Fixed-wing unmanned aerial vehicle capable of quickly disassembling and assembling wings

Abstract

The fixed-wing unmanned aerial vehicle comprises a vehicle body and the wings, mounting grooves are formed in the wings, assembling grooves used for mounting the wings are formed in the two sides of the vehicle body, first air bags are arranged in the assembling grooves, and a first cavity, a second cavity and a third cavity are formed in the vehicle body; a first elastic piece and a first locking block are arranged in the first cavity, the first elastic piece pushes the first locking block to extend into the mounting groove, an adjusting block is arranged in the second cavity, an unlocking piece connected with the first locking block is arranged in the third cavity, and the adjusting block is used for adjusting fluid in the first air bag to be transferred to the first cavity or the third cavity. The flow direction of fluid in the first air bag can be observed through the arranged adjusting block, the wings and the fuselage can be conveniently and rapidly assembled and disassembled, meanwhile, vibration between the wings and the fuselage can be reduced, and the service life of the wings is prolonged.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and more specifically to a fixed-wing UAV with rapidly detachable and detachable wings. Background Technology

[0002] Fixed-wing unmanned aerial vehicles (UAVs) are unmanned flying devices with fixed wings, widely used in surveying, geological exploration, oil inspection, agricultural and forestry monitoring and other fields.

[0003] Fixed-wing drones typically have long and fragile wings. Currently, most drone wings are fixed to the sides of the fuselage using rivets. This makes the wings, being too long, susceptible to collisions, deformation, or even breakage during transport and storage. Furthermore, when users need to maintain the wings, it is difficult to quickly disassemble and reassemble them, increasing the workload of maintenance personnel, reducing work efficiency, and the disassembly and reassembly procedures are complex. Additionally, because existing fixed-wing drones use rivets, vibrations generated during flight can easily cause the wing to break at the connection point with the fuselage. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to overcome the shortcomings of the prior art. The purpose is to provide a fixed-wing UAV with quick detachment and assembly of wings, which facilitates the quick assembly and disassembly of wings and fuselage.

[0005] This invention is achieved through the following technical solution:

[0006] A fixed-wing unmanned aerial vehicle (UAV) with rapidly detachable and detachable wings includes a fuselage and wings. The wings have mounting slots, and both sides of the fuselage have assembly slots for mounting the wings. A first airbag is housed within each assembly slot. The fuselage contains a first cavity, a second cavity, and a third cavity. A first elastic element and a first locking block are located within the first cavity. The first elastic element pushes the first locking block into the mounting slot. An adjustment block is located within the second cavity, and an unlocking element connected to the first locking block is located within the third cavity. The adjustment block is used to adjust the transfer of fluid from the first airbag to the first or third cavity. When fluid is transferred to the first cavity, the fluid prevents the first locking block from retracting into the first cavity; when fluid is transferred to the third cavity, the fluid pushes the unlocking element to pull the first locking block back into the first cavity.

[0007] Furthermore, it also includes a connecting rod connected to the tail fin. The fuselage has a fourth cavity with an inner diameter that is the same as the outer diameter of the connecting rod. The connecting rod can move within the fourth cavity. The second cavity also has a second elastic element, which is connected to an adjusting block. The second elastic element is used to extend one end of the adjusting block into the fourth cavity.

[0008] Furthermore, the end of the adjusting block located in the fourth cavity has a conical structure; a first channel is provided between the first cavity and the third cavity, a second channel is provided between the first airbag and the third cavity, and a third channel is provided between the third cavity and the second cavity, with the third channel and the second channel in the same direction; the adjusting block is provided with a vertical hole and an L-shaped connecting hole, the vertical hole being used to connect the second channel and the third channel, and the connecting hole being used to connect the second channel and the first channel.

[0009] Furthermore, the unlocking component includes a first movable block and a first movable rod. The outer diameter of the first movable block is the same as the inner diameter of the third cavity. One end of the first movable rod is connected to the first movable block, and the other end extends into the first cavity and is connected to the first locking block.

[0010] Furthermore, the tail of the fuselage is provided with a blind connection hole, in which a second airbag and an adjustment disc are provided. The second airbag and the adjustment disc are both sleeved on the connecting rod. The adjustment disc is connected to the blind connection hole by a thread. The fuselage is also provided with a fifth cavity communicating with the second airbag. The fifth cavity is provided with a third elastic element and a limiting rod. The limiting rod can extend into the fourth cavity. The fourth cavity is also provided with a pull rope, which is connected to the connecting rod.

[0011] Furthermore, the fuselage is also provided with a sixth cavity and a seventh cavity. The sixth cavity is connected to the second airbag through a fourth channel. The sixth cavity is provided with a fourth elastic element and a blocking ball. The elastic force of the fourth elastic element is greater than that of the third elastic element. The fourth elastic element is used to push the blocking ball to block the fourth channel. The seventh cavity is connected to the second cavity. The seventh cavity is provided with a third airbag and a protrusion connected to the side wall of the adjusting block. The third airbag is connected to the sixth cavity through a fifth channel.

[0012] Furthermore, it also includes a first drive mechanism detachably connected to the wing. The first drive mechanism includes a first housing, a first motor, and a first propeller connected to the first motor. A connecting post is provided on the side wall of the first housing, and a strip groove is provided on the side wall of the connecting post.

[0013] The wing end is provided with a connecting groove and a fourth airbag. The connecting groove is provided with a first mounting blind hole. The first mounting blind hole is provided with a fifth elastic element, a second locking block and a limiting block. The fifth elastic element is used to push the second locking block into the strip groove. The outer diameter of the limiting block is the same as the inner diameter of the first mounting blind hole. The fourth airbag is connected to the first mounting blind hole.

[0014] Furthermore, the wing is provided with an eighth cavity, and the eighth cavity is provided with a second movable block and a second movable rod. The outer diameter of the second movable block is the same as the inner diameter of the eighth cavity. One end of the second movable rod is connected to the first movable block, and the other end passes through the limiting block and is connected to the second locking block.

[0015] The wing is provided with a connection port that communicates with the eighth cavity. The fuselage has a connecting pipe in the mounting slot that communicates with the first airbag. The outer diameter of the connecting pipe is the same as the inner diameter of the connection port.

[0016] Furthermore, the connecting rod is also provided with a second driving mechanism, which includes a second housing, a second motor and a second propeller. The second housing is provided with a second mounting blind hole, and the inner wall of the second mounting blind hole is provided with a third mounting blind hole. The third mounting blind hole is provided with a sixth elastic element and a locking rod. The side wall of the connecting rod is provided with a fixing hole, and the sixth elastic element is used to push the locking rod into the fixing hole.

[0017] Furthermore, the connecting rod is provided with a ninth cavity, which is connected to the fourth cavity through a through hole. The ninth cavity is provided with a seventh elastic element and a sealing plate. The seventh elastic element is used to push the sealing plate to seal the through hole. A sixth channel is provided between the ninth cavity and the fixing hole. The pull rope is connected to the sealing plate.

[0018] Compared with the prior art, the present invention has the following advantages and beneficial effects:

[0019] This invention utilizes an adjustable block to connect the first airbag to either the first cavity or the third cavity. When the first airbag is connected to the first cavity, the vibration generated by the wing during flight compresses the first airbag, forcing the air inside the first airbag to transfer into the first cavity. This ensures that the wing can be stably connected to the fuselage even under vibration, and the first airbag absorbs some of the energy generated by the wing vibration. When the first airbag is connected to the third cavity, the air compressed by the connecting rod during retraction can be transferred into the third cavity, thereby quickly removing the first locking block from the wing's mounting slot and achieving rapid disassembly between the wing and the fuselage. Attached Figure Description

[0020] The accompanying drawings, which are included to provide a further understanding of embodiments of the invention and form part of this application, do not constitute a limitation thereof. In the drawings:

[0021] Figure 1 This is a schematic diagram of the structure of the present invention;

[0022] Figure 2 This is a schematic diagram of the structure when the wing and fuselage of the present invention are connected;

[0023] Figure 3 For the present invention Figure 2 A magnified structural diagram of section A in the middle;

[0024] Figure 4 For the present invention Figure 2 A magnified structural diagram of section B in the middle;

[0025] Figure 5 For the present invention Figure 2 A magnified structural diagram of section C in the middle;

[0026] Figure 6 This is a schematic diagram of the structure of the adjusting block of the present invention;

[0027] Figure 7 This is a schematic diagram of the structure of the first driving mechanism of the present invention;

[0028] Figure 8 This is a schematic diagram of the structure of the wing of the present invention;

[0029] Figure 9 This is a schematic diagram of the structure of the fuselage of the present invention;

[0030] Figure 10 This is a schematic diagram of the structure of the second driving mechanism of the present invention;

[0031] Figure 11 For the present invention Figure 10 A magnified structural diagram of section D in the middle.

[0032] The attached diagram shows the markings and corresponding component names:

[0033] 1. Fuselage; 2. Wing; 3. First drive mechanism; 4. Connecting rod; 5. Second drive mechanism; 6. Fifth elastic element; 8. Fourth airbag; 9. Connecting column; 10. Strip groove; 11. Second locking block; 12. Second movable block; 13. Second movable rod; 14. Limiting block; 15. Mounting groove; 16. First locking block; 17. First airbag; 18. First elastic element; 19. First movable rod; 20. First movable block; 21. Second elastic element; 22. Protrusion 23. Third airbag; 24. Adjusting block; 25. Vertical hole; 26. Connecting hole; 27. Adjusting disc; 28. Sixth channel; 29. ​​Second airbag; 30. Seventh elastic element; 31. Sealing plate; 32. Limiting rod; 33. Pull rope; 34. Sealing ball; 35. Fifth channel; 36. First housing; 37. First motor; 38. Connecting port; 39. Connecting pipe; 40. Second housing; 41. Second propeller; 42. Sixth elastic element; 43. Locking rod. Detailed Implementation

[0034] To make the objectives, technical solutions, and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the embodiments and accompanying drawings. The illustrative embodiments and descriptions of the present invention are only used to explain the present invention and are not intended to limit the present invention.

[0035] Example

[0036] like Figures 1 to 11 As shown in the figure, the present invention includes a fuselage 1 and a wing 2. The wing 2 is provided with a mounting groove 15. Both sides of the fuselage 1 are provided with assembly grooves for mounting the wing 2. A first airbag 17 is provided in the assembly groove. The fuselage 1 is provided with a first cavity, a second cavity, and a third cavity. A first elastic element 18 and a first locking block 16 are provided in the first cavity. The first elastic element 18 pushes the first locking block 16 into the mounting groove 15. An adjusting block 24 is provided in the second cavity. An unlocking element connected to the first locking block 16 is provided in the third cavity. The adjusting block 24 is used to adjust the fluid in the first airbag 17 to transfer to the first cavity or the third cavity. When the fluid is transferred to the first cavity, the fluid can prevent the first locking block 16 from retracting into the first cavity. When the fluid is transferred to the third cavity, the fluid can push the unlocking element to pull the first locking block 16 back into the first cavity.

[0037] In most existing fixed-wing drones, the wings 2 are connected to the fuselage 1 using rivets. However, the wings 2 of fixed-wing drones are generally long and relatively fragile. To prevent the wings 2 from being easily deformed or even broken due to collisions during transportation and storage, it is usually necessary to remove the wings 2 from the fuselage 1. This makes the rivet connection method inconvenient. Furthermore, the rivet connection between the wings 2 and the fuselage 1 makes the connection between the wings 2 and the fuselage prone to breakage due to vibrations generated by the wings 2 during flight. Therefore, this technical solution provides a first cavity, a second cavity, and a third cavity in the existing fuselage 1. The first cavity is provided with a first elastic element 18 and a first locking block 16 for fixing the wings 2 to the mounting slots in the fuselage 1. During installation, the wings 2 are inserted into the mounting slots on the side of the fuselage 1, and the elastic force generated by the first elastic element 18 pushes the first locking block 16 into the mounting slots 15 on the wings 2, thereby quickly connecting the wings 2 to the fuselage 1.

[0038] Meanwhile, in order to facilitate the quick removal of the wing 2 from the fuselage 1, a first airbag 17, an adjusting block 24, and an unlocking component are also provided. When it is necessary to remove the wing 2 from the fuselage 1, the adjusting block 24 is moved so that the fluid in the first airbag 17 can be transferred to the third cavity. In this way, the fluid entering the third cavity can push the unlocking component to move, thereby causing the first locking block 16, which was originally inserted into the mounting slot 15, to retract into the first cavity, thus achieving the purpose of quickly removing the wing 2 from the fuselage 1.

[0039] Meanwhile, the width of the mounting groove 15 in this technical solution is greater than the width of the first locking block 16, which allows relative movement between the first locking block 16 and the wing 2. That is, when the wing 2 vibrates during the flight of the UAV, the wing 2 will compress the first airbag 17, using the first airbag 17 to absorb some of the energy generated by the vibration, thereby preventing the connection between the wing 2 and the fuselage 1 from breaking. During the flight of the UAV, the adjusting block 24 keeps the first airbag 17 and the first cavity in a certain position. In the connected state, when the first airbag 17 is vibrated by the wing 2, it is compressed by the wing 2, causing the air inside the first airbag 17 to transfer into the first cavity. The air pressure entering the first cavity acts on the first locking block 16, preventing the first locking block 16 from retracting. This avoids the situation where, when the wing 2 vibrates violently, the vibration of the wing 2 forces the first locking block 16 to squeeze the first elastic element 18, thereby causing the first locking block 16 to move out of the mounting groove 15, and ultimately causing the wing 2 to fall off from the mounting groove of the fuselage 1.

[0040] It also includes a connecting rod 4 connected to the tail fin. The fuselage 1 has a fourth cavity with an inner diameter that is the same as the outer diameter of the connecting rod 4. The connecting rod 4 can move in the fourth cavity. The fourth cavity is connected to the first airbag 17. The second cavity also has a second elastic element 21. The second elastic element 21 is connected to the adjusting block 24. The second elastic element 21 is used to extend one end of the adjusting block 24 into the fourth cavity.

[0041] In this embodiment, in order to adjust the position of the adjusting block 24, a fourth cavity for installing the connecting rod 4 is provided inside the fuselage 1. When the drone is finished and the wing 2 needs to be removed, the connecting rod 4 is retracted into the fourth cavity. When the connecting rod 4 retracts to the adjusting block 24, the outer surface of the connecting rod 4 pushes the adjusting block 24 back into the second cavity. When the end of the adjusting block 24 is completely retracted from the fourth cavity into the second cavity, the adjusting block 24 connects the first airbag 17 with the third cavity. Therefore, as the connecting rod 4 continues to retract in the fourth cavity, the connecting rod 4 compresses the air in the fourth cavity into the first airbag 17. Then the air in the first airbag 17 enters the third cavity. Under the pull of the unlocking component, the first locking block 16 is moved out of the mounting slot 15, thereby achieving the purpose of quickly removing the wing 2 from the fuselage 1.

[0042] The end of the adjusting block 24 located in the fourth cavity has a conical structure; a first channel is provided between the first cavity and the third cavity, a second channel is provided between the first airbag 17 and the third cavity, and a third channel is provided between the third cavity and the second cavity, with the third channel and the second channel in the same direction; the adjusting block 24 is provided with a vertical hole 25 and an L-shaped connecting hole 26, the vertical hole 25 is used to connect the second channel and the third channel, and the connecting hole 26 is used to connect the second channel and the first channel.

[0043] In this embodiment, in order to ensure that the end of the connecting rod 4 can pass smoothly through the adjusting block 24 during the retraction of the connecting rod 4 in the fourth cavity, the end of the adjusting block 24 located in the fourth cavity is a conical structure. This allows the end of the connecting rod 4 to act on the conical surface of the adjusting block 24 during the retraction, forcing the connecting rod 4 to retract the adjusting block 24 into the second cavity.

[0044] In this embodiment, when the initial state adjustment block 24 is not subjected to external force, the adjustment block 24 extends into the fourth cavity under the action of the second elastic member 21. At this time, the connecting hole 26 on the adjustment block 24 connects the second channel with the first channel, and the second channel and the third channel are in a staggered state. This allows the air inside the first airbag 17 to be transferred to the first cavity when the wing 2 vibrates and squeezes it during the flight of the UAV. This prevents the wing 2 from vibrating violently during the flight of the UAV, which would cause the first locking block 16 to be removed from the mounting slot 15, thereby causing the wing 2 to detach from the fuselage 1.

[0045] When disassembling the drone and retracting the connecting rod 4 into the fourth cavity, the connecting rod 4 pushes the adjusting block 24 back into the second cavity. At this time, the second channel and the third channel are connected, while the second channel and the first channel are disconnected. In this way, the connecting rod 4 can compress the air in the fourth cavity into the first airbag 17 during retraction. The air in the first airbag 17 is then transferred to the third cavity, thereby pushing the unlocking component in the third cavity to move and removing the first locking block 16 in the mounting slot 15, thus achieving the purpose of disassembling the wing 2 from the fuselage 1.

[0046] In another embodiment, the body 1 has two first cavities, two third cavities, two first locking blocks 16, two first elastic elements 18, and two locking elements, and the two first cavities are interconnected, and the two third cavities are interconnected.

[0047] The unlocking component includes a first movable block 20 and a first movable rod 19. The outer diameter of the first movable block 20 is the same as the inner diameter of the third cavity. One end of the first movable rod 19 is connected to the first movable block 20, and the other end passes through the first cavity and is connected to the first locking block 16.

[0048] In this embodiment, in order to ensure that the unlocking lever can drive the first locking block 16 to retract and unlock the first locking block 16, the unlocking component includes a first movable block 20 and a first movable lever 19. When the air in the first airbag 17 is transferred to the third cavity, the air entering the third cavity will push the first movable block 20 to move in the third cavity. Under the pull of the first movable lever 19, the first locking block 16 can be pulled out of the mounting slot 15, thereby achieving the purpose of unlocking the first locking block 16.

[0049] In another embodiment, in order to ensure that the first movable block 20 can move smoothly in the third cavity, a pressure relief hole communicating with the third cavity is provided on one side of the body 1. This allows the air in the other part of the fourth cavity to be discharged through the pressure relief hole while the first movable block 20 moves in the third cavity, ensuring that the first movable block 20 can move smoothly in the third cavity.

[0050] The tail of the body 1 is also provided with a connection blind hole. The connection blind hole is provided with a second airbag 29 and an adjustment plate 27. The second airbag 29 and the adjustment plate 27 are both sleeved on the connecting rod 4. The adjustment plate 27 is connected to the connection blind hole by threads. The body 1 is also provided with a fifth cavity communicating with the second airbag 29. The fifth cavity is provided with a third elastic element and a limiting rod 32. The limiting rod 32 can extend into the fourth cavity. The fourth cavity is also provided with a pull rope 33, which is connected to the connecting rod 4.

[0051] In this embodiment, to ensure that the connecting rod 4 is stably fixed to the fuselage 1 during the flight of the UAV, a connecting blind hole is also provided at the tail of the fuselage 1. The second airbag 29 and the adjusting plate 27 are provided in the connecting blind hole. The adjusting plate 27 is connected to the connecting blind hole by a thread. Thus, when the connecting rod 4 is pulled outward so that the pull rope 33 is in a taut state, the adjusting plate 27 is rotated so that the adjusting plate 27 moves towards the second airbag 29 in the blind hole and squeezes the second airbag 29, thereby squeezing the air inside the second airbag 29 into the fifth cavity, pushing the limiting rod 32 in the fifth cavity to extend into the fourth cavity. Together with the pull rope 33, the connecting rod 4 is stably fixed to the fuselage 1.

[0052] During disassembly, the adjustment disc 27 is rotated in the opposite direction, causing it to retract away from the second airbag 29, thus removing the pressure on the second airbag 29. Under the action of the third elastic element, the limiting rod 32 can be pulled from the fourth cavity to the fifth cavity, thereby allowing the connecting rod 4 to retract smoothly into the fourth cavity, reducing the space occupied by the connecting rod 4 and making it easier to carry.

[0053] The fuselage 1 is also provided with a sixth cavity and a seventh cavity. The sixth cavity is connected to the second airbag 29 through a fourth channel. The sixth cavity is provided with a fourth elastic element and a blocking ball 34. The elastic force of the fourth elastic element is greater than that of the third elastic element. The fourth elastic element is used to push the blocking ball 34 to block the fourth channel. The seventh cavity is connected to the second cavity. The seventh cavity is provided with a third airbag 23 and a protrusion 22 connected to the side wall of the adjusting block 24. The third airbag 23 is connected to the sixth cavity through a fifth channel 35.

[0054] In this embodiment, to prevent the wing 2 from colliding violently with obstacles during flight and potentially breaking, a sixth and seventh cavity are provided within the fuselage 1. Initially, the fourth elastic element pushes the blocking ball 34 to block the fourth channel. When the drone is in normal use and collisions with obstacles are not a concern, the number of rotations of the adjusting disc 27 is controlled to adjust the compression of the second airbag 29. This forces the air in the second airbag 29 to just push the limiting rod 32 into the fourth cavity, preventing the blocking ball 34 from moving. However, when the drone is flying in areas with many obstacles and to prevent the wing 2 from breaking due to collision, the number of rotations of the adjusting disc 27 is increased. This allows the limiting rod 32 to extend into the fourth cavity at its maximum displacement, preventing the second airbag 29 from being moved by the adjusting disc 27. The compressed air will push the sealing ball 34 to compress the fourth elastic element, opening the fourth channel. This allows the compressed air in the second airbag 29 to be transferred to the third airbag 23 through the fifth channel, forcing the third airbag 23 to inflate. During the expansion of the third airbag 23, the protrusion 22 on the side wall of the adjusting block 24 moves, thereby causing the adjusting block 24 to retract from the fourth cavity into the second cavity. The vertical hole 25 on the adjusting block 24 connects the second channel and the third channel. Thus, when the wing 2 of the UAV collides violently with an obstacle during flight, the wing 2 is compressed by the collision, causing the air in the first airbag 17 to be squeezed into the third cavity. This pushes the first movable block 20 in the third cavity to retract. Under the action of the first movable rod 19, the first locking block 16 is pulled out of the mounting slot 15, forcing the wing 2 to detach from the fuselage 1, thereby preventing the wing 2 from colliding violently with the obstacle and achieving a certain degree of protection for the wing 2.

[0055] It also includes a first drive mechanism 3 detachably connected to the wing 2. The first drive mechanism 3 includes a first housing 36, a first motor 37, and a first propeller connected to the first motor 37. A connecting post 9 is provided on the side wall of the first housing 36, and a strip groove 10 is provided on the side wall of the connecting post 9. The end of the wing 2 is provided with a connecting groove and a fourth airbag 8. A first mounting blind hole is provided in the connecting groove. A fifth elastic element 6, a second locking block 11, and a limiting block 14 are provided in the first mounting blind hole. The fifth elastic element 6 is used to push the second locking block 11 into the strip groove 10. The outer diameter of the limiting block 14 is consistent with the inner diameter of the first mounting blind hole. The fourth airbag 8 communicates with the first mounting blind hole.

[0056] In this embodiment, the first drive mechanism 3 serves as the power source for the UAV. During operation, the first motor 37 drives the first propeller to rotate, thereby driving the UAV to fly. To facilitate the assembly and disassembly of the first drive mechanism 3 and the wing 2, a connecting post 9 is provided on the first housing 36 for mounting the first motor 37. During installation, the connecting post 9 is inserted into the connecting groove at the end of the wing 2, and the second locking block 11 is inserted into the strip groove 10 of the connecting post 9, thereby connecting the first housing 36 and the wing 2.

[0057] The first drive mechanism 3 will vibrate during operation, forcing the fourth airbag 8 to be squeezed, transferring the air inside the fourth airbag 8 to the first mounting blind hole, pushing the limiting block 14 in the first mounting blind hole to move towards the fifth elastic member 6, preventing the second locking block 11 from moving out of the strip groove 10 due to the vibration generated by the first drive mechanism 3 during the flight of the drone, thereby preventing the first drive mechanism 3 from falling off the wing 2.

[0058] The wing 2 is also provided with an eighth cavity, in which a second movable block 12 and a second movable rod 13 are provided. The outer diameter of the second movable block 12 is the same as the inner diameter of the eighth cavity. One end of the second movable rod 13 is connected to the second movable block 12, and the other end passes through the limiting block 14 and is connected to the second locking block 11. The wing 2 is provided with a connection port 38, which communicates with the eighth cavity. The assembly slot of the fuselage 1 is provided with a connecting pipe 39 that communicates with the first airbag 17. The outer diameter of the connecting pipe 39 is the same as the inner diameter of the connecting pipe 39.

[0059] In this embodiment, when the first drive mechanism 3 needs to be disassembled from the wing 2, when the connecting rod 4 is retracted to the center and before the connecting rod 4 moves to the adjusting block 24, the air squeezed by the connecting rod 4 during its retraction in the fourth cavity will sequentially enter the eighth cavity through the first airbag 17, the connecting pipe 39, and the connecting port 38, pushing the second movable block 12 in the eighth cavity to retract. Under the action of the second movable rod 13, the second locking block 11 is pulled out from the strip groove 10, thereby achieving the purpose of disassembling the wing 2 from the first drive mechanism 3.

[0060] The connecting rod 4 is also provided with a second driving mechanism 5. The second driving mechanism 5 includes a second housing 40, a second motor, and a second propeller 41. The second housing 40 is provided with a second mounting blind hole. The inner wall of the second mounting blind hole is provided with a third mounting blind hole. The third mounting blind hole is provided with a sixth elastic element 42 and a locking rod 43. The side wall of the connecting rod 4 is provided with a fixing hole. The sixth elastic element 42 is used to push the locking rod 43 into the fixing hole.

[0061] In this embodiment, in order to achieve a quick connection between the second drive mechanism 5 and the connecting rod 4, a second mounting blind hole is provided on the second housing 40. During installation, the end of the connecting rod 4 is inserted into the second mounting blind hole, and the sixth elastic member 42 is used to push the locking rod 43 into the fixing hole on the side wall of the connecting rod 4, thereby stably fixing the second housing 40 on the connecting rod 4.

[0062] The end of the connecting rod 4 is a conical structure, which facilitates the retraction of the locking rod 43 into the second blind mounting hole during installation.

[0063] The connecting rod 4 is also provided with a ninth cavity, which is connected to the fourth cavity through a through hole. The ninth cavity is provided with a seventh elastic element 30 and a sealing plate 31. The seventh elastic element 30 is used to push the sealing plate 31 to seal the through hole. A sixth channel 28 is provided between the ninth cavity and the fixing hole. The pull rope is connected to the sealing plate 31.

[0064] In this embodiment, in order to facilitate quick disassembly of the second drive mechanism 5 from the connecting rod 4, a seventh elastic element 30 and a sealing plate 31 are provided inside the connecting rod 4. When the drone is working, the sealing plate 31 can be pulled tightly to seal the through hole under the action of the pull rope. When disassembling, when the connecting rod 4 is retracted into the fourth cavity, the air in the fourth cavity squeezes the sealing plate 31, forcing the air to open the through hole. The air entering the through hole is transferred to the fixing hole through the sixth channel 28, pushing the locking rod 43 in the fixing hole back into the third mounting blind hole, forcing the connecting rod 4 to be quickly removed from the second mounting blind hole, thereby realizing the disassembly between the second drive mechanism 5 and the connecting rod 4.

[0065] The specific embodiments described above further illustrate the purpose, technical solution, and beneficial effects of the present invention. It should be understood that the above description is only a specific embodiment of the present invention and is not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A fixed-wing unmanned aerial vehicle (UAV) with rapidly detachable and detachable wings, comprising a fuselage (1) and wings (2), characterized in that, The wing (2) is provided with a mounting groove (15), and both sides of the fuselage (1) are provided with mounting grooves for mounting the wing (2). The mounting groove is provided with a first airbag (17). The fuselage (1) is provided with a first cavity, a second cavity and a third cavity. The first cavity is provided with a first elastic element (18) and a first locking block (16). The first elastic element (18) pushes the first locking block (16) into the mounting groove (15). The second cavity is provided with an adjustment block (24). The third cavity is provided with an unlocking element connected to the first locking block (16). The adjustment block (24) is used to adjust the fluid in the first airbag (17) to transfer to the first cavity or the third cavity. When the fluid is transferred to the first cavity, the fluid can prevent the first locking block (16) from retracting into the first cavity. When the fluid is transferred to the third cavity, the fluid can push the unlocking element to pull the first locking block (16) back into the first cavity.

2. A fixed-wing UAV with rapidly detachable and detachable wings according to claim 1, characterized in that, It also includes a connecting rod (4) connected to the tail fin. The fuselage (1) has a fourth cavity with an inner diameter that is the same as the outer diameter of the connecting rod (4). The connecting rod (4) can move in the fourth cavity. The second cavity also has a second elastic element (21). The second elastic element (21) is connected to the adjusting block (24). The second elastic element (21) is used to extend one end of the adjusting block (24) into the fourth cavity.

3. A fixed-wing UAV with rapidly detachable and detachable wings according to claim 2, characterized in that, The end of the adjusting block (24) located in the fourth cavity is a conical structure; a first channel is provided between the first cavity and the third cavity, a second channel is provided between the first airbag (17) and the third cavity, and a third channel is provided between the third cavity and the second cavity, and the third channel and the second channel are in the same direction; the adjusting block (24) is provided with a vertical hole (25) and an L-shaped connecting hole (26), the vertical hole (25) is used to connect the second channel and the third channel, and the connecting hole (26) is used to connect the second channel and the first channel.

4. A fixed-wing UAV with rapidly detachable and detachable wings according to claim 1, characterized in that, The unlocking component includes a first movable block (20) and a first movable rod (19). The outer diameter of the first movable block (20) is the same as the inner diameter of the third cavity. One end of the first movable rod (19) is connected to the first movable block (20), and the other end passes through the first cavity and is connected to the first locking block (16).

5. A fixed-wing UAV with rapidly detachable and detachable wings according to claim 2, characterized in that, The tail of the fuselage (1) is also provided with a connection blind hole. The connection blind hole is provided with a second airbag (29) and an adjustment plate (27). The second airbag (29) and the adjustment plate (27) are both sleeved on the connecting rod (4). The adjustment plate (27) is connected to the connection blind hole by a thread. The fuselage (1) is also provided with a fifth cavity that communicates with the second airbag (29). The fifth cavity is provided with a third elastic element and a limiting rod (32). The limiting rod (32) can extend into the fourth cavity. The fourth cavity is also provided with a pull rope (33). The pull rope (33) is connected to the connecting rod (4).

6. A fixed-wing UAV with rapidly detachable and detachable wings according to claim 5, characterized in that, The fuselage (1) is also provided with a sixth cavity and a seventh cavity. The sixth cavity is connected to the second airbag (29) through a fourth channel. The sixth cavity is provided with a fourth elastic element and a blocking ball (34). The elastic force of the fourth elastic element is greater than that of the third elastic element. The fourth elastic element is used to push the blocking ball (34) to block the fourth channel. The seventh cavity is connected to the second cavity. The seventh cavity is provided with a third airbag (23) and a protrusion (22) connected to the side wall of the adjusting block (24). The third airbag (23) is connected to the sixth cavity through a fifth channel (35).

7. A fixed-wing UAV with rapidly detachable and detachable wings according to claim 2, characterized in that, It also includes a first drive mechanism (3) that is detachably connected to the wing (2). The first drive mechanism (3) includes a first housing (36), a first motor (37), and a first propeller connected to the first motor (37). A connecting column (9) is provided on the side wall of the first housing (36), and a strip groove (10) is provided on the side wall of the connecting column (9). The end of the wing (2) is provided with a connecting groove and a fourth airbag (8). The connecting groove is provided with a first mounting blind hole. The first mounting blind hole is provided with a fifth elastic element (6), a second locking block (11) and a limiting block (14). The fifth elastic element (6) is used to push the second locking block (11) into the strip groove (10). The outer diameter of the limiting block (14) is consistent with the inner diameter of the first mounting blind hole. The fourth airbag (8) is connected to the first mounting blind hole.

8. A fixed-wing UAV with rapidly detachable and detachable wings according to claim 7, characterized in that, The wing (2) is also provided with an eighth cavity, and the eighth cavity is provided with a second movable block (12) and a second movable rod (13). The outer diameter of the second movable block (12) is the same as the inner diameter of the eighth cavity. One end of the second movable rod (13) is connected to the second movable block (12), and the other end passes through the limiting block (14) and is connected to the second locking block (11). The wing (2) is provided with a connection port (38) which is connected to the eighth cavity. The assembly slot of the fuselage (1) is provided with a connecting pipe (39) which is connected to the first airbag (17). The outer diameter of the connecting pipe (39) is the same as the inner diameter of the connection port (38).

9. A fixed-wing UAV with rapidly detachable and detachable wings according to claim 2, characterized in that, The connecting rod (4) is also provided with a second driving mechanism (5). The second driving mechanism (5) includes a second housing (40), a second motor and a second propeller (41). The second housing (40) is provided with a second mounting blind hole. The inner wall of the second mounting blind hole is provided with a third mounting blind hole. The third mounting blind hole is provided with a sixth elastic element (42) and a locking rod (43). The side wall of the connecting rod (4) is provided with a fixing hole. The sixth elastic element (42) is used to push the locking rod (43) into the fixing hole.

10. A fixed-wing UAV with rapidly detachable and detachable wings according to claim 9, characterized in that, The connecting rod (4) is also provided with a ninth cavity, which is connected to the fourth cavity through a through hole. The ninth cavity is provided with a seventh elastic element (30) and a sealing plate (31). The seventh elastic element (30) is used to push the sealing plate (31) to seal the through hole. A sixth channel (28) is provided between the ninth cavity and the fixing hole. The pull rope is connected to the sealing plate (31).

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