An unmanned aerial vehicle landing gear

Abstract

The utility model relates to unmanned plane equipment technical field especially relates to a kind of unmanned plane landing gear, the landing gear is set below unmanned plane main body, the landing gear includes: connecting component, the connecting component includes connecting plate, the connecting plate is connected with the lower end surface of unmanned plane main body;Several support components, the support component includes support seat, the support seat is symmetrically set in the two side edges of the connecting plate, landing component, one end of the landing component is movably connected with the support seat, and the other end of the landing component is rotatably provided with landing rod;By connecting component provides stable installation reference, support component maintains left and right force balance and landing component real-time response ground slope difference, so that landing rod can automatically adjust grounding angle to adhere uneven surface, thereby dispersing impact energy in the instant of landing, reduce the damage risk of local concentrated load to the body, finally improve the safe take-off and landing performance of unmanned plane in unstructured environment.

Description

Technical Field

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

[0002] As an important branch of modern aviation technology, drones have been widely used in various fields such as aerial photography, surveying and mapping, agricultural plant protection, logistics and transportation, and emergency rescue.

[0003] Especially with the continuous expansion and deepening of the agricultural plant protection field, drones need to frequently take off and land in complex and ever-changing terrain environments, such as mountains, hills, or uneven farmland, which places extremely high demands on the adaptability, stability, and cushioning performance of the landing gear.

[0004] Currently, most drones on the market use fixed landing gear or simple spring-damped designs. While these structures are rigid, they lack effective active adjustment capabilities. Upon landing, such landing gear relies primarily on the elastic deformation of the materials themselves or simple mechanical structures to absorb impact energy, offering limited cushioning. Furthermore, when the drone lands in an undesirable attitude or on a steep incline, it is highly susceptible to overload, leading to aircraft tipping, equipment damage, or even mission failure. In addition, fixed landing gear cannot be dynamically adjusted according to different landing conditions (such as ground hardness and slope). Its support span and ground contact angle are immutable parameters, severely limiting the drone's operational capabilities and safety in unstructured environments.

[0005] Therefore, the main drawback of existing technologies is that the landing gear structure has a single function, the buffer mechanism is passive, and it lacks intelligent adaptability to complex landing conditions, making it difficult to meet the urgent needs of high-end UAVs for highly reliable and adaptable landing systems. Utility Model Content

[0006] The main purpose of this invention is to provide a drone landing gear that solves the problem that existing fixed landing gears cannot adaptively adjust to the terrain.

[0007] To achieve the above objectives, this utility model provides a drone landing gear and a connecting assembly, the connecting assembly including a connecting plate for connecting to the lower end face of the drone body; Several support components, each support component including a support base, are symmetrically arranged on both sides of the connecting plate. The lifting assembly has one end movably connected to the support base, and the other end of the lifting assembly is rotatably equipped with a lifting rod.

[0008] Optionally, the lifting assembly includes a transmission rod and a first driving member, with both ends of the first driving member connected to the support base and the middle of the transmission rod, respectively.

[0009] Optionally, the landing assembly further includes a second drive member, the two ends of which are respectively connected to the middle of the landing rod and the transmission rod.

[0010] Optionally, the landing gear further includes an adjustment assembly disposed on the connecting plate, the adjustment assembly being used to adjust the position of the support base.

[0011] Optionally, the adjustment assembly includes a telescopic member, the two ends of which are respectively connected to the connecting plate and the support base.

[0012] Optionally, when the main body of the drone lands, the side of the transmission rod closer to the connecting plate is higher than the side farther away from the connecting plate.

[0013] Optionally, both the first driving member and the second driving member include a gas spring.

[0014] Optionally, the landing bar includes an outer landing bar and an inner landing bar. The outer landing bar is sleeved on the outer periphery of the inner landing bar. A spring is provided inside the outer landing bar, and the free end of the spring is connected to the inner landing bar.

[0015] Optionally, a lifting pad is provided at the end of the inner lifting rod.

[0016] Optionally, a buffer is connected between the lifting inner rod and the transmission rod.

[0017] This invention provides a stable installation reference through connecting components, maintains lateral force balance through support components, and allows the landing gear to respond in real time to differences in ground slope. This enables the landing bar to automatically adjust its grounding angle to conform to uneven surfaces, thereby dispersing impact energy at the moment of landing, reducing the risk of damage to the aircraft from localized concentrated loads, and ultimately improving the safe take-off and landing performance of UAVs in unstructured environments. In summary, the above solution avoids the shortcomings of existing fixed landing gears that cannot dynamically adjust to terrain due to their strong structural rigidity, and achieves intelligent adaptability to complex landing conditions. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the structure of the drone body on the landing gear in an embodiment of this utility model; Figure 2 This is a schematic diagram of the landing gear structure in an embodiment of this utility model; Figure 3 This is a schematic diagram of the lifting arm structure in an embodiment of this utility model.

[0019] Figure label: 1-UAV body, 2-Connection component, 3-Support component, 4-Landing and takeoff component, 5-Adjustment component; 21-Connecting plate; 31-Support base; 41-Landing rod, 42-Drive rod, 43-First drive component, 44-Second drive component; 411 - Outer lifting rod, 412 - Inner lifting rod, 413 - Spring, 414 - Lifting pad.

[0020] The realization of the purpose, functional features and advantages of this utility model will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0021] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0022] It should be noted that all directional indicators (such as up, down, left, right, front, back, etc.) in this utility model embodiment are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indicator will also change accordingly.

[0023] In this utility model, unless otherwise explicitly specified and limited, the terms "connection," "fixing," etc., should be interpreted broadly. For example, "fixing" can mean a fixed connection, a detachable connection, or an integral part; it can mean a mechanical connection or an electrical connection; it can mean a direct connection or an indirect connection through an intermediate medium; it can mean the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0024] Furthermore, if the embodiments of this utility model involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the meaning of "and / or" throughout the text includes three parallel solutions; for example, "A and / or B" includes solution A, solution B, or a solution where both A and B are satisfied simultaneously. Furthermore, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed by this utility model.

[0025] Example: Please refer to the attached document as well. Figures 1 to 3 This embodiment provides a drone landing gear, the landing gear comprising: Connection component 2, the connection component 2 includes a connection plate 21, the connection plate 21 is used to connect to the lower end face of the UAV body 1; Several support components 3, each support component 3 including a support base 31, the support base 31 being symmetrically arranged on both sides of the connecting plate 21. The lifting assembly 4 has one end movably connected to the support base 31, and the other end of the lifting assembly 4 is rotatably provided with a lifting rod 41.

[0026] It should be noted that traditional UAV landing gear structures commonly suffer from insufficient stability during landing, low impact energy absorption efficiency, and a tendency for localized overload to cause overturning due to the lack of terrain-adaptive adjustment mechanisms. Specifically, the rigid design of fixed landing gear cannot dynamically adjust the support angle according to ground slope, resulting in uneven stress distribution at the moment of touchdown, which in turn affects the overall structural safety and mission continuity of the aircraft. Furthermore, the immutable nature of the support span and touchdown angle makes it difficult for the landing gear to evenly distribute the load in unstructured environments, thereby exacerbating the risk of instability when the aircraft's landing attitude is not ideal.

[0027] Based on the above problems, this embodiment provides a UAV landing gear, which aims to solve the problems of insufficient stability, limited cushioning effect, and easy overturning caused by the lack of adaptive adjustment capability of the landing gear when UAVs take off and land in complex and variable terrain environments.

[0028] The connecting plate 21 is a structural component fixedly connected to the lower end face of the UAV body 1. It can be made of metal sheet through bolt fastening or welding, such as aluminum alloy plate or carbon fiber composite plate. Furthermore, the support base 31 refers to the support base symmetrically arranged on both sides of the connecting plate 21. It can be made of cast or machined metal brackets, for example, fixed to the connecting plate 21 by bolt connection or integral molding process. In addition, the landing assembly 4 includes a mechanism with one end movably connected to the support base 31 and the other end rotatably mounted on the landing stick 41. The movable connection can be achieved using a hinge or sliding bearing, and the rotatable mounting can be achieved using a rotary joint or ball joint, such as ball bearing or universal joint.

[0029] Therefore, this structural design provides a stable installation reference through connecting component 2, maintains lateral force balance through support component 3, and allows landing component 4 to respond in real time to differences in ground slope. This enables landing boom 41 to automatically adjust its ground contact angle to conform to uneven surfaces, thereby dispersing impact energy at the moment of landing, reducing the risk of damage to the airframe from localized concentrated loads, and ultimately improving the safe take-off and landing performance of the UAV in unstructured environments. In summary, the above solution avoids the shortcomings of existing fixed landing gear, which cannot dynamically adjust to terrain due to their high structural rigidity. It achieves intelligent adaptability to complex landing conditions. As a preferred implementation, the above features are all achieved based on conventional mechanical structures and can complete the terrain adaptation process without relying on additional drive devices.

[0030] In this embodiment, the lifting assembly 4 includes a transmission rod 42 and a first driving member 43, with the two ends of the first driving member 43 connected to the support base 31 and the middle of the transmission rod 42, respectively.

[0031] It is understandable that by connecting the two ends of the first driving component 43 to the support base 31 and the middle of the transmission rod 42 respectively, the linear displacement of the first driving component 43 is converted into an angular change of the transmission rod 42 using the lever principle, thereby driving the landing stick 41 to adjust its attitude. During the landing process of the UAV, this design enables the landing assembly 4 to dynamically adjust the support angle according to the ground slope, and effectively prevent the aircraft from overturning by actively controlling and dispersing the impact force.

[0032] In this embodiment, the landing assembly 4 further includes a second drive member 44, the two ends of which are connected to the middle of the landing boom 41 and the transmission rod 42, respectively. Through the connection between the second drive member 44 and the middle of the transmission rod 42, during the UAV landing process, the second drive member 44 can extend and retract according to real-time terrain feedback, driving the landing boom 41 to rotate around its rotation point and dynamically adjust the grounding angle. Simultaneously, this connection method complements the first drive member 43, which controls the overall displacement of the transmission rod 42, while the second drive member 44 performs fine-tuning of the landing boom 41. Together, they achieve the dispersion and absorption of impact energy and active attitude adaptation, effectively addressing the local overload problem caused by changes in ground slope.

[0033] In this embodiment, the landing gear further includes an adjustment component 5 disposed on the connecting plate 21, the adjustment component 5 being used to adjust the position of the support base 31.

[0034] Understandably, the adjustment component 5 is mounted on the connecting plate 21 and connected to the support base 31. Since the connecting plate 21 is directly fixed to the UAV body 1, the above structure ensures stable transmission and efficient response of the adjustment action. When the UAV faces uneven ground or changes in slope, the adjustment component 5 drives the support base 31 to move horizontally along both sides of the connecting plate 21 based on the external terrain information, thereby dynamically adjusting the span between the support bases 31. This allows the landing gear to evenly distribute the landing impact force, preventing the risk of overturning due to insufficient local support. At the same time, it simplifies the overall structural complexity and can achieve adaptive adjustment without relying on additional external equipment.

[0035] In this embodiment, the adjustment component 5 includes a telescopic member 51, and the two ends of the telescopic member 51 are respectively connected to the connecting plate 21 and the support base 31.

[0036] Specifically, one end of the telescopic component 51 is fixed to the connecting plate 21 as a reference point, and the other end is connected to the support base 31 as the execution end. When the external control system issues an adjustment command, the telescopic component 51 directly drives the support base 31 to move along the plane of the connecting plate 21 through the change of length. This connection design transforms the telescopic motion into the linear displacement of the support base 31. At the same time, relying on the rigid connection between the connecting plate 21 and the UAV body 1, it ensures that there is no energy loss during the adjustment process and the motion trajectory is stable. At the moment of UAV landing, this mechanism can quickly respond to the slope information fed back by the terrain sensor and dynamically adjust the position of the support base 31 to optimize the landing gear grounding angle, thereby evenly dispersing the landing impact force.

[0037] In this embodiment, when the drone body 1 lands, the side of the transmission rod 42 closer to the connecting plate 21 is higher than the side farther away from the connecting plate 21.

[0038] It should be noted that, through the movable connection between the transmission rod 42, the support base 31, and the landing bar 41, the transmission rod 42 is tilted at a specific angle during the descent phase. At this time, the side away from the connecting plate 21 serves as the initial contact point and preferentially contacts the ground. As the aircraft descends, the ground reaction force is gradually transmitted from the far end to the near end along the transmission rod 42. This transmission process, in conjunction with the rotational characteristics of the landing bar 41, disperses the impact energy to multiple support points rather than concentrating it at a single point, thereby avoiding the tendency of the aircraft to tilt due to sudden changes in local stress. This mechanism, together with the symmetrical layout of the support base 31 and the rotational freedom of the landing bar 41, ensures a smooth and continuous impact absorption process under complex terrain conditions.

[0039] In some preferred embodiments, both the first driving member 43 and the second driving member 44 include a gas spring 413. The gas spring 413 is a buffer device that uses compressed gas to generate nonlinear elastic force. It can be implemented using a single-acting gas spring 413, a double-acting gas spring 413, or an adjustable damping gas spring 413. Its purpose is to automatically match the buffer characteristics according to the landing impact intensity, effectively disperse the local overload stress caused by uneven ground, and prevent the support structure from failing due to rigid impact.

[0040] In this embodiment, the lifting rod 41 includes an outer lifting rod 411 and an inner lifting rod 412. The outer lifting rod 411 is sleeved on the outer periphery of the inner lifting rod 412. A spring 413 is provided inside the outer lifting rod 411, and the free end of the spring 413 is connected to the inner lifting rod 412.

[0041] Understandably, the axial displacement of the inner landing rod 412 within the outer rod triggers the compression of the spring 413, converting the landing impact energy into the deformation potential energy of the spring 413, thereby reducing the peak load transmitted to the main body of the UAV 1. The sleeve structure of the outer landing rod 411 and the inner landing rod 412 ensures axial consistency during movement and prevents lateral deviation, while the fixed connection between the free end of the spring 413 and the inner rod ensures that the buffer stroke is proportional to the magnitude of the impact force, achieving gradual energy absorption. At the moment the UAV touches the ground, the inner landing rod 412 is compressed downwards, causing the spring 413 to compress synchronously, effectively dispersing the impact energy and preventing rigid impact from being directly transmitted to the main structure.

[0042] In some preferred embodiments, a landing pad 414 is provided at the end of the inner landing rod 412. The landing pad 414 refers to a soft contact layer provided at the end of the inner landing rod 412. It can be made of elastic materials such as rubber, silicone or polyurethane. Its purpose is to disperse the impact force at the moment of landing and enhance the friction with the ground, thereby avoiding stress concentration caused by hard collision between the hard end and the ground, and preventing the risk of lateral slippage.

[0043] In some preferred embodiments, a buffer (not shown) is connected between the inner lifting rod 412 and the transmission rod 42. The buffer is a component used to absorb and disperse impact energy, and can be implemented using one or more of a rubber elastomer, a hydraulic damper, or a metal coil spring 413. Its purpose is to reduce stress concentration at critical connection points by providing an additional buffer path, thereby enhancing the structure's adaptability under dynamic loads.

[0044] The above are merely preferred embodiments of this utility model and do not limit the patent scope of this utility model. Any equivalent structural or procedural transformations made based on the description and drawings of this utility model, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of this utility model.

Claims

1. An unmanned aerial vehicle landing gear, characterized by, include: A connecting component, the connecting component including a connecting plate for connecting to the lower end face of the drone body; Several support components, each support component including a support base, are symmetrically arranged on both sides of the connecting plate. The lifting assembly has one end movably connected to the support base, and the other end of the lifting assembly is rotatably equipped with a lifting rod.

2. The UAV landing gear of claim 1, wherein, The lifting assembly includes a transmission rod and a first driving member, with both ends of the first driving member connected to the support base and the middle of the transmission rod, respectively.

3. The UAV landing gear of claim 2, wherein, The landing assembly also includes a second drive member, the two ends of which are respectively connected to the middle of the landing rod and the transmission rod.

4. The UAV landing gear of claim 1, wherein, The landing gear also includes an adjustment assembly disposed on the connecting plate, the adjustment assembly being used to adjust the position of the support base.

5. The UAV landing gear of claim 4, wherein, The adjustment assembly includes a telescopic component, the two ends of which are connected to the connecting plate and the support base, respectively.

6. The UAV landing gear of claim 3, wherein, When the main body of the drone lands, the side of the transmission rod closer to the connecting plate is higher than the side farther away from the connecting plate.

7. The unmanned aerial vehicle landing gear as described in claim 3, characterized in that, Both the first driving component and the second driving component include gas springs.

8. The UAV landing gear of claim 2, wherein, The lifting boom includes an outer lifting boom and an inner lifting boom. The outer lifting boom is sleeved around the outer periphery of the inner lifting boom. A spring is installed inside the outer lifting boom, and the free end of the spring is connected to the inner lifting boom.

9. The UAV landing gear of claim 8, wherein, The end of the inner lifting rod is provided with a lifting pad.

10. The UAV landing gear of claim 8, wherein, A buffer is connected between the lifting inner rod and the transmission rod.

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