Vertical take-off and landing fixed-wing unmanned aerial vehicle with wings capable of being rapidly disassembled and assembled

Abstract

The vertical take-off and landing fixed-wing unmanned aerial vehicle comprises a fuselage and a tail, the tail is positioned and mounted on the right side of the fuselage, inclined empennages are positioned and mounted at the front end and the rear end of the tail, mounting grooves are formed in the inner ends of two wing bodies, and the two wing bodies are mounted in the mounting grooves. And mounting plates are slidably connected into the two mounting grooves in a penetrating manner, and the two mounting plates are symmetrically mounted at the front end and the rear end of the machine body. According to the vertical take-off and landing fixed-wing unmanned aerial vehicle with the wings capable of being rapidly disassembled and assembled, the mounting bases are mounted on the two sides of the bottom of the vehicle body through the two dampers, and then the monitoring assemblies are mounted in the grooves in the inner sides of the bottoms of the mounting bases; and two moving seats are moved to simultaneously drive two transmission gears through a first rack to simultaneously drive two sealing plates to perform position expansion movement through a second rack, otherwise, the two sealing plates can be driven to perform contraction movement, the practicability is better, and the monitoring assembly is better protected.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft UAVs, in particular to a vertical take-off and landing fixed-wing UAV with rapidly detachable wings. Background Art

[0002] Fixed-wing UAVs are UAVs with fixed wings that rely on the wings to generate lift for flight. The thrust generated by the propellers is the main power for flight, and the main lift comes from the relative movement of the wings and the air. They have the advantages of long flight time, good wind resistance and wide shooting area, and are widely used in many fields such as aerial survey, regional monitoring and pipeline inspection. When using fixed-wing drones, it is often necessary to disassemble and replace the wings. Traditionally, the wings are disassembled and replaced by installing screws and bolts, which is time-consuming and laborious. It not only reduces the efficiency of disassembly and replacement, but also increases the workload of the operator, and has poor practicality. In order to overcome the above defects, prior art 1 (application number CN202021843283.3, Chinese patent application date August 29, 2020) is a fixed-wing drone that can be quickly disassembled and folded, in which the arm of the lifting assembly is divided into a front section, a middle section and a rear section, the middle section is fixed to the bottom of the wing, and the two ends of the middle section are respectively connected to the front section and the rear section through a folding portion, wherein the front section and the rear section can rotate along the folding portion, effectively solving the problem that the fuselage and wings of drones in the prior art and on the market are mostly fixedly connected, and the installation and transportation process are very troublesome; There is also prior art 2 (application number CN201922102509.8, Chinese patent application date November 29, 2019) in which a fixed-wing UAV is used for quick replacement of wings, in which the wing block and slider are clamped with the slot and guide groove on the mounting plate, and the clamp device is used to fix the block, which effectively meets the needs of fast installation and disassembly of the fixed-wing UAV wing, thereby greatly improving the convenience, flexibility and work efficiency of the production, assembly and transportation of fixed-wing UAVs; and prior art 3 (application number CN202120135106.8, Chinese patent application date January 19, 2021) in which a vertical take-off and landing fixed-wing UAV with fast wing disassembly and assembly can be used. Since the power gear and the transmission gear form a meshing transmission relationship, and the connecting ring installed on the transmission gear ring and the wing body form a clamping rotating structure, the power gear will cause the transmission gear to rotate, so that the limit rod is disengaged from the clamping groove on the connecting plate, so that the wing body can be separated from the connecting plate; Although the existing technology can realize the rapid disassembly and replacement of the wings, the operation is more time-saving and labor-saving, and the work intensity of the staff is reduced, but when the drone is lifted, started, and stopped, there is no protective mechanism at the bottom to seal and protect the monitoring components at the bottom of the drone, which causes the drone to shake and fall, reducing the safety of the drone. Therefore, we propose a vertical take-off and landing fixed-wing UAV with quickly disassembled wings to solve the above-mentioned problems. Summary of the invention

[0003] The purpose of the present invention is to provide a vertical take-off and landing fixed-wing UAV with quickly disassembled wings, so as to solve the problem raised in the above-mentioned background technology that the current prior art does not have a protective mechanism at the bottom to seal and protect the monitoring components at the bottom of the UAV when the UAV is lifted, lowered, started and stopped, which causes the UAV to shake and fall, thereby reducing the safety of the UAV.

[0004] To achieve the above object, the present invention provides the following technical solution: a vertical take-off and landing fixed-wing UAV with rapidly detachable wings, comprising a fuselage and a tail, wherein the tail is positioned and installed on the right side of the fuselage, and inclined tail wings are positioned and installed at the front and rear ends of the tail; The left end of the fuselage is screwed with a head, and the outer end of the head is installed with an auxiliary propeller, the front and rear ends of the fuselage are penetrated by wing bodies, and the two wing bodies are symmetrically arranged about the transverse center line of the fuselage, and the bottoms of the two wing bodies are screwed with positioning plates, and two sets of main propellers are arranged at both ends of the two positioning plates; It also includes: two groups of dampers are screwed on both ends of the bottom of the fuselage, and the two groups of dampers are symmetrically arranged about the vertical center line of the fuselage, and the bottom of the two groups of fuselages are screwed with mounting seats; The inner ends of the two wing bodies are each provided with a mounting groove, and mounting plates are slidably connected to the inside of the two mounting grooves, and the two mounting plates are symmetrically mounted at the front and rear ends of the fuselage; The bottom groove of the mounting seat is installed with a monitoring component by screws, and the bottom of the monitoring component corresponds to two sealing plates, and the two sealing plates are slidably installed on the inner side of the bottom of the mounting seat, and the slots at both ends of the top of the mounting seat are slidably installed with moving seats, and the two moving seats have the same structure, and the bottom of the two moving seats is provided with a first rack.

[0005] Preferably, two sets of swing rods are rotatably mounted at both ends of the bottom of the fuselage via movable shafts, and the two sets of swing rods are in an inclined and staggered shape, and the bottom ends of the two sets of swing rods are rotatably connected to movable seats via movable shafts.

[0006] Preferably, the bottom ends of the two movable seats are meshedly connected with a transmission gear via a first rack, and the bottom ends of the two transmission gears are meshedly connected with a sealing plate via a second rack.

[0007] Preferably, the output ends of the two transmission gears are wound and connected with a second torsion spring, and the two second torsion springs have the same structure, and the outer ends of the two second torsion springs are connected to both sides of the inner wall of the mounting seat, and the two transmission gears are rotatably mounted at both ends inside the mounting seat.

[0008] Preferably, the internal slot of the wing body is rotatably mounted with a limit block, and the limit block is in an arc shape, and a row of limit slots corresponds to the outer side of the limit block, and the row of limit slots is evenly spaced and arranged on the outer side of the mounting plate.

[0009] Preferably, a compression spring is provided in the internal slot of the wing body, and the outer end of the compression spring is connected to a limiting block.

[0010] Preferably, the internal slot of the limit block is provided with a first torsion spring, and the inner side of the first torsion spring is wound and connected with a rotating rod, and the rotating rod is rotatably mounted on the outer sides of the tops of the two wing bodies.

[0011] Preferably, a gravity sensor is installed in the internal slot of the wing body by means of screws, and the gravity sensor is connected to an external controller via a central processing module, and an extrusion block is fitted and connected to the outer side of the gravity sensor.

[0012] Preferably, a buffer pad is fittedly installed on the outer side of the mounting plate, and an extrusion plate is fittedly connected to the outer side of the buffer pad, extrusion rods are rotatably installed on both sides of the inner end of the extrusion plate through a movable shaft, and the two extrusion rods are inclined, and the outer ends of the two extrusion rods are rotatably connected to moving blocks through a movable shaft, and the two moving blocks are slidably installed on both sides of the interior of the wing body.

[0013] Preferably, tension springs are provided in grooves on both sides of the interior of the wing body, and the outer ends of the two tension springs are connected to extrusion plates, and the extrusion plates are slidably installed through the interior of the wing body.

[0014] Compared with the prior art, the present invention has the following beneficial effects: (1) A sealing plate is provided, and a mounting seat is installed on both sides of the bottom of the fuselage through two groups of dampers, and then a monitoring component is installed in a groove on the inner side of the bottom of the mounting seat. At the same time, two sealing plates are correspondingly provided at the bottom of the monitoring component. When the UAV rises, the two moving seats can be moved to simultaneously drive the two transmission gears through the first rack and drive the two sealing plates to expand and move through the second rack. Conversely, the two sealing plates can be driven to shrink and move, which is more practical and better protects the monitoring component. (2) Furthermore, by winding a second torsion spring around the output ends of the two transmission gears, and then connecting the two second torsion springs to the mounting seat, the positions of the two transmission gears after rotation can be elastically reset by the elastic force of the two second torsion springs themselves, and then the two transmission gears can be driven to simultaneously drive the two sealing plates to retract and move through the second rack, so that the monitoring component can be automatically sealed and protected, thereby preventing the monitoring component from being damaged due to the fall of the drone in the later stage, and increasing the service life of the drone; (3) Furthermore, two sets of swing arms are rotatably mounted on both sides of the bottom of the fuselage through movable shafts, and then the bottom ends of the two sets of swing arms are rotatably connected with a moving seat through movable shafts. When the UAV stops on the ground, the gravity of the UAV itself will drive the mounting seat to move by squeezing through the two sets of dampers. At this time, the two sets of swing arms will simultaneously drive the two moving seats to move by squeezing through the movable shafts, thereby achieving sealing protection for the monitoring components, which not only improves the cushioning and shock absorption effect of the UAV, but also reduces the workload of the staff; (4) A mounting plate is provided. The mounting plates are positioned and installed at the front and rear ends of the fuselage. When the two wing bodies need to be quickly installed later, the two wing bodies only need to be slidably connected to the mounting plate through the two mounting grooves. When the wing bodies are slid through, the extrusion springs can sequentially pop out the limit blocks into a row of limit grooves through their own elastic force. At this time, the wing bodies can be slidably limited, thereby avoiding the phenomenon of misalignment and offset of the wing bodies during use later, thereby improving the installation stability of the wing bodies. (5) Furthermore, a rotating rod is installed by rotating the first torsion spring through the internal grooves of the two limit blocks, and then the two rotating rods are extended to the top outer sides of the two wing bodies. When the wing bodies need to be quickly disassembled and replaced, it is only necessary to rotate the rotating rod to drive the limit blocks to separate from the limit grooves. At this time, the wing bodies can be separated from the mounting plate, so that the two wing bodies can be quickly disassembled and replaced, and the operation is more time-saving and labor-saving.

[0015] (6) Furthermore, a compression plate is slidably installed through a tension spring in the internal grooves of the two wing bodies, and then compression rods are rotatably connected to the two outer ends of the two compression plates through movable shafts. At the same time, moving blocks are rotatably connected to the outer ends of the two compression rods through movable shafts. After the installation plate extends into the interior of the wing body, the compression plate can be squeezed to drive the two moving blocks to move their positions through the two compression rods. Then, the compression block can squeeze the gravity sensor, and then the compression value can be adjusted to the same value as the squeezed gravity sensor through the external controller. When the wing body becomes loose, the compression block will be separated from the gravity sensor, and then the gravity sensor will transmit the information to the controller through the central processing module to remind the staff to order the drone to return for maintenance in time. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a schematic diagram of the three-dimensional structure of the present invention; Figure 2 It is a schematic diagram of the three-dimensional structure of the present invention after the fuselage and the wing body are separated; Figure 3 It is a schematic diagram of the top cross-sectional structure of the wing body and the mounting plate of the present invention; Figure 4 It is a schematic diagram of a partial top-sectional structure of a wing body and a mounting plate of the present invention; Figure 5 For the present invention Figure 4 The enlarged structural diagram at A in the middle; Figure 6 It is a schematic diagram of a partial cross-sectional structure of a wing body and an extruded plate of the present invention; Figure 7 It is a schematic diagram of the three-dimensional structure of the fuselage and the mounting seat of the present invention when viewed from above; Figure 8 It is a schematic diagram of the three-dimensional structure of the fuselage and the mounting base of the present invention when viewed from above after being retracted; Fig. 9 It is a schematic diagram of the main cross-sectional structure of the fuselage and the mounting seat of the present invention; Fig.10 It is a schematic diagram of the three-dimensional structure of the sealing plate and the movable seat of the present invention.

[0017] In the figure: 1. fuselage; 2. tail; 3. nose; 4. tail; 5. wing body; 6. auxiliary propeller; 7. positioning plate; 8. main propeller; 9. damper; 10. mounting seat; 11. mounting slot; 12. mounting plate; 13. gravity sensor; 14. buffer pad; 15. extrusion rod; 16. moving block; 17. extrusion block; 18. extrusion plate; 19. tension spring; 20. limit slot; 21. limit block; 22. extrusion spring; 23. first torsion spring; 24. monitoring component; 25. sealing plate; 26. swing rod; 27. transmission gear; 28. first rack; 29. ​​moving seat; 30. second torsion spring; 31. rotating rod; 32. second rack. DETAILED DESCRIPTION

[0018] 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 described embodiments 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 creative work are within the scope of protection of the present invention.

[0019] The present invention provides the following technical solutions: Embodiment 1, in order to solve the problem that when the existing drone is lifted, started and stopped, there is no protective mechanism at the bottom to seal and protect the monitoring component 24 at the bottom of the drone, which may cause the drone to fall due to shaking, thereby reducing the safety performance of the drone, the following embodiment is disclosed: A fuselage 1 and a tail 2, wherein the tail 2 is positioned and installed on the right side of the fuselage 1, and inclined tail wings 4 are positioned and installed at the front and rear ends of the tail 2; The left end of the fuselage 1 is screwed with a head 3, and an auxiliary propeller 6 is installed at the outer end of the head 3. The front and rear ends of the fuselage 1 are penetrated with wing bodies 5, and the two wing bodies 5 are symmetrically arranged about the transverse center line of the fuselage 1. The bottoms of the two wing bodies 5 are screwed with positioning plates 7, and two sets of main propellers 8 are arranged at both ends of the two positioning plates 7. It also includes: two groups of dampers 9 are screwed on both ends of the bottom of the fuselage 1, and the two groups of dampers 9 are symmetrically arranged about the vertical center line of the fuselage 1, and the bottom of the fuselage 1 of the two groups is screwed with mounting seats 10; The inner ends of the two wing bodies 5 are each provided with a mounting groove 11, and the insides of the two mounting grooves 11 are penetrated by mounting plates 12 which are slidably connected, and the two mounting plates 12 are symmetrically mounted at the front and rear ends of the fuselage 1; The bottom groove of the mounting base 10 is installed with a monitoring component 24 by screws, and the bottom of the monitoring component 24 corresponds to two sealing plates 25, and the two sealing plates 25 are slidably installed on the bottom inner side of the mounting base 10, and the top two ends of the mounting base 10 are slotted and slidably installed with moving seats 29, and the two moving seats 29 have the same structure, and the bottom of the two moving seats 29 is provided with a first rack 28.

[0020] Two sets of swing arms 26 are rotatably installed at both ends of the bottom of the fuselage 1 through movable shafts, and the two sets of swing arms 26 are in an inclined and staggered shape, and the bottom ends of the two sets of swing arms 26 are rotatably connected to movable seats 29 through movable shafts, and the bottom ends of the two movable seats 29 are meshedly connected to transmission gears 27 through first racks 28, and at the same time, the bottom ends of the two transmission gears 27 are meshedly connected to sealing plates 25 through second racks 32.

[0021] The output ends of the two transmission gears 27 are wound and connected with a second torsion spring 30, and the two second torsion springs 30 have the same structure, and the outer ends of the two second torsion springs 30 are connected to the two sides of the inner wall of the mounting base 10, and the two transmission gears 27 are rotatably mounted at the two ends inside the mounting base 10.

[0022] like Figure 1-Figure 10 As shown, when the UAV is lowered and parked, the weight of the fuselage 1 itself will drive the mounting seat 10 to move through the two groups of dampers 9 to squeeze the position, so that the fuselage 1 can be buffered and shock-absorbed. At this time, the two groups of swing rods 26 arranged at both ends of the bottom of the fuselage 1 squeeze the two moving seats 29 through the movable shaft to expand the position, and then the first racks 28 arranged at the bottom of the two moving seats 29 will simultaneously drive the two transmission gears 27 to rotate, and then the two transmission gears 27 will also drive the two sealing plates 25 to shrink and move through the two second racks 32, so that the two shrinking sealing plates 25 can seal and protect the monitoring component 24 arranged on the inner side of the bottom of the mounting seat 10, so as to avoid the phenomenon that the UAV shakes and falls later and causes damage to the monitoring component 24, thereby improving the service life of the monitoring component 24. On the contrary, when the drone rises, the two groups of dampers 9 will drive the mounting seat 10 to reset and move, and at the same time, the two second torsion springs 30 will elastically reset the positions of the two rotating rear transmission gears 27 through their own elastic force, thereby driving the two groups of swing rods 26 to reset the two moving seats 29. At this time, the two moving seats 29 will simultaneously drive the two sealing plates 25 to expand and move through the two transmission gears 27, so that the monitoring component 24 is exposed, which is better for monitoring and use, thereby improving the practicality of the drone.

[0023] Embodiment 2 is different from Embodiment 1 in that the two wing bodies 5 can be quickly disassembled and replaced, which saves time and effort, reduces the workload of the staff, and discloses: The wing body 5 has an internal slotted and rotatably mounted limit block 21 , which is in an arc shape, and a row of limit slots 20 corresponding to the outer side of the limit block 21 , and a row of limit slots 20 are evenly spaced and arranged on the outer side of the mounting plate 12 .

[0024] The internal groove of the wing body 5 is provided with an extrusion spring 22, and the outer end of the extrusion spring 22 is connected to the limit block 21, the internal groove of the limit block 21 is provided with a first torsion spring 23, and the inner side of the first torsion spring 23 is wound and connected with a rotating rod 31, and the rotating rod 31 is rotatably installed on the top outer side of the two wing bodies 5.

[0025] like Figure 1-Figure 5 As shown, when the two wing bodies 5 need to be quickly disassembled and replaced, the mounting plate 12 only needs to be slidably extended through the mounting groove 11 to the inside of the wing body 5. At this time, the extrusion spring 22 will use its own elastic force to pop out the limit blocks 21 in sequence to the row of limit grooves 20 opened on the outside of the mounting plate 12, so that the wing body 5 can be slidably limited, avoiding the phenomenon of dislocation and deviation of the wing body 5 during use in the later stage, thereby improving the installation stability of the wing body 5. When the wing body 5 needs to be quickly disassembled and replaced, it is only necessary to rotate the rotating rod 31 to drive the limit block 21 to rotate, so that the limit block 21 is separated from the limit groove 20, and then the wing body 5 can be taken out from the mounting plate 12, which is more time-saving and labor-saving. Finally, the elastic force of the first torsion spring 23 itself is used to elastically reset the position of the rotating rod 31 after rotation for later reuse.

[0026] Embodiment 3 is different from Embodiment 2 in that the stability of the wing body 5 after installation can be monitored to prevent the wing body 5 from loosening and falling off due to shaking during flight, thereby improving the stability of the drone. The internal slot of the wing body 5 is installed with a gravity sensor 13 by screws, and the gravity sensor 13 is connected to an external controller through a central processing module, and an extrusion block 17 is attached to the outer side of the gravity sensor 13 .

[0027] A buffer pad 14 is fitted on the outer side of the mounting plate 12, and an extrusion plate 18 is fitted on the outer side of the buffer pad 14, and extrusion rods 15 are rotatably mounted on both sides of the inner end of the extrusion plate 18 through a movable shaft, and the two extrusion rods 15 are inclined, and the outer ends of the two extrusion rods 15 are rotatably connected to moving blocks 16 through a movable shaft, and the two moving blocks 16 are slidably mounted on both sides of the interior of the wing body 5.

[0028] Tension springs 19 are provided in grooves on both sides of the interior of the wing body 5 , and the outer ends of the two tension springs 19 are connected to the extrusion plates 18 , and the extrusion plates 18 are slidably installed in the interior of the wing body 5 .

[0029] like Figure 1-Figure 6 As shown, when the wing body 5 extends through the outside of the mounting plate 12, the outer end of the mounting plate 12 will squeeze the squeezing plate 18 through the buffer pad 14 to move the position, so that the squeezing plate 18 squeezes the two squeezing rods 15 through the movable shaft and drives the two moving blocks 16 to move the position through the movable shaft. At this time, the squeezing block 17 set at the inner end of the squeezing plate 18 will squeeze the gravity sensor 13, and then the squeezing value is adjusted to the same as the value of the squeezed gravity sensor 13 through the external controller. When the wing body 5 becomes loose and shaken, the two tension springs 19 will reset the squeezed squeezing plate 18 through their own elastic force, so that the squeezing block 17 is separated from the gravity sensor 13. At this time, the squeezing value of the gravity sensor 13 will change, and the information will be transmitted to the external controller through the central processing module to promptly remind the staff to order the drone to return for maintenance in time, which is more practical and completes a series of tasks.

[0030] Although the present invention has been described in detail with reference to the aforementioned embodiments, it is still possible for those skilled in the art to modify the technical solutions described in the aforementioned embodiments, or to make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A vertical take-off and landing fixed-wing drone with rapidly detachable wings, comprising a fuselage (1) and a tail (2), wherein the tail (2) is positioned and mounted on the right side of the fuselage (1), and inclined tail wings (4) are positioned and mounted at the front and rear ends of the tail (2); The left end of the fuselage (1) is screwed with a head (3), and the outer end of the head (3) is installed with a secondary propeller (6); the front and rear ends of the fuselage (1) are penetrated by wing bodies (5), and the two wing bodies (5) are symmetrically arranged about the transverse center line of the fuselage (1); and the bottoms of the two wing bodies (5) are screwed with positioning plates (7), and two sets of main propellers (8) are arranged at both ends of the two positioning plates (7); It is characterized in that Also includes: Two groups of dampers (9) are screwed on both ends of the bottom of the fuselage (1), and the two groups of dampers (9) are symmetrically arranged about the vertical center line of the fuselage (1), and the bottom of the two groups of fuselage (1) is screwed with mounting seats (10); The inner ends of the two wing bodies (5) are each provided with a mounting groove (11), and mounting plates (12) are slidably connected to the inside of the two mounting grooves (11), and the two mounting plates (12) are symmetrically mounted at the front and rear ends of the fuselage (1); The bottom of the mounting seat (10) is slotted with a monitoring component (24) mounted thereon by screws, and the bottom of the monitoring component (24) has two corresponding sealing plates (25), and the two sealing plates (25) are slidably mounted on the inner side of the bottom of the mounting seat (10); The top ends of the mounting seat (10) are slotted with movable seats (29) slidably mounted therethrough, and the two movable seats (29) have the same structure, and the bottoms of the two movable seats (29) are provided with first racks (28).

2. The vertical take-off and landing fixed-wing UAV with rapidly detachable wings according to claim 1, characterized in that: Two sets of swing rods (26) are rotatably mounted at both ends of the bottom of the fuselage (1) via movable shafts, and the two sets of swing rods (26) are in an inclined and staggered shape, and the bottom ends of the two sets of swing rods (26) are rotatably connected to movable seats (29) via movable shafts.

3. The vertical take-off and landing fixed-wing UAV with rapidly detachable wings according to claim 2, characterized in that: The bottom ends of the two movable seats (29) are meshedly connected to the transmission gear (27) via the first rack (28), and the bottom ends of the two transmission gears (27) are meshedly connected to the sealing plate (25) via the second rack (32).

4. The vertical take-off and landing fixed-wing UAV with rapidly detachable wings according to claim 3, characterized in that: The output ends of the two transmission gears (27) are wound and connected with a second torsion spring (30), and the two second torsion springs (30) have the same structure, and the outer ends of the two second torsion springs (30) are connected to the inner walls of the mounting seat (10), and the two transmission gears (27) are rotatably mounted at the inner ends of the mounting seat (10).

5. The vertical take-off and landing fixed-wing UAV with rapidly detachable wings according to claim 1, characterized in that: The wing body (5) has an internal slotted therein for rotatably mounting a limit block (21), the limit block (21) being in an arc shape, and a row of limit slots (20) corresponding to the outer side of the limit block (21), and the row of limit slots (20) being arranged at equal intervals on the outer side of the mounting plate (12).

6. The vertical take-off and landing fixed-wing UAV with rapidly detachable wings according to claim 5, characterized in that: The internal slot of the wing body (5) is provided with a pressing spring (22), and the outer end of the pressing spring (22) is connected to a limiting block (21).

7. The vertical take-off and landing fixed-wing UAV with rapidly detachable wings according to claim 6, characterized in that: The internal slot of the limit block (21) is provided with a first torsion spring (23), and the inner side of the first torsion spring (23) is wound and connected with a rotating rod (31), and the rotating rod (31) is rotatably mounted on the outer sides of the tops of the two wing bodies (5).

8. The vertical take-off and landing fixed-wing UAV with rapidly detachable wings according to claim 1, characterized in that: The internal slot of the wing body (5) is equipped with a gravity sensor (13) via screws, the gravity sensor (13) is connected to an external controller via a central processing module, and an extrusion block (17) is attached to the outside of the gravity sensor (13).

9. The vertical take-off and landing fixed-wing UAV with rapidly detachable wings according to claim 1, characterized in that: A buffer pad (14) is fitted and mounted on the outer side of the mounting plate (12), and an extrusion plate (18) is fitted and connected to the outer side of the buffer pad (14), and extrusion rods (15) are rotatably mounted on both sides of the inner end of the extrusion plate (18) via a movable shaft, and the two extrusion rods (15) are inclined, and the outer ends of the two extrusion rods (15) are rotatably connected to moving blocks (16) via a movable shaft, and the two moving blocks (16) are slidably mounted on both sides of the interior of the wing body (5).

10. A vertical take-off and landing fixed-wing UAV with rapidly detachable wings according to claim 9, characterized in that: Tension springs (19) are provided in grooves on both sides of the interior of the wing body (5), and the outer ends of the two tension springs (19) are connected to extrusion plates (18), and the extrusion plates (18) are slidably installed through the interior of the wing body (5).

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