A drone with foldable wings that can improve the space utilization of the drone

Abstract

The present invention discloses a drone with foldable wings capable of improving the space utilization of the drone, which relates to the technical field of drones, and includes a fuselage, four mounting axle frames and mounting frames are symmetrically arranged on both sides of the fuselage, a support frame is arranged at the bottom of the fuselage, and a support mechanism is arranged inside the four mounting axle frames. When the wheelbase adjustment mechanism provided in the present invention is located directly below the folding mechanism, the special structural design can promote air flow, so that the fuselage responds to control instructions more quickly in the air, thereby improving the overall maneuverability and agility, and the synergistic effect of the folding mechanism and the wheelbase adjustment mechanism reduces the impact of wind on the drone, and the design of the wheelbase adjustment mechanism can effectively reduce resistance, consume less energy at the same speed, or achieve higher speed and efficiency at the same energy.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and in particular to an unmanned aerial vehicle with foldable wings capable of improving the space utilization rate of the unmanned aerial vehicle. Background Art

[0002] The drone with foldable wings is designed to facilitate transportation, storage and operation in small spaces. The foldable wing design allows the drone to reduce its footprint when not in use, making it easy to put into vehicles, warehouses or any means of transportation.

[0003] For example, publication number CN218477647U is named as a UAV, which mainly solves the problem that most existing agricultural fixed-wing UAVs are manned aircraft and cannot take off and land vertically. The wings cannot be folded during transportation, or the aircraft must be disassembled and transported to the destination before being assembled. This process will take a lot of time. Under the same load condition, a single-wing fixed-wing UAV requires a larger wingspan, and cannot be placed on an existing agricultural vehicle after the wings are folded, and the longer wingspan affects the stiffness of the wing.

[0004] However, the above-mentioned UAVs are difficult to fly stably in complex environments or bad weather, and the wheelbase is fixed or has a limited adjustment range, which makes it difficult for the UAV to fly stably in strong winds or when carrying heavy loads, and it is easy to lose control of the flight. There is a lack of mechanism adjustment capabilities to adapt to different flight conditions, and it is difficult to cope with changing weather conditions and flight mission requirements. In addition, the large size of the UAV limits its usage occasions and scope. Therefore, the present application provides a UAV with foldable wings that can improve the space utilization of the UAV to meet the needs. Summary of the invention

[0005] The purpose of this application is to provide a drone with foldable wings that can improve the space utilization of the drone, which can effectively solve the problems raised in the above-mentioned background technology.

[0006] To achieve the above-mentioned purpose, the present application provides the following technical solutions: A foldable wing drone capable of improving the space utilization of the drone, comprising a fuselage, four mounting shaft frames and mounting frames are symmetrically arranged on both sides of the fuselage, a support frame is arranged at the bottom of the fuselage, a support mechanism is arranged inside the four mounting shaft frames, and a folding mechanism for improving the agility of the fuselage is arranged on one side of the support mechanism, and a wheelbase adjustment mechanism for adjusting the wheelbase of blades to improve the stability of the fuselage is arranged at the bottom of the folding mechanism;

[0007] The folding mechanism comprises a trumpet shell, the inner wall of which is provided with a plurality of rotating blades distributed in a circular array for assisting the air intake of the wheelbase adjustment mechanism, and trumpet tubes in the shape of a trumpet mouth are provided inside the plurality of rotating blades.

[0008] Among them, the supporting mechanism includes a supporting shaft rotatably mounted inside a mounting shaft frame and a protective shell fixedly mounted on the mounting frame, a first bearing is arranged inside the protective shell, and the first bearing sleeve is arranged on the outer surface of the supporting shaft, a first mounting plate is arranged on the outer surface of the supporting shaft and located inside the protective shell, a telescopic rod is rotatably mounted on one side of the first mounting plate, a second mounting plate is arranged on the inner wall of the protective shell, and the telescopic rod is rotatably connected to the second mounting plate.

[0009] Among them, the outer surface of the horn shell is provided with an annular shell, the annular shell is fixedly connected to the support shaft, the outer surface of the annular shell is provided with a mounting shell, the outer surface of the annular shell and the inside of the mounting shell are provided with a stopper, the bottom of the stopper is provided with a clamping tube, the outer surface of the stopper is provided with a mounting ring, the inside of the mounting ring is provided with a driving motor, and the output end of the driving motor is provided with a first gear.

[0010] A groove is provided on one side of the lower end of the horn shell and the ring shell, and a ring rail is fixedly mounted on the inner wall of the horn shell and the outer surface of the ring shell, and the ring rail is located inside the groove.

[0011] The horn shell is in the shape of a horn mouth, and the ring track is in the shape of a circular ring. A semi-arc frame is arranged on the outer surface of the ring shell, and a retaining ring sheet is arranged on the bottom of the semi-arc frame.

[0012] Wherein, the wheelbase adjustment mechanism comprises a sleeve, a fixing block is arranged on one side of the outer surface of the sleeve, a connecting rod is arranged on the upper end of the fixing block, and a mounting tube for increasing the load-bearing capacity of the connecting rod is arranged at the bottom of the outer surface of the connecting rod, a second bearing is sleeved on the outer surface of the mounting tube, and the second bearing is clamped in the inside of the clamping tube;

[0013] One end of the connecting rod passes through the stopper and is fixedly mounted with a second gear, and the second gear is meshed with the first gear.

[0014] The inner wall of the sleeve is provided with a plurality of holes in a circular array, the outer surface of the sleeve is provided with a plurality of cone rings distributed at equal intervals, the bottom wall of the sleeve is provided with a bottom frame, a driving motor is provided inside the bottom frame, and an organic leaf is provided at the output end of the driving motor.

[0015] Wherein, a rail housing is arranged at the upper end of the sleeve, the rail housing is in a quarter arc shape, and the rail housing is slidably mounted on the outer surface of the ring rail.

[0016] In summary, the technical effects and advantages of the present invention are as follows:

[0017] 1. When the wheelbase adjustment mechanism provided in the present invention is located directly below the folding mechanism, the special structural design can promote air flow, so that the fuselage can respond to control commands more quickly in the air, thereby improving the overall maneuverability and agility, and the synergistic effect of the folding mechanism and the wheelbase adjustment mechanism reduces the impact of wind on the UAV. The design of the wheelbase adjustment mechanism can effectively reduce resistance, consume less energy at the same speed, or achieve higher speed and efficiency at the same energy. When the distance between the four wheelbase adjustment mechanisms increases, the stability of the UAV is enhanced. The longer wheelbase provides a larger moment arm, which maintains stability when the wind is strong or complex movements are performed. At the same time, it is also conducive to carrying heavier loads. The folding mechanism and the wheelbase adjustment mechanism not only improve the flight performance, but also allow the UAV to be folded into a more compact form when not in use, which is convenient for storage and transportation.

[0018] 2. The UAV of the present invention can dynamically adjust the angles of the folding mechanism and the wheelbase adjustment mechanism according to flight requirements. By adjusting the angles of the folding mechanism and the wheelbase adjustment mechanism, the aerodynamic layout of the UAV can be optimized, flight resistance can be reduced, and flight efficiency can be improved. When flying in a complex environment, the mechanism angle can be adjusted in real time to avoid collision risks and improve the safety of the UAV, especially in scenarios where it is necessary to cross narrow spaces or avoid obstacles.

[0019] 3. The trumpet shape of the trumpet shell and the trumpet tube provided in the present invention can effectively collect and guide the surrounding air into the wheelbase adjustment mechanism, thereby increasing the air intake volume and utilizing the principle of fluid dynamics, that is, when the air flows through a gradually shrinking cross-section, the flow velocity will increase, thereby generating suction and introducing more air into the trumpet shell and the trumpet tube; the spiral blade structure of the rotor can guide the air to enter the wheelbase adjustment mechanism in a vortex state, forming a stable airflow pattern, reducing turbulence and airflow separation, thereby improving the efficiency of the airflow and the working performance of the wheelbase adjustment mechanism, and under crosswind conditions, the trumpet tube and the rotor can guide and convert the lateral wind force into a direction that is conducive to flight, thereby reducing the negative impact of the side wind on the attitude of the UAV, and by converting the side wind into an airflow that is conducive to the wheelbase adjustment mechanism, the flight stability and controllability of the UAV under complex meteorological conditions can be improved.

[0020] 4. The deployment of the wheelbase adjustment mechanism in the present invention can increase the wheelbase between each adjustment mechanism, thereby improving the stability of the UAV. A wider wheelbase has a larger moment arm, which can maintain balance under the action of wind and can also withstand heavier loads. The presence of the retaining ring ensures that the wheelbase adjustment mechanism will not deflect excessively, preventing it from being unable to align correctly with the ring shell, thereby protecting the wheelbase adjustment mechanism from damage and ensuring the structural integrity of the UAV. The ring rail provides guidance and support for the rotation of the wheelbase adjustment mechanism, ensuring its smooth operation during deployment and folding, avoiding fuselage shaking caused by unstable rotation, and when flying in a complex environment, the wheelbase can be adjusted instantly to avoid collision risks, thereby improving the safety of the UAV, especially in scenarios where it is necessary to cross narrow spaces or avoid obstacles. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For those skilled in the art, other drawings can be obtained based on these drawings without paying any creative work.

[0022] Figure 1 A schematic diagram of the first-person perspective stereoscopic structure of a drone with foldable wings capable of improving the space utilization of the drone;

[0023] Figure 2 A schematic diagram of a second-perspective stereoscopic structure of a drone with foldable wings capable of improving the space utilization of the drone;

[0024] Figure 3 A schematic diagram of a partial three-dimensional connection structure of a UAV with foldable wings capable of improving the space utilization of the UAV;

[0025] Figure 4 It is a schematic diagram of the three-dimensional connection structure of the fuselage;

[0026] Figure 5 It is a schematic diagram of the three-dimensional connection structure of the support mechanism, the folding mechanism and the wheelbase adjustment mechanism;

[0027] Figure 6 It is a schematic diagram of the unfolded three-dimensional connection structure of the wheelbase adjustment mechanism and the folding mechanism;

[0028] Figure 7 It is a schematic diagram of the three-dimensional connection structure of the wheelbase adjustment mechanism and the folding mechanism;

[0029] Figure 8 It is a cross-sectional view of the three-dimensional connection structure of the support mechanism;

[0030] Fig. 9It is a schematic diagram of a three-dimensional connection structure of a folding mechanism from a first-person perspective;

[0031] Fig.10 A schematic diagram of a three-dimensional connection structure of the folding mechanism from a second viewing angle;

[0032] Fig.11 It is a schematic diagram of the three-dimensional connection structure of the folding mechanism from a third-person perspective;

[0033] Fig.12 It is a schematic diagram of the third-dimensional connection structure of the folding mechanism from the fourth perspective;

[0034] Fig.13 A schematic diagram of a three-dimensional connection structure of a wheelbase adjustment mechanism from a first-person perspective;

[0035] Fig.14 A schematic diagram of a three-dimensional connection structure of a wheelbase adjustment mechanism from a second viewing angle;

[0036] Fig.15 It is a cross-sectional view of the three-dimensional connection structure of the wheelbase adjustment mechanism.

[0037] In the figure: 1, fuselage; 2, supporting mechanism; 21, supporting shaft; 22, protective shell; 23, first bearing; 24, first mounting plate; 25, telescopic rod; 26, second mounting plate; 3, folding mechanism; 31, horn shell; 32, rotating blade; 33, horn tube; 34, mounting shell; 35, ring track; 36, ring shell; 37, semi-arc frame; 38, retaining ring; 39, groove; 311, stopper; 312, clamping tube; 313, mounting ring; 314, driving motor; 315, first gear; 4, wheelbase adjustment mechanism; 41, fixing block; 42, mounting tube; 43, second bearing; 44, connecting rod; 45, second gear; 46, sleeve; 47, cone ring; 48, hollow hole; 49, clamping rail shell; 411, machine blade; 412, bottom frame; 413, driving motor; 5, supporting frame; 6, mounting frame; 7, mounting shaft frame. DETAILED DESCRIPTION

[0038] 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.

[0039] Example 1, Reference Figures 1 to 15A foldable wing drone capable of improving the space utilization of the drone is shown, comprising a fuselage 1, four mounting shaft frames 7 and mounting frames 6 are symmetrically arranged on both sides of the fuselage 1, a support frame 5 is arranged at the bottom of the fuselage 1, a support mechanism 2 is arranged inside the four mounting shaft frames 7, and a folding mechanism 3 for improving the agility of the fuselage 1 is arranged on one side of the support mechanism 2, and a wheelbase adjustment mechanism 4 for adjusting the wheelbase of blades to improve the stability of the fuselage 1 is arranged at the bottom of the folding mechanism 3;

[0040] It is worth noting that when in use, the shaft frame 7 is rotated inside to drive the folding mechanism 3 to deflect, and the folding mechanism 3 drives the wheelbase adjustment mechanism 4 to deflect. The steering and angle adjustment of the fuselage 1 can be controlled by controlling the deflection angles of the folding mechanism 3 and the wheelbase adjustment mechanism 4 through the support mechanism 2. When the wheelbase adjustment mechanism 4 is located directly below the folding mechanism 3, the special structural design inside the folding mechanism 3 can accelerate the air circulation into the wheelbase adjustment mechanism 4. The design of the folding mechanism 3 can improve the agility of the entire fuselage 1.

[0041] When the wheelbase adjustment mechanism 4 and the bottom of the folding mechanism 3 rotate, the wheelbase between the four wheelbase adjustment mechanisms 4 increases, and the overall structural design of the wheelbase adjustment mechanism 4 can reduce the impact of wind, so that the wheelbase of the wheelbase adjustment mechanism 4 can be adjusted according to the flight requirements of the fuselage 1. When the distance between the four wheelbase adjustment mechanisms 4 increases, the flight stability of the fuselage 1 can be increased.

[0042] Among them, when the wheelbase adjustment mechanism 4 is located directly below the folding mechanism 3, the special structural design can promote air flow, so that the fuselage can respond to control commands more quickly in the air, thereby improving the overall maneuverability and agility. Moreover, the synergistic effect of the folding mechanism 3 and the wheelbase adjustment mechanism 4 reduces the impact of wind on the UAV. The design of the wheelbase adjustment mechanism 4 can effectively reduce resistance, consume less energy at the same speed, or achieve higher speed and efficiency at the same energy.

[0043] When the distance between the four wheelbase adjustment mechanisms 4 increases, the stability of the drone is enhanced, and the longer wheelbase provides a larger moment arm, which keeps the drone stable when the wind is strong or when performing complex maneuvers. At the same time, it is also conducive to carrying heavier loads. The folding mechanism 3 and the wheelbase adjustment mechanism 4 not only improve the flight performance, but also enable the drone to be folded into a more compact form when not in use, which is convenient for storage and transportation.

[0044] The supporting mechanism 2 includes a supporting shaft 21 rotatably mounted inside the mounting shaft frame 7 and a protective shell 22 fixedly mounted on the mounting frame 6, a first bearing 23 is arranged inside the protective shell 22, and the first bearing 23 is sleeved on the outer surface of the supporting shaft 21, a first mounting plate 24 is arranged on the outer surface of the supporting shaft 21 and located inside the protective shell 22, a telescopic rod 25 is rotatably mounted on one side of the first mounting plate 24, a second mounting plate 26 is arranged on the inner wall of the protective shell 22, and the telescopic rod 25 is rotatably connected to the second mounting plate 26.

[0045] It is worth mentioning that when the angle of the folding mechanism 3 and the wheelbase adjustment mechanism 4 needs to be adjusted, the telescopic rod 25 is extended and retracted to drive the first mounting plate 24 to move, and the first mounting plate 24 drives the support shaft 21 to rotate inside the mounting shaft frame 7, and the first bearing 23 is installed inside the protective shell 22 to support the rotation of the support shaft 21, and the protective shell 22 is covered on the outside of the telescopic rod 25 to prevent obstacles from jamming the support shaft 21, thereby hindering the rotation of the support shaft 21. The angle of the folding mechanism 3 and the wheelbase adjustment mechanism 4 can be changed through the support shaft 21 according to the flight requirements of the fuselage 1.

[0046] Among them, the angles of the folding mechanism 3 and the wheelbase adjustment mechanism 4 can be dynamically adjusted according to flight requirements. By adjusting the angles of the folding mechanism 3 and the wheelbase adjustment mechanism 4, the aerodynamic layout of the UAV can be optimized, flight resistance can be reduced, and flight efficiency can be improved. When flying in a complex environment, the mechanism angle can be adjusted in real time to avoid collision risks and improve the safety of the UAV, especially in scenarios where it is necessary to cross narrow spaces or avoid obstacles.

[0047] Example 2, Reference Figures 9 to 12 The folding mechanism 3 shown includes a trumpet shell 31 , the inner wall of which is provided with a plurality of rotary vanes 32 distributed in a ring array for assisting the wheelbase adjustment mechanism 4 in air intake, and a trumpet tube 33 in the shape of a trumpet mouth is provided inside the plurality of rotary vanes 32 .

[0048] It is worth mentioning that when the wheelbase adjustment mechanism 4 is started, the air first enters the wheelbase adjustment mechanism 4 through the guidance of the horn shell 31 and the horn tube 33, and the horn shell 31 and the horn tube 33 are both in the shape of a trumpet mouth, which can quickly absorb the air around the horn shell 31 into the wheelbase adjustment mechanism 4, and a rotor 32 is arranged inside the horn shell 31, and the rotor 32 is a spiral blade structure. The rotor 32 guides the air to be sent into the wheelbase adjustment mechanism 4 in a vortex state, thereby increasing the air intake of the wheelbase adjustment mechanism 4. When encountering a large side wind, the horn tube 33 and the rotor 32 can guide the side wind to blow into the horn shell 31, thereby reducing the influence of wind on the flight of the fuselage 1.

[0049] The bell-mouth shape of the horn housing 31 and the horn tube 33 can effectively collect and guide the surrounding air into the wheelbase adjustment mechanism 4, thereby increasing the air intake amount and utilizing the principle of fluid dynamics, that is, when the air flows through a gradually decreasing cross-section, the flow velocity will increase, thereby generating suction and introducing more air into the horn housing 31 and the horn tube 33;

[0050] The spiral blade structure of the rotary blade 32 can guide the air to enter the wheelbase adjustment mechanism 4 in a vortex state, forming a stable airflow pattern, reducing turbulence and airflow separation, thereby improving the efficiency of the airflow and the working performance of the wheelbase adjustment mechanism 4;

[0051] Moreover, under crosswind conditions, the trumpet 33 and the rotor blades 32 can guide and convert the side wind force into a direction that is beneficial to flight, reducing the negative impact of the side wind on the UAV's posture. By converting the side wind into an airflow that is beneficial to the wheelbase adjustment mechanism 4, the flight stability and controllability of the UAV under complex weather conditions can be improved.

[0052] The design of the horn housing 31 and the rotor blades 32 optimizes the airflow path to reduce air resistance during flight, thereby reducing energy consumption required for flight, extending the endurance of the drone and improving efficiency.

[0053] The outer surface of the speaker shell 31 is sleeved with an annular shell 36, and the annular shell 36 is fixedly connected to the support shaft 21. The outer surface of the annular shell 36 is provided with a mounting shell 34. A stopper 311 is provided on the outer surface of the annular shell 36 and located inside the mounting shell 34. A clamping tube 312 is provided at the bottom of the stopper 311. A mounting ring 313 is provided on the outer surface of the stopper 311. A driving motor 314 is provided inside the mounting ring 313. A first gear 315 is provided at the output end of the driving motor 314.

[0054] When encountering bad weather or heavy materials need to be transported, the drive motor 314 inside the mounting shell 34 drives the wheelbase adjustment mechanism 4 to rotate through the first gear 315, and the wheelbase adjustment mechanism 4 rotates slowly out from the bottom of the ring shell 36, and the state of the wheelbase adjustment mechanism 4 rotating out from the bottom of the ring shell 36 is Figure 6 As shown, when the wheelbase adjustment mechanism 4 is fully unfolded, the wheelbase between each wheelbase adjustment mechanism 4 will increase, thereby improving the flight stability of the fuselage 1, and the retaining ring 38 arranged at the bottom of the semi-arc frame 37 plays a limiting role. When the wheelbase adjustment mechanism 4 is rotated and stored to the bottom of the ring shell 36 and coincides with the central axis of the ring shell 36, the set retaining ring 38 can play a protective limiting role to prevent the wheelbase adjustment mechanism 4 from deflecting too much and failing to coincide with the ring shell 36.

[0055] A groove 39 is provided on one side of the lower end of the horn shell 31 and the ring shell 36. A ring rail 35 is fixedly installed on the inner wall of the horn shell 31 and the outer surface of the ring shell 36. The ring rail 35 is located inside the groove 39 and is fixedly installed on the inner wall of the groove 39, making the installation of the ring rail 35 more secure.

[0056] The horn housing 31 is in a horn shape, and the ring track 35 is in a circular ring shape. A semi-arc frame 37 is provided on the outer surface of the ring housing 36 , and a retaining ring sheet 38 is provided at the bottom of the semi-arc frame 37 .

[0057] It is worth mentioning that when the wheelbase adjustment mechanism 4 rotates, the annular rail 35 provided can assist the rotation of the wheelbase adjustment mechanism 4. The annular rail 35 can provide a support track for the rotation of the wheelbase adjustment mechanism 4, so that the wheelbase adjustment mechanism 4 can operate more stably when rotating, and can prevent the wheelbase adjustment mechanism 4 from rotating during operation, causing the fuselage 1 to shake during flight.

[0058] When encountering bad weather or heavy objects need to be transported, the deployment of the wheelbase adjustment mechanism 4 can increase the wheelbase between the wheelbase adjustment mechanisms 4, thereby improving the stability of the drone. A wider wheelbase has a larger moment arm, which can maintain balance under the action of wind and can also withstand heavier loads.

[0059] The presence of the retaining ring 38 ensures that the wheelbase adjustment mechanism 4 will not be excessively deflected, preventing it from being unable to align correctly with the ring shell 36, thereby protecting the wheelbase adjustment mechanism 4 from damage and also ensuring the structural integrity of the UAV; the ring rail 35 provides guidance and support for the rotation of the wheelbase adjustment mechanism 4, ensuring its smooth operation during the deployment and folding process, and avoiding the shaking of the fuselage caused by unstable rotation.

[0060] Example 3, Reference Figures 13 to 15 The wheelbase adjustment mechanism 4 shown includes a sleeve 46, a fixing block 41 is provided on one side of the outer surface of the sleeve 46, a connecting rod 44 is provided on the upper end of the fixing block 41, and a mounting tube 42 for increasing the load-bearing capacity of the connecting rod 44 is provided on the bottom of the outer surface of the connecting rod 44, a second bearing 43 is sleeved on the outer surface of the mounting tube 42, and the second bearing 43 is clamped in the inside of the clamping tube 312;

[0061] One end of the connecting rod 44 passes through the stopper 311 and is fixedly mounted with a second gear 45 , which is meshed with the first gear 315 .

[0062] It is worth noting that when the driving motor 314 drives the first gear 315 to rotate through the output shaft, the first gear 315 drives the second gear 45 to rotate, and the second gear 45 drives the connecting rod 44 to rotate, and the connecting rod 44 drives the mounting tube 42 to rotate, and the second bearing 43 is clamped inside the clamping tube 312. When the mounting tube 42 rotates, the second bearing 43 can further support the connecting rod 44 to prevent the connecting rod 44 from being deformed when the fuselage 1 transports heavier materials;

[0063] The inner wall of the sleeve 46 is provided with a plurality of holes 48 in a circular array, the outer surface of the sleeve 46 is provided with a plurality of cone rings 47 distributed at equal intervals, the bottom wall of the sleeve 46 is provided with a bottom frame 412, a driving motor 413 is provided inside the bottom frame 412, and an organic leaf 411 is provided at the output end of the driving motor 413.

[0064] A rail housing 49 is disposed at the upper end of the sleeve 46 . The rail housing 49 is in a quarter arc shape and is slidably mounted on the outer surface of the ring rail 35 .

[0065] When the fixing block 41 rotates, the sleeve 46 is driven to rotate. When the sleeve 46 rotates, the rail housing 49 is driven to rotate on the outer surface of the ring rail 35. The rail housing 49 can play a supporting role. The rail housing 49 is arranged with the connecting rod 44 as the axis to assist the rotation of the sleeve 46. It can ensure that the sleeve 46 can be smoothly unfolded during the rotation process, and the sleeve 46 and the ring housing 36 have the same diameter and can fit together.

[0066] When the driving motor 413 drives the blade 411 to rotate, the blade 411 rotates to extract the air inside the folding mechanism 3 and discharges it through the bottom of the sleeve 46. When encountering a strong side wind, the blade 411 rotates to guide the air through the holes 48 into the sleeve 46 through the cone ring 47. The high-speed rotation of the blade 411 can extract the air between each cone ring 47 through the holes 48, thereby reducing the impact of the side wind on the flight of the fuselage 1.

[0067] When the blades 411 rotate, the influence of wind on the flight of the fuselage 1 can be reduced through the structural design of the cone ring 47 and the sleeve 46. Therefore, when the wheelbase between the four blades 411 increases, the fuselage 1 can have greater stability during flight, and the entire wheelbase adjustment mechanism 4 can be unfolded during flight to adjust the wheelbase to adapt to different weather environments. When the drone is not in use, the wheelbase adjustment mechanism 4 can be stored in the lower part of the folding mechanism 3 to save storage space.

[0068] Among them, the combined design of the blades 411 and the cone ring 47 can effectively adjust and utilize the airflow. Under crosswind conditions, air can be drawn in through the high-speed rotation of the blades 411 and discharged through the hollow holes 48, thereby reducing the impact of the side wind on the UAV and maintaining flight stability.

[0069] The adjustability of the wheelbase adjustment mechanism 4 enables the UAV to adjust its wheelbase according to different flight conditions such as weather and load, which not only improves the flight stability, but also enhances the versatility and adaptability of the UAV. Moreover, when flying in a complex environment, the wheelbase can be adjusted instantly to avoid collision risks, thereby improving the safety of the UAV, especially in scenarios where it is necessary to cross narrow spaces or avoid obstacles.

[0070] 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, 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 drone with foldable wings capable of improving the space utilization of the drone, comprising a fuselage (1), characterized in that: Four mounting shaft frames (7) and mounting frames (6) are symmetrically arranged on both sides of the fuselage (1); a support frame (5) is arranged at the bottom of the fuselage (1); a support mechanism (2) is arranged inside each of the four mounting shaft frames (7); a folding mechanism (3) for improving the agility of the fuselage (1) is arranged on one side of the support mechanism (2); and a wheelbase adjustment mechanism (4) for adjusting the wheelbase of blades to improve the stability of the fuselage (1) is arranged at the bottom of the folding mechanism (3); The folding mechanism (3) comprises a trumpet shell (31), the inner wall of the trumpet shell (31) being provided with a plurality of rotating blades (32) distributed in a ring array for assisting the wheelbase adjustment mechanism (4) in air intake, and trumpet tubes (33) in the shape of a trumpet mouth being provided inside the plurality of rotating blades (32); The support mechanism (2) comprises a support shaft (21) rotatably mounted inside a mounting shaft frame (7) and a protective shell (22) fixedly mounted on the mounting frame (6); a first bearing (23) is arranged inside the protective shell (22), and the first bearing (23) is sleeved on the outer surface of the support shaft (21); a first mounting plate (24) is arranged on the outer surface of the support shaft (21) and inside the protective shell (22); a telescopic rod (25) is rotatably mounted on one side of the first mounting plate (24); a second mounting plate (26) is arranged on the inner wall of the protective shell (22), and the telescopic rod (25) is rotatably connected to the second mounting plate (26); The outer surface of the speaker housing (31) is sleeved with an annular housing (36), the annular housing (36) is fixedly connected to the support shaft (21), the outer surface of the annular housing (36) is provided with a mounting housing (34), a stopper (311) is provided on the outer surface of the annular housing (36) and inside the mounting housing (34), a clamping tube (312) is provided at the bottom of the stopper (311), a mounting ring (313) is provided on the outer surface of the stopper (311), a driving motor (314) is provided inside the mounting ring (313), and a first gear (315) is provided at the output end of the driving motor (314); The wheelbase adjustment mechanism (4) comprises a sleeve (46), a fixing block (41) is provided on one side of an outer surface of the sleeve (46), a connecting rod (44) is provided at the upper end of the fixing block (41), and a mounting tube (42) for increasing the load-bearing capacity of the connecting rod (44) is provided at the bottom of the outer surface of the connecting rod (44), a second bearing (43) is sleeved on the outer surface of the mounting tube (42), and the second bearing (43) is clamped inside the clamping tube (312); One end of the connecting rod (44) passes through the stopper (311) and is fixedly mounted with a second gear (45), and the second gear (45) is meshed with the first gear (315).

2. The UAV with foldable wings capable of improving the space utilization of the UAV according to claim 1, characterized in that: A groove (39) is provided on one side of the lower end of the horn housing (31) and the ring housing (36); a ring rail (35) is fixedly mounted on the inner wall of the horn housing (31) and the outer surface of the ring housing (36); and the ring rail (35) is located inside the groove (39).

3. The UAV with foldable wings capable of improving the space utilization of the UAV according to claim 2, characterized in that: The horn housing (31) is in the shape of a horn mouth, and the ring track (35) is in the shape of a circular ring. The outer surface of the ring housing (36) is provided with a semi-arc frame (37), and the bottom of the semi-arc frame (37) is provided with a retaining ring sheet (38).

4. The UAV with foldable wings capable of improving the space utilization of the UAV according to claim 1, characterized in that: The inner wall of the sleeve (46) is provided with a plurality of hollow holes (48) in a ring array, the outer surface of the sleeve (46) is provided with a plurality of cone rings (47) distributed at equal intervals, the bottom wall of the sleeve (46) is provided with a bottom frame (412), a driving motor (413) is provided inside the bottom frame (412), and an organic leaf (411) is provided at the output end of the driving motor (413).

5. The UAV with foldable wings capable of improving the space utilization of the UAV according to claim 4, characterized in that: A rail housing (49) is provided at the upper end of the sleeve (46); the rail housing (49) is in a quarter arc shape, and the rail housing (49) is slidably mounted on the outer surface of the ring rail (35).

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