Unmanned aerial vehicle landing platform

Abstract

The utility model provides an unmanned aerial vehicle landing platform, and relates to the technical field of unmanned aerial vehicles. The utility model provides an unmanned aerial vehicle landing platform. The unmanned aerial vehicle landing platform comprises a central landing part and a plurality of peripheral landing parts, the central landing part is provided with a central landing preparation area; the plurality of peripheral landing parts are arranged around the central landing part, and the plurality of peripheral landing parts are respectively provided with a peripheral landing preparation area; and in the state that the fuselage of the unmanned aerial vehicle lands in the central landing preparation area or any peripheral landing preparation area, the arms of the unmanned aerial vehicle are located above the central landing part and the peripheral landing parts and transversely extend. According to the unmanned aerial vehicle landing platform, the position precision requirement of unmanned aerial vehicle landing is reduced, the unmanned aerial vehicle can be prevented from toppling during landing, the vehicle arms are effectively prevented from being collided and damaged, and the crash risk during unmanned aerial vehicle landing is reduced.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a UAV landing platform. Background Technology

[0002] During drone landing operations, unexpected situations such as equipment malfunctions or external environmental interference often arise, which can significantly affect the accuracy of the landing position. Especially in cases requiring an emergency landing or diversion, not only is it difficult to achieve precise control over the drone's landing point, but there is also the possibility of hangar skylights failing to open properly, further increasing the risk of landing failure or even drone crash. Utility Model Content

[0003] The purpose of this invention is to provide a drone landing platform to reduce the risk of drone crashes due to insufficient positioning accuracy during landing.

[0004] In the first aspect, the drone landing platform provided by this utility model includes: a central landing section and multiple peripheral landing sections;

[0005] The central landing section has a central alternate landing area;

[0006] Multiple peripheral landing sections are arranged around the central landing section, and each of the multiple peripheral landing sections is provided with a peripheral backup landing area;

[0007] When the drone's fuselage lands in the central alternate landing area or any of the peripheral alternate landing areas, the drone's arms are positioned above the central landing section and the peripheral landing section and extend laterally.

[0008] In conjunction with the first aspect, the present invention provides a first possible implementation of the first aspect, wherein a visual landing guidance module is installed at the bottom of the central landing part.

[0009] In conjunction with the first possible implementation of the first aspect, the present invention provides a second possible implementation of the first aspect, wherein the visual landing guidance module includes: a base portion connected to the central landing portion, and a protrusion portion protruding upward relative to the base portion, the surface of the protrusion portion being provided with an optical label.

[0010] In conjunction with the first possible implementation of the first aspect, this utility model provides a third possible implementation of the first aspect, wherein a base is connected below the central landing part or the peripheral landing part, and the visual landing guidance module is connected to the base.

[0011] In conjunction with the first aspect, this utility model provides a fourth possible implementation of the first aspect, wherein the side wall of the central landing part is provided with a side slot communicating with the central alternate landing area.

[0012] In conjunction with the first aspect, this utility model provides a fifth possible implementation of the first aspect, wherein the upper edge of the sidewall of the central alternate landing area is higher than the upper edge of the sidewall of the peripheral alternate landing area.

[0013] In conjunction with the first aspect, this utility model provides a sixth possible implementation of the first aspect, wherein the drone landing platform further includes an outer ring frame surrounding the central landing section;

[0014] The central landing section is coaxial with the outer ring frame, and the multiple peripheral landing sections are located between the central landing section and the outer ring frame.

[0015] In conjunction with the sixth possible implementation of the first aspect, this utility model provides a seventh possible implementation of the first aspect, wherein the peripheral landing portion is configured as an arc surface at the connection point with the outer ring frame, so that the cross-section of the peripheral alternate landing area forms an arc near the outer ring frame.

[0016] In conjunction with the first aspect, this utility model provides an eighth possible implementation of the first aspect, wherein the plurality of peripheral landing portions are a plurality of alternate landing groups, each alternate landing group includes a plurality of peripheral landing portions spaced apart around the central landing portion, and the plurality of alternate landing groups are distributed sequentially from the inside to the outside along the radial direction of the central landing portion.

[0017] In conjunction with the first aspect, this utility model provides a ninth possible implementation of the first aspect, wherein the cross-section of the central alternate landing area is configured as a circle or a polygon.

[0018] The present invention provides the following advantages: by employing a central landing section with a central alternate landing area and multiple peripheral landing sections arranged around the central landing section and having peripheral alternate landing areas, when the UAV fuselage lands in the central alternate landing area or any of the peripheral alternate landing areas, the UAV's arms are located above the central landing section and the peripheral landing sections and extend laterally. This reduces the positional accuracy requirements for UAV landing with a smaller footprint, and is especially suitable for cylindrical UAVs with a columnar fuselage. It can prevent the UAV from tipping over during landing, effectively prevent the arms from being damaged by impact, and reduce the risk of UAV crashing during landing.

[0019] To make the above-mentioned objectives, features and advantages of this utility model more apparent and understandable, preferred embodiments are described below in detail with reference to the accompanying drawings. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in the specific embodiments or related technologies of this utility model, the drawings used in the description of the specific embodiments or related technologies will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0021] Figure 1 A schematic diagram of the drone landing platform provided in this embodiment of the present invention during the drone landing process;

[0022] Figure 2 A schematic diagram of the drone landing platform provided in this embodiment of the present invention in the state after the drone has landed;

[0023] Figure 3 A schematic diagram of a drone landing platform provided in an embodiment of this utility model;

[0024] Figure 4 A schematic diagram of the visual landing guidance module of the UAV landing platform provided in this embodiment of the utility model;

[0025] Figure 5 This is a schematic diagram of the central landing section, the outer landing section, and the outer ring frame of the UAV landing platform provided in this embodiment of the utility model.

[0026] Icons: 100 - Central landing section; 101 - Central alternate landing area; 102 - Side slot; 200 - Outer landing section; 201 - Outer alternate landing area; 202 - Circular curved surface; 300 - Outer ring frame; 400 - UAV; 410 - Fuselage; 420 - Arm; 500 - Visual landing guidance module; 510 - Base section; 520 - Protrusion. Detailed Implementation

[0027] The technical solution of this utility model will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this utility model. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

[0028] In the description of this utility model, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings and are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on this utility model. Furthermore, the terms "first," "second," and "third" are only used to describe differences in name and should not be construed as indicating or implying relative importance. Physical quantities in formulas, unless otherwise specified, should be understood as basic quantities of the International System of Units (SI) base units, or derived quantities derived from basic quantities through mathematical operations such as multiplication, division, differentiation, or integration.

[0029] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0030] like Figure 1 and Figure 2 As shown, the drone landing platform provided in this embodiment includes: a central landing section 100 and multiple peripheral landing sections 200; the central landing section 100 has a central backup landing area 101; the multiple peripheral landing sections 200 are arranged around the central landing section 100, and each of the multiple peripheral landing sections 200 is provided with a peripheral backup landing area 201; when the fuselage 410 of the drone 400 lands in the central backup landing area 101 or any of the peripheral backup landing areas 201, the arms 420 of the drone 400 are located above the central landing section 100 and the peripheral landing sections 200 and extend laterally. The central backup landing area 101 and the peripheral backup landing areas 201 are respectively configured as receiving slots with top openings, and the fuselage 410 of the drone 400 is inserted into the receiving slots when landing.

[0031] In a favorable landing condition, the drone 400's fuselage 410 lands within the central alternate landing area 101. The arms 420 extend from the central alternate landing area 101 to above the outer alternate landing areas 201, supporting and limiting the fuselage 410 against the inner wall of the central alternate landing area 101. The arms 420 are also supported by the tops of the central landing section 100 and multiple outer landing sections 200, thus preventing the drone 400 from tipping over during landing. If the fuselage 410 fails to align with the drone 400 during landing, it can land within the outer alternate landing area 201, where its inner wall supports and limits it. The arms 420 can also extend laterally above the central landing section 100 and the outer landing sections 200. This reduces the required positioning accuracy for drone landing with a smaller footprint, thereby ensuring a safe landing. It is especially suitable for cylindrical drones with a columnar fuselage 410, which can prevent the cylindrical drone from tipping over when landing, effectively prevent the arm 420 from being damaged by impact, and reduce the risk of crash when the drone 400 lands.

[0032] The drone landing platform described in this embodiment can be made of metal or non-metal materials and processed by bonding, welding and other processes. The production cost is low, and the safety of the drone landing can be achieved at a low cost, avoiding greater property losses.

[0033] In an optional implementation, the upper edge of the side wall of the central alternate landing area 101 is higher than the upper edge of the side wall of the outer alternate landing area 201. This height difference can be configured to be 6mm, 7mm, or 8mm, etc. When the fuselage 410 lands in the central alternate landing area 101, the upper edge of the side wall of the central alternate landing area 101 supports the arm 420, which can prevent the arm 420 from hitting the upper edge of the side wall of the outer alternate landing area 201, and can also prevent the rotor from touching the side wall of the outer alternate landing area 201 when rotating, thus ensuring the safety of the UAV 400 landing.

[0034] In one optional embodiment, the ratio of the diameter of the circumscribed circle of the fuselage 410 to the diameter of the central alternate landing area 101 is 0.27 to 0.29; wherein the cross-section of the fuselage 410 and the cross-section of the central alternate landing area 101 are circular or can be considered as approximately circular, and the ratio of the diameter D3 of the circumscribed circle of the fuselage 410 to the diameter D1 of the central alternate landing area 101 can be configured as 0.27, 0.28, or 0.29, etc.

[0035] In another optional embodiment, the ratio of the diameter of the circumscribed circle of the fuselage 410 to the diameter of the inscribed circle of the central alternate landing area 101 is 0.27 to 0.29. When the cross-section of the central alternate landing area 101 is polygonal or irregular in shape, the inscribed circle of the central alternate landing area 101 is used as a design reference, and the ratio of the diameter of the circumscribed circle of the fuselage 410 to the diameter of the inscribed circle of the central alternate landing area 101 can be configured as 0.27, 0.28, or 0.29, etc.

[0036] When the drone 400 lands in the central alternate landing area 101 described in the above embodiment, on the one hand, the diameter of the central alternate landing area 101 is large enough, making it easier for the fuselage 410 to align when it lands, and it can avoid frequent collisions between the fuselage 410 and the inner wall of the central alternate landing area 101; on the other hand, when the fuselage 410 tilts significantly, the fuselage 410 will be righted by touching the inner wall of the central alternate landing area 101, which can effectively prevent the drone 400 from tipping over.

[0037] In one optional embodiment, the ratio of the diameter of the circumscribed circle of the fuselage 410 to the diameter of the cross-section of the peripheral alternate landing area 201 is 0.41 to 0.45; wherein the cross-section of the fuselage 410 and the cross-section of the peripheral alternate landing area 201 are circular or can be considered as approximately circular, and the ratio of the diameter of the circumscribed circle of the fuselage 410 to the diameter of the cross-section of the peripheral alternate landing area 201 can be configured as 0.41, 0.42, 0.43 or 0.44, etc.

[0038] In another optional embodiment, the ratio of the circumscribed circle diameter D3 of the fuselage 410 to the maximum radial dimension D2 of the outer landing zone 201 in the cross-section of the fuselage 410 is 0.41 to 0.45. When the cross-section of the outer landing zone 201 is polygonal or irregular in shape, the maximum radial dimension D2 of the outer landing zone 201 in the cross-section of the fuselage 410 is used as a design reference, and the ratio of the circumscribed circle diameter D3 of the fuselage 410 to the maximum radial dimension D2 of the outer landing zone 201 in the cross-section of the fuselage 410 can be configured as 0.41, 0.42, 0.43, or 0.44, etc.

[0039] When the UAV 400 lands in the outer alternate landing area 201 described in the above embodiment, the outer alternate landing area 201 has sufficient space for the fuselage 410 to align and land in the outer alternate landing area 201. Compared with landing in the central alternate landing area 101, the fuselage 410 can be supported by the side walls of the outer alternate landing area 201 with a smaller tilt amplitude. In other words, in the emergency state when the fuselage 410 lands in the outer alternate landing area 201, the limit on the tilt amplitude of the fuselage 410 is more stringent, which further improves the landing safety of the UAV 400.

[0040] In an optional embodiment, the UAV landing platform further includes an outer ring frame 300 surrounding the central landing section 100; the central landing section 100 and the outer ring frame 300 are coaxial, and multiple peripheral landing sections 200 are located between the central landing section 100 and the outer ring frame 300. The central landing section 100 and the outer ring frame 300 form a concentric circle structure, and multiple peripheral landing sections 200 are arranged circumferentially within the annular area between the central landing section 100 and the outer ring frame 300. This design not only features a compact structure and high space utilization but also excellent structural stability.

[0041] In an optional implementation, the multiple peripheral landing units 200 are divided into multiple backup landing groups. Each backup landing group includes multiple peripheral landing units 200 spaced apart around the central landing unit 100. The multiple backup landing groups are distributed sequentially from the inside to the outside along the radial direction of the central landing unit 100. This increases the number and arrangement area of ​​the peripheral landing units 200, further reducing the positional accuracy requirements for the UAV 400 landing and ensuring the landing safety of the UAV 400 over a wider range.

[0042] In an optional embodiment, the diameter of the outer ring frame 300 is 780mm to 820mm, wherein the diameter of the outer ring frame 300 can be configured as 780mm, 800mm, 810mm or 820mm, etc.

[0043] Furthermore, the cross-section of the central alternate landing area 101 is configured as a circle with a diameter of 330mm to 360mm, or the cross-section of the central alternate landing area 101 is configured as a polygon with an inscribed circle diameter of 330mm to 360mm. The cross-section of the central alternate landing area 101 or the inscribed circle diameter of the cross-section of the central alternate landing area 101 can be configured as 330mm, 340mm, 350mm, or 360mm, etc.

[0044] like Figure 1 and Figure 5 As shown, in an optional embodiment, the outer landing section 200 is configured with an arc-shaped surface 202 at the connection between the outer ring frame 300 and the outer landing section 201, so that the cross-section of the outer landing section 201 forms an arc with a radius of 70mm to 90mm near the outer ring frame 300. By setting this, a smooth transition (arc-shaped surface 202) can be formed at the connection between the landing section 200 and the outer ring frame 300. On the cross-section, multiple outer landing sections 201 form multiple petal-shaped structures surrounding the central landing section 101, avoiding small gaps or sharp corner areas within the outer landing sections 201, thereby reducing the risk of jamming or collision during the landing of the UAV 400.

[0045] like Figure 1 , Figure 3 and Figure 4As shown, a visual landing guidance module 500 is installed at the bottom of the central landing section 100. The visual landing guidance module 500 can be configured with visual optical tags such as QR codes or characters. The UAV 400 can identify the visual signal by installing a corresponding visual detection device in the pod, and then confirm the landing position through visual recognition.

[0046] In an optional embodiment, the visual landing guidance module 500 includes a base portion 510 connected to the central landing portion 100, and a protrusion portion 520 that protrudes upward relative to the base portion 510. The surface of the protrusion portion 520 is provided with an optical label such as a QR code. The surface of the protrusion portion 520 is 20mm to 30mm higher than the base portion 510, thus creating a height difference. Dust and water falling onto the protrusion portion 520 can be discharged downwards with the airflow during the landing of the drone 400, thereby preventing water or dust accumulation from obscuring the optical label.

[0047] In an optional embodiment, a base is connected to the lower part of the central landing section 100 or the peripheral landing section 200, and the visual landing guidance module 500 is connected to the base. Alternatively, the base can be installed on the ground or on a frame above the ground.

[0048] like Figure 3 As shown, in an optional embodiment, the side wall of the central landing section 100 is provided with a side slot 102 that communicates with the central alternate landing area 101. When the UAV 400 lands, the propeller generates a downward airflow that can enter the central alternate landing area 101 and be discharged through the side slot 102, ensuring smooth airflow under the UAV 400 and avoiding interference with the landing attitude of the UAV 400 due to airflow blockage between the landing platform and the UAV 400.

[0049] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this utility model, and are not intended to limit it. Although the utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this utility model.

Claims

1. A drone landing platform, characterized in that, The unmanned aerial vehicle landing platform comprises: a central landing part (100) and a plurality of peripheral landing parts (200); the central landing part (100) has a central landing area (101); the plurality of peripheral landing parts (200) are arranged around the central landing part (100), and each of the peripheral landing parts (200) is provided with a peripheral landing area (201); in a state where the body (410) of the unmanned aerial vehicle (400) lands in the central landing area (101) or any of the peripheral landing areas (201), the arms (420) of the unmanned aerial vehicle (400) are located above the central landing part (100) and the peripheral landing parts (200) and extend laterally.

2. The drone landing platform of claim 1, wherein, The bottom of the central landing part (100) is provided with a visual landing guide module (500).

3. The drone landing platform of claim 2, wherein, The visual landing guide module (500) comprises a base part (510) connected to the central landing part (100) and a raised part (520) raised upward relative to the base part (510), and the surface of the raised part (520) is provided with an optical label.

4. The drone landing platform of claim 2, wherein, A base is connected below the central landing part (100) or the peripheral landing part (200), and the visual landing guide module (500) is connected to the base.

5. The drone landing platform of claim 1 or 2, wherein, The sidewall of the central landing part (100) is provided with a side notch (102) in communication with the central landing area (101).

6. The drone landing platform of claim 1, wherein, The upper edge of the sidewall of the central landing area (101) is higher than the upper edge of the sidewall of the peripheral landing area (201).

7. The drone landing platform of claim 1, wherein, The unmanned aerial vehicle landing platform further comprises an outer ring frame (300) surrounding the central landing part (100). The central landing part (100) is coaxial with the outer ring frame (300), and the plurality of peripheral landing parts (200) are located between the central landing part (100) and the outer ring frame (300).

8. The drone landing platform of claim 7, wherein, The peripheral landing part (200) is configured as a circular arc surface at the connection with the outer ring frame (300), so that the cross section of the peripheral landing area (201) forms an arc near the outer ring frame (300).

9. The drone landing platform of claim 1, wherein, The plurality of peripheral landing parts (200) are divided into a plurality of landing groups, each of which comprises a plurality of peripheral landing parts (200) arranged at intervals around the central landing part (100), and the plurality of landing groups are distributed in sequence from the inside to the outside along the radial direction of the central landing part (100).

10. The drone landing platform of claim 1, wherein, The cross section of the central landing area (101) is configured as a circle or a polygon.

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