two slide plates 15 to gradually move away, and the two slide plates 15 drive the two connecting rods 6 to gradually move away, thereby improving the connection and buckling effect between the connecting rods 6 and the fuselage 1. When the ring 22 moves upward, the ring 22 pulls the spring 24 during the upward movement, and the elastic force of the spring 24 further reduces the impact force between the bracket 4 and the ground, and when the buffer frame 5 contacts the ground, the buffer frame 5 also pulls the spring 24 when driving the ring 22 upward, which can buffer the bracket 4 and improve the connection stability between the connecting rod 6 and the fuselage 1.

[0046] Working principle of the present invention:

[0047] Refer to the instruction manual Figure 1-2, when limiting the wing 2 and the fuselage 1, the rotating sleeve 11 is rotated, and the waist circular plate 7 is limited by the clamping groove 9. At this time, the connecting rod 6 cannot rotate with the rotating sleeve 11, and the square rod of the connecting rod 6 and the square groove of the pressure ring 13 are limited, and at this time, the two pressure rings 13 cannot rotate on the surface of the connecting rod 6. Since the two ends of the rotating sleeve 11 are respectively spirally matched with the inner end surfaces of the two pressure rings 13, and the spiral lines of the circumferential sides of the two pressure rings 13 are in opposite directions, the connecting rod 6 is rotated by the spacer 12 and the clamping ring to limit the position of the rotating sleeve 11, and the rotating sleeve 11 is prevented from sliding on the surface of the connecting rod 6. When the rotating sleeve 11 rotates, the two ends of the rotating sleeve 11 are respectively spirally matched with the inner ends of the two pressure rings 13, so that the two pressure rings 13 gradually approach or move away. When the two pressure rings 13 gradually move away, the outer ends of the two pressure rings 13 are respectively corresponding to the side of the fuselage 1 and the inner side of the wing 2. Through the extrusion limitation of the two pressure rings 13, the wing 2 can be stably fixed on the side of the fuselage 1.

[0048] When the entire drone needs to land on the ground through the bracket 4, the bottom end of the inner rod 18 contacts the ground first. The rubber inner rod 18 can reduce part of the impact force between the bracket 4 and the ground. The inner rod 18 moves upward inside the inner groove under the impact force, and the inner rod 18 drives the top frame 20 to move upward synchronously on the surface of the bracket 4. The top frame 20 squeezes the elastic plate 21 during the upward movement, and the elastic plate 21 further reduces the impact force between the bracket 4 and the ground, thereby preventing the impact force of the drone landing from directly acting on the wing 2 and the fuselage 1.

[0049] When the top frame 20 moves upward, the top frame 20 pulls the ring 22 through the pull rope 23, and the ring 22 moves upward, driving the buffer frame 5 upward, and the buffer frame 5 moves upward and pushes the bottom ends of the two rotating plates 501 upward, and the two rotating plates 501 rotate so that the top ends of the two rotating plates 501 drive the two slide plates 15 to gradually move away, and the two slide plates 15 drive the two connecting rods 6 to gradually move away, thereby improving the connection and buckling effect between the connecting rods 6 and the fuselage 1. When the ring 22 moves upward, the ring 22 pulls the spring 24 during the upward movement, and the elastic force of the spring 24 further reduces the impact force between the bracket 4 and the ground, and when the buffer frame 5 contacts the ground, the buffer frame 5 also pulls the spring 24 when driving the ring 22 upward, which can buffer the bracket 4 and improve the connection stability between the connecting rod 6 and the fuselage 1.

[0050] Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent substitutions for some of the technical features therein; and these modifications or substitutions do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A drone with obstacle avoidance and warning function, comprising a fuselage (1) and wings (2), characterized in that: The fuselage (1) and the wing (2) are correspondingly connected via a connecting structure; Both ends of the wing (2) are provided with a bracket (4), and the bracket (4) passes through the wing (2); the first end of the bracket (4) is connected to the rotor (3), and a buffer frame (5) is connected between the second ends of the bracket (4) located at the two ends of the wing (2), and the two ends of the buffer frame (5) are respectively movably sleeved on the surfaces of the two brackets (4); The buffer frame (5) is connected to the wing (2) via two rotating plates (501), and the two rotating plates (501) are arranged at the center of the top surface of the buffer frame (5); a buffer structure for buffering the fuselage (1) is provided on the surface of the bracket (4), and the buffer frame (5) is connected to the buffer structure; The buffer structure comprises an inner rod (18), an inner groove which is slidably matched with the inner rod (18) is arranged inside the bracket (4), and a plurality of limiting grooves (19) are arranged on the circumferential outer side surface of the bracket (4), and the limiting grooves (19) are equidistantly distributed along the circumference of the bracket (4); a top frame (20) is fixedly connected to the top of the inner rod (18), and the top surface of the top frame (20) is fixedly connected to the bottom surface of the wing (2) through an elastic plate (21), and the top frame (20) is slidably sleeved on the surface of the bracket (4) through the limiting grooves (19); Both ends of the buffer frame (5) are fixedly connected with a ring (22), the ring (22) is movably sleeved on the surface of the bracket (4), and the top surface of the ring (22) is fixedly connected to the bottom surface of the top frame (20) through a plurality of pull ropes (23); the bottom surface of the ring (22) is fixedly connected with a spring (24), and one end of the spring (24) away from the ring (22) is fixedly connected to the bottom of the bracket (4).

2. The unmanned aerial vehicle with obstacle avoidance and warning function according to claim 1, characterized in that: The connection structure comprises a connection rod (6), the connection rod (6) is configured as a square rod, the inner end of the connection rod (6) is provided with a waist round plate (7), both sides of the fuselage (1) are provided with a slide groove (8) corresponding to the inner end of the connection rod (6), the inner end of the slide groove (8) is provided with a clamping groove (9) corresponding to the buckle of the waist round plate (7), and the inner end of the connection rod (6) is slidably matched with the clamping groove (9) inside the slide groove (8) through the waist round plate (7); The width of the slide groove (8) is smaller than the width of the waist round plate (7), and a first through groove (10) corresponding to and matching the waist round plate (7) is arranged at the center of the slide groove (8), and the waist round plate (7) enters into the clamping groove (9) through the first through groove (10).

3. The unmanned aerial vehicle with obstacle avoidance and warning function according to claim 2, characterized in that: The connection structure further comprises a rotating sleeve (11), the rotating sleeve (11) being rotatably sleeved on the surface of the connecting rod (6), a spacer block (12) being arranged at the center of the connecting rod (6), and a clamping ring at the center of the rotating sleeve (11) being rotatably matched with two side surfaces of the spacer block (12); The spacer (12) is provided with a pressure ring (13) on both sides, and the inner sides of the two pressure rings (13) are provided with a square round groove corresponding to the square round rod. The two sides of the rotating sleeve (11) are respectively spirally sleeved on the inner ends of the two pressure rings (13), and the outer ends of the two pressure rings (13) are respectively fitted with the fuselage (1) and the wing (2).

4. The unmanned aerial vehicle with obstacle avoidance and warning function according to claim 3, characterized in that: A movable groove (14) is provided at the center of the top surface of the wing (2); a slide plate (15) is fixedly connected to the outer end of the connecting rod (6); a second through groove (16) corresponding to and communicating with the movable groove (14) is provided at the center of the inner side surface of the wing (2); the outer end of the connecting rod (6) passes through the second through groove (16), and the outer end of the connecting rod (6) is slidably matched with the movable groove (14) through the slide plate (15); The top and bottom of the slide plate (15) are both provided with limiting plates (17), and the two limiting plates (17) correspond to the top surface and the bottom surface of the wing (2) respectively.

5. The unmanned aerial vehicle with obstacle avoidance and warning function according to claim 4, characterized in that: The bottom of the limiting plate (17) at the bottom of the slide plate (15) is connected to a connecting frame, and connecting frames are arranged on both sides of the center of the top surface of the buffer frame (5), and the top and bottom ends of the rotating plate (501) are rotatably connected to the connecting frame of the limiting plate (17) at the bottom of the slide plate (15) and the connecting frame of the buffer frame (5), respectively, and the wing (2), the buffer frame (5) and the two rotating plates (501) form an inverted isosceles trapezoidal structure.

6. The unmanned aerial vehicle with obstacle avoidance and warning function according to claim 1, characterized in that: The bottom end of the inner rod (18) passes through the bracket (4).

7. The unmanned aerial vehicle with obstacle avoidance and warning function according to claim 1, characterized in that: The ferrule (22) is located below the top frame (20).

8. The unmanned aerial vehicle with obstacle avoidance and warning function according to claim 6, characterized in that: The inner rod (18) is made of rubber material, and the circumferential side surface of the inner rod (18) is correspondingly fitted with the inner side surface of the inner groove.

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