Landing device for aircraft

Abstract

The utility model relates to a landing device of an aircraft, a skid is arranged at the bottom of the aircraft, and the landing device comprises a landing platform and a clamping jaw mechanism; the bearing surface of the landing platform gradually inclines downwards from outside to inside, a hollow area is formed in the center of the landing platform, and the landing platform is used for bearing an aircraft landing on the landing device; the clamping jaw mechanism comprises a plurality of clamping jaws located in the hollowed-out area, and the clamping jaw mechanism is configured to control the multiple clamping jaws to move so that the clamping jaws can lock the skid. According to the invention, the landing deviation can be automatically adapted and the dynamic disturbance influence can be counteracted, so that the high-reliability locking of the skid and the chassis can be realized, the dependence on a complex electronic system can be reduced, and the requirements of light weight and low cost of the hovercar can be met.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft, in particular to a landing device of an aircraft. BACKGROUND

[0002] With the rapid development of Urban Air Mobility (UAM), flying cars as an innovative carrier integrating aviation and ground transportation have become a research hotspot. At present, some flying cars adopt a "body-chassis separation type" design, and the flying car body is equipped with a skid structure, which is quickly combined and locked with the ground driving chassis after landing. However, the flying car body is easily affected by low air flow disturbances (such as gusts and ground effect) during near-ground landing, which causes large horizontal position deviation and deflection angle deviation of the skid, thereby increasing the locking difficulty.

[0003] Traditional locking schemes mostly rely on high-precision positioning mechanisms or electronic compensation systems, but have obvious defects: first, poor fault tolerance, the skid needs to be strictly aligned for slot type locking, and deviation can easily cause jamming; second, insufficient dynamic adaptation, rigid locking is difficult to buffer the continuous shaking caused by air flow, which can easily cause structure wear; finally, high-cost systems such as visual sensing and servo closed-loop control can also increase system complexity and failure risk. CONTENT OF THE UTILITY MODEL

[0004] In view of the above, it is necessary to provide a landing device of an aircraft, which can automatically adapt to landing deviation and offset the influence of dynamic disturbance, so as to realize high-reliability locking of the skid and chassis, and can reduce the dependence on complex electronic systems, thereby meeting the lightweight and low-cost needs of flying cars.

[0005] The present application provides a landing device of an aircraft for carrying an aircraft, the bottom of the aircraft being provided with a skid, comprising a landing platform and a claw mechanism; the bearing surface of the landing platform is gradually inclined downward from outside to inside and has a hollow area at the center position, and the landing platform is used to carry the aircraft landing on the landing device; the claw mechanism comprises a plurality of claws located in the hollow area, and the claw mechanism is configured to control the displacement of the plurality of claws to lock the skid.

[0006] In the landing device of the aircraft of the present application, the inclined bearing surface can guide the skid to slide to the center hollow area, preliminarily compensating for the position and angle errors during landing, and the claw mechanism can clamp the skid by means of displacement movement, realizing passive positioning and preliminary locking of the skid. Through the cooperative design of the inclined bearing surface and the self-adaptive claw, the skid can still be guided to the locking center under position / angle deviation, and the stability can be enhanced by using the mechanical self-locking property, thereby automatically adapting to the landing deviation and offsetting the influence of dynamic disturbance, realizing high-reliability locking of the skid and chassis, and reducing the dependence on complex electronic systems, thereby meeting the lightweight and low-cost needs of flying cars.

[0007] In some embodiments, the bearing surface of the landing platform is in the shape of a circular ring, and the bearing surface of the landing platform is a concave arc surface, a flat surface or a convex arc surface.

[0008] In some embodiments, the landing device further comprises a plurality of fixing blocks and a rotating base, the landing platform and the claw mechanism are arranged on the rotating base, the number of the fixing blocks is consistent with the number of the claws, and the fixing blocks are arranged in pairs with the claws, and the fixing blocks are arranged between the landing platform and the rotating base and are used for connecting the landing platform and the rotating base.

[0009] In some embodiments, the claw mechanism comprises a plurality of sliding guide columns, the fixing blocks are provided with first mounting holes for mounting the sliding guide columns, the claws are provided with first matching holes for mounting the sliding guide columns, and the fixing blocks and the claws at the same straight line position are movably connected through the sliding guide columns.

[0010] In some embodiments, the claw mechanism further comprises a plurality of transmission lead screws, the fixing blocks are provided with second mounting holes for mounting the transmission lead screws, the claws are provided with second matching holes for mounting the transmission lead screws, and the fixing blocks and the claws at the same straight line position are movably connected through the transmission lead screws.

[0011] In some embodiments, the transmission lead screw is provided with a transmission thread, the claw is in transmission connection with the transmission lead screw through the transmission thread, and the transmission directions of the threads at the two ends of the transmission lead screw are opposite.

[0012] In some embodiments, the top end of the claw is provided with a first matching surface and a second matching surface, the first matching surface intersects with the second matching surface to form a clamping space, and the clamping space is used for clamping the skid.

[0013] In some embodiments, the claw mechanism further comprises a first driving assembly, the first driving assembly is in transmission connection with the transmission lead screw and is used for driving the transmission lead screw to rotate.

[0014] In some embodiments, the claw mechanism further comprises a hinge block arranged at the center position of the rotating base, the plurality of sliding guide columns are hingedly connected through the hinge block to form a symmetrical distribution, and the bottom of the rotating base is provided with a second driving assembly, and the second driving assembly is used for driving the rotating base to rotate.

[0015] In some embodiments, the landing device further comprises a conveying base plate, the rotating base is rotatably arranged on the conveying base plate, and the conveying base plate is used for conveying the landing device. BRIEF DESCRIPTION OF DRAWINGS

[0016] Figure 1 FIG. 1 is a structural schematic diagram of a landing device according to an embodiment of the present application.

[0017] Figure 2 FIG. 4 is a structural schematic diagram of a claw according to an embodiment of the present application.

[0018] Figure 3 Figure 1 is an assembly schematic diagram of a pawl mechanism and a rotating base according to an embodiment of the present application.

[0019] Figure 4 Figure 2 is a structural schematic diagram of a partial mechanism of the pawl mechanism according to an embodiment of the present application.

[0020] Figure 5 Figure 3 is a distribution schematic diagram of a fixed block and a hinged block on the rotating base according to an embodiment of the present application.

[0021] Figure 6 Figure 4 is a schematic diagram of a first state of the pawl mechanism according to an embodiment of the present application.

[0022] Figure 7 Figure 5 is a schematic diagram of a second state of the pawl mechanism according to an embodiment of the present application.

[0023] Main element symbol explanation:

[0024] 1, landing device; 2, skid; 11, landing platform; 12, pawl mechanism; 13, rotating base; 14, fixed block; 15, transport chassis; 111, bearing surface; 112, hollowed-out area; 121, pawl; 122, sliding guide column; 123, transmission screw; 124, first driving assembly; 125, hinged block; 131, second driving assembly; 1211, first matching surface; 1212, second matching surface; 1213, first matching hole; 1214, second matching hole; 141, first mounting hole; 142, second mounting hole; 1241, first motor; 1242, first transmission member; 1311, second motor; 1312, second transmission member.

[0025] The following detailed description will further describe the present application in conjunction with the above-mentioned drawings. DETAILED DESCRIPTION

[0026] In the description of the present application, the words "exemplary", "or", "for example" and the like are used to mean serving as an example, instance or illustration. Any embodiment or design solution described as "exemplary" or "for example" in the present application should not be interpreted as being more preferred or advantageous than other embodiments or design solutions. Rather, the use of the words "exemplary", "or", "for example" and the like is intended to present the relevant concept in a specific way.

[0027] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used in the description of the application herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the application. It is to be understood that the use of "a", "an" or "the" herein includes singular and plural referents unless the context clearly dictates otherwise. For example, "an" or "the" can include multiple instances of the element and the inclusion of "a" or "the" is not limited to usage of a singular noun form. It is further to be understood that the use of "or" in the inclusion of, for example, a limitation means that an item will be either one or the other of the elements or a combination of them. For example, the use of "A / B" means "A or B" and the use of "A / B / C" means "A, B, or C". It is to be understood that "comprising" is not intended to mean "consisting of" or "consisting exclusively of" unless otherwise indicated. It is to be understood that "and / or" is intended to mean "and" or "or" or both, for example, "A and / or B" means "A or B or both". It is to be understood that "at least one of" is intended to mean "one or more of" for example, "at least one of A or B" means "A or B or both".

[0028] In addition, it should be pointed out that the terms "first", "second" in the specification and claims of the present application and the drawings are used to distinguish similar objects, and are not used to describe a specific order or sequence.

[0029] With the rapid development of urban air mobility (UAM), flying cars as an innovative carrier integrating aviation and ground transportation have become a research hotspot. Currently, some flying cars adopt a "body-chassis separation" design, with the flying car body carrying a skid structure, which is quickly combined with the ground driving chassis after landing. However, this technology faces severe challenges in practical application: the flying car body is easily disturbed by low air flow (such as ground effect, gust, etc.) during near-ground landing, resulting in significant increase in position deviation (horizontal offset) and angle deviation (tilt or yaw) when the skid and chassis are docked.

[0030] Traditional locking solutions often rely on rigid positioning mechanisms or high-precision sensors for guidance, making it difficult to achieve reliable locking under dynamic air flow interference. Specifically, first, the fault tolerance is insufficient, as most locking mechanisms are designed as precise slots or plug-in structures, requiring the skid and chassis to be strictly centered and angled, and even slight deviation can cause jamming or locking failure. Second, the dynamic adaptability is poor, as air flow disturbances can cause the skid to continue to shake after landing, and traditional rigid locking is prone to structural fatigue or mechanical damage due to transient vibration. Third, it needs to rely on complex control, as some solutions require high-cost systems such as visual recognition and servo motor closed-loop control to achieve locking compensation, increasing technical complexity and failure risk.

[0031] The technical solution of the present application aims to solve the problem of high-reliability locking of flying car skid-chassis under dynamic air flow interference through innovative mechanical structure design, and promote the practicalization process of separation type flying cars.

[0032] To this end, the embodiment of the present application provides a landing device of an aircraft, which can automatically adapt to landing deviation and offset dynamic disturbance to achieve high reliability locking of the skid and the chassis, and can reduce the dependence on complex electronic systems, thereby meeting the lightweight and low-cost requirements of the flying car. Some embodiments will be described below with reference to the accompanying drawings. In the case of no conflict, the embodiments described below and the features in the embodiments can be combined with each other.

[0033] Figure 1 is a structural schematic diagram of the landing device 1 of the embodiment of the present application.

[0034] Please refer to Figure 1 , the present application provides a landing device 1 of an aircraft, wherein the aircraft can be a low-altitude aircraft such as a unmanned aerial vehicle, a manned aircraft or a flying car, and the bottom of the aircraft can be provided with a skid 2 (see Figure 6 or Figure 7 , for the convenience of description, the drawings of the present application only show the skid 2 of the aircraft), the skid 2 is used to provide stability when the aircraft lands.

[0035] Please refer to Figure 1 , the landing device 1 of the embodiment of the present application can include a landing platform 11 and a claw mechanism 12.

[0036] Please refer to Figure 1 , in the embodiment of the present application, the bearing surface 111 of the landing platform 11 is gradually inclined downward from outside to inside and has a hollow area 112 at the center position, and the landing platform 11 is used to bear the aircraft landing on the landing device 1. When the aircraft approaches the landing device 1, the skid 2 of the aircraft will first contact the outer edge part of the landing platform 11. Due to the inclined design of the bearing surface 111, the skid 2 will naturally slide along the inclined surface to the center hollow area 112. During the sliding process, the bearing surface 111 not only provides a smooth landing experience for the aircraft, but also can preliminarily compensate for the position and angle errors that may occur when the aircraft lands, greatly improving the safety and accuracy of the aircraft landing.

[0037] In some embodiments, the bearing surface 111 of the landing platform 11 can be circular ring-shaped, and the bearing surface 111 of the landing platform 11 can be concave arc surface. It can be understood that the concave arc surface is a surface composed of a sag and its corresponding chord. Specifically, the two chords (i.e. the innermost and outermost chords with reference to the hollow area 112) of the bearing surface 111 and the sag (i.e. the concave part mainly used for bearing the aircraft) of the bearing surface 111 can constitute the concave arc surface. In this case, the symmetrical design of the circular ring-shaped bearing surface 111 and the normal force of the concave arc surface can enhance the self-centering ability of the skid 2, thereby reducing the sensitivity of the angle error caused by different landing directions of the aircraft.

[0038] In other embodiments, the bearing surface 111 of the landing platform 11 may also be shaped to fit the shape of the aircraft or the shape of the aircraft's skid 2, such as a rectangular ring, a square ring, an elliptical ring, or other rings. Similarly, the bearing surface 111 of the landing platform 11 may also be a plane or a convex arc surface. It can be understood that a convex arc surface is a surface composed of a major arc and its corresponding chord. Specifically, the two chords of the bearing surface 111 (i.e., the innermost and outermost sides with reference to the hollowed-out area 112) and the major arc of the bearing surface 111 (i.e., the protruding part mainly used to support the aircraft) can form the convex arc surface.

[0039] In some embodiments, the shape of the hollowed-out area 112 of the bearing surface 111 can be consistent with the shape of the bearing surface 111, such as a circle, or it can be a shape adapted to the shape of the aircraft or the shape of the aircraft skid 2, such as a rectangle, square, ellipse or other shapes.

[0040] In some embodiments, the area of ​​the hollowed-out region 112 is smaller than the overall area of ​​the aircraft's skid 2 projected onto the bearing surface 111. This reduces the likelihood of the aircraft's skid 2 accidentally sliding into the hollowed-out region 112, leading to abnormal landings.

[0041] In the embodiments of this application, the claw mechanism 12 may include claws 121 located in the hollowed-out area 112. The number of claws 121 may be multiple, such as two, three, four, or more. The claw mechanism 12 may be configured to manipulate the displacement of multiple claws 121 to lock the skid 2. When the aircraft's skid 2 slides into the central hollowed-out area 112, the claw mechanism 12 will immediately activate. Through precise mechanical control, multiple claws 121 can simultaneously move, locking the skid 2 from different directions. This achieves initial clamping of the skid 2, ensuring it is firmly fixed in a predetermined position. The automatic positioning of the aircraft on the landing platform 11 and the initial locking mechanism of the claw mechanism 12 not only improve the stability of the landing process but also provide a reliable foundation for subsequent operations.

[0042] In some embodiments, please refer to Figure 1 The landing device 1 may also include a rotating base 13. The landing platform 11 and the claw mechanism 12 are disposed on the rotating base 13. Thus, the landing platform 11 and the claw mechanism 12 can be supported by the rotating base 13.

[0043] Figure 2 This is a schematic diagram of the structure of the claw 121 in an embodiment of this application.

[0044] In some embodiments, please refer to Figure 2The top of the jaw 121 may have a first mating surface 1211 and a second mating surface 1212. The first mating surface 1211 and the second mating surface 1212 intersect to form a locking space, which can be used to lock the slide 2. The first mating surface 1211 is formed by bending the top of the jaw 121, and the second mating surface 1212 is formed by obliquely cutting the top of the jaw 121. In this case, the bidirectional mating surfaces at the top of the jaw 121 form a wedge-shaped locking space, which can adapt to the shape and tilt angle of the slide 2, enhancing the clamping force through a self-locking effect, thereby reducing the dependence on precise angles.

[0045] In some embodiments, the height of the space between the claws 121 can be greater than the lowest height of the bearing surface 111 of the landing platform 11, thereby facilitating the locking of the claws 121 onto the skid 2. In other embodiments, the height of the space between the claws 121 can be less than the lowest height of the bearing surface 111 of the landing platform 11. In this case, the skid 2 can have an engaging portion protruding from the hollowed-out area 112 to below the bearing surface 111 of the landing platform 11, and the claws 121 can lock the skid 2 by engaging the engaging portion.

[0046] Figure 3 This is an assembly diagram of the claw mechanism 12 and the rotating base 13 according to an embodiment of this application. Figure 4 This is a schematic diagram of part of the claw mechanism 12 in an embodiment of this application.

[0047] Please see Figure 3 In embodiments of this application, the claw mechanism 12 may further include a sliding guide post 122, a transmission lead screw 123, and a drive assembly (see...). Figure 4 As shown in the diagram, for ease of distinction, the driving component of the claw mechanism 12 is referred to as the first driving component 124. The number of sliding guide posts 122 and transmission screws 123 can be multiple, for example, two, three, four, or more.

[0048] In some embodiments, the number of sliding guide posts 122 and transmission screws 123 can be half the number of pawls 121. For example, when there is an even number of pawls 121, such as 2n (n is a positive integer), the number of sliding guide posts 122 and transmission screws 123 can be n.

[0049] In some embodiments, please refer to Figure 2 and Figure 3The chuck 121 may have a first mating hole 1213 for mounting the sliding guide post 122, and the chuck 121 may also have a second mating hole 1214 for mounting the transmission screw 123. The positions of the first mating hole 1213 and the second mating hole 1214 are different. The chuck 121 can be movably connected to the sliding guide post 122 through the first mating hole 1213, and the chuck 121 can also be drive-connected to the transmission screw 123 through the second mating hole 1214.

[0050] In some embodiments, the lead screw 123 may have a transmission thread, and the pawl 121 may be connected to the lead screw 123 via the transmission thread. In some embodiments, the transmission directions of the threads at both ends of the lead screw 123 may be opposite. In this case, the reverse threads at both ends of the lead screw 123 can facilitate bidirectional synchronous movement of the two pawls 121, reduce transmission backlash, and improve the accuracy and stability of the locking action.

[0051] In some embodiments, please refer to Figure 3 The landing device 1 may further include multiple fixing blocks 14, the number of which is the same as the number of claws 121, and the fixing blocks 14 are paired with the claws 121, for example, two, three, four or more, with each fixing block 14 corresponding to each claw 121. The fixing blocks 14 may be disposed between the landing platform 11 and the rotating base 13, and are used to connect the landing platform 11 and the rotating base 13, that is, the fixing blocks 14 may be disposed outside the hollow area 112 relative to the claws 121. In this case, the fixing blocks 14 can connect the landing platform 11 and the rotating base 13 to form a modular support structure, which can enhance the rigidity and impact resistance of the mechanical structure, distribute the locking load, and reduce local deformation; at the same time, since the position of the fixing blocks 14 is fixed, the pairing of the fixing blocks 14 with the claws 121 can facilitate the guidance of the movement of the claws 121 by the sliding guide post 122 and the fixing blocks 14, so as to improve the locking accuracy of the claws 121.

[0052] Figure 5 This is a schematic diagram showing the distribution of the fixing block 14 and the hinge block 125 on the rotating base 13 according to an embodiment of this application.

[0053] In some embodiments, please refer to Figure 4 The fixing block 14 may have a first mounting hole 141 for mounting the sliding guide post 122, and the fixing block 14 may also have a second mounting hole 142 for mounting the transmission screw 123. The positions of the first mounting hole 141 and the second mounting hole 142 are different. The position of the first mounting hole 141 corresponds to the first mating hole 1213 of the pawl 121, and the position of the second mounting hole 142 corresponds to the second mating hole 1214 of the pawl 121.

[0054] As described above, the chuck mechanism 12 may include multiple sliding guide posts 122, and the fixed block 14 and the chuck 121 located on the same straight line can be movably connected through the sliding guide posts 122. In this case, the sliding guide posts 122, through the linear engagement between the fixed block 14 and the chuck 121, can restrict the degree of freedom of movement of the chuck 121, ensuring that the chuck 121 moves along a preset trajectory, reducing lateral offset, and improving locking accuracy.

[0055] As described above, the chuck mechanism 12 may further include multiple transmission screws 123, with the fixed block 14 and the chuck 121 in the same linear position movably connected by the transmission screws 123. In this case, the transmission screws 123 pass through the fixed block 14 and the chuck 121, converting the rotational motion into linear displacement of the chuck 121, driving multiple chucks 121 to synchronously retract or disperse to lock or release the skid 2, and reducing locking deviations caused by asynchronous actions.

[0056] As described above, the chuck mechanism 12 may further include a first drive assembly 124, which can be connected to the lead screw 123 and used to drive the lead screw 123 to rotate. In this case, the first drive assembly 124 directly drives the lead screw 123 to rotate, providing closed-loop power control, realizing automatic locking, and improving response speed and operating efficiency.

[0057] In some embodiments, please refer to Figure 4 The first drive assembly 124 may include a first motor 1241 and a first transmission member 1242. The first transmission member 1242 is disposed on the transmission lead screw 123, and the first motor 1241 is connected to the first transmission member 1242 in a transmission connection. In some embodiments, the first transmission member 1242 may be a transmission device such as a gear or a coupling.

[0058] In some embodiments, please refer to Figure 3 or Figure 5 The chuck mechanism 12 may also include a hinge block 125 disposed at the center of the rotating base 13, with multiple sliding guide posts 122 hinged together by the hinge block 125 to form a symmetrical distribution. In this case, the sliding guide posts 122 are symmetrically distributed on the rotating base 13 by the hinge block 125, which can improve the stability between the sliding guide posts 122, thereby improving the guiding accuracy of the sliding guide posts 122 on the chuck 121.

[0059] In some embodiments, please refer to Figure 5A drive assembly can also be provided at the bottom of the rotating base 13. For ease of distinction, it is referred to here as the second drive assembly 131. The second drive assembly 131 can be used to drive the rotating base 13 to rotate. In this case, the second drive assembly 131 drives the rotating base 13 to rotate, which can dynamically adjust the orientation of the landing platform 11, thereby adapting to the yaw landing of the aircraft and omnidirectionally compatible with locking the aircraft.

[0060] In some embodiments, the second drive assembly 131 may include a second motor 1311 and a second transmission member 1312. The second transmission member 1312 is disposed on the rotation shaft of the rotating base 13, and the second motor 1311 is connected to the second transmission member 1312 in a transmission manner. In some embodiments, the second transmission member 1312 may be a transmission device such as a gear or a coupling.

[0061] In some embodiments, please refer to Figure 1 The landing device 1 may also include a transport chassis 15, on which a rotating base 13 is rotatably mounted. The transport chassis 15 can be used to transport the landing device 1. In this case, the rotatable connection between the rotating base 13 and the transport chassis 15 enables the overall structure to be rotatable and movable, improving the deployment flexibility of the landing device 1 and thus supporting the dynamic adjustment of the aircraft and the needs of transportation scenarios.

[0062] In some embodiments, the landing device 1 may further include a sensing component and a control system (not shown). The sensing component may be disposed at least one of the following: the bearing surface 111 of the landing platform 11, a reference within the hollowed-out area 112, or a claw mechanism 12 within the hollowed-out area 112. The control system may be disposed on the rotating base 13 or the transport chassis 15. The sensing component can be used to sense whether the aircraft is landing on the landing device 1, and the control system can be used to control the operation of the first drive component 124 and the second drive component 131, thereby driving the claw mechanism 12 to lock the aircraft's skid 2 and driving the rotating base 13 to dynamically adjust its orientation. The sensing component may include, but is not limited to, at least one of the following sensing methods: force sensing, photoelectric sensing, electromagnetic sensing, or image recognition sensing.

[0063] Figure 6 This is a schematic diagram of the first state of the claw mechanism 12 in an embodiment of this application. Figure 7 This is a schematic diagram of the second state of the claw mechanism 12 in an embodiment of this application.

[0064] In the landing device 1 of the aircraft of this application, the inclined bearing surface 111 can guide the skid 2 to slide towards the hollow area 112 at the center, initially compensating for position and angle errors during landing, while the claw mechanism 12 can clamp the skid 2 by means of displacement movement, realizing the passive positioning and initial locking of the skid 2. Specifically, as Figure 6 and Figure 7As shown, when landing device 1 senses that the aircraft has landed (see...) Figure 6 The jaw 121 of the jaw mechanism 12 can be controlled to move toward the skid 2 to lock the skid 2 (see...). Figure 7 This completes the aircraft locking process.

[0065] This application, through the coordinated design of the inclined bearing surface 111 and the adaptive claw 121, enables the skid 2 to still be guided to the locking center under position / angle deviation, and can enhance stability by utilizing mechanical self-locking characteristics. This allows it to automatically adapt to landing deviations and counteract the effects of dynamic disturbances, thereby achieving a highly reliable lock between the skid 2 and the chassis. It also reduces the reliance on complex electronic systems, thus meeting the needs of lightweight and low-cost flying cars.

[0066] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this application and are not intended to limit it. Although this application has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solutions of this application without departing from the spirit and scope of the technical solutions of this application.

Claims

1. A landing device for an aircraft, used to carry the aircraft, wherein the aircraft has a skid at its bottom, characterized in that, Including the landing platform and the gripper mechanism; The landing platform's bearing surface gradually slopes downwards from the outside in and has a hollow area in the center. The landing platform is used to support the aircraft that lands on the landing device. The claw mechanism includes multiple claws located in the hollowed-out area, and the claw mechanism is configured to manipulate the displacement of the multiple claws to lock the skid.

2. The landing device for an aircraft according to claim 1, characterized in that, The bearing surface of the landing platform is annular, and the bearing surface of the landing platform is a concave arc surface, a plane, or a convex arc surface.

3. The landing device for an aircraft according to claim 1, characterized in that, It also includes multiple fixed blocks and a rotating base. The landing platform and the claw mechanism are disposed on the rotating base. The number of fixed blocks is the same as the number of claws, and the fixed blocks are arranged in pairs with the claws. The fixed blocks are disposed between the landing platform and the rotating base and are used to connect the landing platform and the rotating base.

4. The landing device for an aircraft according to claim 3, characterized in that, The claw mechanism includes multiple sliding guide posts. The fixed block has a first mounting hole for mounting the sliding guide posts, and the claw has a first mating hole for mounting the sliding guide posts. The fixed block and the claw, which are in the same straight line position, are movably connected through the sliding guide posts.

5. The landing device for an aircraft according to claim 4, characterized in that, The chuck mechanism further includes multiple transmission screws. The fixed block has a second mounting hole for mounting the transmission screws, and the chuck has a second mating hole for mounting the transmission screws. The fixed block and the chuck, which are in the same straight line position, are movably connected through the transmission screws.

6. The landing device for an aircraft according to claim 5, characterized in that, The transmission screw has a transmission thread, and the pawl is connected to the transmission screw via the transmission thread; The two ends of the transmission screw have opposite transmission directions.

7. The landing device for an aircraft according to claim 1, characterized in that, The top of the claw has a first mating surface and a second mating surface. The first mating surface and the second mating surface intersect to form a locking space, which is used to lock the skid in place.

8. The landing device for an aircraft according to claim 5, characterized in that, The chuck mechanism further includes a first drive component, which is connected to the transmission screw and is used to drive the transmission screw to rotate.

9. The landing device for an aircraft according to claim 4, characterized in that, The chuck mechanism also includes a hinge block located at the center of the rotating base, and the plurality of sliding guide posts are hinged through the hinge block to form a symmetrical distribution; A second drive assembly is provided at the bottom of the rotating base, and the second drive assembly is used to drive the rotating base to rotate.

10. The landing device for an aircraft according to claim 4, characterized in that, The landing device also includes a transport chassis, on which the rotating base is rotatably mounted, and the transport chassis is used to transport the landing device.

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