Framework structure of unmanned aerial vehicle

Abstract

The utility model provides an unmanned aerial vehicle skeleton structure, which relates to the technical field of unmanned aerial vehicles, and comprises a cushioning landing mechanism, the outer surface wall of the cushioning landing mechanism is fixedly connected with a wing protection mechanism, and the cushioning landing mechanism comprises a machine body protection bottom plate. According to the unmanned aerial vehicle landing device, under the action of the cushioning landing mechanism, the fixed plate is connected with the four supporting plates through the tension springs, the landing wheels are additionally arranged at the bottoms of the supporting plates, when the unmanned aerial vehicle lands, the supporting plates are forked towards the two sides under the action of the landing wheels and the gravity, and meanwhile the speed of opening the supporting plates towards the two sides is reduced under the action of the tension springs; the impact force is effectively dispersed and absorbed, when the tension spring is reset, the stability of the fuselage is guaranteed, the impact force and vibration borne by the unmanned aerial vehicle during landing are effectively relieved, the damage risk of the unmanned aerial vehicle is reduced, the stability and safety of the unmanned aerial vehicle are improved, and the service life of the unmanned aerial vehicle is prolonged.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a skeleton structure of an unmanned aerial vehicle. Background Art

[0002] In the early development stages of drones, the frames were mainly made of wood, metal or other traditional materials. The development history of drone frames is a process of continuous innovation and progress. With the continuous emergence of new materials, new technologies and new applications, drone frames will gradually develop and improve, providing strong support for the widespread application of drones.

[0003] In the prior art, the landing gear of the drone frame mostly uses a rigid structure to directly support the drone. When the drone lands, it will generate a large impact force, increasing the risk of damage to the fuselage. The unbuffered impact force will also cause the drone to be damaged by ground objects during landing, and even cause irreversible damage to the precision components inside the fuselage. At the same time, the existing drone frame cannot effectively protect the wings during flight. Utility Model Content

[0004] The purpose of the utility model is to solve the problem that when the above-mentioned equipment is in use, since most of the existing UAV skeleton landing gears are supported by a rigid structure, they cannot play a good buffering role in the face of the impact force generated when the UAV lands, resulting in an increased risk of damage to the fuselage, and a UAV skeleton structure is proposed.

[0005] In order to achieve the above-mentioned purpose, the utility model adopts the following technical solutions: a skeleton structure of a UAV, including a shock-absorbing landing mechanism, the outer surface wall of the shock-absorbing landing mechanism is fixedly connected to a wing protection mechanism;

[0006] The shock-absorbing landing mechanism includes an organism protection bottom plate, and four groups of brackets are fixedly connected to the bottom of the organism protection bottom plate. One side of the outer wall of the four groups of brackets is provided with a hole A, and a connecting shaft A is fixedly inserted between the inner walls of the four groups of holes A. The outer walls of the four connecting shafts A are movably sleeved with support plates, and one side of the outer wall of the four support plates is provided with a group of holes B.

[0007] Preferably, a connecting shaft B is fixedly inserted into the inner wall of the four groups of holes B, three landing wheels are movably sleeved on the outer walls of the four connecting shafts B, and a tension spring is fixedly connected to one side of the outer wall of the four support plates.

[0008] Preferably, a fixing plate is fixedly connected between the outer walls of the four tension springs, and the top of the fixing plate is fixedly connected to the bottom of the machine body protection bottom plate.

[0009] Preferably, the wing protection mechanism includes a fuselage, and four wings are fixedly installed on the outer wall of the fuselage, and the outer walls of the four wings are fixedly covered with arm protection shells, and the outer walls of the four arm protection shells are fixedly connected with internal baffles.

[0010] Preferably, the outer walls of the four internal baffles are all fixedly connected with a group of telescopic rods, and the outer walls of the four groups of telescopic rods are all movably sleeved with buffer springs.

[0011] Preferably, an external baffle is fixedly connected between the outer surfaces of the four groups of telescopic rods, and anti-collision rubber strips are fixedly connected to the outer surfaces of the four external baffles.

[0012] Preferably, the top of the machine body protection bottom plate is fixedly connected to the bottom of the machine body, and the outer wall of the machine body protection bottom plate is fixedly connected to one side of the outer wall of the four machine arm protection shells.

[0013] Compared with the prior art, the advantages and positive effects of the utility model are:

[0014] 1. In the utility model, under the action of the shock-absorbing landing mechanism, a tension spring is used to connect the fixing plate and four support plates, and a plurality of landing wheels are added at the bottom of the support plate. When the UAV lands, the support plate is forked to both sides by the landing wheels and gravity, and at the same time, the speed of the support plate opening to both sides is slowed down under the action of the tension spring, so that the impact force is effectively dispersed and absorbed. When the tension spring is reset, the stability of the fuselage is ensured, the impact force and vibration of the UAV during landing are effectively slowed down, the risk of damage to the UAV is reduced, and the stability, safety and service life of the UAV are improved.

[0015] 2. In the utility model, under the action of the wing protection mechanism, the internal baffle is set on the periphery of the propeller part of the wing by using the arm protection cover, so that the internal baffle can effectively protect the propeller. At the same time, multiple buffer devices are used to connect the external baffle with the internal baffle, and anti-collision strips are further added to the outer wall of the external baffle to effectively improve the protection mechanism's absorption of the impact force when facing a collision with an obstacle, effectively protecting the wings of the drone and reducing the risk of wing damage. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 A main structural stereogram of a UAV skeleton structure is proposed for the utility model;

[0017] Figure 2 A three-dimensional diagram of a shock-absorbing landing mechanism in a skeleton structure of a UAV is proposed for the utility model;

[0018] Figure 3 A three-dimensional disassembled diagram of a shock-absorbing landing mechanism in the skeleton structure of a UAV is proposed for the utility model;

[0019] Figure 4 The utility model provides a three-dimensional disassembled diagram of a wing protection mechanism in a skeleton structure of a UAV.

[0020] Legend:

[0021] 1. Shock-absorbing landing mechanism; 101. Body protection bottom plate; 102. Bracket; 103. Hole A; 104. Connecting shaft A; 105. Support plate; 106. Hole B; 107. Connecting shaft B; 108. Landing wheel; 109. Tension spring; 110. Fixing plate;

[0022] 2. Wing protection mechanism; 201. Fuselage; 202. Wing; 203. Arm protection cover; 204. Internal baffle; 205. Telescopic rod; 206. Buffer spring; 207. External baffle; 208. Anti-collision rubber strip. DETAILED DESCRIPTION

[0023] In order to more clearly understand the above-mentioned purpose, features and advantages of the utility model, the utility model is further described below in conjunction with the accompanying drawings and embodiments. It should be noted that the embodiments of the present application and the features in the embodiments can be combined with each other without conflict.

[0024] In the following description, many specific details are set forth to facilitate a full understanding of the present invention. However, the present invention may also be implemented in other ways than those described herein. Therefore, the present invention is not limited to the specific embodiments of the following disclosure.

[0025] Embodiment 1, as Figure 1-Figure 4 As shown, the utility model provides a UAV skeleton structure, including a shock absorbing landing mechanism 1, and an outer surface wall of the shock absorbing landing mechanism 1 is fixedly connected with a wing protection mechanism 2;

[0026] The shock-absorbing landing mechanism 1 includes an organism protection base plate 101, and four groups of brackets 102 are fixedly connected to the bottom of the organism protection base plate 101. One side of the outer wall of the four groups of brackets 102 is provided with holes A103, and a connecting shaft A104 is fixedly inserted between the inner walls of the four groups of holes A103. The outer walls of the four connecting shafts A104 are movably sleeved with support plates 105, and one side of the outer wall of the four support plates 105 is provided with a group of holes B106, and the inner walls of the four groups of holes B106 are fixedly inserted with a connecting shaft B107, and the outer walls of the four connecting shafts B107 are movably sleeved with three landing wheels 108. One side of the outer wall of the four support plates 105 is fixedly connected with tension springs 109, and a fixing plate 110 is fixedly connected between the outer walls of the four tension springs 109, and the top of the fixing plate 110 is fixedly connected to the bottom of the organism protection base plate 101.

[0027] The effect achieved by the entire embodiment 1 is that, under the action of the shock-absorbing landing mechanism 1, four groups of holes A103 are opened on one side of the outer wall of the four groups of brackets 102, and four connecting shafts A104 are respectively fixedly inserted between the inner surface walls of the four groups of holes A103, and at the same time, the outer surface walls of the four connecting shafts A104 are movably sleeved with support plates 105, and one group of holes B106 is opened on one side of the outer wall of the four support plates 105, and the inner surface walls of the four groups of holes B106 are fixedly inserted with a connecting shaft B107, and the three landing wheels 108 movably sleeved on the outer surface walls of the four connecting shafts B107 are used to support the drone during landing. The plate 105 can be opened to both sides under the action of the landing wheel 108. At the same time, tension springs 109 are fixedly connected to one side of the outer wall of the four support plates 105, and a fixed plate 110 is fixedly connected between the outer walls of the four tension springs 109. In this way, the speed of the support plates 105 opening to both sides is slowed down under the action of the tension springs 109, so that the impact force is effectively dispersed and absorbed. When the tension springs 109 are reset, the stability of the fuselage 201 is guaranteed, which effectively reduces the impact force and vibration of the drone during landing, reduces the risk of damage to the drone, and improves the stability, safety and service life of the drone.

[0028] Embodiment 2, as Figure 2-Figure 4 As shown, the wing protection mechanism 2 includes a fuselage 201, four wings 202 are fixedly installed on the outer wall of the fuselage 201, the outer walls of the four wings 202 are fixedly sleeved with arm protection shells 203, the outer walls of the four arm protection shells 203 are fixedly connected with internal baffles 204, the outer walls of the four internal baffles 204 are fixedly connected with a group of telescopic rods 205, the outer walls of the four groups of telescopic rods 205 are movably sleeved with buffer springs 206, an external baffle 207 is fixedly connected between the outer walls of the four groups of telescopic rods 205, the outer walls of the four external baffles 207 are fixedly connected with anti-collision rubber strips 208, the top of the body protection bottom plate 101 is fixedly connected to the bottom of the fuselage 201, and the outer wall of the body protection bottom plate 101 is fixedly connected to one side of the outer wall of the four arm protection shells 203.

[0029] The effect achieved by the entire embodiment 2 is that, under the action of the wing protection mechanism 2, four arm protection shells 203 are fixedly sleeved on the outer walls of the four wings 202, so as to protect the wings 202. At the same time, the outer walls of the four arm protection shells 203 are fixedly connected with internal baffles 204, and the outer walls of the four internal baffles 204 are also fixedly connected with four groups of telescopic rods 205, and the outer walls of the four groups of telescopic rods 205 are movably sleeved with buffer springs 206, and then the outer walls of the four groups of telescopic rods 205 are fixedly connected with four The outer walls of the four external baffles 207 are fixedly connected with anti-collision rubber strips 208. By using this connection method, when the drone wing 202 collides, the anti-collision rubber strips 208 will first absorb and disperse a part of the impact force. At the same time, the external baffles 207 move in the impact direction under the action of the impact force and compress the buffer spring 206. Under the action of the buffer spring 206, the protection mechanism improves its absorption of the impact force when facing a collision with an obstacle, effectively protecting the drone wing 202 and reducing the risk of damage to the wing 202.

[0030] Working principle: First, during flight, four arm protection covers 203 are fixedly sleeved on the outer walls of the four wings 202 to protect the wings 202. At the same time, the outer walls of the four arm protection covers 203 are fixedly connected with internal baffles 204, and the outer walls of the four internal baffles 204 are also fixedly connected with four groups of telescopic rods 205. Buffer springs 206 are movably sleeved on the outer walls of the four groups of telescopic rods 205. Then, four external baffles 207 are fixedly connected between the outer walls of the four groups of telescopic rods 205. The outer wall is fixedly connected with an anti-collision rubber strip 208. By using this connection method, when the drone wing 202 collides, the anti-collision rubber strip 208 will first absorb and disperse a part of the impact force. At the same time, the external baffle plate 207 moves in the impact direction under the action of the impact force and compresses the buffer spring 206. Under the action of the buffer spring 206, the protection mechanism improves the absorption of the impact force when facing the collision with the obstacle, effectively protecting the drone wing 202 and reducing the risk of damage to the wing 202. When landing is required, the four sets of brackets 102 are used to open one side of the outer wall. There are four groups of holes A103, and four connecting shafts A104 are fixedly inserted between the inner surface walls of the four groups of holes A103, and at the same time, the outer surface walls of the four connecting shafts A104 are movably sleeved with support plates 105, and one side of the outer wall of the four support plates 105 is opened with a group of holes B106, and the inner surface walls of the four groups of holes B106 are fixedly inserted with a connecting shaft B107, and the three landing wheels 108 movably sleeved on the outer surface walls of the four connecting shafts B107 are used to enable the support plates 105 to open to both sides under the action of the landing wheels 108 when the drone lands. At the same time, tension springs 109 are fixedly connected to one side of the outer wall of the four support plates 105, and a fixing plate 110 is fixedly connected between the outer walls of the four tension springs 109. In this way, the speed at which the support plates 105 open to both sides is slowed down under the action of the tension springs 109, so that the impact force is effectively dispersed and absorbed. When the tension springs 109 are reset, the stability of the fuselage 201 is ensured, and the impact force and vibration received by the drone during landing are effectively slowed down, thereby reducing the risk of damage to the drone and improving the stability, safety and service life of the drone.

[0031] The above description is only a preferred embodiment of the present invention and does not limit the present invention in other forms. Any technician familiar with the profession may use the technical content disclosed above to change or modify it into an equivalent embodiment with equivalent changes and apply it to other fields. However, any simple modification, equivalent change and modification made to the above embodiment based on the technical essence of the present invention without departing from the content of the technical solution of the present invention still falls within the protection scope of the technical solution of the present invention.

Claims

1. A drone skeleton structure, comprising a shock absorbing landing mechanism (1), characterized in that: The outer surface wall of the shock absorbing landing mechanism (1) is fixedly connected with a wing protection mechanism (2); The shock absorbing landing mechanism (1) comprises an organism protection bottom plate (101), the bottom of which is fixedly connected with four groups of brackets (102), one side of the outer wall of each of the four groups of brackets (102) being provided with a hole A (103), a connecting shaft A (104) being fixedly inserted between the inner surface walls of each of the four groups of holes A (103), the outer surface walls of each of the four connecting shafts A (104) being movably sleeved with a supporting plate (105), and one side of the outer wall of each of the four supporting plates (105) being provided with a group of holes B (106).

2. The UAV skeleton structure according to claim 1, characterized in that: A connecting shaft B (107) is fixedly inserted into the inner surface wall of the four groups of holes B (106), three landing wheels (108) are movably sleeved on the outer surface wall of the four connecting shafts B (107), and tension springs (109) are fixedly connected to one side of the outer wall of the four support plates (105).

3. The UAV skeleton structure according to claim 2, characterized in that: A fixing plate (110) is fixedly connected between the outer walls of the four tension springs (109), and the top of the fixing plate (110) is fixedly connected to the bottom of the machine body protection bottom plate (101).

4. The UAV skeleton structure according to claim 3, characterized in that: The wing protection mechanism (2) comprises a fuselage (201), four wings (202) are fixedly mounted on the outer wall of the fuselage (201), the outer walls of the four wings (202) are all fixedly sleeved with an arm protection cover (203), and the outer walls of the four arm protection cover (203) are all fixedly connected with an internal baffle (204).

5. The UAV skeleton structure according to claim 4, characterized in that: The outer walls of the four internal baffles (204) are all fixedly connected with a group of telescopic rods (205), and the outer walls of the four groups of telescopic rods (205) are all movably sleeved with buffer springs (206).

6. The UAV skeleton structure according to claim 5, characterized in that: An external baffle (207) is fixedly connected between the outer walls of the four groups of telescopic rods (205), and an anti-collision rubber strip (208) is fixedly connected to the outer walls of the four external baffles (207).

7. The UAV skeleton structure according to claim 6, characterized in that: The top of the machine body protection bottom plate (101) is fixedly connected to the bottom of the machine body (201), and the outer wall of the machine body protection bottom plate (101) is fixedly connected to one side of the outer wall of the four machine arm protection casings (203).

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