Multi-functional landing gear with load bearing capacity

Abstract

This invention discloses a multi-functional landing gear with load-bearing capacity, belonging to the field of multi-rotor unmanned aerial vehicle (UAV) technology. It includes: a landing gear mainboard, a first connecting assembly, a second connecting assembly, a payload bay, and a support member. The first connecting assembly includes a first connecting member disposed on the landing gear mainboard and a first mating member disposed on the UAV. The second connecting assembly includes a second connecting member disposed below the landing gear mainboard and a second mating member disposed on top of the payload bay, with the payload bay located below the landing gear mainboard. The support member is connected to the lower part of the landing gear mainboard via an angle adjustment device. The support member is configured as a telescopic structure, allowing adjustment of its length via the telescopic structure. The angle adjustment device allows adjustment of the angle between the support member and the landing gear mainboard. This invention enables rapid replacement of landing gear with different loads according to mission site requirements, reducing the number of UAV types carried during multi-mission operations and improving transportation efficiency.

Description

Technical Field

[0001] This invention relates to the field of multi-rotor unmanned aerial vehicle (UAV) technology, and more particularly to a multi-functional landing gear with load-bearing capacity. Background Technology

[0002] Multi-rotor drones have a wide range of applications and are characterized by low cost, good maneuverability, and ease of use. They have broad prospects and huge development opportunities in the civilian sector, and the trend of intelligentization and integration is significant.

[0003] A multi-rotor drone is a special type of unmanned rotary-wing aircraft with three or more rotor shafts. Each rotor shaft is powered by an electric motor, which drives the rotors to rotate, generating lift. By changing the relative speeds between the different rotors, the torque of the thrust can be altered, thus controlling the aircraft's trajectory. Multi-rotor drones can now easily enter various harsh environments that are difficult for humans to access, performing tasks such as aerial filming, real-time monitoring, and terrain reconnaissance.

[0004] To facilitate transportation and improve flight efficiency, existing multi-rotor drones are designed to be small, lightweight, have limited functionality, and have fixed landing gear structures. This limits the materials that multi-rotor drones can carry. In different altitude regions, to ensure the successful completion of missions, multiple drones must be used for material transport for tasks that require carrying large amounts of materials. This makes multi-rotor drones prone to damage during transportation, and also makes transportation difficult, costly, and space-consuming. Summary of the Invention

[0005] To address some or all of the technical problems existing in the prior art, the present invention provides a multi-functional landing gear with load-bearing capacity. It can quickly replace landing gear with different loads according to the needs of the mission site, has high interchangeability and versatility, and can effectively reduce the types of drones carried during multiple missions, improve transportation efficiency, reduce transportation costs, and avoid damage to drones during transportation.

[0006] The technical solution of the present invention is as follows: A multi-functional landing gear with load-bearing capacity is provided, comprising: Landing gear mainboard; A first connection component, comprising a first connector and a first mating component that mates with the first connector, wherein the first connector is disposed on the landing gear mainboard and the first mating component is disposed on the UAV; The second connecting assembly includes a second connector and a second mating component that mates with the second connector. The second connector is located below the landing gear main board, and the second mating component is fixedly located on the top of the payload bay. The load compartment is located below the landing gear mainboard so that it can be detachably connected to the landing gear mainboard for material transport via the cooperation of the second connector and the second mating component. A support member is connected to the lower part of the landing gear mainboard via an angle adjustment device. The support member is configured as a telescopic structure so that the length of the support member can be adjusted via the telescopic structure, and the angle between the support member and the landing gear mainboard can be adjusted via the angle adjustment device.

[0007] In some alternative implementations, the first connecting component includes a slider and a slide rail.

[0008] In some alternative implementations, the second connecting component includes a slider and a slide rail or a snap-fit ​​and a clamp.

[0009] In some alternative implementations, the number of payload compartments may be multiple, and the multiple payload compartments may have different capacities.

[0010] In some alternative implementations, the position of the second connector in the second connection assembly on the landing gear mainboard is determined by the size of the payload bay.

[0011] In some alternative implementations, the angle adjustment device includes: The third connector is located below the landing gear main board. One end of the third connector is fixedly connected to the landing gear main board, and a through hole is provided on the other end of the third connector. A rotating shaft is rotatably disposed within the through hole, and the rotating shaft is fixedly connected to the other end of the support member; A ratchet mechanism, wherein the ratchet in the ratchet mechanism is fixedly connected to the rotating shaft, and the pawl in the ratchet mechanism is movably disposed on the third connecting member; When it is necessary to adjust the deflection angle of the support member, the support member is rotated to rotate around the third connector. The rotating shaft and the ratchet rotate synchronously, so that the support member faces or moves away from the load chamber. When the support member is adjusted to a preset angle, the pawl engages with the tooth groove of the ratchet to fix the ratchet, the rotating shaft and the support member.

[0012] In some alternative embodiments, the support member includes: A telescopic support rod, one end of which is connected to the angle adjustment device, and the other end of which faces the ground and is set as a support end.

[0013] In some alternative embodiments, the support is located on the outside of the load chamber.

[0014] In some alternative implementations, the shortest vertical height of the support is greater than or equal to the maximum height of the load chamber.

[0015] In some alternative embodiments, the support member further includes a horizontal support rod, which is fixedly connected to the end of the support end.

[0016] The main advantages of the technical solution of this invention are as follows: This invention discloses a multi-functional landing gear with load-bearing capacity. By fixing a first mating component in a first connecting assembly to a drone, and mates the first mating component on the drone with a first connecting component on the landing gear mainboard, the drone's flight is facilitated by the interaction of the first connecting component and the first mating component, which in turn drives the landing gear mainboard to fly synchronously. This, in turn, drives the multi-functional landing gear connected to and formed by the landing gear mainboard to fly synchronously. When the drone needs to carry or transport materials, a suitable payload bay is selected based on the task requirements and the amount of materials. This allows the drone to carry the payload bay during operations. Furthermore, to ensure smooth landing in different operating environments, the length and angle of the support components can be adjusted to adapt the landing gear to various terrains, ensuring a stable landing and guaranteeing the drone's safety and the successful completion of the task. This invention also allows for the replacement of the payload bay and rapid adjustment of the support component length to provide landing gear with different load capacities, effectively reducing the number of aircraft types carried during multi-mission operations, improving transportation efficiency, reducing transportation costs, and preventing damage to the drone during transport. Attached Figure Description

[0017] The accompanying drawings, which are included to provide a further understanding of embodiments of the invention and constitute a part of this invention, illustrate exemplary embodiments of the invention and, together with their description, serve to explain the invention and do not constitute an undue limitation thereof. In the drawings: Figure 1 A schematic diagram of a multi-functional landing gear with load-bearing capacity provided in an embodiment of the present invention; Figure 2 A schematic diagram of the structure of a multi-functional landing gear angle adjustment device with load-bearing capacity provided in an embodiment of the present invention; Explanation of reference numerals in the attached figures: 1. Landing gear mainboard; 2. First connecting member; 3. Load cell; 4. Support member; 41. Vertical support rod; 42. Extension assembly; 43. Extension locking assembly; 44. Extension rod; 45. Horizontal support rod; 5. Angle adjustment device; 51. Third connecting member; 52. Rotating shaft; 53. Ratchet mechanism; 530. Ratchet; 531. Pawl. Detailed Implementation

[0018] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions of this invention will be clearly and completely described below in conjunction with specific embodiments and corresponding drawings. Obviously, the described embodiments are only a part of the embodiments of this invention, and not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention.

[0019] The following is in conjunction with the appendix Figure 1-2 The technical solutions provided in the embodiments of the present invention will be described in detail.

[0020] As attached Figure 1-2 As shown, this embodiment of the invention provides a multi-functional landing gear with load-bearing capacity. The multi-functional landing gear includes: a landing gear main board 1, a first connecting assembly, a second connecting assembly, a load compartment 3, and a support member 4, wherein: The first connecting assembly includes a first connector 2 and a first mating component that mates with the first connector 2. The first connector 2 is mounted on the landing gear mainboard 1, and the first mating component is mounted on the UAV. The second connecting assembly includes a second connector and a second mating component that mates with the second connector. The second connector is located below the landing gear mainboard 1, and the second mating component is fixedly mounted on the top of the payload bay 3. The payload bay 3 is located below the landing gear mainboard 1 so that, through the mating connection of the second connector and the second mating component, the payload bay 3 can be detachably connected to the lower part of the landing gear mainboard 1 for material transport. The support member 4 is connected to the lower part of the landing gear mainboard 1 via an angle adjustment device 5. The support member 4 is configured as a telescopic structure so that the length of the support member 4 can be adjusted via the telescopic structure, and the angle between the support member 4 and the landing gear mainboard 1 can be adjusted via the angle adjustment device 5.

[0021] Specifically, the method of using a multi-functional landing gear with load-bearing capacity according to the present invention includes: The first mating component in the first connecting assembly is fixedly installed on the UAV. The first mating component on the UAV cooperates with the first connecting component 2 installed on the landing gear mainboard 1. During the flight of the UAV, the cooperation of the first connecting component and the first mating component can drive the landing gear mainboard 1 to fly synchronously. This, in turn, can drive the multi-functional landing gear connected to the landing gear mainboard 1 to fly synchronously. When the UAV needs to carry or transport materials, the appropriate payload bay 3 is selected according to the requirements of the task and the amount of materials. This allows the multi-rotor UAV to carry the payload bay 3 to carry out the task. In order for the UAV to land smoothly in different working environments when carrying the payload bay 3, the length and angle of the support component 4 can be adjusted to make the landing gear adapt to different terrains, thereby enabling the UAV to land smoothly and ensuring the safety of the multi-rotor UAV and the smooth progress of the task.

[0022] Therefore, the multi-functional landing gear with load-bearing capacity of the present invention can not only match and replace different load cells 3 according to different mission requirements to perform different tasks, but also quickly adjust the length and angle of the support member 4 according to the mission site requirements, so that the multi-rotor UAV can have landing gear with different loads. Moreover, this landing gear has high interchangeability and versatility, which can effectively reduce the types of multi-rotor UAVs carried in multi-mission, improve transportation efficiency, reduce transportation costs, and avoid damage to multi-rotor UAVs during transportation.

[0023] Understandably, regardless of the size or weight of the payload bay 3, when the multi-rotor UAV is used to carry out the operation, the multi-rotor UAV can be smoothly driven and safely take off and fly without affecting the normal flight of the multi-rotor UAV.

[0024] As an example, the first mating component can be fixedly connected to the multi-rotor UAV by means of cable ties, Velcro, bolts or studs, and the first mating component on the multi-rotor UAV can be mated with the first connecting component 2 on the landing gear main board 1, so that the multi-rotor UAV drives the landing gear main board 1 to fly synchronously, and the payload compartment 3 is fixedly set directly below the landing gear main board 1, thereby enabling the multi-rotor UAV to drive the payload compartment 3 to perform different operation tasks.

[0025] In some optional implementations of this embodiment, the multi-functional landing gear with load-bearing capacity of the present invention, in conjunction with a drone, enables seed sowing or pesticide spraying. For example, by configuring the multi-functional landing gear of the present invention on a multi-rotor drone, seeds are placed in the payload compartment 3, and an opening is provided in the payload compartment 3, allowing the seeds to fall orderly through the opening. Simultaneously, the multi-rotor drone flies at a certain speed, thereby completing the sowing task. This is particularly useful in environments where workers cannot easily access or where operations are slow, such as mountainous areas, forests, sandy areas, or saline-alkali lands. Furthermore, by using the multi-functional landing gear of the present invention in conjunction with a multi-rotor drone, operational efficiency can be improved, manual labor output reduced, and worker safety ensured.

[0026] In some optional implementation scenarios of this embodiment, the multi-functional landing gear with load-bearing capacity of the present invention, in conjunction with a drone, can also be used for aquatic feeding. For example, by configuring the multi-functional landing gear of the present invention on a multi-rotor drone, aquatic feed is placed in the payload compartment 3, and an opening is provided on the payload compartment 3, allowing the aquatic feed to fall orderly through the opening on the payload compartment 3. At the same time, the multi-rotor drone flies at a certain speed, thereby completing aquatic feeding and improving feeding efficiency.

[0027] In another optional implementation scenario of this embodiment, the multi-functional landing gear with load-bearing capacity of the present invention, in conjunction with the UAV, can also be used for fixed-point marking. For example, by configuring the multi-functional landing gear of the present invention on a multi-rotor UAV, by placing markers in the payload compartment 3, and after the multi-rotor UAV flies to a preset position, the payload compartment 3 is opened to release the markers, thereby completing the fixed-point marking task. Especially in environments where it is difficult for workers to enter or where operations are slow, such as mountains, forests, sandy areas, or saline-alkali lands, this can reduce the output of manpower and resources, save costs, ensure the safety of workers, and improve operational efficiency.

[0028] In some optional implementations of this embodiment, the landing gear mainboard 1 is made of carbon fiber material. On the one hand, this can reduce the overall weight of the multi-functional landing gear in this invention. On the other hand, it can ensure the strength of the connection between the landing gear mainboard 1 and the multi-rotor UAV, as well as ensure the load-bearing capacity of the connection between the payload compartment 3 and the landing gear mainboard 1.

[0029] As can be imagined, the landing gear mainboard 1 is the core component connecting the multi-rotor UAV and the landing gear. The landing gear mainboard 1 can be set to any shape, but it is necessary to ensure that the landing gear mainboard 1 has a certain strength. At the same time, the landing gear mainboard 1 and the payload bay 3 cooperate to form a closed or semi-closed space. As an example, the landing gear mainboard 1 is set as a plate structure and the shape is set as rectangular.

[0030] In another optional implementation of this embodiment, the connection positions of any one of the connectors or mating parts in the first and second connecting components can be interchanged during the connection process. The specific installation positions of the connectors and mating parts are determined according to actual needs.

[0031] In some optional implementations of this embodiment, the first connecting component includes a slider and a slide rail, and the second connecting component includes a slider and a slide rail or a buckle and a clamp.

[0032] For example, both the first connecting component and the second connecting component are configured as sliders and slide rails. The landing gear mainboard 1 and the multi-rotor UAV, as well as the payload bay 3 and the landing gear mainboard 1 are detachably connected by sliders and slide rails, thereby facilitating disassembly and installation and improving disassembly and installation efficiency.

[0033] To prevent the first and second connecting components from loosening and falling off due to factors such as vibration or tilting during flight of the multi-rotor UAV, fixing devices are adaptively provided on the first and second connecting components.

[0034] For example, the first connecting component is configured as a slider and a slide rail, and a fixing member is provided at the end of the slide rail so that the fixing member can block the slider and prevent the slider from sliding out along the slide rail or the slide rail from falling out of the slider, causing the load chamber 3 to fall.

[0035] For example, the first connecting component is configured as a buckle and a clamp, and an anti-slip pad is provided at the connection position of the buckle and the clamp to increase the friction after the buckle and the clamp are connected, so as to prevent the buckle and the clamp from loosening during the flight vibration of the multi-rotor UAV, causing the payload compartment 3 to fall off. Alternatively, a locking switch is provided after the buckle and the clamp are engaged, so that the buckle and the clamp can be fixed again after they are engaged. This can effectively prevent the buckle and the clamp from falling off and loosening, ensuring the stable flight of the multi-rotor UAV, and also ensuring the safety of the payload compartment 3 and the materials inside the payload compartment 3.

[0036] In order to reduce energy loss, improve flight efficiency, reduce flight drag, and ensure flight safety and stability during the flight of the UAV, the number of payload compartments 3 is set to multiple, and the capacity of the multiple payload compartments 3 is different.

[0037] This configuration allows the multi-rotor UAV to select a matching payload bay 3 based on the quantity and size of the material, enabling the multi-rotor UAV and payload bay 3 to work together effectively to complete the task while achieving the aforementioned effects.

[0038] To ensure a safe and reliable connection between the second connecting component and the payload bay 3, and to ensure a stable connection between the payload bay 3 and the landing gear mainboard 1, the position of the second connecting component on the landing gear mainboard 1 is determined by the size of the payload bay 3. This allows for precise matching between the second connecting component and the second mating component, facilitating assembly and disassembly, improving assembly and disassembly efficiency, and preventing the payload bay 3 from falling off or loosening due to an insecure fit between the second mating component and the second connecting component, which could lead to unstable flight, crash, or damage to the multi-rotor UAV.

[0039] Further, see Figures 1-2 In this embodiment of the invention, the angle adjustment device 5 includes: a third connecting member 51, a rotating shaft 52, and a ratchet mechanism 53, wherein: The third connecting member 51 is located below the landing gear main board 1. One end of the third connecting member 51 is fixedly connected to the landing gear main board 1, and a through hole is provided on the other end of the third connecting member 51. The rotating shaft 52 is rotatably disposed in the through hole, and the rotating shaft 52 is fixedly connected to the other end of the support member 4. The ratchet 530 in the ratchet mechanism 53 is fixedly connected to the rotating shaft 52, and the pawl 531 in the ratchet mechanism 53 is movably disposed on the third connecting member 51. When it is necessary to adjust the deflection angle of the support member 4, rotate the support member 4 to rotate around the third connector 51. The rotating shaft 52 and the ratchet 530 rotate synchronously, so that the support member 4 faces or moves away from the load chamber 3. When the support member 4 is adjusted to the preset angle, the pawl 531 engages with the tooth groove of the ratchet 530, thereby fixing the ratchet 530, the rotating shaft 52 and the support member 4, and completing the angle adjustment of the support member 4.

[0040] With this configuration, the angle adjustment device 5 in this invention not only has the function of adjusting the angle, but also has a fixing function. After the support member 4 is adjusted to the preset angle and preset position, the angle adjustment device 5 can keep the adjusted position and angle of the support member 4 fixed, so as to avoid the support member 4 from changing its angle, position and length during flight, thus ensuring the smooth start and stop of the multi-rotor UAV and the smooth completion of the operation task.

[0041] Further, see Figure 1 In this embodiment of the invention, the support member 4 includes a telescopic support rod, one end of which is connected to the angle adjustment device 5, and the other end of which faces the ground and is set as the support end.

[0042] For example, the support member 4 is configured as a telescopic support rod including: a vertical support rod 41, an extension component 42, an extension locking component 43, and an extension rod 44. Specifically, both the vertical support rod 41 and the extension rod 44 are configured as hollow structures, and the extension rod 44 is sleeved inside the vertical support rod 41. The extension component 42 and the extension locking component 43 are disposed at the position where the vertical support rod 41 connects to the extension rod 44, so that when adjusting the length of the support member 4, the extension rod 44 inside the vertical support rod 41 extends to a preset length and is then locked by the extension component 42 and the extension locking component 43.

[0043] In some optional implementations of this embodiment, the extension assembly 42 and the extension locking assembly 43 are configured as an eccentric structure to lock the extension rod 44 inside the vertical support rod 41. Specifically, the extension rod 44 is configured as a normal circular tube structure and fixedly sleeved on the vertical support rod 41. The extension locking assembly 43 is configured as an internally eccentric circular tube structure, so that after adjusting the length of the extension rod 44, it can be locked by the eccentric structure of the extension locking assembly 43.

[0044] To prevent changes in the length of the support member 4 after the extension locking assembly 43 with the eccentric structure locks the extension rod 44, a coarse thread connection is made between the extension assembly 42 and the extension locking assembly 43. This allows for further connection between the extension assembly 42 and the extension locking assembly 43 after the extension rod 44 is locked by the eccentric structure extension locking assembly 43. This ensures that the length of the support member 4 will not change due to vibration, drag, or tilting during the flight of the multi-rotor UAV, thus guaranteeing the smooth start-up and shutdown and flight safety of the multi-rotor UAV.

[0045] In some optional implementations of this embodiment, the support 4 is disposed on the outside of the load chamber 3.

[0046] This configuration allows the payload bay 3 to be positioned directly below the multi-rotor drone, ensuring that the center of gravity of the multi-rotor drone and the payload bay 3 on it is in the center, thereby guaranteeing the flight stability and start-stop stability of the multi-rotor drone.

[0047] In some optional implementations of this embodiment, the shortest vertical height of the support 4 is greater than or equal to the height of the maximum load chamber 3.

[0048] This configuration allows the multi-functional landing gear of the present invention to support the multi-rotor UAV during start-up, stop-and-landing operations by supporting the multi-rotor UAV via the support member 4. This avoids the load compartment 3 supporting the multi-rotor UAV due to the support member 4 being too short, thus preventing damage to the load compartment 3 and the materials inside the load compartment 3 during the start-up and stop of the multi-rotor UAV.

[0049] In some optional implementations of this embodiment, the support member 4 further includes a horizontal support rod 45, which is fixedly connected to the end of the support end.

[0050] Specifically, the horizontal support rod 45 is vertically connected to the end of the extension rod 44. The horizontal support rod 45 can be configured as a long hollow rod to connect the two extension rods 44 synchronously, or the horizontal support rod 45 can be configured as a short hollow rod to connect one extension rod 44 accordingly.

[0051] This configuration allows for the selection of different support methods based on the different start-stop and operation environments of the multi-rotor UAV, ensuring the stability of start-stop, the effectiveness and safety of the multi-rotor UAV carrying the multi-functional landing gear of this invention to perform different tasks, and also ensuring the safety of the multi-functional landing gear installed on the multi-rotor UAV and the materials in the payload bay 3 installed on the multi-functional landing gear.

[0052] As an example, the load chamber 3 in this invention is set as a semi-enclosed box structure in the shape of a "U". The second mating parts of the second connecting component are set at the two symmetrical positions at the two ends of the top opening of the "U" shaped load chamber 3.

[0053] This configuration serves two purposes. First, the second connector and the second mating component work together to connect the payload compartment 3 to the landing gear mainboard 1, while simultaneously using the landing gear mainboard 1 as a cover for the payload compartment 3. This creates a fully enclosed structure, preventing spillage, loss, and damage to materials within the payload compartment 3. Second, the second connector and the second mating component work together to prevent deformation of the U-shaped opening of the payload compartment 3. The fit between the second connector and the second mating component ensures the fixed shape of the opening of the payload compartment 3, guaranteeing the safety of the payload compartment 3 and its internal materials, and ensuring the stability and safety of the multi-rotor UAV's flight.

[0054] To ensure the strength of the payload compartment 3 and to reduce its weight, the payload compartment 3 is made of aluminum alloy.

[0055] In another optional implementation of this embodiment, the payload compartment 3 can also be manufactured using 3D printing technology.

[0056] In summary, the present invention provides a multi-functional landing gear with load-bearing capacity, which can quickly replace landing gear with different loads according to the needs of the mission site. It has high interchangeability and versatility, which can effectively reduce the types of UAVs carried, improve transportation efficiency, reduce transportation costs, and avoid damage to multi-rotor UAVs during transportation.

[0057] It should be noted that, in this document, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Additionally, the terms "front," "back," "left," "right," "upper," and "lower" in this document refer to the placement shown in the accompanying drawings.

[0058] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention 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 of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A multi-functional landing gear with load bearing capacity, characterized in that, include: Landing gear mainboard; A first connection component, comprising a first connector and a first mating component that mates with the first connector, wherein the first connector is disposed on the landing gear mainboard and the first mating component is disposed on the UAV; The second connecting assembly includes a second connector and a second mating component that mates with the second connector. The second connector is located below the landing gear main board, and the second mating component is fixedly located on the top of the payload bay. The load compartment is located below the landing gear mainboard so that it can be detachably connected to the landing gear mainboard for material transport via the cooperation of the second connector and the second mating component. A support member is connected to the lower part of the landing gear mainboard via an angle adjustment device. The support member is configured as a telescopic structure so that the length of the support member can be adjusted via the telescopic structure, and the angle between the support member and the landing gear mainboard can be adjusted via the angle adjustment device.

2. The multi-functional landing gear with load capacity according to claim 1, wherein, The first connecting component includes a slider and a slide rail.

3. The multi-functional landing gear with load capacity according to claim 1, wherein, The second connecting component includes a slider and a slide rail or a buckle and a clamp.

4. The multi-functional landing gear with load capacity according to claim 1, wherein, The number of payload compartments includes multiple compartments, and the multiple payload compartments have different capacities.

5. The multi-functional landing gear with load capacity according to claim 1, wherein, The position of the second connector in the second connection assembly on the landing gear mainboard is determined by the size of the payload bay.

6. The multi-functional landing gear with load bearing capacity according to claim 1, wherein, The angle adjustment device includes: The third connector is located below the landing gear main board. One end of the third connector is fixedly connected to the landing gear main board, and a through hole is provided on the other end of the third connector. A rotating shaft is rotatably disposed within the through hole, and the rotating shaft is fixedly connected to the other end of the support member; A ratchet mechanism, wherein the ratchet in the ratchet mechanism is fixedly connected to the rotating shaft, and the pawl in the ratchet mechanism is movably disposed on the third connecting member; When it is necessary to adjust the deflection angle of the support member, the support member is rotated to rotate around the third connector. The rotating shaft and the ratchet rotate synchronously, so that the support member faces or moves away from the load chamber. When the support member is adjusted to a preset angle, the pawl engages with the tooth groove of the ratchet to fix the ratchet, the rotating shaft and the support member.

7. The multi-functional landing gear with load bearing capacity as claimed in claim 1, wherein, The support member includes: A telescopic support rod, one end of which is connected to the angle adjustment device, and the other end of which faces the ground and is set as a support end.

8. The multi-functional landing gear with load bearing capacity according to claim 7, wherein, The support member is located on the outside of the load chamber.

9. The multi-functional landing gear with load bearing capacity according to claim 1, wherein, The shortest vertical height of the support member is greater than or equal to the maximum height of the load chamber.

10. The multi-functional landing gear with load bearing capacity as claimed in claim 7, wherein, The support also includes a horizontal support rod, which is fixedly connected to the end of the support.

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