Aircraft parking area and vehicles

Abstract

The present application provides an aircraft apron, including: a docking platform for carrying an aircraft; at least two position adjustment mechanisms arranged on the docking platform, the position adjustment mechanism including a movable first rocker arm and a second rocker arm, the first rocker arm and the second rocker arm can cross each other to form a clamping portion for clamping a structural member of the aircraft, and as the first rocker arm and the second rocker arm move, the formation position of the clamping portion changes, thereby driving the aircraft to move from a landing position to a target position. In addition, the present application also provides a vehicle including the above-mentioned aircraft apron. The aircraft apron provided by the present application can use a position adjustment mechanism to drag / push an aircraft that has landed on the docking platform, and move the aircraft from a landing position to a target position, thereby facilitating the operating device of the ground equipment to charge the aircraft, replace the load, replace the battery, or replenish raw materials.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft, and in particular to an aircraft landing pad and a vehicle equipped with the aircraft landing pad. Background Art

[0002] With the continuous development of science and technology and aircraft technology, aircraft have been widely used in many fields. Correspondingly, aircraft helipads used in conjunction with aircraft have also emerged. The aircraft helipad can provide a landing platform for the aircraft, and after the aircraft lands, it can interact with ground devices such as the aircraft helipad, such as charging, changing loads, changing batteries, replenishing raw materials, etc. However, if the landing position of the aircraft deviates, it will be difficult to interact with the ground device later.

[0003] Therefore, providing an aircraft parking apron capable of adjusting the position of an aircraft after landing has become an urgent problem to be solved. Utility Model Content

[0004] In view of the problems existing in the background technology, one aspect of the utility model provides an aircraft parking apron, comprising:

[0005] A docking platform for carrying an aircraft;

[0006] At least two position adjustment mechanisms are arranged on the docking platform, and the position adjustment mechanisms include a movable first rocker arm and a second rocker arm. The first rocker arm and the second rocker arm can cross each other to form a clamping portion for clamping the structural member of the aircraft. As the first rocker arm and the second rocker arm move, the formation position of the clamping portion changes, thereby driving the aircraft to move from the landing position to the target position.

[0007] In some embodiments of the present invention, the first rocker arm and the second rocker arm can move linearly or curve synchronously or asynchronously to change the forming position of the clamping portion.

[0008] In some embodiments of the present invention, the first rocker arm and the second rocker arm can rotate with different rotation centers to change the forming position of the clamping portion.

[0009] In some embodiments of the utility model, the first rocker arm and the second rocker arm have an idle state and a working state; when they are in the idle state, the clamping portion is not formed between the two, and they are arranged in a stacked manner; when they are in the working state, the clamping portion with a variable position is formed between the two.

[0010] In some embodiments of the utility model, the aircraft apron includes: a rotating plate arranged on the docking platform, the rotating plate is connected to the first rocker arm and the second rocker arm, the first rocker arm and the second rocker arm move under the drive of the rotating plate to change the formation position of the clamping portion.

[0011] In some embodiments of the utility model, the aircraft apron includes: a connecting rod having one end pivotally connected to the rotating plate and the other end pivotally connected to the first rocker arm and / or the second rocker arm, the first rocker arm and the second rocker arm moving under the drive of the connecting rod to change the forming position of the clamping portion.

[0012] In some embodiments of the present invention, the aircraft apron includes: a driving mechanism for driving the rotating plate or the connecting rod to rotate.

[0013] In some embodiments of the utility model, the aircraft apron includes: a handle with a stowed state and an unfolded state provided on the docking platform, when it is in the stowed state, the handle is embedded in the docking platform; when it is in the unfolded state, the handle protrudes from the docking platform.

[0014] In some embodiments of the present invention, the aircraft parking apron includes: a suction cup disposed on the docking platform for adsorbing on an external component.

[0015] Another aspect of the present invention provides a carrier, comprising:

[0016] A power system for driving the vehicle to move; and

[0017] Any aircraft parking apron as described above carried by the vehicle.

[0018] The aircraft parking apron provided by the utility model can utilize a position adjustment mechanism to drag / push an aircraft that has landed on the docking platform, and move the aircraft from a landing position to a target position, thereby facilitating the operating device of ground equipment to charge the aircraft, replace loads, replace batteries, or replenish raw materials. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 A schematic diagram of the structure of an aircraft parking apron provided in one embodiment of the utility model (the position adjustment mechanism is in an idle state);

[0020] Figure 2 for Figure 1 A schematic diagram of an aircraft parking apron shown in FIG. 1 when carrying an aircraft;

[0021] Figure 3 for Figure 1 The structural diagram of the aircraft apron shown in (the position adjustment mechanism is in working state);

[0022] Figure 4 for Figure 3 A schematic diagram of an aircraft parking apron shown in FIG. 1 when carrying an aircraft;

[0023] Figure 5 for Figure 1 A schematic diagram of the bottom structure of the aircraft parking apron shown in;

[0024] Figure 6 for Figure 1 Schematic diagram of the structure of the aircraft parking apron after the compartment cover is installed (the handle is in the storage state);

[0025] Figure 7 for Figure 1 Schematic diagram of the structure of the aircraft parking apron after the hatch cover is installed (the handle is in the unfolded state);

[0026] Figure 8 A schematic structural diagram of a carrier provided in another embodiment of the utility model.

[0027] Description of reference numerals:

[0028] Aircraft parking apron 100;

[0029] Aircraft 200;

[0030] Vehicle 300;

[0031] Powertrain 400;

[0032] Docking platform 10;

[0033] Position adjustment mechanism 20; first rocker arm 21; second rocker arm 22; clamping portion 23;

[0034] Transmission mechanism 30; rotating plate 31; connecting rod 32; main connecting rod 32a; auxiliary connecting rod 32b;

[0035] Driving mechanism 40;

[0036] Speed ​​reducer 50; shift fork 50a; small protrusion 50b;

[0037] Handle 60;

[0038] Suction cup 70;

[0039] Bin cover 80. DETAILED DESCRIPTION

[0040] In order to make the purpose, technical solution and advantages of the embodiment of the utility model clearer, the technical solution in the embodiment of the utility model will be clearly and completely described below in conjunction with the drawings in the embodiment of the utility model. Obviously, the described embodiment is a part of the embodiment of the utility model, not all of the embodiments. Based on the embodiment of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0041] like Figure 1-4 As shown, an embodiment of the utility model provides an aircraft parking apron 100, comprising a docking platform 10 for carrying an aircraft 200 and at least two position adjustment mechanisms 20 arranged on the docking platform 10. The position adjustment mechanism 20 comprises a movable first rocker arm 21 and a second rocker arm 22, and the first rocker arm 21 and the second rocker arm 22 can cross each other to form a clamping portion 23 for clamping a structural member of the aircraft 200. As the first rocker arm 21 and the second rocker arm 22 move, the formation position of the clamping portion 23 changes, thereby driving the aircraft 200 to move from the landing position to the target position.

[0042] Exemplarily, the aircraft 200 may be an unmanned aerial vehicle, which may be applied to at least one of the following fields: aerial photography, agriculture, plant protection, express delivery, disaster relief, monitoring of infectious diseases, surveying and mapping, power inspection, etc.

[0043] For example, the aircraft 200 may be a rotary-wing unmanned aerial vehicle, a fixed-wing unmanned aerial vehicle, an unmanned helicopter, or a fixed-wing-rotor hybrid unmanned aerial vehicle, etc. The rotary-wing unmanned aerial vehicle may be a single-rotor aircraft, a dual-rotor aircraft, a three-rotor aircraft, a four-rotor aircraft, a six-rotor aircraft, an eight-rotor aircraft, a ten-rotor aircraft, a twelve-rotor aircraft, etc.

[0044] Exemplarily, the structural member of the aircraft 200 may be at least one of the following: a fuselage, an arm connected to the fuselage, a tripod connected to the fuselage or the arm, etc.

[0045] In this embodiment, the structural member of the aircraft 200 refers to the arm connected to the fuselage. The position adjustment mechanism 20 has two Figure 1 The Y direction shown in FIG. 2 is arranged in parallel so that it can act on a pair of front arms or rear arms of the aircraft 200.

[0046] In other embodiments, the position adjustment mechanism 20 may be arranged along Figure 1 200, so that it can act on a pair of left arms or right arms located on the same side of the aircraft 200. Alternatively, the position adjustment mechanism 20 can be arranged along the X direction shown in FIG. Figure 1The Z direction shown in FIG. 1 (ie, the diagonal direction of the docking platform 10 ) is set so that it can act on a left arm and a right arm located on different sides of the aircraft 200 .

[0047] In other embodiments, there may be more position adjustment mechanisms 20, for example, four, six, eight, etc. The number of position adjustment mechanisms 20 may be less than or equal to the number of structural members, or may be greater than the number of structural members.

[0048] In summary, the specific position of the position adjustment mechanism 20 can be determined according to the position of the structural components of the aircraft 200. The specific number of the position adjustment mechanism 20 can be increased or decreased according to the number of the structural components of the aircraft 200.

[0049] In this embodiment, the first rocker arm 21 and the second rocker arm 22 are arc-shaped arms, which intersect each other. Figure 3 The A region shown in the figure forms a clamping portion 23 for clamping a structural member of the aircraft 200, and the curvatures of the two are substantially the same. The clamping portion 23 formed by the first rocker arm 21 and the second rocker arm 22 is similar to a "clamp" structure.

[0050] In other embodiments, the first rocker arm 21 and the second rocker arm 22 may be arc-shaped arms that intersect each other. Figure 3 The B, C or D region shown in the figure forms a clamping portion 23 for clamping a structural member of the aircraft 200. The curvatures of the first rocker arm 21 and the second rocker arm 22 may be different.

[0051] In other embodiments, the first rocker arm 21 and the second rocker arm 22 may both be straight arms, or one may be a straight arm and the other may be an arc-shaped arm, as long as the two can form a clamping portion 23 for clamping a structural member of the aircraft 200 when they intersect.

[0052] Those skilled in the art should be able to understand that after the aircraft 200 lands on the docking platform 10, the position of the aircraft 200 may deviate from the target position, and the position adjustment mechanism 20 on one side first contacts the structural member on the corresponding side of the aircraft 200, thereby starting to drag / push the aircraft 200 to move, and then the position adjustment mechanism 20 on the other side gradually contacts the structural member on the corresponding side, and under the coordinated action of the position adjustment mechanisms 20 on both sides, the aircraft 200 is dragged / pushed toward the middle of the docking platform 10 until the aircraft 200 moves to the target position, thereby facilitating the operating device of the ground equipment (not shown) to charge the aircraft 200, replace the load, replace the battery, or replenish raw materials.

[0053] Exemplarily, the target position may include at least one of the following: a charging position, a position for conveniently operating the device to change the load, a position for the battery, or a position for replenishing raw materials. In common cases, the target position is the center position on the docking platform 10, and the position adjustment mechanism 20 actually helps the aircraft 200 that deviates from the center position to complete the "return to the center".

[0054] Exemplarily, the operating device includes a replacement mechanism (not shown) for replacing the load or other components of the aircraft 200 (such as a battery or a water tank of the aircraft 200). The replacement mechanism may include at least one of the following: a replacement manipulator, other auxiliary mechanical structures, etc. For example, the operating device of the ground equipment may include components such as a manipulator and a charging head set on the aircraft apron.

[0055] Exemplarily, the charging method includes at least one of the following: charging the aircraft 200 by magnetically contacting the charging contacts provided on the aircraft apron 100 with the charging contacts on the aircraft 200. Alternatively, charging the aircraft 200 by a wireless charging device provided on the aircraft apron 100. Alternatively, charging the aircraft 200 by plugging a charging cable into a charging module provided on the aircraft apron 100 and a charging interface of the aircraft 200.

[0056] Exemplarily, the payload may include at least one of the following: a pan / tilt platform, an imaging device, a detection sensor, etc. The imaging device includes at least one of the following: a camera, a video camera, a mobile phone, an ultrasonic imaging device, an infrared imaging device, etc.

[0057] Exemplarily, the replenishment raw materials may include liquid raw materials and solid raw materials. The liquid raw materials include at least one of the following: gasoline, detergent, liquid pesticide, etc.; the solid raw materials include at least one of the following: solid pesticide, fire extinguishing powder, etc.

[0058] Furthermore, the first rocker arm 21 and the second rocker arm 22 can be moved linearly or curved synchronously or asynchronously to change the forming position of the clamping portion 23 .

[0059] For example, the linear movement may be that a linear guide groove is provided on the docking platform 10, and a part of the first rocker arm 21 or the second rocker arm 22 may be disposed in the guide groove and move along the guide groove. The curved movement may be that a curved guide groove is provided on the docking platform 10, and a part of the first rocker arm 21 or the second rocker arm 22 may be disposed in the guide groove and move along the guide groove. Alternatively, the first rocker arm 21 or the second rocker arm 22 is connected to the docking platform 10 by a rotating shaft, a hinge, etc., so that it can pivot relative to the docking platform 10.

[0060] In this embodiment, the first rocker arm 21 and the second rocker arm 22 can make synchronous curved movements from a position relative to the middle of the docking platform 10 toward a position relative to the edge, or from a position relative to the edge toward a position relative to the middle, and the clamping portion 23 continuously acts on the structural parts of the aircraft 200, thereby driving the aircraft 200 to move from the landing position to the target position.

[0061] In other embodiments, the first rocker arm 21 and the second rocker arm 22 can make asynchronous curved movements from a position relative to the middle of the docking platform 10 toward a position relative to the edge, or from a position relative to the edge toward a position relative to the middle, and the clamping portion 23 continuously acts on the structural parts of the aircraft 200, thereby driving the aircraft 200 to move from the landing position to the target position.

[0062] In other embodiments, the first rocker arm 21 and the second rocker arm 22 can be synchronously moved linearly from a position relative to the middle of the docking platform 10 toward a position relative to the edge, or from a position relative to the edge toward a position relative to the middle, and the clamping portion 23 continuously acts on the structural parts of the aircraft 200, thereby driving the aircraft 200 to move from the landing position to the target position.

[0063] In other embodiments, the first rocker arm 21 and the second rocker arm 22 can be asynchronously moved linearly from a position relative to the middle of the docking platform 10 toward a position relative to the edge, or from a position relative to the edge toward a position relative to the middle, and the clamping portion 23 continuously acts on the structural parts of the aircraft 200, thereby driving the aircraft 200 to move from the landing position to the target position.

[0064] In other embodiments, one of the first rocker arm 21 and the second rocker arm 22 can make a linear movement from a position relative to the middle of the docking platform 10 toward a position relative to the edge, or from a position relative to the edge toward a position relative to the middle, and the other can make a curved movement from a position relative to the middle of the docking platform 10 toward a position relative to the edge, or from a position relative to the edge toward a position relative to the middle. The first rocker arm 21 and the second rocker arm 22 can move synchronously or asynchronously, and the clamping portion 23 continuously acts on the structural parts of the aircraft 200, thereby driving the aircraft 200 to move from the landing position to the target position.

[0065] Those skilled in the art should be able to understand that as the first rocker arm 21 and the second rocker arm 22 move, the formation position of the clamping portion 23 changes, thereby driving the aircraft 200 to move from the landing position to the target position, and can facilitate the operating device of the ground equipment (not shown) to charge the aircraft 200, replace the load, replace the battery or replenish raw materials.

[0066] Furthermore, the first rocker arm 21 and the second rocker arm 22 can rotate at different rotation centers to change the formation position of the clamping portion 23 .

[0067] In this embodiment, the first rocker arm 21 is Figure 3 Point E in FIG. 1 is pivotally connected to the docking platform 10 (i.e., point E is its rotation center) and rotates in the direction indicated by the dotted arrow. The second rocker arm 22 is Figure 3 Point F in the figure is pivotally connected to the docking platform 10 (i.e., point F is its rotation center) and rotates in the direction indicated by the dotted arrow. During the movement of the two, the formation position of the clamping portion 23 is changed. The clamping portion 23 continuously acts on the structural parts of the aircraft 200, thereby driving the aircraft 200 to move from the landing position to the target position.

[0068] Those skilled in the art should be able to understand that as the first rocker arm 21 and the second rocker arm 22 rotate, the formation position of the clamping portion 23 changes, thereby driving the aircraft 200 to move from the landing position to the target position, and can facilitate the operating device of the ground equipment (not shown) to charge the aircraft 200, replace the load, replace the battery or replenish raw materials.

[0069] Still refer to Figure 1-4 As shown, further, the first rocker arm 21 and the second rocker arm 22 have an idle state and a working state; when they are in the idle state, no clamping portion 23 is formed between the two, and they are arranged in a stacked manner; when they are in the working state, a clamping portion 23 with a variable position is formed between the two.

[0070] In this embodiment, in the working state, the first rocker arm 21 and the second rocker arm 22 are Figure 3 The first rocker arm 21 and the second rocker arm 22 rotate in the direction indicated by the dotted arrow, and a clamping portion 23 is formed between the two. As the two continue to rotate, the position of the clamping portion 23 changes. Figure 3 Rotate in the opposite direction as indicated by the dashed arrow until the first rocker arm 21 and the second rocker arm 22 are arranged in a stacked manner (the two can be completely stacked or only partially stacked), and the clamping portion 23 therebetween disappears.

[0071] Those skilled in the art should understand that the first rocker arm 21 and the second rocker arm 22 in the idle state are stacked on each other, which can minimize the space occupied by the position adjustment mechanism 20 as a whole on the docking platform 10, and avoid interference with the landing of the aircraft 200. Therefore, in the case where the landing position of the aircraft 200 is significantly different from the target position, the first rocker arm 21 and the second rocker arm 22 in the working state can also drive the aircraft 200 to move from the landing position to the target position.

[0072] In this embodiment, after the aircraft 200 moves to the target position, the clamping portion 23 generates a pre-tightening force on the structural components of the aircraft 200 .

[0073] Those skilled in the art will appreciate that the clamping portion 23 generates a pre-tightening force on the structural parts of the aircraft 200 that has moved to the target position, which can prevent the aircraft 200 from shaking and moving away from the target position during subsequent operations (e.g., charging, changing loads, changing batteries, or replenishing raw materials, etc.). Figure 3 Movement in the opposite direction indicated by the dashed arrow can release the constraints on the structural members on the corresponding side.

[0074] like Figure 5 As shown, further, the aircraft apron 100 includes a rotating plate 31 arranged on the docking platform 10, and the rotating plate 31 is connected to the first rocker arm 21 and the second rocker arm 22. The first rocker arm 21 and the second rocker arm 22 move under the drive of the rotating plate 31 to change the forming position of the clamping portion 23.

[0075] Furthermore, the aircraft apron 100 includes a connecting rod 32 having one end pivotally connected to the rotating plate 31 and the other end pivotally connected to the first rocker arm 21 and / or the second rocker arm 22. The first rocker arm 21 and / or the second rocker arm 22 moves driven by the connecting rod 32 to change the forming position of the clamping portion 23.

[0076] In this embodiment, the rotating plate 31 and the connecting rod 32 actually together constitute the transmission mechanism 30. Specifically, a rotating plate 31 is horizontally rotatably arranged near the center of the bottom of the docking platform 10. The connecting rod 32 includes two main connecting rods 32a and four secondary connecting rods 32b. One end of the main connecting rod 32a is pivotally connected to the rotating plate 31, and the other end is pivotally connected to the bottom of the docking platform 10. One end of the secondary connecting rod 32b is pivotally connected to the main connecting rod 32b, and the other end is connected to the rotating shaft of the first rocker arm 21 or the second rocker arm 22. Furthermore, the horizontal rotation of the rotating plate 31 is transmitted to the first rocker arm 21 and the second rocker arm 22 through the connecting rod 32. Figure 5 In the embodiment, the main connecting rod 32a located at the top is designed as a two-stage type.

[0077] In other embodiments, the connecting rod 32 may also be designed as having only the main connecting rod 32a without the secondary connecting rod 32b as required, and one end of the main connecting rod 32a is pivotally connected to the rotating plate 31, and the other end is pivotally connected to at least one of the first rocker arm 21 and the second rocker arm 22. That is, the connecting rod 32 may be designed in a variety of ways, which are not limited in the present application.

[0078] In other embodiments, the transmission mechanism 30 may further include at least one of the following: a transmission belt structure, a transmission chain, a transmission gear, etc. For example, the first rocker arm 21 and the second rocker arm 22 are pivotally connected to the docking platform 10 by a rotating shaft, and the rotating shaft can be regarded as a rotating wheel. The two rotating shafts are then connected by a transmission belt or a transmission chain, and a transmission mechanism 30 including a rotating wheel, a transmission belt, and a transmission chain is formed between the first rocker arm 21 and the second rocker arm 22. Further, the aircraft apron 100 includes a driving mechanism 40 for driving the rotating plate 31 or the connecting rod 32 to rotate.

[0079] Exemplarily, the driving mechanism 40 may be a motor, a cylinder, an electric push rod, an electro-hydraulic push rod, or the like.

[0080] In this embodiment, the driving mechanism 40 is a motor, and the rotational motion of the motor is converted into the swinging motion of the fork 50a through the reduction box 50 and the fork 50a disposed on the reduction box 50. A small protrusion 50b capable of cooperating with the fork 50a is disposed on any connecting rod 32 (main connecting rod 32a), so that the driving mechanism 40 can drive the corresponding connecting rod 32 to pivot.

[0081] In other embodiments, the rotating plate 31 may be independently provided with a plurality of them, and the first rocker arm 21 and the second rocker arm 22 of the position adjustment mechanism 20 are respectively connected to an independent rotating plate 31. There are also a plurality of driving mechanisms 40, and each driving mechanism 40 independently drives an independent rotating plate 31 to rotate, thereby driving the corresponding first rocker arm 21 and the second rocker arm 22 to move asynchronously.

[0082] In other embodiments, the rotating plate 31 may be independently provided with a plurality of them, and the first rocker arm 21 and the second rocker arm 22 of each position adjustment mechanism 20 are connected to the same rotating plate 31. There are also a plurality of driving mechanisms 40, and each driving mechanism 40 independently drives an independent rotating plate 31 to rotate, thereby driving the corresponding first rocker arm 21 and the second rocker arm 22 to move synchronously. The movement of each position adjustment mechanism 20 is also independent of each other.

[0083] In other embodiments, multiple connecting rods 32 may be directly used to replace multiple rotating plates 31, and the first rocker arm 21 and the second rocker arm 22 of the position adjustment mechanism 20 are respectively connected to an independent connecting rod 32, and there are multiple driving mechanisms 40, each driving mechanism 40 independently drives an independent connecting rod 32 to rotate, thereby driving the corresponding first rocker arm 21 and the second rocker arm 22 to move asynchronously. Those skilled in the art should understand that when only one rotating plate 31 is used to connect multiple connecting rods 32, during the rotation of the rotating plate 31, it can drive all the position adjustment mechanisms 20 to move, thereby reducing the number of driving mechanisms 40, effectively reducing the cost of the aircraft apron 100, and can also reduce the volume and weight of the aircraft apron 100 to a certain extent. As the weight becomes lighter, the energy consumption of the vehicle including the aircraft apron 100 can also be reduced. In addition, when only two position adjustment mechanisms 20 are provided, the aircraft apron 100 is not likely to interfere with the aircraft 200 or components provided thereon, so that the aircraft apron 100 can be adapted to aircraft 200 of more sizes.

[0084] like Figure 6-7 As shown, further, the aircraft apron 100 includes a handle 60 with a stowed state and an unfolded state disposed on the docking platform 10. When it is in the stowed state, the handle 60 is embedded in the docking platform 10. When it is in the unfolded state, the handle 60 protrudes from the docking platform 10.

[0085] In this embodiment, a compartment cover 80 that can be opened and closed is provided on the docking platform 10. The handle 60 is provided on the side of the docking platform 10 and can be ejected and stored by pressing. The handle 60 is substantially flush with the surface of the docking platform 10 in the stored state.

[0086] In other embodiments, the handle 60 may also be disposed at other locations of the docking platform 10, such as the front and rear sides, and may be stored by snapping or other means.

[0087] Those skilled in the art will appreciate that the handle 60 increases the portability of the aircraft apron 100, and facilitates users to carry the aircraft apron 100 over short distances. The handle 60 is integrated with the docking platform 10 in the stowed state, and does not affect the appearance of the aircraft apron 100.

[0088] Furthermore, the aircraft parking apron 100 includes a suction cup 70 disposed on the docking platform 10 for adsorbing on an external component.

[0089] Exemplarily, the suction cup 70 may be a conventional rubber suction cup, or an electric suction cup with air leakage detection and self-suction functions.

[0090] Those skilled in the art should be able to understand that the aircraft apron 100 can be attached to the roof of the vehicle by means of the suction cup 70, and the aircraft apron 100 can be quickly disassembled by deflating the suction cup 70. Compared with the conventional method of directly fixing the aircraft apron 100 on the roof or roof luggage rack using additional accessories, it is more convenient and simple. In addition, the suction cup 70 can be attached to both metal and glass, unlike the conventional aircraft apron that can only be installed on the metal roof. The aircraft apron 100 provided by the present application has better versatility.

[0091] like Figure 8 As shown, another embodiment of the present invention provides a vehicle 300 , including a power system 400 for driving the vehicle 300 to move and any aircraft apron 100 as described above carried by the vehicle 300 .

[0092] Exemplarily, the power system 400 includes at least one of the following: a motor, a sail, a rudder, a drive wheel, a cylinder, etc.

[0093] Exemplarily, the vehicle 300 includes at least one of the following: a movable vehicle, a movable robot, a movable ship, etc.

[0094] Those skilled in the art should be able to understand that the vehicle 300 provided in this embodiment has the same beneficial effects as the above-mentioned aircraft apron 100. For example, after the aircraft 200 lands on the docking platform 10, the position of the aircraft 200 may deviate from the target position, and the position adjustment mechanism 20 on one side first contacts the structural member on the corresponding side of the aircraft 200, thereby starting to drag / push the aircraft 200 to move, and then the position adjustment mechanism 20 on the other side gradually contacts the structural member on the corresponding side, and under the coordinated action of the position adjustment mechanisms 20 on both sides, the aircraft 200 is dragged / pushed toward the middle of the docking platform 10 until the aircraft 200 moves to the target position, thereby facilitating the operation device of the ground equipment (not shown) to charge the aircraft 200, replace the load, replace the battery, or replenish raw materials.

[0095] In the description of this specification, the description with reference to the terms "certain embodiments", "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0096] In the present invention, the terms "first", "second", and "third" are used for descriptive purposes only and should not be understood as indicating or implying relative importance; the term "plurality" refers to two or more, unless otherwise clearly defined. The terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense. For example, "connected" can be a fixed connection, a detachable connection, or an integral connection; "connected" can be a direct connection or an indirect connection through an intermediate medium. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to the specific circumstances.

[0097] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the utility model and are not restrictive. Although the utility model is described in detail with reference to the embodiments, it should be understood by those skilled in the art that any modification or equivalent replacement of the technical solution of the utility model does not deviate from the spirit and scope of the technical solution of the utility model, and should be included in the scope of the claims of the utility model.

Claims

1. Aircraft parking apron, characterized in that: include: A docking platform for carrying an aircraft; At least two position adjustment mechanisms are arranged on the docking platform, and the position adjustment mechanisms include a movable first rocker arm and a second rocker arm. The first rocker arm and the second rocker arm can cross each other to form a clamping portion for clamping the structural member of the aircraft. As the first rocker arm and the second rocker arm move, the formation position of the clamping portion changes, thereby driving the aircraft to move from the landing position to the target position.

2. The aircraft parking apron according to claim 1, characterized in that: The first rocker arm and the second rocker arm can be linearly or curvilinearly moved synchronously or asynchronously to change a forming position of the clamping portion.

3. The aircraft parking apron according to claim 1, characterized in that: The first rocker arm and the second rocker arm can rotate at different rotation centers to change the formation position of the clamping portion.

4. The aircraft parking apron according to claim 1, characterized in that: The first rocker arm and the second rocker arm have an idle state and a working state; when they are in the idle state, the clamping portion is not formed between the two, and they are arranged in a stacked manner; when they are in the working state, the clamping portion with a variable position is formed between the two.

5. The aircraft parking apron according to claim 1, characterized in that: include: A rotating plate is arranged on the docking platform, and the rotating plate is connected to the first rocker arm and the second rocker arm. The first rocker arm and the second rocker arm move under the drive of the rotating plate to change the forming position of the clamping portion.

6. The aircraft parking apron according to claim 5, characterized in that: include: A connecting rod having one end pivotally connected to the rotating plate and the other end pivotally connected to the first rocker arm and / or the second rocker arm, wherein the first rocker arm and the second rocker arm move driven by the connecting rod to change the forming position of the clamping portion.

7. The aircraft parking apron according to claim 6, characterized in that: include: A driving mechanism for driving the rotating plate or the connecting rod to rotate.

8. The aircraft parking apron according to claim 1, characterized in that: include: A handle having a stowed state and an unfolded state is disposed on the docking platform, and when the handle is in the stowed state, the handle is embedded in the docking platform; When it is in the unfolded state, the handle protrudes from the docking platform.

9. The aircraft parking apron according to claim 1, characterized in that: include: A suction cup is arranged on the docking platform and is used for adsorbing on the external component.

10. A carrier, characterized in that: include: A power system for driving the vehicle to move; as well as An aircraft parking apron as claimed in any one of claims 1 to 9 carried by the vehicle.

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