Aircraft docking platform

Abstract

The present application provides an aircraft docking platform, comprising: a bracket, a first side of the bracket having a bearing surface and a first air outlet, the first air outlet being disposed on at least a portion of an outer periphery of the bearing surface; a first airflow generator, the first airflow generator being capable of generating a first airflow, the first airflow flowing toward the first side of the bracket through the first air outlet to form a wind wall on the first side of the bracket extending away from the bearing surface, the wind wall being capable of separating an area on the first side of the bracket into a first area and a second area in a first direction, the bearing surface being located in the first area, and the wind wall being capable of exerting a force on an aircraft located in the first area toward the interior of the first area. The aircraft docking platform provided by the present application can guide the position of an aircraft located in the first area through the wind wall, thereby guiding the aircraft to land precisely on the bearing surface.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft equipment, and more specifically, to an aircraft docking platform. Background Art

[0002] Drones offer advantages such as small size, light weight, portability, good maneuverability, and the ability to explore confined spaces. However, when miniaturized drones use image recognition or satellite positioning to land, they lack precision and can easily deviate from their intended landing point, causing damage to the drone. Summary of the Invention

[0003] One purpose of this application is to provide a new technical solution for an aircraft docking platform, which can at least solve the problem in the prior art that aircraft have difficulty in landing accurately.

[0004] The present application provides an aircraft docking platform, comprising: a bracket, a first side of the bracket having a bearing surface and a first air outlet, the first air outlet being arranged at at least a portion of the outer periphery of the bearing surface; a first airflow generator, the first airflow generator being capable of generating a first airflow, the first airflow flowing toward the first side of the bracket through the first air outlet to form a wind wall on the first side of the bracket extending in a direction away from the bearing surface, the wind wall being capable of dividing an area on the first side of the bracket into a first area and a second area in a first direction, the bearing surface being located in the first area, and the wind wall being capable of exerting a force toward the interior of the first area on an aircraft located in the first area.

[0005] Optionally, the first air outlet is arranged around the outer periphery of the bearing surface.

[0006] Optionally, the bracket includes: a main body, at least a portion of the first side surface of the main body is formed as the bearing surface; an extension portion, the extension portion is arranged on the first side surface of the main body and extends away from the main body, the extension portion is arranged around the bearing surface, the extension portion has a first channel extending along its own extension direction, the first airflow enters the first channel through the first end of the first channel, and the second end of the first channel is formed as the first air outlet.

[0007] Optionally, the first channel is trumpet-shaped, so that an angle of not less than 90° and not more than 120° is formed between the extension direction of the wind wall and the bearing surface.

[0008] Optionally, a grid is provided in the first channel, and the grid divides the first channel into a plurality of microchannels, each of the microchannels extending along an extension direction of the extension portion.

[0009] Optionally, the supporting surface has a second air outlet, and the aircraft docking platform also includes: a second airflow generator, the second airflow generator is used to generate a second airflow, the second airflow flows to the first side of the bracket through the second air outlet, and the second airflow forms a counter-action with the airflow of the aircraft flowing to the supporting surface to form a negative pressure area on the first side of the bracket.

[0010] Optionally, the bracket has a accommodating cavity, and the aircraft docking platform further includes: a partition, which is arranged in the accommodating cavity to separate the accommodating cavity into a first chamber and a second chamber, the first chamber is connected to the first air outlet, and the second chamber is connected to the second air outlet.

[0011] Optionally, the first airflow generator is provided in the first chamber, the second airflow generator is provided in the second chamber, and the first chamber is isolated from the second chamber.

[0012] Optionally, the chamber has a top wall, a bottom wall and side walls, the top wall corresponds to the bearing surface, and the partition includes: a first partition, the first partition is connected to the top wall, a portion of the first partition is spaced apart from the top wall, and the second airflow generator is installed on the first partition; a second partition, the second partition is arranged on the side of the first partition close to the bottom wall, and a first airflow generator is provided between the second partition and the bottom wall; a third partition, the third partition is located between the second partition and the side wall, the first end of the third partition is connected to the outer surface of the second partition, the second end of the third partition extends toward the first air outlet, and the outer surface of the third partition is spaced apart from the side wall.

[0013] Optionally, the aircraft docking platform further includes: a charger, the charger being disposed on the bracket, at least a portion of the charger corresponding to the carrying surface to form a charging area on a first side of the carrying surface.

[0014] According to the aircraft docking platform provided by the present application, a first air outlet is arranged at the outer edge of the bearing surface of the bracket, so that the first airflow forms a wind wall on the first side of the bracket through the first air outlet, dividing the first side of the bracket into two areas, and the bearing surface is arranged in the first area. Since the existence of the wind wall can guide the position of the aircraft located in the first area, it is difficult for the aircraft located in the first area to pass through the wind wall to enter the second area during the descent process, so that the wind wall can guide the aircraft to land accurately on the bearing surface, which is conducive to performing work such as charging, data transmission, and maintenance on the aircraft after landing, and avoiding damage to the aircraft due to inaccurate landing.

[0015] Other features and advantages of the present application will become apparent from the following detailed description of exemplary embodiments of the present application with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The accompanying drawings, which are incorporated in and constitute a part of the specification, illustrate embodiments of the application and, together with the description, serve to explain the principles of the application.

[0017] Figure 1 is a schematic diagram of the three-dimensional structure of an aircraft docking platform according to an embodiment of the present application;

[0018] Figure 2 is an exploded view of an aircraft docking platform according to one embodiment of the present application;

[0019] Figure 3 is a top view of an aircraft docking platform according to one embodiment of the present application;

[0020] Figure 4 yes Figure 3 A cross-sectional view of the aircraft docking platform taken along line AA;

[0021] Figure 5 yes Figure 3 A cross-sectional view of the aircraft docking platform taken along line segment BB;

[0022] Figure 6 is a schematic diagram of force analysis of an aircraft during landing according to one embodiment of the present application;

[0023] Figure 7 This is a schematic diagram of force analysis of an aircraft approaching a wind wall during landing according to an embodiment of the present application.

[0024] Reference numerals

[0025] Aircraft docking platform 100;

[0026] Bracket 10; main body 11; bearing surface 111; first area 112; second area 113; first air outlet 114; second air outlet 115; wind wall 116; extension portion 12; first channel 121; grille 122; first extension plate 123; second extension plate 124; accommodating chamber 13; first chamber 131; second chamber 132; partition 14; first partition 141; second partition 142; third partition 143; support column 15;

[0027] a first airflow generator 20;

[0028] a second air flow generator 30;

[0029] Charger 40; induction element 41; circuit board 42; wire 43; battery 44;

[0030] Drone 200; Airflow 201. DETAILED DESCRIPTION

[0031] Various exemplary embodiments of the present application will now be described in detail with reference to the accompanying drawings. It should be noted that unless otherwise specifically stated, the relative arrangements of components and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present application.

[0032] The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the present disclosure, its application, or uses.

[0033] Technologies, methods, and equipment known to ordinary technicians in the relevant art may not be discussed in detail, but where appropriate, the technologies, methods, and equipment should be considered part of the specification.

[0034] In all examples shown and discussed herein, any specific values should be interpreted as merely exemplary and not limiting. Therefore, other examples of the exemplary embodiments may have different values.

[0035] It should be noted that like reference numerals and letters refer to like items in the following figures, and therefore, once an item is defined in one figure, it need not be further discussed in subsequent figures.

[0036] The aircraft docking platform 100 according to an embodiment of the present application is described in detail below with reference to the accompanying drawings.

[0037] like Figures 1 to 5 As shown, the aircraft docking platform 100 according to an embodiment of the present application includes: a bracket 10 and a first airflow generator 20 .

[0038] Specifically, the first side of the bracket 10 has a bearing surface 111 and a first air outlet 114. The first air outlet 114 is disposed on at least a portion of the outer periphery of the bearing surface 111. The first airflow generator 20 is capable of generating a first airflow, which flows toward the first side of the bracket 10 through the first air outlet 114, thereby forming a wind wall 116 on the first side of the bracket 10 that extends away from the bearing surface 111. The wind wall 116 is capable of dividing the first side of the bracket 10 into a first area 112 and a second area 113 in a first direction. The bearing surface 111 is located within the first area 112, and the wind wall 116 is capable of exerting a force on the aircraft within the first area 112 toward the interior of the first area 112.

[0039] In other words, the aircraft docking platform 100 according to the embodiment of the present application is mainly composed of a bracket 10 and a first airflow generator 20. The aircraft docking platform 100 can be used as a landing and take-off platform for an aircraft, which may include a drone.

[0040] Specifically, the first side of the bracket 10 may have a bearing surface 111 and a first air outlet 114. For example, the side of the bracket 10 facing the landing direction of the aircraft may serve as the first side, so that the aircraft can land on the bearing surface 111. Optionally, at least a portion of the bearing surface 111 may extend horizontally to facilitate the aircraft to maintain balance after landing on it.

[0041] The first air outlet 114 can be provided at a portion of the outer periphery of the support surface 111. The first airflow generated by the first airflow generator 20 can flow out through the first air outlet 114. The first airflow flowing out of the first air outlet 114 can flow on the first side of the bracket 10 in a direction away from the support surface 111, thereby forming a wind wall 116 on the first side of the bracket 10. In other words, the wind wall 116 can extend from the first air outlet 114 in a direction away from the support surface 111. Optionally, the first airflow generator 20 can include a first fan.

[0042] Due to the presence of the wind wall 116, the area corresponding to the first side of the bracket 10 can be separated by the wind wall 116 in the first direction to form a first area 112 and a second area 113. In other words, the boundary between the first area 112 and the second area 113 is the wind wall 116. The first direction can have an angle with the extension direction of the wind wall 116. Optionally, the bearing surface 111 can be a horizontal plane extending along the first direction. For example, the first direction can be Figure 4 and Figure 5 For the sake of convenience of explanation, the left and right directions shown may be defined as a second direction, which may be an up and down direction, including a vertical direction.

[0043] Furthermore, within the separated first and second regions 112, 113, first region 112 may accommodate a support surface 111. During landing of an aircraft within first region 112, when the aircraft approaches wind wall 116 from the side of wind wall 116 closer to first region 112, the high-speed airflow contained within wind wall 116 may form an airflow barrier, preventing the aircraft from passing through wind wall 116. In other words, the presence of wind wall 116 may, to a certain extent, prevent an aircraft within first region 112 from passing through wind wall 116 and entering second region 113 during its descent, thereby enabling the aircraft to land precisely on support surface 111.

[0044] For example, Figure 6 and Figure 7As shown, the aircraft can be a drone 200. When drone 200 is not affected by wind wall 116, during descent, drone 200 is subject to its own gravity G, air friction f, and lift forces F1 and F2 generated by wing airflow 201. When drone 200 accelerates downward, the resultant force F acting on drone 200 is directed vertically downward. When drone 200 descends at a constant speed, the resultant force F acting on drone 200 is zero.

[0045] During the descent of the drone 200 in the first area 112, when the drone 200 approaches Figure 7 When the wind wall 116 is on the right side as shown, the airflow 201 blown out by the wing blades on the side of the drone 200 close to the wind wall 116 will be affected by the airflow of the wind wall 116 and deviate from the flow direction of the airflow of the wind wall 116. The deviated airflow 201 can merge with the airflow of the wind wall 116, and the merged airflow can apply a driving force F3 to the drone 200 toward the first area 112.

[0046] At this point, the lift on the wing of drone 200 near wind wall 116 is reduced from F2 to F2', while the weight of drone 200 remains unchanged. Because the lift on one wing of drone 200 is reduced, the wing on the other side of drone 200 increases its blade speed to provide greater lift to maintain its balance. In other words, the lift on the wing on the other side of drone 200 increases from F1 to F1'. Furthermore, due to the influence of wind wall 116, the air friction also increases from f to f'.

[0047] Under the influence of the propulsion force F3, gravity G, air friction force f', lift force F1', and lift force F2', the resultant force F' acting on the drone 200 can be roughly oriented toward the central axis of the support surface 111, that is, toward the center of the first region 112. When the drone 200 accelerates downward, the resultant force F' acting on the drone 200 can be tilted downward toward the central axis of the support surface 111; when the drone 200 descends at a constant speed, the resultant force F' acting on the drone 200 can be horizontally directed to the left toward the central axis of the support surface 111. Under the influence of the resultant force F', the drone 200 moves toward the central axis of the support surface 111 and away from the wind wall 116, preventing the drone 200 from passing through the wind wall 116 on the right.

[0048] During the descent of drone 200 within first area 112, when drone 200 approaches left wind wall 116, the resultant force acting on drone 200 may also be approximately directed toward the central axis of support surface 111. In other words, the resultant force acting on drone 200 has a component directed toward the right. Under the action of this resultant force, drone 200 can move rightward, away from left wind wall 116, thereby preventing drone 200 from passing through left wind wall 116. Optionally, drone 200, guided by wind wall 116, descends to aircraft docking platform 100 in a spiral descent.

[0049] It should be noted that the wind wall 116 is a flow field provided at the interface between the first region 112 and the second region 113. The effective area of the wind wall 116 is related to the intensity of the first airflow flowing out of the first air outlet 114. The stronger the intensity of the first airflow flowing out of the first air outlet 114, the greater the distance between the end of the first region 112 separated by the wind wall 116 and the load-bearing surface 111. Optionally, the speed of the first fan can be greater than 800 rpm.

[0050] Optionally, the outer periphery of the bearing surface 111 may be polygonal, the first air outlet 114 may be located on one or more sides of the polygon, and blocking structures may be provided on other sides of the polygon. The first area 112 may be an area formed by the wind wall 116 and the blocking structure. During the landing of the aircraft, the aircraft may be blocked by the wind wall 116 and the blocking structure so that the aircraft can land accurately on the bearing surface 111.

[0051] Optionally, the outer periphery of the bearing surface 111 may also be circular, and the first air outlet 114 may be located on at least a portion of the arc of the circle. The remaining arc portion of the circle may be provided with the above-mentioned blocking structure to cooperate with the wind wall 116 to enable the aircraft to land accurately, which will not be elaborated here.

[0052] Therefore, according to the aircraft docking platform 100 provided in this embodiment, a first air outlet 114 is provided at the outer edge of the bearing surface 111 of the bracket 10, so that the first airflow forms a wind wall 116 on the first side of the bracket 10 through the first air outlet 114, dividing the first side of the bracket 10 into two areas, and the bearing surface 111 is provided in the first area 112. Since the existence of the wind wall 116 can guide the position of the aircraft located in the first area 112, it is difficult for the aircraft located in the first area 112 to pass through the wind wall 116 to enter the second area 113 during the falling process, so that the wind wall 116 can guide the aircraft to land accurately on the bearing surface 111, which is beneficial for performing work such as charging, data transmission, maintenance, etc. on the aircraft after landing, and avoiding damage to the aircraft due to inaccurate landing of the aircraft.

[0053] According to an embodiment of the present application, the first air outlet 114 is disposed around the outer periphery of the bearing surface 111. In other words, the air wall 116 may be annular and disposed around the bearing surface 111.

[0054] Specifically, the first area 112 defined by the annular wind wall 116 on the first side of the bracket 10 can be formed into a guide channel. The lower end of the guide channel can correspond to the support surface 111 of the bracket 10, and the upper end of the guide channel can face away from the support surface 111, for example, toward an oblique upward direction. In addition, the guide channel can extend along the second direction.

[0055] Optionally, the bearing surface 111 may be rectangular, and the first air outlet 114 may be arranged around the four sides of the rectangle; the bearing surface 111 may also be circular, and the first air outlet 114 may be arranged around the arc edge of the circle.

[0056] In this embodiment, since the first air outlet 114 surrounds the outer periphery of the supporting surface 111, the first airflow flowing out from the first air outlet 114 can form an annular wind wall 116, and the annular wind wall 116 can surround the first area 112. Therefore, when the aircraft lands in the first area 112, when the aircraft deviates from the supporting surface 111, the strong airflow in the wind wall 116 can blow the aircraft back into the first area 112, which is conducive to the precise landing of the aircraft.

[0057] According to one embodiment of the present application, Figure 1 As shown, the bracket 10 includes a main body 11 and an extension portion 12. At least a portion of the first side surface of the main body 11 forms a bearing surface 111. The extension portion 12 is disposed on the first side surface of the main body 11 and extends away from the main body 11. The extension portion 12 surrounds the bearing surface 111 and defines a first channel 121 extending along the extension portion 12. A first airflow enters the first channel 121 through a first end of the first channel 121, and a second end of the first channel 121 forms a first air outlet 114.

[0058] That is to say, the bracket 10 is mainly composed of a main body 11 and an extension part 12, wherein the main body 11 may have a bearing surface 111, and the bearing surface 111 may be composed of part or all of the first side surface of the main body 11. For example, the first side surface of the main body 11 may be the upper side surface of the main body 11, and a part of the upper side surface may be formed as the bearing surface 111.

[0059] In addition, the outer periphery of the first side surface of the main body 11 can be connected to the extension portion 12. The extension portion 12 can extend in a direction away from the main body 11, and the extension portion 12 has a first channel 121. The first channel 121 can extend along the extension direction of the extension portion 12. The extension direction of the extension portion 12 can be a direction from one end of the extension portion 12 to the other end of the extension portion 12, wherein the one end of the extension portion 12 is connected to the support surface 111, and the other end of the extension portion 12 is located on the first side of the support surface 111.

[0060] For example, the first airflow can flow into the first channel 121 from the lower end of the first channel 121 and flow out of the first channel 121 from the upper end of the first channel 121. The upper end of the first channel 121 can be formed as a first air outlet 114, so that the first airflow forms an air wall 116 after flowing out of the upper end of the first channel 121. In other words, the lower end of the first channel 121 can serve as the inflow end of the first airflow, and the upper end of the first channel 121 can serve as the outflow end of the first airflow.

[0061] Among them, the extension direction of the first channel 121 can be a vertical direction. At this time, the extension direction of the wind wall 116 can be a vertical direction. When the bearing surface 111 extends in the horizontal direction, the angle between the extension direction of the wind wall 116 and the extension direction of the bearing surface 111 is 90°.

[0062] In this embodiment, a first channel 121 is provided within the extension portion 12, allowing the first airflow to flow out of the first air outlet 114 along the extension direction of the first channel 121. Therefore, the extension direction of the wind wall 116 can be controlled by the extension direction of the first channel 121, thereby controlling the range of the first area 112 separated by the wind wall 116 to meet the needs of different aircraft. Furthermore, because the first air outlet 114 is provided at the second end of the first channel 121, the first air outlet 114 is closer to the landing aircraft than to the support surface 111, thereby preventing the aircraft from being disturbed by the airflow from the wind wall 116 when it approaches the support surface 111.

[0063] According to one embodiment of the present application, Figure 4 and Figure 5 As shown, the first channel 121 is trumpet-shaped, so that the angle between the extension direction of the wind wall 116 and the bearing surface 111 is not less than 90° and not more than 120°.

[0064] Specifically, the shape of the first channel 121 can be approximately trumpet-shaped, with the trumpet-shaped small opening facing the support surface 111 and the trumpet-shaped large opening facing away from the support surface 111. For example, the trumpet-shaped small opening can face downward, and the trumpet-shaped large opening can face upward. In other words, the first channel 121 can be approximately funnel-shaped.

[0065] The wind wall 116 formed after the first airflow flows along the trumpet-shaped first channel 121 can be inclined relative to the support surface 111. For example, if the support surface 111 extends along the first direction, the direction perpendicular to the support surface 111 can be the second direction. The angle between the wind wall 116 and the second direction can be α, where 0°<α≤30°. The angle between the extension direction of the first channel 121 and the support surface 111 is the same as the angle between the extension direction of the wind wall 116 and the support surface 111. For example, the angle between the extension direction of the wind wall 116 and the support surface 111 can be 100°, 110°, 115°, 120°, etc.

[0066] For example, the bearing surface 111 can be rectangular and extend in the horizontal direction, the first channel 121 can be arranged at the four sides of the rectangle, and the angle between the first channel 121 and the vertical direction can be 25°. At this time, the angle between the formed wind wall 116 and the vertical direction can also be 25°, and the shape of the first area 112 can be a quadrangular pyramid; the bearing surface 111 can also be circular, the first channel 121 can be arranged at the circumference of the circle, and the angle between the first channel 121 and the vertical direction can be 25°. At this time, the angle between the formed wind wall 116 and the vertical direction can also be 25°, and the shape of the first area 112 can be a truncated cone.

[0067] In this embodiment, by setting the shape of the first channel 121 to a trumpet shape, the angle between the wind wall 116 and the supporting surface 111 can be controlled, so that the first area 112 is formed into a shape with a small end close to the supporting surface 111 and a large end away from the supporting surface 111, so as to form a convergence for the aircraft during the landing process and guide the aircraft to land at a predetermined position.

[0068] According to one embodiment of the present application, Figure 1 and Figure 2 As shown, a grid 122 is provided in the first channel 121 , and the grid 122 divides the first channel 121 into a plurality of microchannels, each of which extends along the extension direction of the extension portion 12 .

[0069] Specifically, the grille 122 within the first channel 121 can extend along the extension direction of the extension portion 12, thereby dividing the first channel 121 into a plurality of microchannels. The grille 122 can include a plurality of partition plates, each of which can extend along the extension direction of the extension portion 12, and adjacent partition plates can be spaced apart to form microchannels. Each microchannel can extend along the extension direction of the extension portion 12, and the inner wall of each microchannel is formed by the side surfaces of two adjacent partition plates facing each other and a portion of the inner wall of the first channel 121.

[0070] For example, the support surface 111 extends horizontally, and the first channel 121 extends diagonally upward. The extension portion 12 may include a first extension plate 123 and a second extension plate 124. The first extension plate 123 and the second extension plate 124 may both be disposed around the support surface 111, wherein the first extension plate 123 may surround the second extension plate 124, and the first extension plate 123 and the second extension plate 124 are spaced apart to form the first channel 121. Each partition plate is located between the first extension plate 123 and the second extension plate 124, with one widthwise end of each partition plate connected to the first extension plate 123 and the other widthwise end of each partition plate connected to the second extension plate 124. The longitudinal direction of each partition plate is diagonally upward. The multiple microchannels formed by the multiple partition plates are spaced apart horizontally, and each microchannel extends diagonally upward.

[0071] In this embodiment, by providing a grille 122 within the first channel 121, the first channel 121 is divided into a plurality of microchannels, thereby reducing the cross-section of the first airflow flowing within the first channel 121, thereby increasing the flow rate of the first airflow and improving the airflow intensity of the wind wall 116. In addition, the provision of the grille 122 can also prevent leaves, mosquitoes, etc. from entering the first channel 121 in outdoor environments.

[0072] According to one embodiment of the present application, Figure 2 As shown, the bearing surface 111 has a second air outlet 115, and the aircraft docking platform 100 also includes a second airflow generator 30, which is used to generate a second airflow. The second airflow flows to the first side of the bracket 10 through the second air outlet 115. The second airflow counteracts the airflow of the aircraft flowing to the bearing surface 111 to form a negative pressure area on the first side of the bracket 10.

[0073] Specifically, the bearing surface 111 may be provided with a second air outlet 115 , and the number of the second air outlet 115 may be one or more, which is not limited herein. The second airflow generator 30 may generate a second airflow, and the generated second airflow may flow toward the first side of the bracket 10 through the second air outlet 115 .

[0074] Taking the second airflow flowing upward along the second direction on the first side of the bracket 10 as an example, during the landing of the aircraft, the rotation of the aircraft's blades can cause the aircraft to generate an airflow flowing toward the load-bearing surface 111. The airflow can flow downward along the second direction and form a counter-flow with the second airflow, so that the air between the aircraft and the load-bearing surface 111 is blown out, thereby forming a pressure difference between the upper and lower sides of the aircraft, so that a negative pressure area can be formed between the aircraft and the load-bearing surface 111. The negative pressure area can have an attractive effect on the aircraft, guiding the aircraft to land toward the load-bearing surface 111.

[0075] Optionally, the second airflow generator 30 may include a second fan, and the rotation speed of the second fan may be 200 r / min to 300 r / min.

[0076] It should be noted that the second airflow generated by the second airflow generator 30 can also exert upward lift on the aircraft during takeoff. In this case, the speed of the second fan can be 600-700 rpm. During takeoff, the intensity of the second airflow generated by the second airflow generator 30 can be controlled to provide flight assistance for the aircraft.

[0077] In this embodiment, the second airflow flowing out from the second air outlet 115 and the airflow flowing from the aircraft to the supporting surface 111 are offset. On the one hand, weeds, flying stones and other foreign objects between the aircraft and the supporting surface 111 can be blown away. On the other hand, the negative pressure area formed can attract the aircraft and guide it to land at the correct position.

[0078] According to one embodiment of the present application, Figure 4 and Figure 5 As shown, the bracket 10 has a accommodating cavity 13, and the aircraft docking platform 100 also includes a partition 14, which is arranged in the accommodating cavity 13 to separate the accommodating cavity 13 into a first chamber 131 and a second chamber 132. The first chamber 131 is connected to the first air outlet 114, and the second chamber 132 is connected to the second air outlet 115.

[0079] Specifically, the main body 11 in the bracket 10 may have a receiving cavity 13, and a partition 14 may be provided in the receiving cavity 13. The partition 14 can separate the receiving cavity 13 into two chambers, namely a first chamber 131 and a second chamber 132. The partition 14 can be connected to the inner wall of the receiving cavity 13.

[0080] In addition, the first chamber 131 can be in communication with the first air outlet 114. For example, the first chamber 131 can be in communication with the lower end of the first channel 121, thereby communicating with the first air outlet 114 through the first channel 121. The second chamber 132 can be in communication with the second air outlet 115. For example, the bearing surface 111 can be provided on a side panel on the upper side of the main body 11, and the side panel has a hole connecting the second chamber 132 and the second air outlet 115. The upper surface of the side panel can form the bearing surface 111, and the lower surface of the side panel can form a portion of the inner wall surface of the second chamber 132.

[0081] Optionally, the first chamber 131 can be located on the side of the second chamber 132 away from the bearing surface 111. For example, the first chamber 131 can be located below the second chamber 132, and the bearing surface 111 can be located above the second chamber 132, so that the first chamber 131 is connected to the first channel 121.

[0082] In this embodiment, the chamber is divided into two parts by the partition 14, which is conducive to separating the first airflow and the second airflow, so that the first airflow and the second airflow can flow out from their respective air outlets.

[0083] According to one embodiment of the present application, Figure 4 and Figure 5 As shown, the first airflow generator 20 is disposed in the first chamber 131 , and the second airflow generator 30 is disposed in the second chamber 132 . The first chamber 131 and the second chamber 132 are isolated from each other.

[0084] For example, the first airflow generator 20 may include a first fan, which may be accommodated in the first chamber 131 to form a first airflow in the first chamber 131 , and the first airflow flows out from the first air outlet 114 along the first channel 121 communicating with the first chamber 131 .

[0085] The second airflow generator 30 may include a second fan. The second fan may be accommodated in the second chamber 132 to form a second airflow in the second chamber 132 . The second airflow may flow out through the second air outlet 115 communicating with the second chamber 132 .

[0086] In addition, the first chamber 131 and the second chamber 132 can be isolated from each other, that is, a seal can be formed between the first chamber 131 and the second chamber 132 to prevent the first airflow from flowing into the second chamber 132 and the second airflow from flowing into the first chamber 131, thereby avoiding interference between the two airflows and affecting the formation of the wind wall 116 and the negative pressure area.

[0087] According to one embodiment of the present application, the chamber has a top wall, a bottom wall and side walls, the top wall corresponds to the carrying surface 111 , and the partition 14 includes a first partition plate 141 , a second partition plate 142 and a third partition plate 143 .

[0088] Specifically, if Figure 4 and Figure 5 As shown, the horizontal direction is defined as the first direction, and the vertical direction is defined as the second direction. The top wall is located above the bottom wall, the upper ends of the side walls are connected to the top wall, and the lower ends of the side walls are connected to the bottom wall. A first partition 141 is connected to the top wall, a portion of the first partition 141 is spaced apart from the top wall, and a second airflow generator 30 is mounted on the first partition 141. A second partition 142 is provided on a side of the first partition 141 close to the bottom wall, and a first airflow generator 20 is provided between the second partition 142 and the bottom wall. A third partition 143 is located between the second partition 142 and the side wall, a first end of the third partition 143 is connected to the outer surface of the second partition 142, a second end of the third partition 143 extends toward the first air outlet 114, and the outer surface of the third partition 143 is spaced apart from the side wall.

[0089] That is to say, the inner wall of the chamber is mainly composed of a top wall, a bottom wall and a side wall, the bearing surface 111 can correspond to the top wall, the lower surface of the top wall can face the chamber, and the upper surface of the top wall can face the first side of the bracket 10 and form a bearing surface 111.

[0090] The partition 14 is mainly composed of a first partition 141, a second partition 142, and a third partition 143. A portion of the first partition 141 can be spaced apart from the top wall, another portion of the first partition 141 can be connected to the top wall, and the second airflow generator 30 can be mounted on the first partition 141, located between the first partition 141 and the top wall. Optionally, a portion of the first partition 141 can be parallel to the bearing surface 111, and the bearing surface 111 can be parallel to the first direction. The shaft of the blades of the second fan can extend along the second direction. The second air outlet 115 can be provided on the top wall, and the second fan can be directly opposite the second air outlet 115, which is conducive to the second airflow flowing out of the second air outlet 115 to flow along the second direction.

[0091] The second partition plate 142 can be connected to the side of the first partition plate 141 facing the bottom wall, and the second airflow generator 30 can be disposed between the second partition plate 142 and the bottom wall. For example, the first end of the second partition plate 142 can be connected to the edge of the first partition plate 141, and the second end of the second partition plate 142 can extend toward the bottom wall. The second end of the second partition plate 142 can be spaced apart from the bottom wall, and the second airflow generator 30 can be located between the second end of the second partition plate 142 and the bottom wall. Alternatively, the second partition plate 142 can be inclined relative to the first partition plate 141 and arranged around the outer edge of the first partition plate 141.

[0092] Optionally, the second end of the second partition 142 is also connected to multiple support columns 15, the upper end of each support column 15 can be connected to the lower end of the second partition 142, the lower end of the support column 15 can be connected to the bottom wall, and adjacent support columns 15 can be spaced apart and distributed.

[0093] The third partition 143 can be located between the second partition 142 and the side wall. For example, the lower end of the third partition 143 can be connected to the lower end of the second partition 142, and the upper end of the third partition 143 can extend toward the first air outlet 114, and the outer surface of the third partition 143 is spaced apart from the side wall to form a channel for allowing the first airflow to flow to the air outlet.

[0094] Optionally, the upper end of the third partition 143 can be staggered with the first air outlet 114 in the horizontal plane, the first channel 121 can extend obliquely relative to the vertical direction, and the third partition 143 can also extend obliquely relative to the vertical direction, and the inclination angle of the first channel 121 and the inclination angle of the third partition 143 can be the same.

[0095] According to one embodiment of the present application, Figure 1 As shown, the aircraft docking platform 100 further includes a charger 40 . The charger 40 is disposed on the bracket 10 , and at least a portion of the charger 40 corresponds to the carrying surface 111 to form a charging area on a first side of the carrying surface 111 .

[0096] The charger 40 may include at least one of a wireless charger and a wired charger. The charger 40 may be disposed on the bracket 10. For example, a portion of the capacitor may be accommodated within the accommodating cavity 13. A portion or all of the charger 40 may be disposed corresponding to the carrying surface 111. For example, the charging interface or induction structure of the charger 40 may be disposed on the carrying surface 111, thereby forming a charging area on the first side of the carrying surface 111. When the aircraft lands in the charging area on the carrying surface 111, the charger 40 may charge the aircraft.

[0097] Optionally, the charger 40 may include an induction member 41, a circuit board 42, a wire 43, and a battery 44. Part of the induction member 41, the circuit board 42, the wire 43, and the battery 44 may be accommodated in the accommodating cavity 13. The induction member 41 may correspond to the carrying surface 111, and the carrying surface 111 may have a mounting hole for the induction member 41. A part of the induction member 41 may be inserted into the mounting hole of the induction member 41 to form an induction area on the first side of the carrying surface 111. The induction member 41 may be electrically connected to the circuit board 42. The circuit board 42 may be located on the side of the first partition 141 facing the bottom wall. The first airflow generator 20 and the second airflow generator 30 may also be electrically connected to the circuit board 42. The circuit board 42 may also be connected to the battery 44 via the wire 43, and the aircraft docked on the carrying surface 111 may be charged via the battery 44 and the induction member 41.

[0098] Optionally, the sensing element 41 may correspond to the middle of the carrying surface 111, the number of second airflow generators 30 may be multiple, the sensing element 41 may be accommodated within the first chamber 131, and the multiple second airflow generators 30 may be arranged around the sensing element 41. The second air outlet 115 may be staggered from the charging area to avoid interference between the second air outlet 115 and the sensing element 41. Furthermore, the annular wind wall 116 may cooperate with the centrally located sensing element 41, facilitating the aircraft's landing in the middle of the carrying surface 111, thereby facing the centrally located sensing element 41.

[0099] Optionally, the aircraft docking platform 100 may further include a data transmitter to exchange data information with the aircraft when the aircraft is docked on the aircraft docking platform 100 .

[0100] In this embodiment, by using the wind wall 116 to guide the landing of the aircraft, the aircraft can be accurately landed within the charging area, so that the charger 40 can charge the aircraft, avoiding the difficulty of docking the aircraft with the charging area due to inaccurate landing of the aircraft and affecting the use of the aircraft.

[0101] The following will describe in detail the specific process of the aircraft landing on the aircraft docking platform 100 in combination with specific embodiments.

[0102] In the first stage, the distance h between the aircraft and the bearing surface 111 is obtained, and it is judged whether h is less than the first preset value. If the judgment is yes, the first air flow generator 20 is started to generate the first air flow, and the first air flow flows out from the first air outlet 114 to form the wind wall 116, and the aircraft slowly descends along the guidance of the wind wall 116.

[0103] In the second stage, it is judged whether h is less than the second preset value. If the judgment is yes, the second air flow generator 30 is started to generate the second air flow, and the second air flow flows out from the second air outlet 115 and forms a negative pressure area by counteracting the air flow flowing towards the bearing surface 111 generated by the aircraft, attracting the aircraft to continue to land.

[0104] In the third stage, it is judged whether h is less than the third preset value. If the judgment is yes, the first air flow generator 20 and the second air flow generator 30 stop generating air flow, the charger 40 is started to charge the aircraft, and the data transmitter can perform data information interaction with the aircraft.

[0105] Optionally, the first preset value is not less than 20 cm and not more than 30 cm, the second preset value is greater than 0 cm and not more than 10 cm, and the third preset value is not more than 0 cm. When 20 cm ≤ h ≤ 30 cm, a wind wall can be formed on the first side of the bearing surface 111 to guide the small aircraft to land within the first area 112; when 0 < h ≤ 10 cm, a negative pressure area can be formed on the first side of the bearing surface 111 to attract the small aircraft to land at the accurate position; when h ≤ 0, the charging area on the bearing surface 111 can charge the small aircraft. That is to say, during the gradual landing of the small aircraft, the docking platform 100 can first form the wind wall 116 to guide the small aircraft, and after the small aircraft continues to descend, the docking platform 100 can generate a negative pressure area to attract the small aircraft. After the small aircraft lands on the bearing surface, the docking platform 100 can start to charge the small aircraft.

[0106] In summary, according to the aircraft docking platform 100 provided in this embodiment, the wind wall 116 can prevent the aircraft located in the first area 112 from passing through the wind wall 116 and entering the second area 113 during the descent, thereby guiding the aircraft to land accurately on the supporting surface 111, which is conducive to performing tasks such as charging, data transmission, and maintenance on the aircraft after landing, and avoiding damage to the aircraft due to inaccurate landing.

[0107] Although some specific embodiments of the present application have been described in detail by way of examples, it should be understood by those skilled in the art that the above examples are for illustration only and are not intended to limit the scope of the present application. It should be understood by those skilled in the art that the above embodiments may be modified without departing from the scope and spirit of the present application. The scope of the present application is defined by the appended claims.

Claims

1. An aircraft docking platform, characterized in that: include: a bracket, wherein a first side of the bracket has a bearing surface and a first air outlet, wherein the first air outlet is provided at least at a portion of an outer periphery of the bearing surface; a first airflow generator capable of generating a first airflow, the first airflow flowing toward the first side of the bracket through the first air outlet to form a wind wall on the first side of the bracket extending away from the bearing surface, the wind wall capable of dividing an area on the first side of the bracket into a first area and a second area in a first direction, the bearing surface being located within the first area, and the wind wall capable of exerting a force on an aircraft located within the first area toward an interior of the first area; The bracket includes: a main body, at least a portion of a first side surface of the main body is formed as the bearing surface; An extension portion is provided on a first side surface of the main body and extends in a direction away from the main body. The extension portion is provided around the supporting surface. The extension portion has a first channel extending along its own extension direction. The first airflow enters the first channel through a first end of the first channel, and the second end of the first channel forms the first air outlet.

2. The aircraft docking platform according to claim 1, characterized in that: The first air outlet is arranged around the outer periphery of the bearing surface.

3. The aircraft docking platform according to claim 1, characterized in that: The first channel is trumpet-shaped, so that an angle between an extension direction of the wind wall and the bearing surface is not less than 90° and not more than 120°.

4. The aircraft docking platform according to claim 1, characterized in that: A grid is provided in the first channel, and the grid divides the first channel into a plurality of microchannels, each of the microchannels extending along an extending direction of the extending portion.

5. The aircraft docking platform according to claim 1, characterized in that: The bearing surface has a second air outlet, and the aircraft docking platform further includes: The second airflow generator is used to generate a second airflow, and the second airflow flows to the first side of the bracket through the second air outlet. The second airflow and the airflow from the aircraft to the bearing surface form a counter-action to form a negative pressure area on the first side of the bracket.

6. The aircraft docking platform according to claim 5, characterized in that: The bracket has a receiving cavity, and the aircraft docking platform further includes: A partition is provided in the accommodating cavity to divide the accommodating cavity into a first chamber and a second chamber, wherein the first chamber is communicated with the first air outlet, and the second chamber is communicated with the second air outlet.

7. The aircraft docking platform according to claim 6, characterized in that: The first airflow generator is disposed in the first chamber, the second airflow generator is disposed in the second chamber, and the first chamber and the second chamber are isolated from each other.

8. The aircraft docking platform according to claim 7, characterized in that: The chamber has a top wall, a bottom wall and side walls, the top wall corresponds to the supporting surface, and the partition comprises: a first baffle, the first baffle being connected to the top wall, a portion of the first baffle being spaced apart from the top wall, and the second airflow generator being mounted on the first baffle; a second partition plate, the second partition plate being arranged on a side of the first partition plate close to the bottom wall, and a first airflow generator being arranged between the second partition plate and the bottom wall; A third partition, the third partition is located between the second partition and the side wall, the first end of the third partition is connected to the outer surface of the second partition, the second end of the third partition extends toward the first air outlet, and the outer surface of the third partition is spaced apart from the side wall.

9. The aircraft docking platform according to any one of claims 1 to 8, characterized in that: Also includes: A charger is provided on the bracket, and at least a portion of the charger corresponds to the carrying surface to form a charging area on a first side of the carrying surface.

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