Wingspan-adjustable fixed-wing unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, and discloses a wingspan-adjustable fixed-wing unmanned aerial vehicle which comprises a main body frame, side wings are fixedly connected to the two sides of the outer wall of the main body frame, sliding grooves are formed in the outer walls of the sides, away from the center of the main body frame, of the side wings, and ailerons are slidably connected into the sliding grooves. Mounting boxes are fixedly connected to the lower surfaces of the side wings, servo motors are fixedly connected to the inner walls of the adjacent sides of the mounting boxes, threaded rods are fixedly connected to the output ends of the servo motors, and threaded sleeve blocks are arranged on the outer walls of rod bodies of the threaded rods in a sleeving mode. According to the fixed-wing unmanned aerial vehicle, when the fixed-wing unmanned aerial vehicle is used, a servo motor is started to drive a threaded rod to rotate and drive a threaded sleeve block to move at the same time, the threaded sleeve block moves to drive a limiting block to slide in a limiting groove, and then the threaded sleeve block is limited to drive an aileron to move; and the length of the aileron can be adjusted as required, so as to adapt to different use environments.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles (UAVs), and in particular to a fixed-wing UAV with adjustable wingspan. Background Art

[0002] As we all know, fixed-wing UAVs are unmanned aerial vehicles with fixed wings that rely on the aerodynamic shape of the wings to generate lift. They are usually used for long-distance flights and high-efficiency aerial operations. Compared with multi-rotor UAVs, fixed-wing UAVs have better endurance and flight speed and are widely used in aerial photography, terrain mapping, agricultural spraying, environmental monitoring, military reconnaissance and other fields.

[0003] Different flight missions and environments require different flight performance from drones. For example, when flying in a confined space, shorter wings may be more conducive to flexible turning and crossing; while for long-distance cruising or when higher stability is required, longer wings can provide better lift and gliding performance. However, traditional fixed-wing drones usually cannot be adjusted according to actual needs due to the fixed length of their wings, which greatly limits their adaptability in different scenarios. Therefore, technical improvements are urgently needed. Utility Model Content

[0004] The purpose of the utility model is to solve the shortcomings of the prior art and to propose a fixed-wing UAV with adjustable wingspan. When the fixed-wing UAV is in use, the servo motor is started to drive the threaded rod to rotate and at the same time drive the threaded sleeve to move. The movement of the threaded sleeve drives the limit block to slide in the limit groove, and then limits the threaded sleeve to drive the aileron to move. The length of the aileron can be adjusted as needed to adapt to different usage environments.

[0005] To achieve the above objectives, the present invention provides the following technical solutions:

[0006] A fixed-wing drone with adjustable wingspan, comprising a main frame, side wings fixedly connected to both sides of the outer wall of the main frame, a slide groove being formed on the outer wall of each side of the side wing away from the center of the main frame, an aileron being slidably connected inside the slide groove, a mounting box being fixedly connected to the lower surface of each side wing, a servo motor being fixedly connected to the inner wall of an adjacent side of the mounting box, a threaded rod being fixedly connected to the output end of the servo motor, and a threaded sleeve being sleeved on the outer wall of each threaded rod;

[0007] A buffer frame is fixedly connected to the rear end of the lower surface of the main frame, a mounting groove is provided at the lower end of the outer wall of the buffer frame, and both sides of the inner wall of the mounting groove are rotatably connected to a fixing rod, the outer wall of the fixing rod is sleeved with a return spring, and both sides of the outer wall of the return spring are fixedly connected with a sliding sleeve, and connecting blocks are provided on both sides of the lower end of the buffer frame, and the upper ends of the connecting blocks are fixedly connected to a damping rod, and the outer walls of the damping rod are sleeved with a shock-absorbing spring.

[0008] Through the above technical solution, compared with the existing fixed-wing UAV, when the fixed-wing UAV is used, when the UAV lands, the damping rod and the shock-absorbing spring are used to preferentially compress and absorb the impact force, which can absorb the impact force generated during landing and reduce damage to the UAV structure. Subsequently, the connecting block is compressed upward while driving the articulated rod to move. At this time, the articulated rod drives the sliding sleeves on both sides to continuously compress the reset spring for secondary buffering, which can further disperse and reduce the impact during landing, and has high practical performance.

[0009] Furthermore, two blades are provided at the front and rear ends of the side wing outer wall;

[0010] Through the above technical solution, the two blades can be coordinated to facilitate ascent.

[0011] Furthermore, a limiting groove is provided in the middle of the lower surface of each side wing, the upper end of the threaded sleeve is fixedly connected to the limiting block, and the limiting blocks slide inside the limiting groove and are fixedly connected to the lower end of the aileron respectively;

[0012] With the above technical solution, the threaded sleeve can be limited to move laterally by sliding the limiting block inside the limiting groove.

[0013] Furthermore, the front end of the lower surface of the main frame is fixedly connected to a support rod, and the lower end of the support rod is fixedly connected to a buffer wheel 1;

[0014] Through the above technical solution, the buffer wheel is used to facilitate movement and buffering.

[0015] Furthermore, the upper ends of the damping rod and the shock absorbing spring are fixedly connected to the lower end of the buffer frame;

[0016] Through the above technical solution, the impact force generated by the landing is reduced by the damping rod and the shock-absorbing spring.

[0017] Furthermore, the sliding sleeves are all slidably connected to the outer wall of the fixed rod via a return spring;

[0018] According to the above technical solution, the sliding sleeve is slidably connected to the outer wall of the fixed rod through the reset spring, which facilitates the compression of the reset spring.

[0019] Furthermore, the front and rear ends of the outer wall of the sliding sleeve are hingedly connected to hinge rods, and the lower ends of the outer walls adjacent to one end of the hinge rods are hingedly connected to the two ends of the outer wall of the connecting block respectively;

[0020] Through the above technical solution, the sliding sleeve is easily driven to move by the hinged rod.

[0021] Furthermore, the lower ends of the connecting blocks are fixedly connected with a second buffer wheel;

[0022] With the above technical solution, the buffer wheel 2 is used to facilitate buffering during landing.

[0023] The utility model has the following beneficial effects:

[0024] 1. The utility model proposes a fixed-wing UAV with adjustable wingspan. Compared with existing fixed-wing UAVs, when the fixed-wing UAV is used, the servo motor is started to drive the threaded rod to rotate and at the same time drive the threaded sleeve to move. The movement of the threaded sleeve drives the limit block to slide in the limit groove, and then limits the threaded sleeve so that it drives the aileron to move. The length of the aileron can be adjusted as needed to adapt to different usage environments.

[0025] 2. The utility model proposes a fixed-wing UAV with adjustable wingspan. Compared with existing fixed-wing UAVs, when the fixed-wing UAV is used, when the UAV lands, the damping rod and the shock-absorbing spring are preferentially compressed to absorb the impact force, which can absorb the impact force generated during landing and reduce damage to the UAV structure. As a result, the connecting block is compressed upward and drives the articulated rod to move. At this time, the articulated rod drives the sliding sleeves on both sides to continuously compress the reset spring for secondary buffering, which can further disperse and reduce the impact during landing and has high practical performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 This is an axonometric diagram of a fixed-wing UAV with adjustable wingspan proposed in the present invention;

[0027] Figure 2 This is an axonometric diagram of a fixed-wing UAV with adjustable wingspan proposed in the present invention;

[0028] Figure 3 This is an axial cross-sectional view of the side wing of a fixed-wing UAV with adjustable wingspan proposed in the present invention;

[0029] Figure 4 for Figure 3 Enlarged view of point A in the middle;

[0030] Figure 5 This is a schematic structural diagram of a fixed-wing UAV with adjustable wingspan proposed in the present invention;

[0031] Figure 6 The utility model provides a schematic axial cross-sectional view of a buffer frame in a fixed-wing UAV with adjustable wingspan.

[0032] Legend:

[0033] 1. Main frame; 2. Side wings; 3. Propeller blades; 4. Mounting box; 5. Servo motor; 6. Threaded rod; 7. Threaded sleeve; 8. Slide groove; 9. Aileron; 10. Limit groove; 11. Limit block; 12. Support rod; 13. Buffer wheel 1; 14. Buffer frame; 15. Mounting groove; 16. Connecting block; 17. Buffer wheel 2; 18. Damping rod; 19. Shock-absorbing spring; 20. Fixed rod; 21. Return spring; 22. Sliding sleeve; 23. Articulated rod. DETAILED DESCRIPTION

[0034] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only 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 making creative efforts are within the scope of protection of the present invention.

[0035] Reference Figure 1-6 , an embodiment provided by the utility model:

[0036] A fixed-wing drone with adjustable wingspan includes a main frame 1, with wings 2 fixedly connected to both sides of the outer wall of the main frame 1, a slide groove 8 is formed on the outer wall of the side wing 2 away from the center of the main frame 1, and an aileron 9 is slidably connected inside the slide groove 8. The lower surface of the side wing 2 is fixedly connected to a mounting box 4, and a servo motor 5 is fixedly connected to the inner wall of the adjacent side of the mounting box 4. The output end of the servo motor 5 is fixedly connected to a threaded rod 6, and the outer wall of the threaded rod 6 is sleeved with a threaded sleeve 7;

[0037] A buffer frame 14 is fixedly connected to the rear end of the lower surface of the main frame 1, and a mounting groove 15 is provided at the lower end of the outer wall of the buffer frame 14. Both sides of the inner wall of the mounting groove 15 are rotatably connected with a fixed rod 20, and the outer wall of the fixed rod 20 is sleeved with a return spring 21. Both sides of the outer wall of the return spring 21 are fixedly connected with a sliding sleeve 22. Connecting blocks 16 are provided on both sides of the lower end of the buffer frame 14, and the upper ends of the connecting blocks 16 are fixedly connected with damping rods 18. The outer walls of the damping rods 18 are sleeved with shock-absorbing springs 19.

[0038] Compared with existing fixed-wing UAVs, when this fixed-wing UAV is in use, when the UAV lands, the damping rod 18 and the shock-absorbing spring 19 are used to preferentially compress and absorb the impact force, which can absorb the impact force generated during landing and reduce damage to the UAV structure. As a result, the connecting block 16 is compressed upward while driving the articulated rod 23 to move. At this time, the articulated rod 23 drives the sliding sleeves 22 on both sides to continuously compress the return spring 21 for secondary buffering, which can further disperse and reduce the impact during landing, and has high practical performance.

[0039] The front and rear ends of the outer wall of the side wing 2 are provided with two blades 3, which are convenient for cooperation to rise. A limiting groove 10 is provided in the middle of the lower surface of the side wing 2, and the upper end of the threaded sleeve 7 is fixedly connected to the limiting block 11. The limiting blocks 11 slide inside the limiting groove 10 and are respectively fixedly connected to the lower end of the aileron 9. The limiting blocks 11 slide inside the limiting groove 10 to facilitate the threaded sleeve 7 to move laterally. The front end of the lower surface of the main frame 1 is fixedly connected to a support rod 12, and the lower end of the support rod 12 is fixedly connected to a buffer wheel 13, which is convenient for cooperation to move and buffer. The upper ends of the damping rod 18 and the shock-absorbing spring 19 are connected to the buffer frame The lower end of 14 is fixedly connected, and the impact force generated by its landing is easily reduced through the damping rod 18 and the shock-absorbing spring 19. The sliding sleeves 22 are slidably connected to the outer wall of the fixed rod 20 through the return spring 21. The sliding sleeves 22 are slidably connected to the outer wall of the fixed rod 20 through the return spring 21, which is convenient for driving the return spring 21 to be compressed. The front and rear ends of the outer wall of the sliding sleeve 22 are hingedly connected with a hinged rod 23, and the lower ends of the outer walls of the adjacent ends of the hinged rod 23 are respectively hingedly connected to the two ends of the outer wall of the connecting block 16. The hinged rod 23 is used to drive the sliding sleeve 22 to move, and the lower end of the connecting block 16 is fixedly connected with a buffer wheel 21, which is convenient for buffering during landing.

[0040] Working principle: When in use, the servo motor 5 is started to drive the threaded rod 6 to rotate and at the same time drive the threaded sleeve 7 to move. The movement of the threaded sleeve 7 drives the limit block 11 to slide in the limit groove 10, and then limits the threaded sleeve 7 so that it drives the aileron 9 to move. The length of the aileron 9 can be adjusted as needed to adapt to different usage environments. When the UAV lands, the damping rod 18 and the shock-absorbing spring 19 are used to preferentially compress and absorb its impact force, which can absorb the impact force generated during landing and reduce damage to the UAV structure. Subsequently, the connecting block 16 is compressed upward and drives the articulated rod 23 to move. At this time, the articulated rod 23 drives the sliding sleeves 22 on both sides to continuously compress the reset spring 21 for secondary buffering, which can further disperse and reduce the impact during landing.

[0041] Finally, it should be noted that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or make equivalent replacements for some of the technical features therein. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A fixed-wing drone with adjustable wingspan, comprising a main frame (1), characterized in that: Side wings (2) are fixedly connected to both sides of the outer wall of the main frame (1), a sliding groove (8) is provided on the outer wall of the side wing (2) away from the center of the main frame (1), and an aileron (9) is slidably connected inside the sliding groove (8), and the lower surface of the side wing (2) is fixedly connected to the installation box (4), and the inner wall of the adjacent side of the installation box (4) is fixedly connected to the servo motor (5), and the output end of the servo motor (5) is fixedly connected to the threaded rod (6), and the outer wall of the rod body of the threaded rod (6) is sleeved with a threaded sleeve block (7); The rear end of the lower surface of the main frame (1) is fixedly connected to a buffer frame (14), the lower end of the outer wall of the buffer frame (14) is provided with a mounting groove (15), both sides of the inner wall of the mounting groove (15) are rotatably connected to fixed rods (20), the outer wall of the fixed rod (20) is sleeved with a reset spring (21), both sides of the outer wall of the reset spring (21) are fixedly connected with sliding sleeves (22), both sides of the lower end of the buffer frame (14) are provided with connecting blocks (16), the upper ends of the connecting blocks (16) are fixedly connected to damping rods (18), and the outer walls of the damping rods (18) are sleeved with shock-absorbing springs (19).

2. The fixed-wing UAV with adjustable wingspan according to claim 1, characterized in that: Two blades (3) are provided at the front end and the rear end of the outer wall of the side wing (2).

3. The fixed-wing UAV with adjustable wingspan according to claim 1, characterized in that: A limiting groove (10) is provided in the middle of the lower surface of each side wing (2); the upper end of the threaded sleeve (7) is fixedly connected to a limiting block (11); and the limiting blocks (11) slide inside the limiting groove (10) and are fixedly connected to the lower end of the aileron (9).

4. The fixed-wing UAV with adjustable wingspan according to claim 1, characterized in that: The front end of the lower surface of the main frame (1) is fixedly connected to a support rod (12), and the lower end of the support rod (12) is fixedly connected to a buffer wheel (13).

5. The fixed-wing UAV with adjustable wingspan according to claim 1, characterized in that: The upper ends of the damping rod (18) and the shock absorbing spring (19) are fixedly connected to the lower end of the buffer frame (14).

6. The fixed-wing UAV with adjustable wingspan according to claim 1, characterized in that: The sliding sleeves (22) are all slidably connected to the outer wall of the fixed rod (20) via a return spring (21).

7. The fixed-wing UAV with adjustable wingspan according to claim 1, characterized in that: The front and rear ends of the outer wall of the sliding sleeve (22) are both hingedly connected to a hinge rod (23), and the lower ends of the outer wall adjacent to one end of the hinge rod (23) are respectively hingedly connected to the two ends of the outer wall of the connecting block (16).

8. The fixed-wing UAV with adjustable wingspan according to claim 1, characterized in that: The lower ends of the connecting blocks (16) are fixedly connected to buffer wheels 2 (17).

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