A landing field for electric aircraft

Abstract

The utility model discloses a kind of landing field for electric aircraft, it is related to electric aircraft landing technical field.The utility model includes adjusting chassis and the landing platform of movable loading in the upper portion of adjusting chassis, the adjusting chassis includes support, the bottom plate of slidingly being arranged on the upper portion of support, and the air rod for the linear reciprocating drive of bottom plate;The landing platform includes the lower support of being fixed in the upper portion of bottom plate, the upper support of being arranged in parallel in the upper portion of lower support, the scissor lift frame of being folded between lower support and upper support, and the receiving platform of being arranged in the upper side of upper support.The utility model is through the sliding structure of setting adjusting chassis and the scissor lift frame of landing platform, the position and height of landing field can be flexibly adjusted, to adapt to different models, size electric aircraft and various complex landing terrain conditions, realize the accurate adjustment of three-dimensional space, greatly improve the versatility and practicality of landing field.

Description

Technical Field

[0001] This utility model belongs to the field of electric aircraft landing technology, and in particular relates to an airport for electric aircraft. Background Technology

[0002] With the rapid development of urban air traffic and the low-altitude economy, electric aircraft are increasingly being used in logistics, urban transportation, and emergency rescue. The construction of supporting infrastructure has also become a research hotspot. Among these, dedicated landing pads for electric aircraft, as key facilities for takeoff, landing, parking, charging, and maintenance, have significant practical importance. Currently, traditional aircraft landing platforms are mostly fixed structures, primarily used for helicopters or large drones. Their design is relatively simple, typically consisting of a fixed, flat platform without altitude adjustment or position movement capabilities. While this structure is suitable for scenarios with stable ground conditions and large aircraft sizes, it has significant shortcomings when facing the following new application scenarios:

[0003] Traditional landing pads cannot dynamically adjust to different aircraft types, landing angles, or terrain conditions, resulting in low docking accuracy and affecting safe takeoffs and landings. They also lack horizontal displacement and vertical takeoff / landing capabilities, making it difficult to meet deployment needs in complex environments, such as rooftops or temporary landing sites on mobile platforms (ships, vehicles).

[0004] To address these issues, we provide an airport for electric aircraft. Utility Model Content

[0005] To solve the above-mentioned technical problems, this utility model is achieved through the following technical solution:

[0006] This utility model relates to a landing pad for an electric aircraft, comprising an adjustable base frame and a landing platform movably mounted on the upper part of the adjustable base frame. The adjustable base frame includes a support frame, a base plate slidably disposed above the edge of the support frame, and a pneumatic strut for linear reciprocating drive of the base plate. The landing platform includes a lower support frame fixed to the upper part of the base plate, an upper support frame parallel to the lower support frame, a scissor lift frame folded between the lower support frame and the upper support frame, and a receiving platform disposed on the upper side of the upper support frame.

[0007] The present invention is further configured such that a slider is fixed on the lower side edge of the base plate, and the slider slides in cooperation with the guide rail structure on the side of the bracket.

[0008] The present invention is further configured such that the telescopic end of the gas rod is fixed at the middle position of the side of the base plate, and the end of the gas rod body is fixed at the middle position of the inner side of the end of the bracket.

[0009] The present invention is further configured such that the top of the scissor lift frame is provided with an upper free end, and the bottom of the scissor lift frame is provided with a lower free end, the upper free end and the lower free end being obliquely opposite each other.

[0010] The present invention is further configured such that the upper free end is movably fitted in the inner groove of the upper support via a roller, the other end of the upper part of the scissor lift frame away from the upper free end is rotatably connected to the upper support, the lower free end is movably fitted in the inner groove of the lower support via a roller, and the other end of the lower part of the scissor lift frame away from the lower free end is rotatably connected to the lower support.

[0011] The present invention is further configured such that a hydraulic rod is movably and symmetrically installed on the lower free end via a connector, a transmission component is rotatably connected to the telescopic end of the hydraulic rod, a connecting rod is fixedly inserted through the end of the transmission component, and the connecting rod is laterally fixed between the scissor lift frames.

[0012] This utility model has the following beneficial effects:

[0013] 1. This utility model, by setting up a sliding structure for adjusting the base frame and a scissor lift for the landing platform, can flexibly adjust the position and height of the landing area, thereby adapting to different models and sizes of electric aircraft and various complex landing terrain conditions, achieving precise adjustment in three-dimensional space, and greatly improving the versatility and practicality of the landing area.

[0014] 2. In the landing platform of this utility model, the scissor lift is movably engaged with the inner sliding grooves of the upper and lower supports via rollers, ensuring the stability and reliability of the lifting process, effectively avoiding damage to the aircraft caused by turbulence or instability during takeoff and landing, and ensuring the safety of the aircraft and operators.

[0015] Of course, any product implementing this utility model does not necessarily need to achieve all of the advantages described above at the same time. Attached Figure Description

[0016] To more clearly illustrate the technical solutions of the embodiments of this utility model, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 This is a schematic diagram of the overall structure of this utility model.

[0018] Figure 2 This is a schematic diagram of one side of the landing platform of this utility model.

[0019] Figure 3This is a schematic diagram of the other side of the landing platform of this utility model.

[0020] The attached diagram lists the components represented by each number as follows:

[0021] 100. Adjustable base frame; 101. Support frame; 102. Gas spring; 103. Base plate; 200. Drop platform; 201. Lower support frame; 202. Scissor lift frame; 203. Hydraulic rod; 204. Receiving platform; 205. Upper support frame; 206. Upper free end; 207. Lower free end; 208. Connecting parts; 209. Connecting rod; 210. Transmission parts. Detailed Implementation

[0022] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0023] Example

[0024] Please see Figure 1-3 This utility model is a landing pad for an electric aircraft, including an adjustable base frame 100 and a landing platform 200 movably mounted on the upper part of the adjustable base frame 100. The adjustable base frame 100 includes a support 101, a base plate 103 slidably disposed above the side of the support 101, and a pneumatic rod 102 for linear reciprocating drive of the base plate 103. The landing platform 200 includes a lower support 201 fixed to the upper part of the base plate 103, an upper support 205 parallel to the lower support 201, a scissor lift 202 folded between the lower support 201 and the upper support 205, and a receiving platform 204 disposed on the upper side of the upper support 205.

[0025] Specifically, the top of the scissor lift 202 is provided with an upper free end 206, and the bottom of the scissor lift 202 is provided with a lower free end 207, with the upper free end 206 and the lower free end 207 being obliquely opposite each other.

[0026] The upper free end 206 is movably fitted in the inner groove of the upper support 205 via rollers. The other end of the upper part of the scissor lift frame 202 away from the upper free end 206 is rotatably connected to the upper support 205. The lower free end 207 is movably fitted in the inner groove of the lower support 201 via rollers. The other end of the lower part of the scissor lift frame 202 away from the lower free end 207 is rotatably connected to the lower support 201.

[0027] The lower free end 207 is symmetrically mounted with a hydraulic rod 203 via a connector 208. The telescopic end of the hydraulic rod 203 is rotatably connected to a transmission component 210. A connecting rod 209 is fixed through and fixed at the end of the transmission component 210. The connecting rod 209 is laterally fixed between the scissor lift frames 202.

[0028] Furthermore, a slider is fixed to the lower side edge of the base plate 103, and the slider slides in cooperation with the guide rail structure on the side of the bracket 101. The telescopic end of the gas rod 102 is fixed to the middle position of the side of the base plate 103, and the main body end of the gas rod 102 is fixed to the middle position of the inner side of the end of the bracket 101.

[0029] In this embodiment, the landing pad for the electric aircraft is first fixedly installed in the designated position to ensure the support 101 is stable and reliable. When the electric aircraft needs to land, the extension and retraction of the pneumatic strut 102 drives the base plate 103 to slide along the guide rail structure on the side of the support 101, thereby moving the entire landing platform 200 back and forth to adjust its position and align it with the landing trajectory of the aircraft. Simultaneously, the scissor lift 202 in the landing platform 200 can be height-adjusted via the hydraulic strut 203: when the hydraulic strut 203 extends or retracts, the transmission component 210 and connecting rod 209 drive the scissor lift 202 to expand or contract, thereby driving the upper support 205 and the receiving platform 204 to rise or fall, achieving the height adjustment required for docking the aircraft. The upper free end 206 and lower free end 207 of the scissor lift 202 slide within the grooves of the upper support 205 and lower support 201 respectively via rollers, ensuring the smoothness of the lifting process. The landing platform 204 is used to support the aircraft after landing. It can be equipped with anti-slip, charging, or fixing devices according to actual needs to ensure stable docking and subsequent operations. The overall structure achieves flexible adjustment in three-dimensional space through the coordinated action of the base frame 100 and the landing platform 200, making it suitable for landing requirements of different environments and aircraft types.

[0030] In the description of this specification, references to terms such as "an embodiment," "example," "specific example," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0031] The preferred embodiments of this utility model disclosed above are merely illustrative of the present utility model. These preferred embodiments do not exhaustively describe all details, nor do they limit the utility model to the specific implementations described. Clearly, many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of this utility model, thereby enabling those skilled in the art to better understand and utilize it. This utility model is limited only by the claims and their full scope and equivalents.

Claims

1. An airfield for electric aircraft, comprising an adjustable base frame (100) and a landing platform (200) movably mounted on the upper part of the adjustable base frame (100), characterized in that: The adjustable base frame (100) includes a support (101), a base plate (103) slidably disposed above the side of the support (101), and a pneumatic rod (102) for linear reciprocating drive of the base plate (103); the landing platform (200) includes a lower support (201) fixed to the upper part of the base plate (103), an upper support (205) parallel to the lower support (201), a scissor lift frame (202) folded between the lower support (201) and the upper support (205), and a receiving platform (204) disposed on the upper side of the upper support (205).

2. The parking area for an electric aircraft according to claim 1, characterized in that, A slider is fixed to the lower side edge of the base plate (103), and the slider slides in cooperation with the guide rail structure on the side of the bracket (101).

3. The parking area for an electric aircraft according to claim 1, characterized in that, The telescopic end of the air rod (102) is fixed to the middle position of the side of the base plate (103), and the end of the main body of the air rod (102) is fixed to the middle position of the inner side of the end of the bracket (101).

4. The parking area for an electric aircraft according to claim 1, characterized in that, The top of the scissor lift (202) is provided with an upper free end (206), and the bottom of the scissor lift (202) is provided with a lower free end (207). The upper free end (206) and the lower free end (207) are obliquely opposite each other.

5. A parking area for an electric aircraft according to claim 4, characterized in that, The upper free end (206) is movably fitted with a roller in the inner groove of the upper support (205). The other end of the upper part of the scissor lift frame (202) away from the upper free end (206) is rotatably connected to the upper support (205). The lower free end (207) is movably fitted with a roller in the inner groove of the lower support (201). The other end of the lower part of the scissor lift frame (202) away from the lower free end (207) is rotatably connected to the lower support (201).

6. The parking area for an electric aircraft according to claim 4, characterized in that, The lower free end (207) is symmetrically mounted with a hydraulic rod (203) via a connector (208). The telescopic end of the hydraulic rod (203) is rotatably connected to a transmission component (210). A connecting rod (209) is fixed through the end of the transmission component (210). The connecting rod (209) is laterally fixed between the scissor lift frames (202).

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