Aircraft carrying platform

Abstract

The utility model discloses an aircraft carrying platform which comprises a frame body, a lifting mechanism, a battery replacing mechanism, a plurality of centering mechanisms and a plurality of lifting platforms. The plurality of lifting platforms are arranged in the frame main body; the lifting mechanism comprises a first driving part and a first transmission part; the fixed end of the first driving piece is connected to the frame body, and the movable end of the first driving piece is connected with the first transmission piece. The plurality of lifting platforms are connected with the first transmission part; the battery replacing mechanism comprises a lifting assembly, a rotating assembly and a battery charging box; the fixed end of the lifting assembly is connected to the frame body, the movable end of the lifting assembly is connected with one end of the rotating assembly, and the other end of the rotating assembly is connected with the battery charging box. The battery charging box is configured to charge the aircraft; the multiple centering mechanisms are arranged on the multiple lifting platforms correspondingly. The weight of the whole aircraft nest is reduced, the purposes of automatic charging and battery replacement of a plurality of aircrafts are achieved, and the technical effect that one nest is provided with multiple aircrafts is achieved.

Description

Technical Field

[0001] This application relates to the technical field of aircraft, and particularly to an aircraft carrying platform. Background Art

[0002] Unmanned aerial vehicles (UAVs) are being increasingly widely used in government affairs applications such as public security bureaus, natural resources, ecological environment, comprehensive law enforcement, and housing construction. Currently, they mainly rely on manual route planning by personnel for flight. For application scenarios that require periodic data collection, automatic storage, transportation, charging, and battery swapping have become the main research directions.

[0003] In UAV carrying platforms, UAVs need to take off, land, and retract automatically. However, the currently used vehicle-mounted UAV systems are overall bulky, prone to damage during transportation, and cannot meet the requirements of multiple UAVs in one nest. Summary of the Utility Model

[0004] Embodiments of this application provide an aircraft carrying platform, which solves the problems in the prior art of complex structure, poor reliability of the aircraft nest, and easy damage of the aircraft during transportation. It realizes reducing the weight of the entire aircraft nest and meeting the purpose of automatic charging and battery swapping for multiple aircraft, achieving the technical effect of multiple aircraft in one nest.

[0005] Embodiments of the present utility model provide an aircraft carrying platform, including a frame main body, a lifting mechanism, a battery swapping mechanism, a plurality of centering mechanisms, and a plurality of lifting platforms; the plurality of lifting platforms are arranged inside the frame main body; the lifting mechanism includes a first driving member and a first transmission member; the fixed end of the first driving member is connected to the frame main body, and the movable end of the first driving member is connected to the first transmission member; the plurality of lifting platforms are all connected to the first transmission member; the battery swapping mechanism includes a lifting assembly, a rotating assembly, and a battery charging box; the fixed end of the lifting assembly is connected to the frame main body, the movable end of the lifting assembly is connected to one end of the rotating assembly, and the other end of the rotating assembly is connected to the battery charging box; the battery charging box is configured to swap batteries for the aircraft; the plurality of centering mechanisms are respectively arranged on the plurality of lifting platforms, and the centering mechanisms are configured to move the aircraft to a target position.

[0006] In a possible implementation manner, the first transmission member includes a first sprocket, a chain, a plurality of connecting members, and a plurality of second sprockets; the first sprocket is connected to the movable end of the first driving member; the plurality of second sprockets are all rotatably connected to the frame main body; the chain is sequentially sleeved on the first sprocket and the plurality of second sprockets; one ends of the plurality of connecting members are respectively connected to different sides of the chain, and the other ends of the plurality of connecting members are respectively connected to the plurality of lifting platforms.

[0007] In a possible implementation, the centering mechanism includes a first centering component and a second centering component; the fixed end of the first centering component is connected to the side of the lifting platform away from the aircraft, the movable end of the first centering component can slide on the lifting platform, and is configured to abut against the aircraft from different directions; the fixed end of the second centering component is connected to the side of the lifting platform away from the aircraft, the movable end of the second centering component can slide on the lifting platform, and is configured to abut against the aircraft from different directions.

[0008] In a possible implementation, the battery swapping mechanism further includes a clamping component and a telescopic component; the clamping component includes a second driving member and a clamping jaw; the telescopic component includes a third driving member and a push rod; the fixed end of the third driving member is connected to the rotating component, the movable end of the third driving member is connected to the push rod; the fixed end of the second driving member is connected to the push rod, the movable end of the second driving member is connected to the clamping jaw, and the clamping jaw is connected to the battery charging box.

[0009] In a possible implementation, the lifting component includes a fourth driving member, a second transmission member and a mounting seat; the fixed end of the fourth driving member is connected to the frame body, the movable end of the fourth driving member is connected to one end of the second transmission member, the other end of the second transmission member is connected to the mounting seat, and the mounting seat is connected to the rotating component.

[0010] In a possible implementation, the battery swapping mechanism further includes a limiting member; the limiting member is arranged on the second transmission member and is configured to limit the lifting stroke of the lifting component.

[0011] In a possible implementation, the rotating component includes a fifth driving member and a turntable; the fixed end of the fifth driving member is connected to the mounting seat, the movable end of the fifth driving member is connected to the turntable, and the turntable is connected to the fixed end of the third driving member.

[0012] In a possible implementation, it further includes a housing; the housing is arranged on the outside of the frame body.

[0013] In a possible implementation, it further includes an environmental monitor, an external monitor and an internal monitor; both the environmental monitor and the external monitor are arranged on the outside of the housing; the internal monitor is connected to the frame body and is arranged above the lifting platform.

[0014] In a possible implementation, it further includes a top cover; the top cover is arranged at the top of the frame body and is configured to slide on the frame body.

[0015] One or more technical solutions provided by this application have at least the following technical effects:

[0016] In the embodiment of the utility model, a flying vehicle carrying platform is adopted, which includes a frame body, a lifting mechanism, a battery swapping mechanism, a plurality of centering mechanisms and a plurality of lifting platforms; the plurality of lifting platforms are arranged inside the frame body; the plurality of lifting platforms can be used for the landing and storage of flying vehicles, and the lifting mechanism includes a first driving member and a first transmission member; the fixed end of the first driving member is connected to the frame body, and the movable end of the first driving member is connected to the first transmission member; the plurality of lifting platforms are all connected to the first transmission member; the plurality of lifting platforms can move up and down in the frame body through the lifting mechanism, and the battery swapping mechanism includes a lifting assembly, a rotating assembly and a battery charging box; the fixed end of the lifting assembly is connected to the frame body, the movable end of the lifting assembly is connected to one end of the rotating assembly, and the other end of the rotating assembly is connected to the battery charging box; the battery charging box is configured to swap batteries for the flying vehicle; the battery charging box can perform lifting and rotating operations through the lifting assembly and the rotating assembly so as to align with and serve flying vehicles at different positions and orientations, thereby realizing the automatic battery swapping operation of multiple flying vehicles by one battery swapping mechanism; the plurality of centering mechanisms are respectively arranged on the plurality of lifting platforms, and the centering mechanism is configured to move the flying vehicle to the target position. This application solves the problems of complex structure, poor reliability of the existing aircraft nest and easy damage of the flying vehicle during transportation, realizes the reduction of the weight of the whole aircraft nest, and meets the purpose of automatic charging and battery swapping of multiple flying vehicles, achieving the technical effect of one nest for multiple aircraft. Description of the Drawings

[0017] In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the drawings required for the description of the embodiments of the present utility model will be briefly introduced below. Obviously, the drawings in the following description are some embodiments of the present utility model. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0018] Figure 1 An isometric view of a flying vehicle carrying platform provided by an embodiment of this application;

[0019] Figure 2 An isometric view of the frame body, the lifting mechanism and the battery swapping mechanism provided by an embodiment of this application;

[0020] Figure 3 A top view of the frame body, the lifting mechanism and the battery swapping mechanism provided by an embodiment of this application;

[0021] Figure 4 An isometric view of the battery swapping mechanism provided by an embodiment of this application;

[0022] Figure 5Isometric view of the centering mechanism provided by the embodiment of the present application;

[0023] Figure 6 Isometric view of the lifting platform and the lifting mechanism provided by the embodiment of the present application;

[0024] Figure 7 Isometric view of the lifting mechanism provided by the embodiment of the present application.

[0025] Icons: 1 - Frame body; 2 - Lifting mechanism; 21 - First driving member; 22 - First transmission member; 221 - First sprocket; 222 - Chain; 223 - Connecting member; 224 - Second sprocket; 23 - Fixed plate; 3 - Battery swapping mechanism; 31 - Lifting assembly; 311 - Fourth driving member; 312 - Second transmission member; 313 - Mounting seat; 32 - Rotating assembly; 321 - Fifth driving member; 322 - Turntable; 33 - Battery charging box; 34 - Clamping assembly; 341 - Second driving member; 342 - Claw; 35 - Telescopic assembly; 351 - Third driving member; 352 - Push rod; 36 - Limiting member; 4 - Centering mechanism; 41 - First centering assembly; 42 - Second centering assembly; 5 - Lifting platform; 6 - Housing; 7 - Environmental monitor; 8 - External monitor; 9 - Internal monitor; 10 - Top cover. Detailed implementation manners

[0026] Next, the technical solutions in the embodiments of the present utility model will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are part of the embodiments of the present utility model, rather than all of the embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present utility model.

[0027] In the description of the embodiments of the present utility model, it should be noted that the orientation or positional relationship indicated by terms such as "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the embodiments of the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation to the present utility model. The terms "first", "second", "third" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance. In addition, the terms "installation", "connection", "connection" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the embodiments of the present utility model can be understood according to specific situations.

[0028] An embodiment of the present utility model provides an aircraft carrying platform, as Figures 1-7 shown, which includes a frame body 1, a lifting mechanism 2, a battery swapping mechanism 3, a plurality of centering mechanisms 4 and a plurality of lifting platforms 5; the plurality of lifting platforms 5 are arranged inside the frame body 1; the lifting mechanism 2 includes a first driving member 21 and a first transmission member 22; the fixed end of the first driving member 21 is connected to the frame body 1, and the movable end of the first driving member 21 is connected to the first transmission member 22; the plurality of lifting platforms 5 are all connected to the first transmission member 22; the battery swapping mechanism 3 includes a lifting assembly 31, a rotating assembly 32 and a battery charging box 33; the fixed end of the lifting assembly 31 is connected to the frame body 1, the movable end of the lifting assembly 31 is connected to one end of the rotating assembly 32, and the other end of the rotating assembly 32 is connected to the battery charging box 33; the battery charging box 33 is configured to swap the battery for the aircraft; the plurality of centering mechanisms 4 are respectively arranged on the plurality of lifting platforms 5, and the centering mechanism 4 is configured to move the aircraft to the target position.

[0029] Exemplarily, sliders are connected to the four sides of the lifting platform 5, and rails are connected to the frame body 1 in the lifting direction of the platform. The sliders are slidably connected to the rails, and the lifting platform 5 can smoothly move on the frame body 1 through the sliders and the rails, thereby improving the movement accuracy of the lifting platform 5.

[0030] Exemplarily, the first driving member 21 can adopt a motor or other power elements, and the first driving member 21 can drive the lifting platform 5 to lift inside the frame body 1 through the first transmission member 22.

[0031] Exemplarily, two lifting platforms 5 are provided. The two lifting platforms 5 are respectively connected to both ends of the first transmission member 22. When one of the lifting platforms 5 rises within the frame body 1, the other lifting platform 5 descends within the frame; when one of the lifting platforms 5 descends within the frame body 1, the other lifting platform 5 rises within the frame. When both lifting platforms 5 are in the middle position, at this time, the aircraft is in the internal recovery state within the hangar.

[0032] Exemplarily, as Figure 2 shown, four lifting platforms 5 are provided. The four lifting platforms 5 are distributed in a "well" shape. Among them, two diagonally distributed lifting platforms 5 form a group. Under the action of the first driving member 21 and the first transmission member 22, the two diagonally distributed lifting platforms 5 are lifted and lowered together. When all four lifting platforms 5 are in the middle position, at this time, the aircraft is in the internal recovery state within the hangar.

[0033] Exemplarily, a centering mechanism 4 is provided on each of the lifting platforms 5. The centering mechanism 4 can move the aircraft to the central position after the aircraft lands on the lifting platform 5, so as to prevent the lifting platform 5 from damaging the wing when descending.

[0034] Exemplarily, the battery swapping mechanism 3 is arranged at the central position of the frame body 1. The battery swapping mechanism 3 includes a lifting assembly 31, a rotating assembly 32 and a battery charging box 33. The lifting assembly 31 can realize the movement of the battery charging box 33 in the height direction. One battery swapping mechanism 3 is provided in this application, and the rotating assembly 32 can meet the operations of swapping and charging multiple aircraft.

[0035] In the embodiment of this application, as Figure 2 、 Figure 6 and Figure 7 shown, the first transmission member 22 includes a first sprocket 221, a chain 222, a plurality of connecting members 223 and a plurality of second sprockets 224; the first sprocket 221 is connected to the movable end of the first driving member 21; a plurality of second sprockets 224 are all rotatably connected to the frame body 1; the chain 222 is sequentially sleeved on the first sprocket 221 and a plurality of second sprockets 224; one ends of the plurality of connecting members 223 are respectively connected to different sides of the chain 222, and the other ends of the plurality of connecting members 223 are respectively connected to the plurality of lifting platforms 5.

[0036] Exemplarily, the lifting mechanism 2 further includes a fixing plate 23 which is fixedly connected to the frame body 1. The first sprocket 221 and multiple second sprockets 224 are all rotatably connected to the fixing plate 23. The chain 222 is sleeved on the first sprocket 221 and multiple second sprockets 224 in sequence, and the chain 222 can mesh with the first sprocket 221 and multiple second sprockets 224. The movable end of the first driving member 21 is fixedly connected to the first sprocket 221, so as to drive the first sprocket 221 to rotate. The first sprocket 221 can drive the chain 222 to move, and the movement of the chain 222 can drive multiple second sprockets 224 to rotate.

[0037] Exemplarily, there are two lifting platforms 5. The two lifting platforms 5 are connected to both sides of the chain 222 through a connecting member 223, so that when one lifting platform 5 rises in the frame body 1, the other lifting platform 5 descends in the frame; when one lifting platform 5 descends in the frame body 1, the other lifting platform 5 rises in the frame. When both lifting platforms 5 are in the middle position, at this time, the aircraft is in the internal recovery state in the hangar.

[0038] Exemplarily, the present application is provided with four groups of lifting mechanisms 2 and four lifting platforms 5. Each lifting mechanism 2 is connected to two lifting platforms 5. The four lifting platforms 5 are distributed in a "well" shape. Among them, two diagonally distributed lifting platforms 5 are a group. Under the action of multiple first driving members 21 and multiple first transmission members 22, the two diagonally distributed lifting platforms 5 are lifted and lowered together. When all four lifting platforms 5 are in the middle position, at this time, the aircraft is in the internal recovery state in the hangar.

[0039] In the embodiment of the present application, as Figures 1-7 shown, the centering mechanism 4 includes a first centering component 41 and a second centering component 42; the fixed end of the first centering component 41 is connected to the side of the lifting platform 5 away from the aircraft. The movable end of the first centering component 41 can slide on the lifting platform 5 and can abut against the aircraft from different directions; the fixed end of the second centering component 42 is connected to the side of the lifting platform 5 away from the aircraft. The movable end of the second centering component 42 can slide on the lifting platform 5 and can abut against the aircraft from different directions.

[0040] Exemplarily, the first movement direction of the first centering component 41 and the second movement direction of the second centering component 42 are perpendicular to each other. The first centering component 41 includes a seventh driving member, a third transmission member, and two first actuating members. The fixed end of the seventh driving member is connected to the side of the lifting platform 5 away from the aircraft, the movable end of the seventh driving member is connected to the input end of the third transmission member, the first output end of the third transmission member is connected to one of the first actuating members; the second output end of the third transmission member is connected to the other first actuating member, and the relative or opposite movement of the two first actuating members can be realized, so as to realize the centering operation of the aircraft in the first movement direction.

[0041] Exemplarily, the second centering component 42 includes a sixth driving member, a fourth transmission member, and a second actuating member. The fixed end of the sixth driving member is connected to the side of the lifting platform 5 away from the aircraft, the movable end of the sixth driving member is connected to the input end of the fourth transmission member, the first output end of the fourth transmission member is connected to one of the second actuating members, and the second output end of the fourth transmission member is connected to the other second actuating member, and the relative or opposite movement of the two second actuating members can be realized, so as to realize the centering operation of the aircraft in the second movement direction.

[0042] In the embodiment of the present application, as Figures 1-7 shown, the battery swapping mechanism 3 further includes a clamping component 34 and a telescopic component 35; the clamping component 34 includes a second driving member 341 and a jaw 342; the telescopic component 35 includes a third driving member 351 and a push rod 352; the fixed end of the third driving member 351 is connected to the rotating component 32, and the movable end of the third driving member 351 is connected to the push rod 352; the fixed end of the second driving member 341 is connected to the push rod 352, and the movable end of the second driving member 341 is connected to the jaw 342, and the jaw 342 is connected to the battery charging box 33.

[0043] Exemplarily, the telescopic component 35 can adopt a power element such as an electric push rod 352 or a cylinder, and the battery can be replaced through the telescopic component 35 and the clamping component 34.

[0044] In the embodiment of the present application, as Figures 1-7 shown, the lifting component 31 includes a fourth driving member 311, a second transmission member 312, and a mounting seat 313; the fixed end of the fourth driving member 311 is connected to the frame body 1, the movable end of the fourth driving member 311 is connected to one end of the second transmission member 312, the other end of the second transmission member 312 is connected to the mounting seat 313, and the mounting seat 313 is connected to the rotating component 32;

[0045] Exemplarily, the fourth driving member 311 adopts a servo stepping motor, and the second transmission member 312 adopts a screw lift. The screw lift can be controlled by the servo stepping motor to lift, so as to drive the battery charging box 33 to lift and realize the battery access at three positions in the height direction.

[0046] In the embodiments of the present application, as Figures 1-7 shown, the battery swapping mechanism 3 further includes a limiting member 36; the limiting member 36 is arranged on the second transmission member 312, and the limiting member 36 is configured to limit the lifting stroke of the lifting assembly 31.

[0047] In the embodiments of the present application, as Figures 1-7 shown, the rotating assembly 32 includes a fifth driving member 321 and a turntable 322; the fixed end of the fifth driving member 321 is connected to the mounting base 313, the movable end of the fifth driving member 321 is connected to the turntable 322, and the turntable 322 is connected to the fixed end of the third driving member 351.

[0048] Exemplarily, the fifth driving member 321 adopts a rotary motor or other power elements, and can realize the 360° rotation of the turntable 322, so as to realize the automatic battery swapping of multiple aircraft by one battery swapping mechanism 3.

[0049] Exemplarily, a mounting plate is further connected between the turntable 322 and the third driving member 351.

[0050] In the embodiments of the present application, as Figure 1 shown, it further includes a housing 6; the housing 6 is arranged on the outside of the frame body 1.

[0051] Exemplarily, during the transportation and storage of the aircraft, the housing 6 around the frame body 1 can protect the aircraft.

[0052] In the embodiments of the present application, as Figure 1 and Figure 2 shown, it further includes an environment monitor 7, an external monitor 8 and an internal monitor 9; the environment monitor 7 and the external monitor 8 are both arranged on the outside of the housing 6; the internal monitor 9 is connected to the frame body 1 and is arranged above the lifting platform 5.

[0053] Exemplarily, through the environment monitor 7, the external monitor 8 and the internal monitor 9, the state of the aircraft during landing, storage and transportation can be monitored, so as to ensure the safety of the lifting and storage of the aircraft.

[0054] In the embodiments of the present application, as Figure 1 shown, it further includes a top cover 10; the top cover 10 is arranged at the top of the frame body 1, and the top cover 10 is configured to slide on the frame body 1.

[0055] Exemplarily, when the aircraft lands, the two top covers 10 at the top of the frame body 1 are in the open state, and when the aircraft is in the internal recovery state, the two top covers 10 at the top of the frame body 1 are in the closed state.

[0056] Exemplarily, the total weight of the four aircraft carried by the aircraft carrying platform of the present application is less than 300 kg; and each aircraft can be individually equipped with two spare batteries. The aircraft carrying platform has the ability of automatic battery replacement and can charge the replaced batteries, realizing the one-key takeoff and recovery operations of the aircraft. The present application meets the requirements of one nest with multiple aircraft, reduces the weight of the entire carrying platform at the same time, and the automatic charging and battery replacement functions can meet the cyclic operation of multiple aircraft at a single time.

[0057] The various embodiments in this specification are described in a progressive manner. For the same or similar parts between the various embodiments, reference can be made to each other, and the key points of each embodiment are the differences from other embodiments.

[0058] The above embodiments are only used to illustrate the technical solutions of the present application, rather than limiting the present application; although the present application has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements on some or all of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the present application.

Claims

1. An aircraft carrying platform, characterized in that: It comprises a frame body (1), a lifting mechanism (2), a power exchange mechanism (3), a plurality of centering mechanisms (4) and a plurality of lifting platforms (5); A plurality of lifting platforms (5) are arranged in the frame body (1); The lifting mechanism (2) comprises a first driving member (21) and a first transmission member (22); The fixed end of the first driving member (21) is connected to the frame body (1), and the movable end of the first driving member (21) is connected to the first transmission member (22); The plurality of lifting platforms (5) are all connected to the first transmission member (22); The battery replacement mechanism (3) comprises a lifting component (31), a rotating component (32) and a battery charging box (33); The fixed end of the lifting component (31) is connected to the frame body (1), the movable end of the lifting component (31) is connected to one end of the rotating component (32), and the other end of the rotating component (32) is connected to the battery charging box (33); The battery charging box (33) is configured to replace power for the aircraft; The plurality of centering mechanisms (4) are respectively arranged on the plurality of lifting platforms (5), and the centering mechanisms (4) are configured to move the aircraft to a target position.

2. The aircraft carrying platform according to claim 1, characterized in that: The first transmission member (22) comprises a first sprocket (221), a chain (222), a plurality of connecting members (223) and a plurality of second sprockets (224); The first sprocket (221) is connected to the movable end of the first driving member (21); A plurality of the second sprockets (224) are all rotatably connected to the frame body (1); The chain (222) is sequentially sleeved on the first sprocket (221) and a plurality of the second sprockets (224); One ends of the plurality of connecting members (223) are respectively connected to different sides of the chain (222), and the other ends of the plurality of connecting members (223) are respectively connected to the plurality of lifting platforms (5).

3. The aircraft carrying platform according to claim 1, characterized in that: The centering mechanism (4) comprises a first centering component (41) and a second centering component (42); The fixed end of the first centering component (41) is connected to a side of the lifting platform (5) away from the aircraft, and the movable end of the first centering component (41) is capable of sliding on the lifting platform (5) and is configured to abut against the aircraft from different directions; The fixed end of the second centering component (42) is connected to a side of the lifting platform (5) away from the aircraft, and the movable end of the second centering component (42) is capable of sliding on the lifting platform (5) and is configured to abut against the aircraft from different directions.

4. The aircraft carrying platform according to claim 1, characterized in that: The power exchange mechanism (3) further comprises a clamping assembly (34) and a telescopic assembly (35); The clamping assembly (34) comprises a second driving member (341) and a clamping claw (342); The telescopic assembly (35) comprises a third driving member (351) and a push rod (352); The fixed end of the third driving member (351) is connected to the rotating assembly (32), and the movable end of the third driving member (351) is connected to the push rod (352); The fixed end of the second driving member (341) is connected to the push rod (352), the movable end of the second driving member (341) is connected to the clamping claw (342), and the clamping claw (342) is connected to the battery charging box (33).

5. The aircraft carrying platform according to claim 4, characterized in that: The lifting assembly (31) comprises a fourth driving member (311), a second transmission member (312) and a mounting seat (313); The fixed end of the fourth driving member (311) is connected to the frame body (1), the movable end of the fourth driving member (311) is connected to one end of the second transmission member (312), the other end of the second transmission member (312) is connected to the mounting seat (313), and the mounting seat (313) is connected to the rotating assembly (32).

6. The aircraft carrying platform according to claim 5, characterized in that: The power exchange mechanism (3) further includes a limiting member (36); The limiting member (36) is arranged on the second transmission member (312), and the limiting member (36) is configured to limit the lifting stroke of the lifting assembly (31).

7. The aircraft carrying platform according to claim 5, characterized in that: The rotating assembly (32) comprises a fifth driving member (321) and a rotating disk (322); The fixed end of the fifth driving member (321) is connected to the mounting seat (313), the movable end of the fifth driving member (321) is connected to the rotating disk (322), and the rotating disk (322) is connected to the fixed end of the third driving member (351).

8. The aircraft carrying platform according to claim 1, characterized in that: Also includes a housing (6); The housing (6) is arranged on the outside of the frame body (1).

9. The aircraft carrying platform according to claim 8, characterized in that: It also includes environmental monitors (7), external monitors (8) and internal monitors (9); The environmental monitoring device (7) and the external monitoring device (8) are both arranged on the outside of the housing (6); The internal monitoring (9) is connected to the frame body (1) and is arranged above the lifting platform (5).

10. The aircraft carrying platform according to claim 1, characterized in that: Also includes a top cover (10); The top cover (10) is provided at the top end of the frame body (1), and the top cover (10) is configured to slide on the frame body (1).

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