Unmanned aerial vehicle carrier loader with self-adaptive flight attitude control function

Abstract

The invention discloses a self-adaptive flight attitude control unmanned aerial vehicle carrier loader, and relates to the technical field of unmanned aerial vehicle carrier lors.The self-adaptive flight attitude control unmanned aerial vehicle carrier loader comprises a carrier loader, device containing bins and a sealing cover plate body, the device containing bins are formed in the carrier loader at equal intervals, and the sealing cover plate body is transversely arranged on the carrier loader in a sliding mode; the unmanned aerial vehicle further comprises a stable driving assembly, an air flow safety monitoring assembly and a self-adaptive flight attitude adjusting assembly. Through the design of the self-adaptive flight attitude adjusting assembly, the direction of the unmanned aerial vehicle during take-off can be adjusted according to detection of the air flow safety monitoring assembly; the operation mode that the unmanned aerial vehicle can only take off on a fixed plane in the take-off process in the prior art is avoided, the self-adaptive design with the adjustable angle can make full use of the surrounding wind current condition to achieve rapid take-off, and the unmanned aerial vehicle can take off in a flat area and a complex terrain area in a mode different from an existing take-off mode with the fixed angle; and in emergency situations such as rescue, the application range and the flight efficiency of the unmanned aerial vehicle are greatly improved.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicle carriers, and in particular to an unmanned aerial vehicle carrier with adaptive flight attitude control. Background Art

[0002] Drone carriers play an important role in a variety of situations; whether it is long-distance cross-regional operations, especially in remote areas with inconvenient transportation, or operations in complex terrain such as mountains, swamps and wetlands, it can ensure the safe and stable transportation of drones; under large-scale operation requirements, multiple drones and a large amount of equipment can be transported at one time, improving operation efficiency and continuity; in emergency response, such as disaster relief and emergency handling, drones can be quickly delivered to the scene.

[0003] Nowadays, drones are widely used, and drone carriers have become important auxiliary equipment; however, existing drone carriers have obvious shortcomings; they can only realize simple carrying functions, and there are still deficiencies in adjusting the angle of the drone when taking off, which makes the drone can only be operated on a fixed plane when taking off, and it is impossible to change the angle according to the surrounding wind flow conditions to achieve rapid take-off; in actual flight environments, wind flow has a significant impact on drone take-off, tailwind can provide thrust, and appropriate tilt angles can use the lift of the wind to improve take-off efficiency, but existing carriers cannot meet these requirements; especially in complex terrains such as mountainous areas and hills, the wind flow changes greatly, and the risk of fixed-angle take-off is high; in emergency situations such as rescue, rapid take-off is crucial, and existing carriers cannot provide effective solutions, which greatly limits the application scope and efficiency of drones;

[0004] Furthermore, in actual flight, changes in wind speed and direction are crucial to the takeoff and flight of drones. However, in the existing technology, the drone only relies on observation by the operator, and the drone cannot adjust its takeoff strategy according to the actual situation. It is easy to face problems such as insufficient power against the headwind or loss of speed control with the wind. It is also difficult to adjust the route according to the real-time wind direction during flight, which increases the flight risk. Especially in special scenarios such as emergency rescue and complex terrain surveys, there are high requirements for the drone to respond quickly and fly safely.

[0005] Therefore, we proposed a UAV carrier vehicle with adaptive flight attitude control to solve the above problems. Summary of the invention

[0006] In view of this, the technical problem to be solved by the present invention is to propose a UAV carrier vehicle with adaptive flight attitude control to solve the problems existing in the prior art.

[0007] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: an adaptive flight attitude control UAV carrier, comprising: a carrier, a device placement bin, and a cover plate, wherein the device placement bin is equidistantly arranged on the carrier, and the cover plate is laterally slidably arranged on the carrier, and further comprising: a stable drive component, a wind flow safety monitoring component, and an adaptive flight attitude adjustment component, wherein the wind flow safety monitoring component and the adaptive flight attitude adjustment component are in the same horizontal plane, and the stable drive component is located below the wind flow safety monitoring component and the adaptive flight attitude adjustment component;

[0008] The wind flow safety monitoring component is mainly used to detect the wind flow direction and wind flow intensity;

[0009] The adaptive flight attitude adjustment component is mainly used to adjust the angle of the drone when starting flight.

[0010] Preferably, the stable drive assembly includes a square cavity located in the device placement bin, a transmission member is arranged in the square cavity, a support plate is hinged on the transmission member, a spring body A is fixedly connected to the bottom surface of the support plate, and one end of the spring body A away from the support plate is fixedly connected to the bottom surface of the square cavity.

[0011] Preferably, the wind flow safety monitoring component includes a connecting piece, the outer end of the connecting piece is fixedly connected to a spherical cavity, and the inner arc surface of the spherical cavity is fixedly connected to a Hall switch cluster.

[0012] Preferably, a sphere is rotatably connected in the spherical cavity, a magnet is fixedly connected to the top of the sphere, a columnar cavity is fixedly connected to the sphere, a sliding plate is slidably connected in the columnar cavity, a spring body B is fixedly connected to the top surface of the sliding plate, and the top of the spring body B is fixedly connected to the spherical cavity.

[0013] Preferably, a wind belt is fixedly connected to the bottom surface of the column cavity, a pull rope is fixedly connected to the bottom surface of the sliding sheet, and a wind cone is fixedly connected to one end of the pull rope away from the sliding sheet.

[0014] Preferably, the adaptive flight attitude adjustment component includes an electric telescopic rod fixedly connected to a supporting plate, an annular ring is fixedly connected to the upper end of the electric telescopic rod, and an inner slide groove is provided on the annular ring.

[0015] Preferably, a motor is fixedly connected to the middle of the support plate, a sleeve is fixedly connected to the top of the motor, a column is laterally slidably connected in the sleeve, an N-shaped component is fixedly connected to the column, and a carrier plate is fixedly connected to the N-shaped component.

[0016] Preferably, one end of the column is fixedly connected to an arc rod, and one end of the arc rod away from the column is fixedly connected to a sliding ball.

[0017] Preferably, the support plate is slidably matched with the square cavity, and can cooperate with the spring body A to provide buffer protection for the drone during transportation.

[0018] Preferably, the Hall switch cluster consists of eight Hall switches, which are equidistantly distributed on the inner arc surface of the spherical cavity and are located at eight positions: east, west, south, north, northeast, southeast, northwest, and southwest.

[0019] Compared with the prior art, the present invention provides a UAV carrier vehicle with adaptive flight attitude control, which has the following beneficial effects:

[0020] 1. The present application can effectively monitor the wind direction and wind speed through the design of the wind flow safety monitoring component, so as to provide assistance for the UAV that is about to fly. The addition of this detection in the actual flight environment can accurately feedback the wind direction through the drifting direction of the wind belt, and detect the wind speed intensity at this time through the effect of the wind force on the wind cone. This design can adjust the take-off strategy according to the actual situation during take-off, avoiding the problems of insufficient power caused by taking off against the wind and speed loss when taking off with the wind, thereby reducing the flight risk and improving the safety of UAV use.

[0021] 2. The present application adopts the design of an adaptive flight attitude adjustment component, which can adjust the direction and tilt angle of the UAV during takeoff, that is, azimuth adjustment, according to the detection of the wind flow safety monitoring component, thereby avoiding the operation mode in the prior art that the UAV can only take off on a fixed plane during takeoff. This design that can adaptively adjust the angle according to the wind flow can make full use of the surrounding wind flow conditions to achieve rapid takeoff, and can achieve the effect of wind flow assisting takeoff instead of hindering takeoff. It can be distinguished from the existing fixed-angle takeoff method in plain areas and complex terrain areas, improves the performance of the UAV, and greatly improves the application range and flight efficiency of the UAV in emergency situations such as rescue.

[0022] 3. The present application adopts the design of the square cavity and the supporting plate. When the carrier vehicle carries the UAV to the designated location, the supporting plate will slide in the square cavity because the transmission parts are in a retracted and unextended state. At this time, the square cavity contains gas filled by an external air pump through an air valve. At the same time, with the assistance of the spring body A, the UAV being carried can obtain a good shock-absorbing effect under the elastic action of the gas and the spring even when the carrier vehicle is traveling in a rugged mountainous area. This can effectively avoid the occurrence of cracks, deformation or breakage of the outer shell, loosening of internal connecting parts, deformation of the bracket, loosening of welding points of electronic components, disconnection of lines or damage of components, and other situations that are not conducive to flight. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 This is the appearance diagram of the main structure of the present invention;

[0024] Figure 2 This is a main structural diagram of the carrier vehicle of the present invention after being cut away;

[0025] Figure 3 This is a distribution diagram of the related structural positions of the stable driving component, the wind flow safety monitoring component, and the adaptive flight attitude adjustment component in the present invention;

[0026] Figure 4 For the present invention Figure 3 A magnified view of the local structure at center A;

[0027] Figure 5 It is a side view of the structure of the present invention;

[0028] Figure 6 For the present invention Figure 5 A magnified view of the local structure at B in the middle;

[0029] Figure 7 This is a structural diagram of the wind flow safety monitoring component of the present invention;

[0030] Figure 8 Another perspective view of the wind flow safety monitoring component related structure of the present invention;

[0031] Fig. 9 For the present invention Figure 8 A magnified view of the local structure at C in the middle;

[0032] Fig.10 For the present invention Figure 8 Enlarged view of the local structure at point D in the middle.

[0033] In the figure:

[0034] 1. Carrier; 2. Device placement compartment; 3. Covering plate;

[0035] 4. Stable driving assembly; 401. Square cavity; 402. Transmission member; 403. Support plate; 404. Spring body A;

[0036] 5. Wind flow safety monitoring component; 501. Connecting piece; 502. Spherical cavity; 503. Hall switch cluster; 504. sphere; 505. magnet; 506. Column cavity; 507. Sliding piece; 508. Spring body B; 509. Wind flow belt; 510. Pull rope; 511. Wind cone;

[0037] 6. Adaptive flight attitude adjustment component; 601. Electric telescopic rod; 602. Annular ring; 603. Inner slide groove; 604. Motor; 605. Set piece; 606. Column rod; 607. N-shaped piece; 608. Carrier board; 609. Arc rod; 610. Sliding ball. 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] The present invention is further described in detail below based on the accompanying drawings and embodiments.

[0040] Example

[0041] Please refer to Figure 1 , Figure 2 , Figures 5 to 10 As shown:

[0042] In order to solve the problems mentioned in the technical solution, the embodiment of the present application provides a UAV carrier vehicle with adaptive flight attitude control, including: a carrier vehicle 1, a device placement compartment 2, and a cover plate 3, wherein the device placement compartment 2 is equidistantly arranged on the carrier vehicle 1, and the cover plate 3 is laterally slidably arranged on the carrier vehicle 1, and further includes: a stable driving component 4, a wind flow safety monitoring component 5, and an adaptive flight attitude adjustment component 6, wherein the wind flow safety monitoring component 5 and the adaptive flight attitude adjustment component 6 are in the same horizontal plane, and the stable driving component 4 is located below the wind flow safety monitoring component 5 and the adaptive flight attitude adjustment component 6; the wind flow safety monitoring component 5 is mainly used to detect the wind flow direction and wind flow intensity;

[0043] The stable driving component 4 includes a square cavity 401 located in the device placement bin 2, a transmission member 402 is arranged in the square cavity 401, a support plate 403 is hinged on the transmission member 402, a spring body A404 is fixedly connected to the bottom surface of the support plate 403, and one end of the spring body A404 away from the support plate 403 is fixedly connected to the bottom surface of the square cavity 401, and the wind flow safety monitoring component 5 includes a connecting piece 501, the outer end of the connecting piece 501 is fixedly connected to the spherical cavity 502, and the inner arc surface of the spherical cavity 502 is fixedly connected to the Hall switch cluster 503. A sphere 504 is rotatably connected inside the spherical cavity 502, a magnet 505 is fixedly connected to the top of the sphere 504, a columnar cavity 506 is fixedly connected to the sphere 504, a sliding sheet 507 is slidably connected in the columnar cavity 506, a spring body B508 is fixedly connected to the top surface of the sliding sheet 507, the top of the spring body B508 is fixedly connected to the spherical cavity 502, a wind belt 509 is fixedly connected to the bottom surface of the columnar cavity 506, a pull rope 510 is fixedly connected to the bottom surface of the sliding sheet 507, and a wind cone 511 is fixedly connected to the end of the pull rope 510 away from the sliding sheet 507.

[0044] in:

[0045] The cover plate 3 is mainly used to seal the device placement compartment 2 opened on the carrier 1 .

[0046] The square cavity 401 is provided with a gas valve for injecting gas therein.

[0047] The supporting plate 403 is slidably matched with the square cavity 401 and can cooperate with the spring body A404 to provide buffer protection for the drone during transportation.

[0048] The wind flow safety monitoring component 5 is mainly used to detect the wind flow direction and wind flow intensity. The spherical cavity 502 and the sphere 504 are adapted to each other.

[0049] The Hall switch cluster 503 consists of eight Hall switches, which are equidistantly distributed on the inner arc surface of the spherical cavity 502 and are located at eight positions of east, west, south, north, northeast, southeast, northwest, and southwest.

[0050] The magnet 505 is mainly used in conjunction with the Hall switch cluster 503. When the magnet 505 interacts with the Hall switches in different orientations, the Hall switches will control the adaptive flight attitude adjustment component 6 to adjust the corresponding attitude through the device master controller.

[0051] When the wind speed is not suitable for the UAV to fly, the wind will pass through the wind cone 511 on the wind belt 509 and pull the sliding sheet 507 to slide in the column cavity 506 through the pull rope 510, and the spring body B508 will be stretched at this time.

[0052] The wind belt 509 is made of corrosion-resistant and wear-resistant cloth, and the wind cone 511 is made of light plastic material.

[0053] For further examples, please refer to Figures 2 to 5 As shown:

[0054] The adaptive flight attitude adjustment component 6 is mainly used to adjust the angle of the drone when starting to fly. The adaptive flight attitude adjustment component 6 includes an electric telescopic rod 601 fixedly connected to the supporting plate 403, and the upper end of the electric telescopic rod 601 is fixedly connected to an annular ring 602, and an inner slide groove 603 is provided on the annular ring 602. A motor 604 is fixedly connected to the middle of the supporting plate 403, and a sleeve 605 is fixedly connected to the top of the motor 604. A column 606 is horizontally slidably connected in the sleeve 605, and an N-shaped part 607 is fixedly connected to the column 606. A carrier plate 608 is fixedly connected to the N-shaped part 607, and one end of the column 606 is fixedly connected to an arc rod 609, and the end of the arc rod 609 away from the column 606 is fixedly connected to a sliding ball 610.

[0055] in:

[0056] The adaptive flight attitude adjustment component 6 is mainly used to adjust the angle of the UAV when starting the flight.

[0057] The motor 604 is mainly used to drive the sleeve 605 to rotate.

[0058] The sleeve 605 is slidably matched with the column rod 606, and the inner slide groove 603 is slidably matched with the sliding ball 610.

[0059] Everything in the above example works like this:

[0060] In the initial state: the stable drive component 4, the wind flow safety monitoring component 5, and the adaptive flight attitude adjustment component 6 are located in the device placement compartment 2, and the device placement compartment 2 is blocked by the wind flow safety monitoring component 5; the magnet 505 overlaps and contacts with the Hall switch on the Hall switch cluster 503; the spring body B508 is in a normal relaxed state.

[0061] The following is the working process of the stable driving component 4 and the wind flow safety monitoring component 5:

[0062] When in use, after the carrier 1 arrives at the designated location, the device master control is started to release the airflow safety monitoring component 5 from blocking the device placement compartment 2. Further, the UAV on the support plate 403 is pushed out of the device placement compartment 2 through the transmission member 402. Furthermore, at this time, driven by the normal wind flow of the environment, reference can be made to Figures 6 to 8 , with the effect of wind flow, the wind flow belt 509 will float, thereby carrying the sphere 504 to move in the spherical cavity 502. At this time, the magnet 505 on the sphere 504 will approach one of the Hall switches in the Hall switch cluster 503 according to the effect of wind flow. Since it is known that the Hall switch cluster 503 is composed of eight Hall switches, they are equidistantly distributed on the inner arc surface of the spherical cavity 502, and are respectively located in eight positions of east, west, south, north, northeast, southeast, northwest, and southwest; the magnet 505 is mainly used in conjunction with the Hall switch cluster 503. When the magnet 505 interacts with the Hall switches in different directions, the Hall switch will control the adaptive flight attitude adjustment component 6 to adjust the corresponding attitude through the device master controller. Therefore, the adaptive flight attitude adjustment component 6 that is electrically connected to the Hall switch cluster 503 will start to work at this time;

[0063] On the other hand, if the wind speed is high, please refer to the attached Figure 8 And attached Fig.10 Specifically, when the wind flow is too strong, the wind cone 511 connected to the pull rope 510 will be moved to a certain extent by the wind flow. At this time, the wind cone 511 will slide in the column cavity 506 by pulling the sliding sheet 507 through the pull rope 510. Since it is known that in the initial state, the pull rope 510 only leaks a part of the wind flow belt 509, the operator can judge the size of the wind force at this time according to the degree of change between the pull rope 510 and the arc rod 609, so as to judge whether the drone flight operation is required at this time;

[0064] Furthermore, the present application adopts the design of the square cavity 401 and the supporting plate 403. When the carrier vehicle 1 carries the UAV to the designated location, since the transmission member 402 is in a contracted and unstretched state, the supporting plate 403 will slide in the square cavity 401. At this time, the square cavity 401 contains gas filled by an external air pump through an air valve. At the same time, with the assistance of the spring body A404, the carried UAV can obtain a good shock-absorbing effect under the elastic action of the gas and the spring even if the carrier vehicle 1 is traveling in a rugged mountainous area. This can effectively avoid the occurrence of cracks, deformation or breakage of the outer shell, loosening of internal connecting parts, deformation of the bracket, loosening of welding points of electronic components, disconnection of lines or damage of components, and other situations that are not conducive to flight.

[0065] Furthermore, the present application can effectively monitor the wind flow direction and wind speed through the design of the wind flow safety monitoring component 5, so as to provide assistance for the UAV that is about to fly. The addition of this detection in the actual flight environment can accurately feedback the wind direction through the fluttering direction of the wind flow belt 509, and detect the wind speed intensity at this time through the effect of the wind force on the wind cone 511. This design can adjust the take-off strategy according to the actual situation during take-off, avoiding the subsequent problems of insufficient power caused by taking off against the wind and speed loss when taking off with the wind, thereby reducing the flight risk and improving the safety of UAV use.

[0066] Please refer to the above working process Figure 1 , Figure 2 , Figures 5 to 10 .

[0067] The following is the working process of the adaptive flight attitude adjustment component 6:

[0068] Further, when the adaptive flight attitude adjustment component 6 is activated by the wind flow safety monitoring component 5, the adaptive flight attitude adjustment component 6 will adjust the corresponding position of the carrier board 608 according to the instruction of the main controller, specifically, adjust the direction and angle;

[0069] For details, please refer to the attached Figure 4 , start the motor 604, the motor 604 will rotate with the column 606 and the carrier board 608 on the N-shaped member 607 through the sleeve 605, and during the rotation, the direction of the drone fixed by the fixing device on the carrier board 608 will change; at this time, the arc rod 609 at one end of the column 606 will slide with the sliding ball 610 in the inner slide groove 603 opened on the annular ring 602;

[0070] In terms of angle, further, the electric telescopic rod 601 is started to move the electric telescopic rod 601 upward with the annular ring 602. At this time, the sliding ball 610 located in the inner slide groove 603 provided on the annular ring 602 is forced to rotate with the column 606 through the arc rod 609. Since the column 606 is fixedly connected to the N-shaped member 607 and the carrier plate 608, the take-off angle of the UAV on the carrier plate 608 can be indirectly adjusted under the extension and contraction of the electric telescopic rod 601.

[0071] Furthermore, the present application can adjust the direction and tilt angle of the drone during takeoff, i.e., adjust the azimuth, through the design of an adaptive flight attitude adjustment component, according to the detection of the wind flow safety monitoring component, to avoid the operation mode in the prior art that the drone can only take off on a fixed plane during takeoff. This design that can adaptively adjust the angle according to the wind flow can make full use of the surrounding wind flow conditions to achieve rapid takeoff, and can achieve the effect of wind flow assisting takeoff rather than hindering takeoff. It can be different from the existing fixed angle takeoff mode in plain areas and complex terrain areas, improve the performance of the drone, and greatly improve the application range and flight efficiency of the drone in emergency situations such as rescue. .

[0072] Please refer to the above working process Figures 2 to 5 .

[0073] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the existence of other identical elements in the process, method, article or device including the elements.

[0074] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. An unmanned aerial vehicle carrier with adaptive flight attitude control, comprising: A carrier vehicle (1), a device placement compartment (2), and a cover plate (3), wherein the device placement compartment (2) is equidistantly arranged on the carrier vehicle (1), and the cover plate (3) is laterally slidably arranged on the carrier vehicle (1), and is characterized in that it also includes: a stable drive component (4), a wind flow safety monitoring component (5), and an adaptive flight attitude adjustment component (6), wherein the wind flow safety monitoring component (5) and the adaptive flight attitude adjustment component (6) are located on the same horizontal plane, and the stable drive component (4) is located below the wind flow safety monitoring component (5) and the adaptive flight attitude adjustment component (6); The wind flow safety monitoring component (5) is mainly used to detect the wind flow direction and wind flow intensity; The adaptive flight attitude adjustment component (6) is mainly used to adjust the angle of the UAV when starting flight.

2. The UAV carrier vehicle with adaptive flight attitude control according to claim 1, characterized in that: The stable driving assembly (4) comprises a square cavity (401) located in the device placement bin (2), a transmission member (402) is arranged in the square cavity (401), a support plate (403) is hinged on the transmission member (402), a spring body A (404) is fixedly connected to the bottom surface of the support plate (403), and one end of the spring body A (404) away from the support plate (403) is fixedly connected to the bottom surface of the square cavity (401).

3. The UAV carrier vehicle with adaptive flight attitude control according to claim 1 is characterized in that: The wind flow safety monitoring component (5) comprises a connecting piece (501), the outer end of the connecting piece (501) is fixedly connected to a spherical cavity (502), and the inner arc surface of the spherical cavity (502) is fixedly connected to a Hall switch cluster (503).

4. The UAV carrier vehicle with adaptive flight attitude control according to claim 3 is characterized in that: A sphere (504) is rotatably connected in the spherical cavity (502), a magnet (505) is fixedly connected to the top of the sphere (504), a column cavity (506) is fixedly connected to the sphere (504), a sliding sheet (507) is slidably connected in the column cavity (506), a spring body B (508) is fixedly connected to the top surface of the sliding sheet (507), and the top of the spring body B (508) is fixedly connected to the spherical cavity (502).

5. The UAV carrier vehicle with adaptive flight attitude control according to claim 4, characterized in that: The bottom surface of the column cavity (506) is fixedly connected with a wind belt (509), the bottom surface of the sliding sheet (507) is fixedly connected with a pull rope (510), and one end of the pull rope (510) away from the sliding sheet (507) is fixedly connected with a wind cone (511).

6. The UAV carrier vehicle with adaptive flight attitude control according to claim 1, characterized in that: The adaptive flight attitude adjustment component (6) comprises an electric telescopic rod (601) fixedly connected to a supporting plate (403), an annular ring (602) being fixedly connected to the upper end of the electric telescopic rod (601), and an inner slide groove (603) being provided on the annular ring (602).

7. The UAV carrier vehicle with adaptive flight attitude control according to claim 2, characterized in that: A motor (604) is fixedly connected to the middle of the supporting plate (403), a sleeve (605) is fixedly connected to the top of the motor (604), a column (606) is laterally slidably connected to the sleeve (605), an N-shaped component (607) is fixedly connected to the column (606), and a carrier plate (608) is fixedly connected to the N-shaped component (607).

8. The UAV carrier vehicle with adaptive flight attitude control according to claim 7, characterized in that: One end of the column (606) is fixedly connected to an arc rod (609), and one end of the arc rod (609) away from the column (606) is fixedly connected to a sliding ball (610).

9. The UAV carrier vehicle with adaptive flight attitude control according to claim 2, characterized in that: The support plate (403) is slidably matched with the square cavity (401), and can cooperate with the spring body A (404) to provide buffer protection for the drone during transportation.

10. The UAV carrier vehicle with adaptive flight attitude control according to claim 3, characterized in that: The Hall switch cluster (503) consists of eight Hall switches, which are equidistantly distributed on the inner arc surface of the spherical cavity (502) and are located at eight positions: east, west, south, north, northeast, southeast, northwest, and southwest.

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