Undercarriage of unmanned aerial vehicle

Abstract

The utility model discloses an unmanned aerial vehicle undercarriage which comprises an undercarriage body arranged on a fuselage of an unmanned aerial vehicle and a supporting structure arranged on the undercarriage body. The undercarriage body comprises two supporting rods and two longitudinal rods, the upper ends of the two supporting rods are connected to the two symmetrical sides of the fuselage respectively, the two longitudinal rods are relatively parallel and arranged at intervals, and the lower ends of the supporting rods are connected to the middles of the corresponding longitudinal rods through three-way connecting pieces respectively; the supporting structure comprises a transverse rod, the transverse rod is vertically arranged between the two longitudinal rods, the two ends of the transverse rod are connected to the two longitudinal rods respectively, and the two ends of the transverse rod are arranged close to the middles of the corresponding longitudinal rods respectively. According to the landing gear, the landing gear body is arranged to be of the triangular structure so as to stably support the unmanned aerial vehicle, the landing gear body is effectively prevented from being deformed due to outward expansion or inward contraction under stress through the supporting structure arranged on the landing gear body, the stability and balance of standing and flying of the unmanned aerial vehicle are facilitated, and the landing gear is simple in structure.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicle equipment, and particularly relates to an undercarriage of an unmanned aerial vehicle. Background Art

[0002] An unmanned aerial vehicle, also called an unmanned aircraft, is an aircraft that can fly by itself without a person sitting inside to control it. They can be used in many places, such as taking pictures, delivering express packages, rescue, etc. In order to enable the unmanned aerial vehicle to take off and land smoothly, designers will install an undercarriage on the unmanned aerial vehicle. The undercarriage is like the "feet" of the unmanned aerial vehicle, allowing it to stand on the ground. The undercarriage not only enables the unmanned aerial vehicle to stand firmly on the ground, but also protects it from damage. However, the setting of the undercarriage will inevitably increase the own weight of the unmanned aerial vehicle and bring flight consumption.

[0003] Therefore, the existing undercarriages are mostly made of carbon fiber composite materials to reduce the load of the unmanned aerial vehicle. Although this material has many performance advantages such as light weight, high strength, anti-creep, corrosion resistance, fatigue resistance, and strong vibration resistance, it will deform after bearing a certain weight of the fuselage or after long-term use, thus affecting the standing stability and flight balance of the unmanned aerial vehicle. Summary of the Invention

[0004] In order to overcome the above defects, the utility model provides an undercarriage of an unmanned aerial vehicle, which is simple and lightweight in structure, and ensures that the undercarriage does not deform through the provided support structure, which is beneficial to the stability and balance of the standing and flight of the unmanned aerial vehicle.

[0005] The technical solution adopted by the utility model to solve its technical problems is: to provide an undercarriage of an unmanned aerial vehicle, which includes an undercarriage body arranged on the fuselage of the unmanned aerial vehicle, and a support structure arranged on the undercarriage body;

[0006] The undercarriage body includes two support rods and two longitudinal rods. The upper ends of the two support rods are respectively connected to the symmetric sides of the fuselage, and are arranged at a certain angle downward and outward from top to bottom. The two longitudinal rods are relatively parallel and arranged at intervals. The lower ends of the support rods are respectively connected to the middle parts of the corresponding longitudinal rods through three-way connectors;

[0007] The support structure includes a cross bar, the cross bar is vertically arranged between the two longitudinal rods, and the two ends of the cross bar are respectively connected to the two longitudinal rods, and the two ends are respectively arranged close to the middle parts of the corresponding longitudinal rods.

[0008] As a further improvement of the utility model, the two ends of the cross bar are respectively detachably connected to the two longitudinal rods through connectors;

[0009] The connecting member is provided with a first mounting hole adapted to the longitudinal rod, a second mounting hole arranged perpendicular to the first mounting hole and adapted to the cross rod, and a slot hole opened along the axial direction of the second mounting hole and communicating with the first mounting hole.

[0010] As a further improvement of the present utility model, the cross rod is a spliced rod composed of two support rods. The docking part of the two support rods is connected by a locking member. The locking member is provided with internal threads, and the outer peripheral walls of the relatively close ends of the two support rods are provided with external threads matching the internal threads.

[0011] As a further improvement of the present utility model, the external threads on one support rod are arranged in a clockwise rotation around its axis, while the external threads on the other support rod are arranged in a counterclockwise rotation around its axis.

[0012] As a further improvement of the present utility model, the locking member is of a cylindrical structure, and anti-slip grooves are provided on its outer peripheral surface.

[0013] As a further improvement of the present utility model, the landing gear body further includes four legs. The legs are of a cylindrical structure. Two legs are respectively arranged on each longitudinal rod, and the two legs are symmetrically arranged near the two ends of the longitudinal rod.

[0014] As a further improvement of the present utility model, the support rod, the longitudinal rod and the cross rod are all hollow tubular structures.

[0015] As a further improvement of the present utility model, dust caps are respectively covered at both ends of the longitudinal rod.

[0016] As a further improvement of the present utility model, both the landing gear body and the support structure are made of carbon fiber composite material or glass fiber composite material.

[0017] The beneficial effects of the present utility model are as follows: On the one hand, by setting the landing gear body as a triangular structure to achieve stable support of the unmanned aerial vehicle, and through the support structure arranged on the landing gear body, it effectively avoids the deformation of the landing gear body due to external force expansion or internal contraction, which is beneficial to the stability and balance of the unmanned aerial vehicle during standing and flight, and the structure is simple; on the other hand, the unmanned aerial vehicle landing gear provided by the present utility model is made of carbon fiber composite material or glass fiber composite material, and each rod is made of a hollow pipe fitting, which further reduces the weight of the unmanned aerial vehicle landing gear to meet the requirement of lightweight landing gear and reduce the load of the unmanned aerial vehicle. Description of the Drawings

[0018] Figure 1 is a structural schematic diagram of the present utility model;

[0019] Figure 2 is a structural schematic diagram of the present utility model without the support structure;

[0020] Figure 3 is a schematic diagram of the state of the front view of the present utility model Figure 1 ;

[0021] Figure 4 is a schematic diagram of the structure of the support structure of the present utility model

[0022] The following description will be made with reference to the accompanying drawings

[0023] 1. Airframe; 11. Camera connection bracket; 2. Landing gear body; 21. Support rod;

[0024] 22. Longitudinal rod; 23. Three-way connector; 24. Leg; 25. Dust cap; 3. Support structure; 31. Connector; 311. First mounting hole; 312. Second mounting hole; 313. Slot hole; 32. Support rod; 321. External thread; 33. Locking member; 331. Anti-slip groove Specific embodiments

[0025] The following will describe in detail a preferred embodiment of the present utility model with reference to the accompanying drawings

[0026] Refer to Figures 1 to 4 , the present utility model provides an unmanned aerial vehicle landing gear, which includes a landing gear body 2 provided on the airframe 1 of the unmanned aerial vehicle, and a support structure 3 provided on the landing gear body 2. The landing gear body 2 is used to stably support the unmanned aerial vehicle, and the support structure 3 is used to support the landing gear body 2 to prevent it from deforming

[0027] Among them, the landing gear body 2 is made of carbon fiber composite material or glass fiber composite material to meet the requirement of light weight of the landing gear body 2. The landing gear body 2 includes two support rods 21 and two longitudinal rods 22, and both the support rods 21 and the longitudinal rods 22 are hollow tubular structures to further reduce the weight of the landing gear body 2. The upper ends of the two support rods 21 are respectively connected to the symmetric two sides of the airframe 1, and are arranged at a certain angle from top to bottom and outward. It should be noted that both the two support rods 21 and the airframe 1 are connected by quick-release joints to realize the quick installation and disassembly of the landing gear body 2 and the airframe. This quick-release joint belongs to the prior art and is not the key point improved in this application, so it will not be elaborated in detail

[0028] The two longitudinal rods 22 are relatively parallel and arranged at intervals, and the lower ends of the support rods 21 are respectively connected to the middle parts of the corresponding longitudinal rods 22 through three-way connectors 23

[0029] With the above settings, on the one hand, the support rod 21 and the longitudinal rod 22 are assembled into an "L"-shaped leg through the three-way connector 23, and two "L"-shaped legs are symmetrically arranged along the fuselage 1 to ensure the balance of the aircraft during flight. On the other hand, the two "L"-shaped legs are arranged in a triangular structure in space (refer to Figure 3 ), and the angle range of the top inner angle α of the triangular structure is 48° to 54°, and preferably 52°, to ensure the stability of the landing gear body 2, so as to ensure that the UAV can be stably supported when standing. It should be noted that generally, patterns are provided inside the tube of the three-way connector 23 to facilitate the connection of the support rod 21 and the longitudinal rod 22 to the three-way connector 23 in an interference fit manner, thereby ensuring the firmness of the connection.

[0030] Furthermore, the landing gear body 2 further includes four legs 24. The legs 24 are cylindrical structures, and two of the legs 24 are respectively arranged on each of the longitudinal rods 22, and the two legs 24 are symmetrically arranged near the two ends of the longitudinal rod 22 to ensure the balance of the forces at both ends of the longitudinal rod 22. In addition, dust caps 25 are respectively provided at both ends of the longitudinal rod 22.

[0031] Refer to Figure 3 and 4 , the support structure 3 is also made of carbon fiber composite material or glass fiber composite material. It includes a cross bar with a hollow tubular structure, and the cross bar is vertically arranged between the two longitudinal rods 22. The two ends of the cross bar are respectively connected to the two longitudinal rods 22, and are respectively arranged near the middle of the corresponding longitudinal rod 22. It should be noted that refer to Figure 1 , a camera connection bracket 11 is provided at the bottom of one side of the conventional fuselage 1. Therefore, although the support structure 3 provided in this embodiment has a light weight and has little impact on the UAV during flight, in order to ensure the rationality of force distribution, the support structure 3 is arranged on the side of the support rod 21 away from the camera connection bracket 11 in this embodiment.

[0032] Specifically, both ends of the cross bar are detachably connected to the two longitudinal bars 22 through connectors 31. The connector 31 is provided with a first mounting hole 311 adapted to the longitudinal bar 22, a second mounting hole 312 perpendicular to the first mounting hole 311 and adapted to the cross bar, and a slot hole 313 axially opened along the second mounting hole 312 and communicating with the first mounting hole 311. The setting of the slot hole 313 makes the first mounting hole 311 and the second mounting hole 312 variable, similar to the existing clamp. After the end of the cross bar is inserted into the second mounting hole 312, a locking screw (not shown in the figure) passes through the connection holes on the connector 31 and the cross bar and is locked. During the locking process, the slot width of the slot hole 313 gradually decreases, so as to realize the detachable connection between the support structure 3 and the longitudinal bar 22. Moreover, this installation method is simple and reliable. By setting the cross bar, the distance between the two longitudinal bars 22 is ensured, effectively avoiding the deformation of the landing gear body 2 caused by the outward expansion or inward contraction due to force.

[0033] Furthermore, the cross bar is a spliced bar composed of two support bars 32. The docking part of the two support bars 32 is connected by a locking member 33. The locking member 33 is a cylindrical structure with a through hole. The through hole is provided with internal threads. The outer peripheral walls of the relatively close ends of the two support bars 32 are provided with external threads 321 matching the internal threads. When the external threads 321 on one support bar 32 are arranged in a clockwise rotation around its axis, the external threads 321 on the other support bar 32 are arranged in a counterclockwise rotation around its axis. Therefore, when the locking member 33 is rotated, the relatively close ends of the two support bars 32 approach or move away from each other along their axes under the action of the positive and negative threads, so as to realize the fine adjustment of the length of the cross bar. The outer peripheral surface of the locking member 33 is provided with anti-slip grooves 331 to facilitate the operator to manually rotate the locking member 33.

[0034] In summary, for the drone landing gear provided by the present utility model, on the one hand, by setting the landing gear body as a triangular structure to realize the stable support of the drone, and through the support structure arranged on the landing gear body, the deformation of the landing gear body caused by the outward expansion or inward contraction due to force is effectively avoided, which is beneficial to the stability and balance of the drone standing and flying, and the structure is simple; on the other hand, the drone landing gear provided by the present utility model is made of carbon fiber composite material or glass fiber composite material, and each rod is made of a hollow pipe fitting, which further reduces the weight of the drone landing gear, so as to meet the requirement of lightweight of the landing gear and reduce the load of the drone.

[0035] In the above description, many specific details are set forth in order to fully understand the present utility model. However, the above description is only a preferred embodiment of the present utility model, and the present utility model can be implemented in many other ways different from those described herein. Therefore, the present utility model is not limited by the specific embodiments disclosed above. At the same time, any person skilled in the art can make many possible changes and modifications to the technical solution of the present utility model by using the methods and technical contents disclosed above without departing from the scope of the technical solution of the present utility model, or modify it into an equivalent embodiment with equivalent changes. All contents that do not depart from the technical solution of the present utility model, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present utility model are still within the scope of protection of the technical solution of the present utility model.

Claims

1. An unmanned aerial vehicle landing gear, characterized in that: It includes a landing gear body (2) provided on the fuselage (1) of the unmanned aerial vehicle, and a support structure (3) provided on the landing gear body (2); The landing gear body (2) includes two support rods (21) and two longitudinal rods (22). The upper ends of the two support rods (21) are respectively connected to the symmetrical two sides of the fuselage (1), and are arranged at a certain angle downward and outward from top to bottom. The two longitudinal rods (22) are relatively parallel and arranged at intervals. The lower ends of the support rods (21) are respectively connected to the middle parts of the corresponding longitudinal rods (22) through tee connectors (23); The support structure (3) includes a cross bar which is vertically arranged between the two longitudinal rods (22). The two ends of the cross bar are respectively connected to the two longitudinal rods (22), and the two ends are respectively arranged close to the middle parts of the corresponding longitudinal rods (22).

2. The landing gear of the drone according to claim 1, characterized in that: The two ends of the cross bar are respectively detachably connected to the two longitudinal rods (22) through connectors (31); The connector (31) is provided with a first mounting hole (311) adapted to the longitudinal rod (22), a second mounting hole (312) arranged perpendicular to the first mounting hole (311) and adapted to the cross bar, and a slot hole (313) opened along the axial direction of the second mounting hole (312) and communicated with the first mounting hole (311).

3. The drone landing gear according to claim 2, characterized in that: The cross bar is a spliced rod composed of two support bars (32). The docking part of the two support bars (32) is connected by a locking member (33). The locking member (33) is provided with internal threads, and the outer peripheral walls of the relatively close ends of the two support bars (32) are provided with external threads (321) matching the internal threads.

4. The drone landing gear according to claim 3, characterized in that: The external threads (321) on one support bar (32) are arranged in a clockwise rotation around its axis, while the external threads (321) on the other support bar (32) are arranged in a counterclockwise rotation around its axis.

5. The drone landing gear according to claim 3, wherein: The locking member (33) is of a cylindrical structure, and its outer peripheral surface is provided with anti-slip grooves (331).

6. The drone landing gear according to claim 4, characterized in that: The landing gear body (2) further includes four legs (24). The legs (24) are of a cylindrical structure. Two legs (24) are respectively arranged on each longitudinal rod (22), and the two legs (24) are symmetrically arranged close to the two ends of the longitudinal rod (22).

7. The drone landing gear according to claim 6, characterized in that: The support rods (21), the longitudinal rods (22) and the cross bar are all hollow tubular structures.

8. The drone landing gear according to claim 7, characterized in that: Dust caps (25) are respectively covered at the two ends of the longitudinal rod (22).

9. The drone landing gear according to claim 8, characterized in that: Both the landing gear body (2) and the support structure (3) are made of carbon fiber composite materials or glass fiber composite materials.

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