Split air-to-ground transport platform docking mechanism

Abstract

The invention discloses a split-type air-to-ground carrier platform docking mechanism, which relates to the technical field of aircraft. The split-type air-to-ground carrier platform docking mechanism includes an active docking component and a passive docking component, wherein the passive docking component is connected to the aircraft; the active docking component includes: a conical guide disk, a central locking adjustment component, wherein the central locking adjustment component includes a telescopic finger, which can be extended outward or retracted inward from the conical guide disk; a peripheral locking component, wherein the peripheral locking component is provided with a peripheral fixing column, which can rotate around the conical guide disk; and the passive docking component includes a docking seat, wherein the docking seat is provided with a first docking groove and a second docking groove, wherein the first docking groove can be used for the telescopic finger to extend into, and the second docking groove can be used for the peripheral fixing column to be inserted into. Thus, by providing the central locking adjustment component and the peripheral locking component, dual axial and dual circumferential locking of the aircraft is achieved, which is beneficial to improving the docking strength of the aircraft in the axial direction, so that the aircraft can carry cargo.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft, and in particular to a split air-to-ground carrier platform docking mechanism. Background Art

[0002] The split-type air-to-ground carrier platform docking mechanism is a professional docking mechanism used for aircraft.

[0003] In the related art, the docking strength of the docking mechanism used in the aircraft is poor, which makes the aircraft unsuitable for the scenario of hanging cargo after docking, affecting the functionality of the aircraft. Summary of the invention

[0004] The present invention aims to solve at least one of the technical problems existing in the prior art. To this end, the present invention proposes a split air-to-ground carrier platform docking mechanism, which has a high docking strength, so that the aircraft can be used in the use scenario of hoisting cargo.

[0005] A split-type air-to-ground carrier platform docking mechanism, comprising an active docking assembly and a passive docking assembly, wherein the passive docking assembly is arranged at the bottom of an aircraft; wherein the active docking assembly comprises: a conical guide disk, the side wall of which is provided with an opening; a central locking adjustment assembly, wherein the central locking adjustment assembly comprises a telescopic finger arranged in the conical guide disk, and the telescopic finger can be extended outward or retracted inward from the opening along the radial direction of the conical guide disk; a peripheral locking assembly, wherein the peripheral locking assembly is provided with a peripheral fixing column located on the circumferential outer side of the conical guide disk, and the peripheral fixing column is provided on the circumferential outer side of the conical guide disk. The peripheral fixing column can rotate around the circumferential direction of the conical guide disk; the passive docking assembly includes: a connecting seat, which is used to be connected to the aircraft; a docking seat, which is connected to the bottom of the connecting seat, and the docking seat is provided with a first docking groove and a second docking groove, the first docking groove is for the telescopic finger to extend into, so as to lock the docking seat and the conical guide disk in the circumferential direction and the axial direction, the second docking groove is for the peripheral fixing column to be inserted, and the docking seat and the active docking assembly are locked in the axial direction and the circumferential direction of the conical guide disk.

[0006] According to the split air-to-ground transport platform docking mechanism of the present invention, a central locking adjustment component and a peripheral locking component are provided to achieve double axial locking of the aircraft, thereby improving the docking strength of the active docking component and the passive docking component in the axial direction, thereby improving the load-bearing capacity of the split air-to-ground transport platform docking mechanism in the axial direction, and then improving the docking strength of the aircraft in the axial direction, so that the aircraft can be used in the use scenario of hoisting cargo, and the functionality of the aircraft is improved. In addition, the central locking adjustment component and the peripheral locking component can also achieve double circumferential locking of the docking seat when the aircraft is docked, further improving the docking reliability of the aircraft.

[0007] According to some embodiments of the present invention, the center locking adjustment assembly includes: a telescopic finger track plate, which is coaxially arranged with the conical guide plate and provided with a slide rail, and a slider of the telescopic finger is arranged in the slide rail and slidingly cooperates with the slide rail; a first driving device, which is connected to the telescopic finger track plate and is used to drive the telescopic finger track plate to rotate around the central axis.

[0008] According to some embodiments of the present invention, a guide groove extending in a radial direction of the conical guide disc is provided on an inner side of a side wall of the conical guide disc, and part of the telescopic fingers are disposed in the guide groove and cooperate with the guide groove.

[0009] According to some embodiments of the present invention, the split-type air-to-ground transport platform docking mechanism also includes: a cockpit, which is used to install the active docking component; a drive fixing seat, which is arranged on the cockpit and is used to install the first drive device, and the drive fixing seat is used to install and fix the conical guide plate.

[0010] According to some embodiments of the present invention, the center locking adjustment assembly also includes: a bearing, the bearing being provided with an inner ring and an outer ring which can rotate relative to each other, the inner ring of the bearing being connected to the telescopic finger track plate; a bearing fixing plate, the bearing fixing plate being arranged on a side of the drive fixing seat away from the cabin and being connected to the outer ring.

[0011] According to some embodiments of the present invention, the peripheral locking assembly includes: a docking plate, which is provided with the peripheral fixing column; a passive wheel, which is coaxially arranged with the conical guide plate and connected to the docking plate, and the passive wheel can drive the docking plate to rotate synchronously; a driving wheel, which is meshed with the passive wheel; and a second driving device, which is arranged in the cockpit and is used to drive the driving wheel to rotate.

[0012] According to some embodiments of the present invention, the docking plate is provided with a limiting portion, and the limiting portion is used to cooperate with the conical guide plate in a radial direction.

[0013] According to some embodiments of the present invention, the limiting portion protrudes from the docking plate toward a side away from the cabin along the axial direction of the docking plate, and there are multiple limiting portions, and the multiple limiting portions are arranged around the conical guide plate in the circumferential direction.

[0014] According to some embodiments of the present invention, the docking plate is arranged on the driving fixed seat, and the middle part of the docking plate is hollowed out and formed with a mating flange extending inward, and a limiting protrusion is provided on the driving fixed seat, and the limiting protrusion is arranged on the side of the mating flange away from the conical guide plate, and is abutted and mated with the mating flange.

[0015] According to some embodiments of the present invention, the second docking groove is configured as a waist-shaped hole; the peripheral fixing column comprises: a connecting section, one end of which is connected to the docking plate; a connecting head, which is connected to the other end of the connecting section, and in the projection in the axial direction of the docking plate, the orthographic projection area of ​​the connecting head is larger than the orthographic projection area of ​​the connecting section.

[0016] According to some embodiments of the present invention, the docking seat includes a first annular docking layer, and the first annular docking layer is provided with the second docking groove, and the second docking groove is arranged to penetrate the first annular docking layer along the thickness direction.

[0017] According to some embodiments of the present invention, the docking seat also includes a second annular docking layer, which is spaced apart from the first annular docking layer in the axial direction of the docking seat, and the connecting seat is connected to a side of the second annular docking layer away from the first annular docking layer.

[0018] According to some embodiments of the present invention, the docking seat also includes: a third annular docking layer, which is located between the first annular docking layer and the second annular docking layer in the axial direction; and a fourth annular docking layer, which is located between the third annular docking layer and the second annular docking layer in the axial direction.

[0019] According to some embodiments of the present invention, the inner diameters of the first annular butt joint layer, the third annular butt joint layer and the fourth annular butt joint layer decrease sequentially.

[0020] According to some embodiments of the present invention, the docking seat further includes connecting ribs, and the connecting ribs are used to connect the first annular docking layer, the second annular docking layer, the third annular docking layer and the fourth annular docking layer.

[0021] According to some embodiments of the present invention, a plurality of the connecting ribs are provided, and the plurality of the connecting ribs are arranged in sequence and spaced apart in the circumferential direction of the docking seat, and at least two of the connecting ribs define the first docking groove with the third annular docking layer and the fourth annular docking layer.

[0022] According to some embodiments of the present invention, the docking seat also includes a central docking angle adjustment bevel, which is located between the third annular docking layer and the fourth annular docking layer and is connected to the connecting rib, and the central docking angle adjustment bevel is used to guide the telescopic direction into the first docking groove.

[0023] According to some embodiments of the present invention, the second annular docking layer is provided with a fixing plate, which bulges along the axial direction toward a side close to the connecting seat and defines an installation cavity, and the camera device is disposed in the installation cavity and installed on the fixing plate.

[0024] According to some embodiments of the present invention, the conical guide disk is provided with a recognizable pattern, and the pattern is used for being recognized by the camera device.

[0025] Additional aspects and advantages of the present invention will be given in part in the following description and in part will be obvious from the following description, or will be learned through practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] The above and / or additional aspects and advantages of the present invention will become apparent and easily understood from the description of the embodiments in conjunction with the following drawings, in which:

[0027] Figure 1 It is a structural schematic diagram of the split air-to-ground transport platform docking mechanism according to an embodiment of the present invention;

[0028] Figure 2 Schematic diagram of the assembly of the central locking adjustment assembly and the peripheral locking assembly according to an embodiment of the present invention Figure 1 ;

[0029] Figure 3 Schematic diagram of the assembly of the central locking adjustment assembly and the peripheral locking assembly according to the embodiment of the present invention Figure 2 ;

[0030] Figure 4 This is a schematic diagram of the internal structure of the conical guide plate according to an embodiment of the present invention;

[0031] Figure 5 The passive docking assembly according to the embodiment of the present invention is shown in FIG. Figure 1 ;

[0032] Figure 6 The passive docking assembly according to the embodiment of the present invention is schematically shown in FIG. Figure 2 .

[0033] Reference numerals:

[0034] Split air-to-ground transport platform docking mechanism 100,

[0035] Active docking assembly 110, conical guide plate 111, opening 1111, guide groove 1112, extension plate 1113,

[0036] Central locking adjustment component 112, telescopic finger 1121, slider 211,

[0037] Telescopic means track plate 1122, slide rail 221,

[0038] The first driving device 1123, the bearing 1124, the bearing fixing plate 1125, the first fixing copper column 1126, the second fixing copper column 1127,

[0039] Peripheral locking assembly 113,

[0040] Peripheral fixing column 1131, connecting section 311, connecting head 312,

[0041] docking plate 1132, limiting portion 321, matching flange 322,

[0042] Passive wheel 1133, driving wheel 1134, second driving device 1135,

[0043] Passive docking assembly 120, connection seat 121, connection hole 1211,

[0044] Docking seat 122, first docking groove 1221, second docking groove 1222, first groove section 1, second groove section 2, transition groove section 3,

[0045] a first annular docking layer 1223, a second annular docking layer 1224, a third annular docking layer 1225, a fourth annular docking layer 1226, a connecting rib 1227, a center docking angle adjustment slope 1228, a fixing plate 1229,

[0046] Cockpit 130

[0047] Driving fixed seat 140, limiting protrusion 141, steering gear fixing frame 142, steering gear fixing plate 143, third fixing copper column 144,

[0048] 150 weight-reducing holes. DETAILED DESCRIPTION

[0049] Embodiments of the present invention are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and cannot be understood as limiting the present invention.

[0050] In the description of the present invention, it should be understood that the terms "center", "upper", "lower", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention 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, and therefore cannot be understood as a limitation on the present invention. In addition, features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0051] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" 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 a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0052] Reference below Figure 1-Figure 6 The split air-to-ground transport platform docking mechanism 100 according to an embodiment of the present invention is described.

[0053] Combination Figure 1 , Figure 2 and Figure 5 , the split air-to-ground carrier platform docking mechanism 100 according to an embodiment of the present invention comprises an active docking component 110 and a passive docking component 120, wherein the passive docking component 120 is disposed at the bottom of an aircraft (not shown).

[0054] Among them, the active docking component 110 includes: a conical guide disk 111, the side wall of which is provided with an opening 1111; a central locking adjustment component 112, the central locking adjustment component 112 includes a telescopic finger 1121 arranged in the conical guide disk 111, and the telescopic finger 1121 can extend outward or retract inward from the opening 1111 along the radial direction of the conical guide disk 111; a peripheral locking component 113, the peripheral locking component 113 is provided with a peripheral fixing column 1131 located on the circumferential outer side of the conical guide disk 111, and the peripheral fixing column 1131 can rotate around the circumferential direction of the conical guide disk 111.

[0055] The passive docking assembly 120 includes: a connecting seat 121, which is used to be connected to the aircraft; a docking seat 122, which is connected to the bottom of the connecting seat 121, and the docking seat 122 is provided with a first docking groove 1221 and a second docking groove 1222. The first docking groove 1221 can be inserted into the telescopic finger 1121 to lock the docking seat 122 and the conical guide disk 111 in the circumferential direction and the axial direction. The second docking groove 1222 can be inserted into the peripheral fixing column 1131 to lock the docking seat 122 and the active docking assembly 110 in the axial direction and the circumferential direction of the conical guide disk 111.

[0056] It should be noted that “inside” refers to the direction extending along the radial direction toward the central axis of the active docking component 110 (or the passive docking component 120), and “outside” refers to the direction extending along the radial direction toward the central axis of the active docking component 110 (or the passive docking component 120).

[0057] Specifically, the connecting seat 121 is connected to the bottom of the aircraft, and the docking seat 122 is connected to the aircraft through the connecting seat 121. When the aircraft needs to dock, it can be achieved through the docking of the passive docking component 120 and the active docking component 110. Specifically, the docking of the aircraft is achieved by docking the docking seat 122 with the active docking component.

[0058] Further integration Figure 1 and Figure 2The telescopic finger 1121 is arranged in the conical guide disk 111, and the telescopic finger 1121 can move in the radial direction relative to the conical guide disk 111. A first docking groove 1221 is arranged on the docking seat 122. When the aircraft needs to dock, the aircraft drives the passive component to fall. At this time, the telescopic finger 1121 moves outward in the radial direction, and the telescopic finger 1121 can extend from the conical guide disk 111 through the opening 1111 on the side wall of the conical guide disk 111. When the first docking groove 1221 is opposite to the telescopic finger 1121, the telescopic finger 1121 can extend into the first docking groove 1221 and cooperate with the inner circumferential wall of the first docking groove 1221 to prevent the docking seat 122 from rotating in the circumferential direction and preventing the docking seat 122 from moving in the axial direction, so as to lock the docking seat 122, thereby realizing the docking of the aircraft.

[0059] Furthermore, the peripheral fixing column 1131 can rotate in the circumferential direction of the conical guide disk 111, and the peripheral fixing column 1131 can be inserted into the second docking groove 122. When the aircraft needs to be docked, the central locking adjustment assembly 112 is first locked with the docking seat 122 to achieve positioning and locking of the docking seat 122, and then the peripheral fixing column 1131 is inserted into the second docking groove 1222, and the peripheral fixing column 1131 can be limitedly matched with the outer wall of the second docking groove 1222 (which can also be understood as the docking seat 122) in the axial direction to prevent the docking seat 122 from moving in the axial direction. At the same time, the peripheral fixing column 1131 can be stopped and matched with the inner side wall of the second docking groove 1222 in the circumferential direction to achieve locking of the aircraft in the circumferential direction and the axial direction, thereby improving the docking reliability of the aircraft.

[0060] Among them, the active docking component 110 can be installed on the cargo hold. When the aircraft is docked with the cargo hold through the active docking component 110 and the passive docking component 120, the aircraft can lift the cargo hold to improve the functionality of the aircraft.

[0061] When the aircraft needs to cancel the docking, it is necessary to cancel the locking state of the passive docking component 120 and the active docking component 110. At this time, the peripheral fixing column 1131 disengages from the second docking groove 1222, and then the telescopic finger 1121 moves inward along the radial direction and disengages from the first docking groove 1221, and the telescopic finger 1121 is further retracted from the outside of the conical guide disk 111 to the inside of the conical guide disk 111 through the opening 1111 on the side wall of the conical guide disk 111, thereby releasing the locking state of the telescopic finger 1121 and the docking seat 122.

[0062] In the related art, the docking mechanism used by the aircraft mainly realizes the docking of the aircraft through a locking structure in the circumferential direction, resulting in poor docking strength of the aircraft in the axial direction, making the aircraft unsuitable for scenarios where cargo is hoisted after docking, affecting the functionality of the aircraft.

[0063] By setting a central locking adjustment component 112 and a peripheral locking component 113, the present application can achieve double axial locking of the docking seat 122 when the aircraft is docked, thereby improving the docking strength of the aircraft in the axial direction and the load-bearing capacity of the split-type air-to-ground transport platform docking mechanism 100 in the axial direction, so that the aircraft can be used in the use scenario of hoisting cargo, thereby improving the functionality of the aircraft.

[0064] In addition, the central locking adjustment assembly 112 and the peripheral locking assembly 113 can also achieve double circumferential locking of the docking seat 122 when the aircraft is docked, thereby improving the docking strength of the aircraft in the circumferential direction, thereby improving the docking reliability of the aircraft.

[0065] According to the split air-to-ground transport platform docking mechanism 100 of the present invention, a central locking adjustment component 112 and a peripheral locking component 113 are provided to achieve double axial locking of the aircraft, thereby improving the docking strength of the active docking component 110 and the passive docking component 120 in the axial direction, thereby improving the load-bearing capacity of the split air-to-ground transport platform docking mechanism 100 in the axial direction, and further improving the docking strength of the aircraft in the axial direction, so that the aircraft can be used in the use scenario of hanging cargo, and the functionality of the aircraft is improved. In addition, the central locking adjustment component 112 and the peripheral locking component 113 can also achieve double circumferential locking of the docking seat 122 when the aircraft is docked, further improving the docking reliability of the aircraft.

[0066] Combination Figure 2 and Figure 3 In some embodiments of the present invention, the center locking adjustment assembly 112 includes: a telescopic finger track plate 1122, the telescopic finger track plate 1122 is coaxially arranged with the conical guide plate 111 and is provided with a slide rail 221, the slider 211 of the telescopic finger 1121 is arranged in the slide rail 221 and slides with the slide rail 221; a first driving device 1123, the first driving device 1123 is connected to the telescopic finger track plate 1122, and is used to drive the telescopic finger track plate 1122 to rotate around the central axis.

[0067] Specifically, the telescopic finger track disk 1122 is arranged in the conical guide disk 111, and the first driving device 1123 is located below the telescopic finger track disk 1122. The output shaft of the first driving device 1123 is transmission-connected to the telescopic finger track disk 1122, and the first driving device 1123 can drive the telescopic finger track disk 1122 to rotate around the central axis of the telescopic finger track disk 1122. A slide rail 221 is provided on the side of the telescopic finger track disk 1122 away from the first driving device 1123, and a slider 211 is formed on the side of the telescopic finger 1121 opposite to the telescopic finger track disk 1122, and the telescopic finger 1121 slides with the slide rail 221 through the slider 211.

[0068] Furthermore, the slide rail 221 is arranged at an angle to the central axis of the telescopic finger track plate 1122, that is, the inner end of the slide rail 221 is arranged close to the central axis of the telescopic finger track plate 1122, and extends obliquely from the inside to the outside. When the first driving device 1123 drives the telescopic finger track plate 1122 to rotate, the telescopic finger track plate 1122 drives the slide rail 221 arranged thereon to rotate, and the inner wall of the slide rail 221 presses against the slider 211 of the telescopic finger 1121 so that it can slide relative to the telescopic finger 1121.

[0069] Among them, a plurality of telescopic fingers 1121 can be provided, and a plurality of telescopic fingers 1121 can improve the locking effect of the central locking adjustment assembly 112 on the docking seat 122. Accordingly, a plurality of slide rails 221 can be provided, and a plurality of slide rails 221 are arranged in a one-to-one correspondence with a plurality of telescopic fingers 1121, and a plurality of slide rails 221 are arranged at intervals in the circumferential direction of the central axis of the telescopic finger track plate 1122, and every two adjacent slide rails 221 are arranged at an angle, that is, each slide rail 221 extends obliquely from the inside to the outside, so as to ensure that the sliding path of the telescopic finger 1121 moves in the radial direction, and is conducive to avoiding interference between the two adjacent telescopic fingers 1121 when sliding.

[0070] Combination Figure 1 Figure 2 and Figure 4 In some embodiments of the present invention, a guide groove 1112 extending in the radial direction of the conical guide disk 111 is provided on the inner side of the side wall of the conical guide disk 111, and a partial telescopic finger 1121 is disposed in the guide groove 1112 and cooperates with the guide groove 1112 for guidance.

[0071] Specifically, two oppositely arranged extension plates 1113 are provided on both sides of the opening 1111 in the circumferential direction, and the extension plates 1113 are provided on one side close to the central axis of the conical guide disk 111, and the extension plates 1113 extend in the radial direction toward the direction close to the central axis of the conical guide disk 111, and the two oppositely arranged extension plates 1113 define a guide groove 1112 extending in the radial direction.

[0072] Furthermore, at least a portion of the telescopic finger 1121 is arranged in the guide groove 1112 to cooperate with the guide groove 1112. When the aircraft needs to dock, the first driving device 1123 drives the telescopic finger track plate 1122 to rotate along the first direction, and the slide rail 221 on the telescopic finger track plate 1122 drives the slider 211 to slide in the slide rail 221. The slider 211 drives the telescopic finger 1121 to slide. At the same time, the guide groove 1112 guides the telescopic finger 1121 to make the telescopic finger 1121 slide outward in the axial direction. In this process, the telescopic finger 1121 gradually slides into the guide groove 1112 and slides in the direction close to the opening 1111. Then, the telescopic finger 1121 can extend from the conical guide plate 111 through the opening 1111 to facilitate docking and cooperation with the first docking groove 1221 on the docking seat 122.

[0073] When it is necessary to cancel the docking state of the aircraft, the first driving device 1123 drives the telescopic finger track plate 1122 to rotate in the second direction, and the slide rail 221 on the telescopic finger track plate 1122 drives the slider 211 to slide in the slide rail 221, and the slider 211 drives the telescopic finger 1121 to slide. At the same time, the guide groove 1112 guides the telescopic finger 1121 to make the telescopic finger 1121 slide inwardly along the axial direction, and the telescopic finger 1121 is retracted into the conical guide plate 111 through the opening 1111, thereby canceling the cooperation between the telescopic finger 1121 and the first docking groove 1221.

[0074] It should be noted that the "first direction" and the "second direction" are opposite. The "first direction" is the rotation direction of the telescopic finger track plate 1122 driving the telescopic finger 1121 to extend outward, for example: clockwise, and the "second direction" is the rotation direction of the telescopic finger track plate 1122 driving the telescopic finger 1121 to retract inward, for example: counterclockwise. Of course, it can be understood that the "first direction" can also be the counterclockwise direction, and correspondingly, the "second direction" can be the clockwise direction. The specific direction limitation can be determined according to actual production requirements and is not specifically limited here.

[0075] By providing the guide groove 1112, the stability of the telescopic finger 1121 during sliding can be effectively guaranteed, while ensuring that the telescopic finger 1121 is opposite to the opening 1111, so that the telescopic finger 1121 can lock the docking seat 122, and at the same time, it is easy to release the locking state of the telescopic finger 1121 and the docking seat 122, thereby avoiding the unlocking and locking failure of the telescopic finger 1121 due to the misalignment of the telescopic finger 1121 with the opening 1111 during the sliding process.

[0076] Combination Figure 1 and Figure 3In some embodiments of the present invention, the split air-to-ground transport platform docking mechanism 100 further includes: a cockpit 130, the cockpit 130 is used to install the active docking assembly 110; a drive fixing seat 140, the drive fixing seat 140 is arranged on the cockpit 130 and is used to install the first drive device 1123, and the drive fixing seat 140 is used to install and fix the conical guide plate 111.

[0077] Specifically, the cockpit 130 can be set on the ground, or when the aircraft needs to carry cargo, the cockpit 130 can be installed on the cargo hold, so that the aircraft split air-to-ground transport platform docking mechanism 100 can be docked with the cargo hold, making it easier for the aircraft to carry cargo.

[0078] Furthermore, a drive fixing seat 140 is provided on the side of the cabin 130 facing away from the ground or the cargo hold. The drive fixing seat 140 can provide a mounting position for the first drive device 1123 to facilitate the installation of the first drive device 1123. At the same time, the drive fixing seat 140 can be connected to the conical guide disk 111 to achieve fixed installation of the conical guide disk 111 and ensure the assembly reliability of the conical guide disk 111.

[0079] Combination Figures 1 to 3 In some embodiments of the present invention, the driving fixed seat 140 includes: a steering gear fixing frame 142, the steering gear fixing frame 142 is used to be connected to the cabin 130; and a steering gear fixing plate 143, the steering gear fixing plate 143 is connected to the steering gear fixing frame 142 and is used to install the first driving device 1123.

[0080] Specifically, the servo mounting bracket 142 is arranged on the upper side of the cabin 130 (i.e., the side of the cabin 130 facing away from the ground or the cargo hold), and a hole is formed on the servo mounting bracket 142. Correspondingly, a hole structure opposite to the hole is formed on the upper side of the cabin 130, and threaded connectors (such as bolts, etc.) can be sequentially passed through the servo mounting bracket 142 and the cabin 130 to connect the servo mounting bracket 142 and the cabin 130.

[0081] Furthermore, the servo fixing plate 143 is arranged on the side of the servo fixing frame 142 away from the cockpit 130, and the middle part of the servo fixing plate 143 is hollowed out to form a mounting hole for the first drive device 1123. The first drive device 1123 can be inserted into the mounting hole and overlapped on the servo fixing plate 143. To ensure the assembly reliability of the first drive device 1123 and the servo fixing plate 143, the part of the first drive device 1123 overlapped on the servo fixing plate 143 can be threadedly connected to the servo fixing plate 143 by means of threaded connection.

[0082] Furthermore, the servo fixing frame 142 can support the servo fixing plate 143, and the servo fixing plate 143 can be connected to the servo fixing frame 142 by screws, thereby ensuring the assembly reliability of the servo fixing plate 143 and the servo fixing frame 142, thereby ensuring the assembly reliability of the first driving device 1123.

[0083] like Figure 2 As shown, in some embodiments of the present invention, the center locking adjustment assembly 112 also includes: a bearing 1124, the bearing 1124 is provided with an inner ring and an outer ring which can rotate relative to each other, and the inner ring of the bearing 1124 is connected to the telescopic finger track plate 1122; a bearing fixing plate 1125, the bearing fixing plate 1125 is arranged on the side of the driving fixing seat 140 away from the cabin 130, and is connected to the outer ring.

[0084] Specifically, the bearing fixing plate 1125 is arranged on the side of the servo fixing plate 143 which is away from the servo fixing frame 142 in the axial direction, and the bearing fixing plate 1125 is spaced apart and connected to the servo fixing plate 143 in the axial direction to realize the installation of the bearing fixing plate 1125, and the bearing fixing plate 1125 is used to install the bearing 1124.

[0085] Further integration Figure 2 and Figure 3 The telescopic finger track plate 1122 is arranged on the side of the bearing 1124 away from the first driving device 1123 in the axial direction, and the output shaft of the first driving device 1123 is passed through the bearing fixing plate 1125 and the bearing 1124 and is transmission-connected to the telescopic finger track plate 1122. The first driving device 1123 can drive the telescopic finger track plate 1122 to rotate, the outer ring of the bearing 1124 is connected to the bearing fixing plate 1125, and the inner ring of the bearing 1124 is connected to the telescopic finger track plate 1122 to facilitate the rotation of the telescopic finger track plate 1122. By setting the bearing 1124, the smoothness of the rotation of the telescopic finger track plate 1122 can be improved and the friction can be reduced.

[0086] Optionally, two bearing fixing plates 1125 can be provided, and the two bearing fixing plates 1125 are respectively located on both sides of the bearing 1124 in the axial direction to improve the assembly stability of the bearing 1124, wherein a first fixed copper column 1126 is arranged between the two bearing fixing plates 1125, and a threaded hole is formed in the first fixed copper column 1126 that penetrates along the axial direction, and the two ends of the first fixed copper column 1126 are respectively arranged opposite to the through-hole structures on the two bearing fixing plates 1125, and screws can be passed through the through-holes on the bearing fixing plates 1125 and threadedly connected to the first fixed copper column 1126, thereby realizing the fixed installation of the two bearing fixing plates 1125.

[0087] like Figure 2As shown, in some embodiments of the present invention, a second fixed copper column 1127 is arranged between the bearing fixing plate 1125 and the servo fixing plate 143, and the bearing fixing plate 1125 and the servo fixing plate 143 can be connected through the second fixed copper column 1127, wherein the connection method between the second fixed copper column 1127 and the bearing fixing plate 1125 and the servo fixing plate 143 is the same as the connection method between the above-mentioned first fixed copper column 1126 and the two bearing fixing plates 1125, which will not be repeated here.

[0088] Combination Figures 1 to 3 In some embodiments of the present invention, the peripheral locking assembly 113 includes: a docking plate 1132, the docking plate 1132 is provided with a peripheral fixing column 1131; a passive wheel 1133, the passive wheel 1133 is coaxially arranged with the conical guide plate 111, and the passive wheel 1133 is connected to the docking plate 1132, and the passive wheel 1133 can drive the docking plate 1132 to rotate synchronously; a driving wheel 1134, the driving wheel 1134 is meshed with the passive wheel 1133; a second driving device 1135, the second driving device 1135 is arranged in the cockpit 130, and is used to drive the driving wheel 1134 to rotate.

[0089] Specifically, a mounting position of a second drive device 1135 is provided on the cockpit 130, and the second drive device 1135 can be installed on the cockpit 130, and the output shaft of the second drive device 1135 is connected to the driving wheel 1134 to drive the driving wheel 1134 to rotate, and the passive wheel 1133 is located on the lower side of the conical guide disk 111 and is spaced apart and concentrically arranged with the conical guide disk 111, and the driving wheel 1134 is meshed with the passive wheel 1133. When the second drive device 1135 drives the driving wheel 1134 to rotate, the driving wheel 1134 can drive the passive wheel 1133 to rotate around the central axis of the conical guide disk 111.

[0090] Among them, the first driving device 1123 and the second driving device 1135 can be configured as a steering gear, a stepper motor or a servo motor. The specific configuration of the first driving device 1123 and the second driving device 1135 can be determined according to actual production requirements and is not specifically limited here.

[0091] Furthermore, an annular docking plate 1132 which is concentrically arranged with the conical guide plate 111 is provided on the side of the passive wheel 1133 which is away from the cabin 130 in the axial direction. The docking plate 1132 is located on the side of the conical guide plate 111 close to the cabin 130. The docking plate 1132 is connected to the passive wheel 1133, and a peripheral fixed column 1131 which extends along the axial direction toward the side away from the cabin 130 is provided on the docking plate 1132. When the passive wheel 1133 rotates, the passive wheel 1133 can drive the docking plate 1132 to rotate, and the docking plate 1132 drives the peripheral fixed column 1131 to rotate around the central axis of the conical guide plate 111.

[0092] Further, the peripheral fixing column 1131 can be inserted into the second docking groove 1222 , and the peripheral fixing column 1131 can slide in the second docking groove 1222 .

[0093] Among them, a plurality of peripheral fixing columns 1131 can be provided, and the plurality of peripheral fixing columns 1131 are arranged at intervals along the circumferential direction of the docking plate 1132. Correspondingly, a plurality of second docking grooves 1222 can be provided, and the plurality of peripheral fixing columns 1131 can correspond one-to-one with the plurality of second docking grooves 1222 to further improve the docking reliability between the docking seat 122 and the active docking assembly 110.

[0094] Combination Figures 1 to 3 In some embodiments of the present invention, the docking disk 1132 is provided with a limiting portion 321, and the limiting portion 321 is used to limit and cooperate with the conical guide disk 111 in the radial direction.

[0095] Specifically, the lower edge of the conical guide disk 111 is located radially inside the limiting portion 321, and the limiting portion 321 can be abutted against the lower edge of the conical guide disk 111 in the radial direction, so that the limiting portion 321 can be limitedly positioned with the conical guide disk 111 in the radial direction, thereby preventing the docking disk 1132 from moving in the radial direction when rotating, thereby improving the stability of the docking disk 1132.

[0096] Combination Figures 1 to 3 In some embodiments of the present invention, the limiting portion 321 is protruded from the docking plate 1132 to a side away from the cockpit 130 along the axial direction of the docking plate 1132 .

[0097] Specifically, the limiting portion 321 is arranged on a side of the docking plate 1132 away from the cabin 130 in the axial direction, and the limiting portion 321 protrudes along the side away from the cabin 130 in the axial direction, and the lower edge of the conical guide plate 111 is arranged opposite to the limiting portion 321 in the radial direction and is located on the radial inner side of the limiting portion 321, so that the limiting portion 321 can be stopped and matched with the lower edge of the conical guide plate 111 in the radial direction, thereby realizing the limiting cooperation between the limiting portion 321 and the conical guide plate 111.

[0098] Further, there are multiple limiting portions 321 , and the multiple limiting portions 321 are arranged around the conical guide disk 111 in the circumferential direction.

[0099] Specifically, a plurality of limiting portions 321 are arranged at intervals along the circumferential direction of the conical guide disk 111 to improve the limiting cooperation effect between the limiting portions 321 and the conical guide disk 111 and further improve the stability of the docking disk 1132 .

[0100] Among them, the limiting portion 321 is constructed as an arc-shaped protrusion adapted to the lower edge of the conical guide disk 111 to ensure the limiting cooperation between the limiting portion 321 and the conical guide disk 111 while avoiding interference between the limiting portion 321 and the conical guide disk 111 in the circumferential direction, thereby ensuring the smooth rotation of the docking disk 1132.

[0101] Combination Figures 1 to 3 In some embodiments of the present invention, the docking plate 1132 is arranged on the driving fixed seat 140, and the middle part of the docking plate 1132 is hollowed out and formed with a matching flange 322 extending inward. A limiting protrusion 141 is provided on the driving fixed seat 140. The limiting protrusion 141 is arranged on the side of the matching flange 322 away from the conical guide plate 111 and abuts against the matching flange 322.

[0102] Specifically, the docking plate 1132 is arranged on the driving fixed seat 140. Specifically, the docking plate 1132 is arranged on the servo fixed frame 142, and the middle part of the docking plate 1132 is hollowed out, the bearing fixing plate 1125 and the bearing 1124 are arranged on the radial inner side of the docking plate 1132 and are spaced apart from the docking plate 1132. It can also be understood that the docking plate 1132 is sleeved on the radial outer side of the bearing fixing plate 1125 and the bearing 1124.

[0103] Further references Figure 2 The docking plate 1132 is formed with a matching flange 322 extending along the radial direction toward its central axis. The steering gear fixing frame 142 is provided with a limiting protrusion 141 at a position directly opposite to the matching flange 322 in the axial direction. The limiting protrusion 141 extends in the axial direction away from the steering gear fixing frame 142, and the top end of the limiting protrusion 141 (which can also be understood as the upper end of the limiting protrusion 141, that is, the end of the limiting protrusion 141 away from the steering gear fixing frame 142) is stopped and matched with the lower surface of the matching flange 322 (that is, the side surface of the matching flange 322 close to the steering gear fixing frame 142 in the axial direction), so that the limiting protrusion 141 can limit the docking plate 1132 in the axial direction, prevent the docking plate 1132 from moving downward in the axial direction, and further improve the stability of the docking plate 1132.

[0104] Combination Figures 2 to 4 In some embodiments of the present invention, a third fixed copper column 144 is provided on the servo fixing frame 142 , and the third fixed copper column 144 is located radially inside the matching flange 322 and is spaced apart from the matching flange 322 in the radial direction.

[0105] Furthermore, a portion of the lower edge of the conical guide disk 111 (i.e., a portion of the lower edge relatively close to the central axis of the conical guide disk 111) is arranged relative to the third fixed copper column 144 in the axial direction, and the third fixed copper column 144 is used to connect the conical guide disk 111 and the servo fixing frame 142 to further improve the assembly reliability of the conical guide disk 111, wherein the connection method between the third fixed copper column 144 and the conical guide disk 111 and the servo fixing frame 142 is the same as the connection method between the above-mentioned first fixed copper column 1126 and the two bearing fixing disks 1125, which will not be repeated here.

[0106] Further references Figure 1 The other part of the lower edge of the conical guide disk 111 (i.e., the part relatively far away from the central axis of the conical guide disk 111) overlaps the docking disk 1132 to engage with the surface of the docking disk 1132 on one side away from the servo fixing frame 142 in the axial direction, thereby limiting the docking disk 1132 in the axial direction and preventing the docking from moving in the axial direction away from the servo fixing frame 142, thereby further improving the stability of the docking disk 1132.

[0107] Therefore, by making the conical guide disk 111 and the limiting protrusion 141 cooperate with each other, the docking disk 1132 is limited in the axial direction to prevent the docking disk 1132 from moving upward or downward, so as to improve the stability of the docking disk 1132.

[0108] Combination Figure 5 and Figure 6 In some embodiments of the present invention, the second docking groove 1222 is configured as a waist-shaped hole.

[0109] Specifically, the second docking groove 1222 includes a first groove section 1, a second groove section 2 and a transition groove section 3, wherein the first groove section 1 and the second groove section 2 are respectively connected to both sides of the transition groove section 3, and in the projection in the axial direction of the docking seat 122, the radial dimension of the first groove section 1 is greater than the radial dimension of the second groove section 2, and the radial dimension of the transition groove section 3 gradually decreases in the direction extending from the first groove section 1 to the second groove section 2.

[0110] The peripheral fixing column 1131 includes a connecting section 311, one end of which is connected to the docking plate 1132; and a connecting head 312, which is connected to the other end of the connecting section 311, and in the axial projection of the docking plate 1132, the orthographic projection area of ​​the connecting head 312 is larger than the orthographic projection area of ​​the connecting section 311.

[0111] Specifically, the connecting section 311 is connected to the docking plate 1132, and the connecting section 311 extends in the axial direction away from the cabin 130, the connecting head 312 is connected to one end of the connecting section 311 away from the docking plate 1132, the peripheral fixing column 1131 can be inserted into the second docking groove 1222 through the first groove section 1, and when the passive wheel 1133 drives the docking plate 1132 to rotate, the peripheral fixing column 1131 can slide in the first groove section 1, specifically, the connecting section 311 slides in the first groove section 1, the connecting head 312 passes through the second docking groove 1222, the transition groove section 3 can guide the connecting section 311 to the second groove section 2, and the connecting section 311 can be stopped and matched with the inner groove wall of the second groove section 2, so that the peripheral fixing column 1131 can lock the docking seat 122 in the circumferential direction through the second docking groove 1222.

[0112] Furthermore, the connector 312 passes through the second docking groove 1222, and when the connecting section 311 slides into the second groove section 2, the connector 312 can be abutted against a side wall of the docking plate 1132 in the axial direction, thereby enabling the peripheral fixing column 1131 to lock the docking seat 122 in the axial direction.

[0113] In addition, when it is necessary to release the locked cooperation state between the peripheral fixing column 1131 and the docking seat 122, it is only necessary to reversely drive the peripheral fixing column 1131 to rotate so that the peripheral fixing column 1131 slides from the second slot section 2 to the first slot section 1. When the aircraft takes off, the peripheral fixing column 1131 escapes from the first slot section 1, thereby achieving the locked cooperation state between the peripheral fixing column 1131 and the docking seat 122, thereby improving the convenience of unlocking.

[0114] Combination Figures 5 and 6 In some embodiments of the present invention, the docking seat 122 includes a first annular docking layer 1223, and the first annular docking layer 1223 is provided with a second docking groove 1222, and the second docking groove 1222 is arranged to penetrate the first annular docking layer 1223 along the thickness direction.

[0115] Specifically, the middle part of the first annular docking layer 1223 is hollowed out to avoid the conical guide disk 111. When the passive docking component 120 is docked with the active docking component 110, the first annular docking layer 1223 is sleeved on the radial outer side of the conical guide disk 111 and is arranged opposite to the docking disk 1132 in the axial direction. The second docking groove 1222 is arranged on the first annular docking layer 1223 to facilitate the peripheral fixing column 1131 to be inserted into the second docking groove 1222, thereby facilitating the peripheral fixing column 1131 to lock the docking seat 122.

[0116] Combination Figures 5 and 6In some embodiments of the present invention, the docking seat 122 also includes a second annular docking layer 1224, which is spaced apart from the first annular docking layer 1223 in the axial direction of the docking seat 122, and the connecting seat 121 is connected to the side of the second annular docking layer 1224 away from the first annular docking layer 1223.

[0117] Specifically, the second annular docking layer 1224 is located on a side of the first annular docking layer 1223 away from the cabin 130 in the axial direction, and the second annular docking layer 1224 is connected to the first annular docking layer 1223. The second annular docking layer 1224 is used to install the connecting seat 121, and the connecting seat 121 is arranged on a side of the second annular docking layer 1224 away from the first annular docking layer 1223 in the axial direction, so as to facilitate the connection between the connecting seat 121 and the bottom of the aircraft.

[0118] Furthermore, a plurality of connection holes 1211 are provided on the side of the connection seat 121 away from the second annular docking layer 1224 in the axial direction, and the plurality of connection holes 1211 are all used for threaded connectors to pass through, so that the connection seat 121 can be threadedly connected to the bottom of the aircraft, thereby facilitating the installation of the aircraft and the connection seat 121.

[0119] Combination Figures 5 and 6 In some embodiments of the present invention, the docking seat 122 also includes: a third annular docking layer 1225, which is located between the first annular docking layer 1223 and the second annular docking layer 1224 in the axial direction; and a fourth annular docking layer 1226, which is located between the third annular docking layer 1225 and the second annular docking layer 1224 in the axial direction.

[0120] Specifically, the third annular docking layer 1225 and the fourth annular docking layer 1226 are both arranged between the first annular docking layer 1223 and the second annular docking layer 1224 , wherein the third annular docking layer 1225 is arranged relatively close to the first annular docking layer 1223 , and the fourth annular docking layer 1226 is arranged relatively close to the second annular docking layer 1224 .

[0121] Furthermore, the middle parts of the third annular docking layer 1225 and the fourth annular docking layer 1226 are hollowed out so that the third annular docking layer 1225 and the fourth annular docking layer 1226 can avoid the conical guide plate 111 to facilitate the docking of the docking seat 122 and the active docking assembly 110.

[0122] like Figure 6 As shown, in some embodiments of the present invention, the inner diameters of the first annular butt joint layer 1223, the third annular butt joint layer 1225 and the fourth annular butt joint layer 1226 decrease sequentially.

[0123] Specifically, along the axial direction, the outer diameter of the conical guide disk 111 gradually decreases from bottom to top, and the inner diameters of the first annular docking layer 1223, the third annular docking layer 1225 and the fourth annular docking layer 1226 decrease successively, so that the radial inner wall surfaces of the first annular docking layer 1223, the third annular docking layer 1225 and the fourth annular docking layer 1226 can be matched with the outer wall surface of the conical guide disk 111 to achieve guidance, thereby ensuring the accuracy of the docking seat 122 when it falls and preventing the docking seat 122 from being misplaced in the radial direction, thereby ensuring the docking effect of the docking seat 122 and the active docking assembly 110.

[0124] like Figure 1 As shown, in some embodiments of the present invention, the spacing between the first annular docking layer 1223 , the third annular docking layer 1225 and the fourth annular docking layer 1226 in the axial direction gradually decreases to ensure the matching reliability between the docking seat 122 and the conical guide disk 111 .

[0125] The spacing between the first annular butt joint layer 1223 , the third annular butt joint layer 1225 and the fourth annular butt joint layer 1226 in the axial direction can be adjusted according to the size of the conical guide disk 111 , which is not specifically limited here.

[0126] like Figure 5 As shown, in some embodiments of the present invention, a plurality of weight-reducing holes 150 are provided on the second annular docking layer 1224 and the third annular docking layer 1225. By providing a plurality of weight-reducing holes 150 to reduce the weight of the passive docking assembly 120, the weight of the aircraft is reduced, thereby improving the performance of the aircraft. In addition, providing a plurality of weight-reducing holes 150 can also reduce the material used in the passive docking assembly 120 and reduce the production cost of the passive docking assembly 120.

[0127] Combination Figure 1 , Figure 5 and Figure 6 In some embodiments of the present invention, the docking seat 122 further includes a connecting rib 1227, and the connecting rib 1227 is used to connect the first annular docking layer 1223, the second annular docking layer 1224, the third annular docking layer 1225 and the fourth annular docking layer 1226.

[0128] Specifically, the connecting rib 1227 extends along the axial direction of the docking seat 122, and the connecting rib 1227 connects the first annular docking layer 1223, the second annular docking layer 1224, the third annular docking layer 1225 and the fourth annular docking layer 1226 respectively, and the connecting rib 1227 can be supported between the first annular docking layer 1223, the second annular docking layer 1224, the third annular docking layer 1225 and the fourth annular docking layer 1226 to ensure the assembly stability of the first annular docking layer 1223, the second annular docking layer 1224, the third annular docking layer 1225 and the fourth annular docking layer 1226, and prevent the first annular docking layer 1223, the second annular docking layer 1224, the third annular docking layer 1225 and the fourth annular docking layer 1226 from moving in the axial direction.

[0129] Combination Figure 1 , Figure 5 and Figure 6 In some embodiments of the present invention, a plurality of connecting ribs 1227 are provided, and the plurality of connecting ribs 1227 are arranged in sequence and spaced apart in the circumferential direction of the docking seat 122, and at least two connecting ribs 1227 and the third annular docking layer 1225 and the fourth annular docking layer 1226 define a first docking groove 1221.

[0130] Specifically, multiple connecting ribs 1227 are arranged in sequence and spaced apart in the circumferential direction of the docking seat 122 to improve the connection reliability and connection strength of the first annular docking layer 1223, the second annular docking layer 1224, the third annular docking layer 1225 and the fourth annular docking layer 1226.

[0131] Among them, refer to Figure 5 Every two connecting ribs 1227 form a group, and the spacing between the two connecting ribs 1227 in each group is smaller than the spacing between the two adjacent groups of connecting ribs 1227, and the two connecting ribs 1227 in each group respectively define a first docking groove 1221 with the third annular docking layer 1225 and the fourth annular docking layer 1226, and the telescopic finger 1121 can extend into the first docking groove 1221 and cooperate with the inner circumferential wall of the first docking groove 1221, so that the telescopic finger 1121 can lock the docking seat 122 in the circumferential and axial directions to prevent the docking seat 122 from rotating, and at the same time prevent the docking seat 122 from moving in the axial direction, thereby improving the docking stability of the passive docking assembly 120 and the active docking assembly 110, thereby improving the docking reliability of the aircraft.

[0132] Combination Figure 5 and Figure 6In some embodiments of the present invention, the docking seat 122 also includes a central docking angle adjustment bevel 1228, which is located between the third annular docking layer 1225 and the fourth annular docking layer 1226 and is connected to the connecting rib 1227. The central docking angle adjustment bevel 1228 is used to guide the telescopic finger 1121 into the first docking groove 1221.

[0133] Specifically, the center docking angle adjustment bevel 1228 is connected to the radial inner side of the connecting rib 1227, and the center docking angle adjustment bevel 1228 is located between the third annular docking layer 1225 and the fourth annular docking layer 1226 in the axial direction, and the center docking angle adjustment bevel 1228 extends obliquely along the radial direction. From the inside to the outside, the distance between the center docking angle adjustment bevel 1228 and the radial extension line of the connecting rib 1227 gradually decreases, that is, from the inside to the outside, the center docking angle adjustment bevel 1228 gradually extends obliquely in the direction close to the first docking groove 1221.

[0134] Furthermore, the telescopic finger 1121 is inserted into the first docking groove 1221 from the inside to the outside, and the central docking angle adjustment slope 1228 can guide the telescopic finger 1121 to ensure that the telescopic finger 1121 can be accurately inserted into the first docking groove 1221, thereby improving the matching accuracy between the telescopic finger 1121 and the first docking groove 1221, thereby ensuring that the passive docking component 120 and the active docking component 110 can be accurately docked, thereby improving the docking effect.

[0135] Combination Figure 5 and Figure 6 In some embodiments of the present invention, a plurality of center docking angle adjustment slopes 1228 are provided, and each group of two connecting ribs 1227 is provided with a center docking angle adjustment slope 1228, that is, the first docking groove 1221 is provided with a center docking angle adjustment slope 1228 on both sides in the circumferential direction, and in the radial direction extending from the connecting rib 1227 to the direction close to the central axis of the docking seat 122, the distance between two adjacent center docking angle adjustment slopes 1228 gradually increases, thereby improving the guiding effect of the telescopic finger 1121 and further ensuring that the telescopic finger 1121 can be accurately inserted into the first docking groove 1221.

[0136] Therefore, by setting the central locking adjustment component 112 and the peripheral locking component 113, double axial locking of the aircraft can be achieved, and the docking strength of the active docking component 110 and the passive docking component 120 in the axial direction can be improved, thereby improving the load-bearing capacity of the split air-to-ground transport platform docking mechanism 100 in the axial direction, and then improving the docking strength of the aircraft in the axial direction, so that the aircraft can be used in the use scenario of hanging cargo, and the functionality of the aircraft is improved. The central locking adjustment component 112 and the peripheral locking component 113 can also achieve double circumferential locking of the docking seat 122 when the aircraft is docked, further improving the docking reliability of the aircraft.

[0137] In addition, the telescopic finger 1121 and the first docking groove 1221 as well as the peripheral fixing column 1131 and the second docking groove 1222 can be easily disengaged, thereby ensuring that the passive docking assembly 120 and the active docking assembly 110 can quickly cancel the docking state, thereby improving the response speed of the aircraft.

[0138] In addition, by setting up a variety of guiding structures (for example, the center docking angle adjustment bevel 1228, the guide groove 1112 and other structures), the docking accuracy of the passive docking component 120 and the active docking component 110 can be effectively guaranteed, so that the passive docking component 120 and the active docking component 110 can be docked even if there is a positioning error between them, thereby improving the docking effect of the passive docking component 120 and the active docking component 110.

[0139] Combination Figure 5 and Figure 6 In some embodiments of the present invention, the second annular docking layer 1224 is provided with a fixing plate 1229, which bulges along the axial direction toward the side close to the connecting seat 121 and defines an installation cavity, and the camera device (not shown) is disposed in the installation cavity and installed on the fixing plate 1229.

[0140] Specifically, the fixing plate 1229 is arranged at the hollowed-out position in the middle of the second annular docking layer 1224. The fixing plate 1229 is used to install a camera device, which is used to identify the pattern and calculate the coordinates of the active docking assembly 110, so that the active docking assembly 110 can be positioned to ensure the accuracy of the aircraft when it falls.

[0141] Furthermore, the fixing plate 1229 bulges along the axial direction toward the side close to the connecting seat 121 and defines an installation cavity, and the camera device is installed in the installation cavity to avoid the connecting seat 121 interfering with the assembly of the camera device, which makes the camera device inconvenient to install. At the same time, since the fixing plate 1229 bulges toward the side close to the connecting seat 121, installing the camera device in the installation cavity can make the camera device and the conical guide disk 111 avoid each other, preventing the conical guide disk 111 and the camera device from interfering with each other and causing the inability to dock, and can also prevent the camera device from being crushed.

[0142] Among them, bolt holes are formed on the fixing plate 1229, and the camera device can be installed on the fixing plate 1229 by means of screws.

[0143] In some embodiments of the present invention, the conical guide disk 111 is provided with a recognizable pattern (not shown), and the pattern is used for recognition by a camera device.

[0144] Specifically, the recognizable pattern set on the conical guide plate 111 can be a QR code. The camera device calculates the coordinates of the active docking component 110 relative to the passive docking component 120 by scanning the pattern, so that the active docking component 110 can be positioned to ensure the accuracy of the aircraft when it falls.

[0145] The recognizable pattern may be disposed on the top of the conical guide plate 111 to facilitate scanning by a camera device.

[0146] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "illustrative embodiments", "examples", "specific examples", or "some examples" means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner.

[0147] Although the 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 claims and their equivalents.

Claims

1. A split-type air-to-ground transport platform docking mechanism, characterized in that: It comprises an active docking component (110) and a passive docking component (120), wherein the passive docking component (120) is arranged at the bottom of the aircraft; wherein: The active docking component (110) comprises: A conical guide plate (111), wherein a side wall of the conical guide plate (111) is provided with an opening (1111); A center locking adjustment assembly (112), the center locking adjustment assembly (112) comprising a telescopic finger (1121) arranged in the conical guide disk (111), and the telescopic finger (1121) can be extended outwardly or retracted inwardly from the opening (1111) along the radial direction of the conical guide disk (111); A peripheral locking assembly (113), wherein the peripheral locking assembly (113) is provided with a peripheral fixing column (1131) located on the circumferential outer side of the conical guide disk (111), and the peripheral fixing column (1131) can rotate around the circumferential direction of the conical guide disk (111); The passive docking assembly (120) comprises: A connecting seat (121), wherein the connecting seat (121) is used to be connected to an aircraft; A docking seat (122), the docking seat (122) is connected to the bottom of the connecting seat (121), and the docking seat (122) is provided with a first docking groove (1221) and a second docking groove (1222), the first docking groove (1221) allows the telescopic finger (1121) to extend into, so as to lock the docking seat (122) and the conical guide disk (111) in the circumferential direction and the axial direction, and the second docking groove (1222) allows the peripheral fixing column (1131) to be inserted, and locks the docking seat (122) and the active docking assembly (110) in the axial direction and the circumferential direction of the conical guide disk (111).

2. The split-type air-to-ground transport platform docking mechanism according to claim 1 is characterized in that: The central locking adjustment assembly (112) comprises: a telescopic finger track plate (1122), the telescopic finger track plate (1122) being coaxially arranged with the conical guide plate (111) and provided with a slide rail (221), a slider (211) of the telescopic finger (1121) being arranged in the slide rail (221) and slidably matched with the slide rail (221); A first driving device (1123), wherein the first driving device (1123) is connected to the telescopic finger track plate (1122) and is used to drive the telescopic finger track plate (1122) to rotate around a central axis.

3. The split-type air-to-ground transport platform docking mechanism according to claim 2 is characterized in that: A guide groove (1112) extending in the radial direction of the conical guide disc (111) is provided on the inner side of the side wall of the conical guide disc (111), and part of the telescopic fingers (1121) are arranged in the guide groove (1112) and are guided and matched with the guide groove (1112).

4. The split-type air-to-ground transport platform docking mechanism according to claim 2 is characterized in that: Also includes: A cockpit (130), the cockpit (130) being used to install the active docking assembly (110); A drive fixing seat (140), the drive fixing seat (140) is arranged on the cabin (130) and is used to install the first drive device (1123), and the drive fixing seat (140) is used to install and fix the conical guide plate (111).

5. The split-type air-to-ground transport platform docking mechanism according to claim 4 is characterized in that: The central locking adjustment assembly (112) further comprises: A bearing (1124), wherein the bearing (1124) is provided with an inner ring and an outer ring that are relatively rotatable, and the inner ring of the bearing (1124) is connected to the telescopic finger track plate (1122); A bearing fixing plate (1125), wherein the bearing fixing plate (1125) is disposed on a side of the driving fixing seat (140) away from the cabin (130) and is connected to the outer ring.

6. The split-type air-to-ground transport platform docking mechanism according to claim 5 is characterized in that: The peripheral locking assembly (113) comprises: A docking plate (1132), wherein the docking plate (1132) is provided with the peripheral fixing column (1131); A passive wheel (1133), wherein the passive wheel (1133) is coaxially arranged with the conical guide disk (111), and the passive wheel (1133) is connected with the docking disk (1132), and the passive wheel (1133) can drive the docking disk (1132) to rotate synchronously; A driving wheel (1134), the driving wheel (1134) meshingly cooperates with the driven wheel (1133); A second driving device (1135), wherein the second driving device (1135) is disposed in the cabin (130) and is used to drive the driving wheel (1134) to rotate.

7. The split-type air-to-ground transport platform docking mechanism according to claim 6 is characterized in that: The docking plate (1132) is provided with a limiting portion (321), and the limiting portion (321) is used for limiting cooperation with the conical guide plate (111) in the radial direction.

8. The split-type air-to-ground transport platform docking mechanism according to claim 7 is characterized in that: The limiting portion (321) is protruding from the docking plate (1132) to a side away from the cabin (130) along the axial direction of the docking plate (1132), and there are multiple limiting portions (321), and the multiple limiting portions (321) are arranged around the conical guide plate (111) in the circumferential direction.

9. The split-type air-to-ground transport platform docking mechanism according to claim 6, characterized in that: The docking plate (1132) is arranged on the driving fixed seat (140), and the middle part of the docking plate (1132) is hollowed out and formed with a matching flange (322) extending inwardly. The driving fixed seat (140) is provided with a limiting protrusion (141), and the limiting protrusion (141) is arranged on a side of the matching flange (322) away from the conical guide plate (111) and abuts against the matching flange (322).

10. The split-type air-to-ground transport platform docking mechanism according to claim 6, characterized in that: The second docking groove (1222) is configured as a waist-shaped hole; The peripheral fixing column (1131) comprises: A connecting section (311), one end of which is connected to the docking plate (1132); A connecting head (312), the connecting head (312) being connected to the other end of the connecting section (311), and in the projection in the axial direction of the docking plate (1132), the orthographic projection area of ​​the connecting head (312) is larger than the orthographic projection area of ​​the connecting section (311).

11. The split-type air-to-ground transport platform docking mechanism according to claim 10, characterized in that: The docking seat (122) comprises a first annular docking layer (1223), and the first annular docking layer (1223) is provided with the second docking groove (1222), and the second docking groove (1222) is arranged to penetrate the first annular docking layer (1223) along the thickness direction.

12. The split-type air-to-ground transport platform docking mechanism according to claim 11, characterized in that: The docking seat (122) further comprises a second annular docking layer (1224), wherein the second annular docking layer (1224) and the first annular docking layer (1223) are spaced apart in the axial direction of the docking seat (122), and the connecting seat (121) is connected to a side of the second annular docking layer (1224) away from the first annular docking layer (1223).

13. The split-type air-to-ground transport platform docking mechanism according to claim 12, characterized in that: The docking seat (122) further comprises: a third annular butt joint layer (1225), the third annular butt joint layer (1225) being located between the first annular butt joint layer (1223) and the second annular butt joint layer (1224) in the axial direction; A fourth annular butt joint layer (1226), wherein the fourth annular butt joint layer (1226) is located between the third annular butt joint layer (1225) and the second annular butt joint layer (1224) in the axial direction.

14. The split-type air-to-ground transport platform docking mechanism according to claim 13, characterized in that: The inner diameters of the first annular butt joint layer (1223), the third annular butt joint layer (1225) and the fourth annular butt joint layer (1226) decrease sequentially.

15. The split-type air-to-ground transport platform docking mechanism according to claim 13, characterized in that: The docking seat (122) further comprises connecting ribs (1227), and the connecting ribs (1227) are used to connect the first annular docking layer (1223), the second annular docking layer (1224), the third annular docking layer (1225) and the fourth annular docking layer (1226).

16. The split-type air-to-ground transport platform docking mechanism according to claim 15, characterized in that: A plurality of the connecting ribs (1227) are provided, and the plurality of the connecting ribs (1227) are arranged in sequence and spaced apart in the circumferential direction of the docking seat (122), and at least two of the connecting ribs (1227) define the first docking groove (1221) with the third annular docking layer (1225) and the fourth annular docking layer (1226).

17. The split-type air-to-ground transport platform docking mechanism according to claim 15, characterized in that: The docking seat (122) further comprises a central docking angle adjustment inclined plane (1228), wherein the central docking angle adjustment inclined plane (1228) is located between the third annular docking layer (1225) and the fourth annular docking layer (1226), and is connected to the connecting rib (1227), and the central docking angle adjustment inclined plane (1228) is used to guide the telescopic finger (1121) into the first docking groove (1221).

18. The split-type air-to-ground transport platform docking mechanism according to claim 13, characterized in that: The second annular docking layer (1224) is provided with a fixing plate (1229), and the fixing plate (1229) is raised along the axial direction toward a side close to the connecting seat (121) and defines a mounting cavity, and the camera device is arranged in the mounting cavity and mounted on the fixing plate (1229).

19. The split-type air-to-ground transport platform docking mechanism according to claim 18, characterized in that: The conical guide plate (111) is provided with a recognizable pattern, and the pattern is used for being recognized by the camera device.

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