Large-load unmanned aerial vehicle supporting frame

Abstract

The utility model belongs to the technical field of unmanned aerial vehicles, and particularly relates to a large-load unmanned aerial vehicle supporting frame which comprises two oppositely-arranged U-shaped supports, a box is installed below the U-shaped supports, the two ends of the two U-shaped supports are connected with first connecting frames, and the connecting frames connected with the ends of the two U-shaped supports extend downwards in an inclined mode. Supporting legs are arranged at the extending ends of the first connecting frames, a second connecting frame is arranged between every two adjacent supporting legs, a buffering assembly is arranged between every two adjacent first connecting frames, a grounding assembly is arranged at the position, making contact with the ground, of a transverse support of each supporting leg, and the buffering assemblies and the grounding assemblies are used for buffering the hedging load on the ground when the unmanned aerial vehicle lands. Rigid conduction between the supports can be reduced, most impact energy can be absorbed after the unmanned aerial vehicle is landed and impacted, overload caused by large loads is buffered, and impact force borne by the undercarriage is reduced.

Description

Technical Field

[0001] The utility model belongs to the technical field of unmanned aerial vehicles (UAVs), and particularly relates to a large-load UAV support frame. Background Art

[0002] A drone typically consists of an airframe, power system, flight control system, and data transmission system. The airframe is the main structure of the drone, while the power system provides the thrust required for flight. The flight control system is responsible for controlling the drone's flight attitude and trajectory, while the data transmission system receives remote control commands and transmits flight data. Drone technology involves sensor technology, communications technology, information processing technology, intelligent control technology, and aerospace propulsion technology. The flight control system is the core of a drone, equivalent to the pilot in a manned aircraft, responsible for the entire flight process, including takeoff, flight, mission execution, and return to the base.

[0003] The drone cushioning system is a key component in drone design. Its primary function is to absorb and disperse impact energy during landing or collision, protecting the drone and its internal components from damage. A drone cushioning system typically consists of a buffer, connectors, mounting brackets, and other components. Prior art techniques mostly use buffers to cushion heavy-load drones, but few improvements have been made to the support frame itself, resulting in rigid damage to the support frame during landing. To address this, the present application proposes several improvements and designs for heavy-load drone support frames. Utility Model Content

[0004] The purpose of this utility model is to provide a large-load UAV support frame, which can reduce the rigidity conduction between the supports, absorb most of the impact energy after the UAV lands and impacts, cushion the overload caused by the relatively large load, and reduce the impact force on the landing gear.

[0005] The technical solutions adopted in this application are as follows:

[0006] A large-load UAV support frame includes two U-shaped brackets arranged opposite to each other, and a box is installed below the U-shaped brackets;

[0007] The two ends of the two U-shaped brackets are connected to a first connecting frame, and the connecting frames connected to the ends of the two U-shaped brackets are both inclined downward and extended, and the extended end of the first connecting frame is provided with a supporting leg, and a second connecting frame is provided between two adjacent supporting legs;

[0008] A buffer component is provided between two adjacent first connecting frames, and a grounding component is provided at the cross-bracing position where the supporting legs contact the ground. The buffer component and the grounding component are used to buffer the impact load on the ground when the drone lands.

[0009] In a preferred embodiment, the support leg is U-shaped, with one end connected to the first connecting frame and the other end connected to the second connecting frame;

[0010] The first connecting frame, the supporting legs and the second connecting frame on both sides are in an outwardly expanding shape away from each other.

[0011] In a preferred embodiment, the second connecting frame is arched.

[0012] In a preferred embodiment, the buffer assembly includes a shell, the interior of the shell is provided with chambers at both ends, a movable and retractable pull rod is provided in the chamber, the pull rod extends out of the shell, and a clamping ring is provided at the end, and the clamping ring is sleeved on the first connecting frame.

[0013] In a preferred solution, a first spring is provided inside the chamber, and the first spring is sleeved on the ring side of the pull rod.

[0014] In a preferred embodiment, the grounding assembly includes a grounding foot, the grounding foot is adapted to support the foot and is provided with a through hole, a protrusion is provided on the grounding foot and located on the inner annular surface of the through hole, and an arc-shaped plug is provided on the protrusion in a clockwise direction.

[0015] In a preferred embodiment, a deformation cavity is provided on the outer ring surface of the support leg at a position corresponding to the protrusion, and a socket is provided in the deformation cavity at a position corresponding to the arc-shaped plug column in a clockwise direction, and an air hole communicating with the outside is provided at the terminal end of the socket.

[0016] In a preferred solution, a second spring is sleeved inside the deformation cavity and on the side of the arc-shaped plug ring.

[0017] The technical effects achieved by this utility model are:

[0018] In the present invention, when the drone touches the ground, the grounding legs retract due to the thrust, the arc-shaped plug post on the protrusion is inserted into the inside of the socket, the second spring is compressed, and as the arc-shaped plug post extends, the internal gas of the socket is discharged from the air hole. In this process, the arc-shaped plug post, the socket and the air hole cooperate to form a simple buffer cavity with a certain damping effect. When the four grounding components are grounded and retracted, the second spring and the socket achieve a good buffering effect.

[0019] In this utility model, the special design of the support frame and the buffer component of the first connecting frame are used as the secondary buffer, and the cooperation of the support legs and the grounding component is used as the tertiary buffer, which can absorb most of the impact energy after the UAV lands and impacts, buffer the overload caused by the relatively large load, and reduce the impact force on the landing gear. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of the overall structure of this utility;

[0021] Figure 2 It is a structural diagram of the support frame in this utility model;

[0022] Figure 3 It is a structural diagram of the buffer component in this utility;

[0023] Figure 4 It is a schematic diagram of the cross-sectional structure of the support legs and the grounding assembly in this utility model;

[0024] Figure 5 This is a schematic diagram of the enlarged structure of the details of point A in this utility model;

[0025] Figure 6 It is a structural diagram of the U-shaped bracket, the first connecting frame, the supporting legs and the grounding component in this utility model.

[0026] In the accompanying drawings, the components represented by the reference numerals are as follows:

[0027] 1. U-shaped bracket; 2. Box; 3. First connecting frame;

[0028] 4. Buffer assembly; 401. Housing; 402. Chamber; 403. Pull rod; 404. First spring; 405. Snap ring;

[0029] 5. Support legs; 501. Deformation cavity; 502. Insertion hole; 503. Air hole;

[0030] 6. Grounding assembly; 601. Grounding foot; 602. Bump; 603. Arc-shaped plug; 604. Second spring;

[0031] 7. Second connecting frame. DETAILED DESCRIPTION

[0032] In order to make the above-mentioned purposes, features and advantages of the present invention more obvious and easy to understand, the specific implementation methods of the present invention are described in detail below in conjunction with the accompanying drawings.

[0033] In the following description, many specific details are set forth to facilitate a full understanding of the present invention, but the present invention may also be implemented in other ways different from those described herein, and those skilled in the art may make similar generalizations without violating the connotation of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0034] Secondly, the term "one embodiment" or "embodiment" herein refers to a specific feature, structure, or characteristic that may be included in at least one implementation of the present invention. The phrase "in a preferred embodiment" appearing in various places in this specification does not necessarily refer to the same embodiment, nor does it constitute a separate or selective embodiment that is mutually exclusive with other embodiments.

[0035] Thirdly, the utility is described in detail in combination with the schematic diagram. In the detailed description of the utility, the sectional view of the device structure is partially enlarged without the general proportion for the convenience of description, and the schematic diagram is only an example, which should not limit the scope of the utility protection. In addition, the three-dimensional spatial dimensions of length, width and depth should be included in the actual manufacturing.

[0036] Please refer to the attached Figure 1-6 The utility provides a large-load unmanned aerial vehicle support frame. The support frame comprises two oppositely arranged U-shaped supports 1, a box body 2 is arranged below the U-shaped supports 1, first connecting frames 3 are connected to the two ends of the two U-shaped supports 1, the connecting frames connected to the ends of the two U-shaped supports 1 are all downwardly inclined and extended, supporting legs 5 are arranged at the extended ends of the first connecting frames 3, second connecting frames 7 are arranged between two adjacent supporting legs 5, buffer assemblies 4 are arranged between two adjacent first connecting frames 3, grounding assemblies 6 are arranged at the positions of the supporting legs 5 contacting the ground, and the buffer assemblies 4 and the grounding assemblies 6 are used to buffer the head-on load on the ground when the unmanned aerial vehicle lands.

[0037] The box body 2 can contain liquid medicine or plant seeds, fertilizers, feed and other materials that need to be filled, for example, during the seeding period, the unmanned aerial vehicle can carry out seeding operation, and the box body 2 is filled with crops such as wheat and rape for sowing in the farmland.

[0038] Please refer to Figure 2 The supporting legs 5 are in the shape of “U”, one end of each supporting leg 5 is connected to the first connecting frame 3, the other end is connected to the second connecting frame 7, and the two first connecting frames 3, the supporting legs 5 and the second connecting frames 7 are outwardly expanded.

[0039] Please refer to Figure 2 The second connecting frame 7 is in the shape of an arch.

[0040] Please refer to Figure 3 The buffer assembly 4 comprises a shell 401, chambers 402 are arranged at the two ends inside the shell 401, pull rods 403 movably and telescopically arranged in the chambers 402, the pull rods 403 extend out of the shell 401, snap rings 405 are arranged at the ends, the snap rings 405 are sleeved on the first connecting frames 3, first springs 404 are arranged inside the chambers 402, and the first springs 404 are sleeved on the ring sides of the pull rods 403.

[0041] Specifically, since the four support legs 5 are far apart and any two adjacent support legs 5 are outwardly inclined, when the unmanned aerial vehicle falls, the outwardly inclined support legs 5 will first deform slightly to buffer the load of the falling, and secondly, the two adjacent first connecting frames 3 have the second level of buffering, when the unmanned aerial vehicle falls with a large load, since the first connecting frame 3 will deform outwardly, the pull rod 403 will stretch to both sides, the internal first spring 404 will buffer and release energy, and the rigidity transmission between the supports will be reduced.

[0042] Please refer to Figure 4-6 The grounding assembly 6 comprises a ground contact leg 601, the ground contact leg 601 is adapted to the support leg 5 and has a through hole, the outer ring surface of the ground contact leg 601 and located in the through hole is provided with a protrusion 602, and the protrusion 602 is provided with an arc-shaped insertion column 603 in the clockwise direction.

[0043] Please refer to Figure 4-6 The outer ring surface of the support leg 5 is provided with a deformation cavity 501 corresponding to the position of the protrusion 602, and the deformation cavity 501 is further provided with an insertion hole 502 in the clockwise direction corresponding to the position of the arc-shaped insertion column 603, the terminal end of the insertion hole 502 is provided with a gas hole 503 communicating with the outside, and the inside of the deformation cavity 501 and located at the side of the arc-shaped insertion column 603 is sleeved with a second spring 604.

[0044] More specifically, in the normal state, due to the supporting force of the second spring 604, the included angle between the support leg 5 and the grounding assembly 6 is obtuse, when the grounding assembly 6 is grounded, the second spring 604 is compressed, and the included angle between the support leg 5 and the grounding assembly 6 is acute.

[0045] In summary, when the unmanned aerial vehicle is grounded, the ground contact leg 601 is retracted due to the thrust, the arc-shaped insertion column 603 on the protrusion 602 is inserted into the inside of the insertion hole 502, and the second spring 604 is compressed, since the arc-shaped insertion column 603 is inserted, the gas in the inside of the insertion hole 502 is discharged from the gas hole 503, in this process, the arc-shaped insertion column 603, the insertion hole 502 and the gas hole 503 cooperate to form a simple buffer cavity, which has a certain damping effect, when the four grounding assemblies 6 are retracted, the second spring 604 and the insertion hole 502 achieve good buffering effect, the special design of the support frame in the application, and the second level of buffering of the buffering assembly 4 of the first connecting frame 3, and the third level of buffering of the cooperation between the support leg 5 and the grounding assembly 6, can absorb most of the impact energy after the unmanned aerial vehicle lands and hits, buffer the overload caused by a relatively large load, and reduce the impact force on the landing gear.

[0046] The above description is only a preferred embodiment of the present invention. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principles of the present invention, and such improvements and modifications should also be considered within the scope of protection of the present invention. Structures, devices, and operating methods not specifically described or explained in this application shall be implemented in accordance with conventional means in the art unless otherwise specified or limited.

Claims

1. A large-load UAV support frame, characterized by: It comprises two U-shaped brackets (1) arranged opposite to each other, with a box (2) installed below the U-shaped brackets (1); The two ends of the two U-shaped brackets (1) are connected to a first connecting frame (3), and the connecting frames connected to the ends of the two U-shaped brackets (1) are both inclined downwardly and extended, and the extended end of the first connecting frame (3) is provided with a supporting leg (5), and a second connecting frame (7) is provided between two adjacent supporting legs (5); A buffer assembly (4) is provided between two adjacent first connecting frames (3), and a grounding assembly (6) is provided at a cross-bracing position where the supporting legs (5) contact the ground. The buffer assembly (4) and the grounding assembly (6) are used to buffer the impact load on the ground when the drone lands.

2. The large-load UAV support according to claim 1, characterized in that: The supporting leg (5) is U-shaped, one end of which is connected to the first connecting frame (3) and the other end of which is connected to the second connecting frame (7); The first connecting frame (3), the supporting legs (5) and the second connecting frame (7) on both sides are in an outwardly expanding shape away from each other.

3. The large-load UAV support according to claim 1, characterized in that: The second connecting frame (7) is arched.

4. The large-load UAV support according to claim 1, characterized in that: The buffer assembly (4) includes a shell (401), wherein chambers (402) are provided at both ends of the shell (401), and a movable and retractable pull rod (403) is provided in the chamber (402). The pull rod (403) extends outside the shell (401) and is provided with a snap ring (405) at the end thereof, and the snap ring (405) is sleeved on the first connecting frame (3).

5. The large-load UAV support according to claim 4, characterized in that: A first spring (404) is provided inside the chamber (402), and the first spring (404) is sleeved on the ring side of the pull rod (403).

6. The large-load UAV support according to claim 1, characterized in that: The grounding assembly (6) comprises a ground contact leg (601), the ground contact leg (601) being adapted to support the leg (5) and provided with a through hole, a protrusion (602) being provided on the ground contact leg (601) and located on the inner annular surface of the through hole, and an arc-shaped plug post (603) being provided on the protrusion (602) in a clockwise direction.

7. The large-load UAV support according to claim 6, characterized in that: A deformation cavity (501) is provided on the outer ring surface of the support leg (5) at a position corresponding to the protrusion (602), and a plug hole (502) is provided in the deformation cavity (501) at a position corresponding to the arc-shaped plug column (603) in a clockwise direction, and an air hole (503) communicating with the outside is provided at the terminal end of the plug hole (502).

8. The large-load UAV support according to claim 7, characterized in that: A second spring (604) is sleeved inside the deformation cavity (501) and on the side of the arc-shaped plug post (603).

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