Folding arm structure of unmanned aerial vehicle

Abstract

The utility model provides a folding arm structure of an unmanned aerial vehicle. The folding arm structure comprises a fuselage fixing end, a sliding handle, an aluminum alloy rotating shaft, an aluminum alloy fixing connecting rod, an arm rotating end, a fixing stop lever, an arm clamping block, an arm, a spring, a hexagon head bolt, a nut and a sliding groove. The screw is matched with the threaded hole in the machine body fixing end, so that the machine body fixing end is connected with the machine body. Bolts penetrate through the vehicle arm rotating ends on the two sides of the vehicle arm and the clamping blocks and then are matched with nuts, and the vehicle arm is fixed. When the machine arm is stretched, the spring exerts pulling force on the sliding handle, the sliding handle is located above a bayonet at the rotating end of the machine arm, meanwhile, the fixed stop lever is located above the right side of the fixed end of the machine body, and the machine arm is in a stretched state. When the arm is folded, the sliding handle is lifted, the rotating end of the arm is rotated by 90 degrees around the aluminum alloy rotating shaft, the sliding handle is reset, the groove in the lower side of the rotating end of the arm is matched with the sliding handle, and the arm is in a folded state. In the folding and unfolding process, complex operation is not needed, and the use flexibility is improved.

Description

Technical Field

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

[0002] With the rapid development of micro sensors, micro computers, aerodynamic theory and control technology, multi-rotor drones have been widely used in aerial photography, agriculture, logistics and scientific research. They have the advantages of simple structure, convenient operation, vertical take-off and landing, and stable hovering. However, most existing multi-rotor drones adopt an integrated fixed structure, which increases the storage area and makes transportation inconvenient. Although the existing folding mechanism attempts to solve this problem, it fails to achieve the purpose of rapid folding due to the inconvenience of assembly, high cost and complex implementation. Utility Model Content

[0003] The purpose of the utility model is to provide a folding arm structure for a multi-rotor drone to solve the above problems in the prior art. The folding process of the folding arm structure is complicated, time-consuming and costly, and at the same time reduces the load of the drone, making it easier to transport, transfer, store and collect. The utility model uses composite materials, and through the action of springs, combined with slide bars and locking blocks, it can easily and quickly realize the folding and unfolding of the arm, while effectively reducing the production cost.

[0004] In order to achieve the above purpose, the technical solution proposed by the utility model is as follows:

[0005] A folding arm structure of an unmanned aerial vehicle, characterized in that it includes a fuselage fixed end, a sliding handle, an aluminum alloy rotating shaft, an aluminum alloy fixed connecting rod, an arm rotating end, a fixed stop rod, an arm clamping block, an arm, a spring, a hexagonal head bolt, a nut and a slide groove, wherein the fuselage fixed end is provided with two identical threaded holes at the upper and lower ends, a slide groove is provided on the right side of the fuselage fixed end, a sliding handle parallel to the aluminum alloy fixed connecting rod is installed on the upper limit of the slide groove, a spring is provided in the middle of the aluminum alloy fixed connecting rod, one end of the spring is placed in the aluminum alloy fixed connecting rod mounting groove, and the other end is placed in the sliding handle mounting groove, the aluminum alloy rotating shaft passes through the fuselage fixed end and the arm rotating end, the arm passes through the arm rotating end through a hexagonal head bolt, and the arm clamping block cooperates with the nut to clamp the arm.

[0006] Furthermore, the aluminum alloy rotating shaft passes through the fixed end of the fuselage and the rotating end of the arm.

[0007] Furthermore, the sliding handle cooperates with a sliding groove on the fixed end of the fuselage.

[0008] Furthermore, the fixed stop rod passes through the fixed end of the fuselage.

[0009] Furthermore, a groove is provided on the lower side of the rotating end of the arm.

[0010] Furthermore, the side surface of the arm clamping block is provided with two circular holes.

[0011] Furthermore, the sliding handle has a pressing portion.

[0012] Furthermore, the left side of the fixed end of the fuselage is arc-shaped.

[0013] Furthermore, the aluminum alloy fixing connecting rod passes through the fixed end of the fuselage.

[0014] Furthermore, the arm rotating end, the arm clamping block and the arm are made of carbon fiber composite materials.

[0015] The beneficial effects of the utility model are:

[0016] The utility model discloses a folding arm structure for a drone, which effectively solves the problem that the folding process of the existing folding mechanism is complicated, time-consuming and laborious. The material sources are carbon fiber and aluminum alloy, which can effectively reduce the weight of the folding arm and reduce the load of the drone. Moreover, the symmetrical structure adopted by the folding arm will greatly increase the stability of the locking mechanism. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The utility model is further described below in conjunction with the accompanying drawings and embodiments.

[0018] Figure 1 It is an explosion diagram of the utility model;

[0019] Figure 2 It is the front view of the utility model;

[0020] Figure 3 for Figure 2 sectional view of

[0021] Figure 4 It is a schematic diagram of the fixed end of the fuselage of the utility model;

[0022] Figure 5 It is a schematic diagram of the rotating end of the machine arm of the utility model;

[0023] Figure 6 It is a schematic diagram of the unfolded state of the utility model;

[0024] Figure 7 It is a schematic diagram of the folded state of the utility model.

[0025] In the figure: 1. Fixed end of the machine body; 2. Sliding handle; 3. Aluminum alloy rotating shaft; 4. Aluminum alloy fixed connecting rod; 5. Rotating end of the machine arm; 6. Fixed stop rod; 7. Machine arm clamping block; 8. Machine arm; 9. Spring; 10. Hexagon head bolt; 11. Nut; 12. Slide groove; 13. Threaded hole; 14. Pressing part. DETAILED DESCRIPTION

[0026] The technical solution of the utility model is further described in detail below in conjunction with specific implementation methods.

[0027] The following is a detailed description of the present invention in conjunction with the accompanying drawings and specific embodiments. In this specification, the size ratios in the drawings do not represent the actual size ratios, but are only used to reflect the relative position relationship and connection relationship between the components. Components with the same name or the same number represent similar or identical structures and are only for illustrative purposes.

[0028] like Figures 1 to 7 As shown, a folding arm structure of an unmanned aerial vehicle comprises a fuselage fixed end 1, a sliding handle 2, an aluminum alloy rotating shaft 3, an aluminum alloy fixed connecting rod 4, an arm rotating end 5, a fixed stop rod 6, an arm clamping block 7, an arm 8, a spring 9, a hexagonal head bolt 10, a nut 11, and a slide groove 12. The fuselage fixed end 1 is provided with two identical threaded holes 13 at the upper and lower sides, a slide groove 12 is provided on the right side of the fuselage fixed end, a sliding handle 2 parallel to the aluminum alloy fixed connecting rod is installed on the upper limit of the slide groove 12, a spring 9 is provided in the middle of the aluminum alloy fixed connecting rod 4, one end of the spring 9 is placed in the mounting groove of the aluminum alloy fixed connecting rod 4, and the other end is placed in the mounting groove of the sliding handle 2, the aluminum alloy rotating shaft 3 passes through the fuselage fixed end 1 and the arm rotating end 5, the arm 8 passes through the arm rotating end 5 through the hexagonal head bolt 10, and the arm clamping block 7 cooperates with the nut 11 to clamp the arm 8.

[0029] Preferably, the aluminum alloy rotating shaft 3 passes through the fixed end 1 of the fuselage and the rotating end 5 of the arm. Preferably, the sliding handle 2 cooperates with the slide groove 12 on the fixed end 1 of the fuselage; preferably, the fixed stopper 6 passes through the fixed end 1 of the fuselage; preferably, the lower side of the rotating end 5 of the arm has a groove; preferably, the side of the arm clamping block 7 has two round holes. The bolt passes through the rotating end 5 of the arm and cooperates with the arm clamping block 7 and the nut to clamp the arm 8; preferably, the sliding handle 2 has a pressing part 14 to increase the friction with the hand and facilitate lifting and resetting; preferably, the left side of the fixed end 1 of the fuselage is arc-shaped; preferably, the aluminum alloy fixed connecting rod 4 passes through the fixed end 1 of the fuselage; preferably, the rotating end 5 of the arm, the clamping block 7, and the arm 8 are made of carbon fiber composite materials, which reduces the weight of the folding arm and reduces the load of the drone.

[0030] The working principle of the utility model is as follows: the utility model connects the fixed end 1 of the fuselage to the fuselage by screws and the threaded holes 13 which are the same above and below the fixed end 1 of the fuselage. The clamping block 7 of the arm is connected to the end of the arm 8, and the hexagonal bolt 10 penetrates the rotating end 5 of the arm and the clamping block 7 on both sides of the arm 8 and cooperates with the nut 11 to apply force to the end of the arm 8 to fix the arm 8. When the arm 8 is extended, the spring 9 applies a pulling force to the sliding handle 2, so that the sliding handle 2 is directly above the bayonet of the rotating end 5 of the arm. At the same time, the fixed stopper 6 is above the right side of the fixed end 1 of the fuselage to prevent the arm 8 from rotating counterclockwise. At this time, the arm 8 is in an extended state. When the arm 8 is folded, a force is applied to lift the sliding handle 2 along the slide groove, and the rotating end 5 of the arm is rotated 90° clockwise around the aluminum alloy rotating axis 3, and the sliding handle 2 is reset, so that the groove on the lower side of the rotating end 5 of the arm cooperates with the sliding handle 2 to prevent the rotating end 5 of the arm from moving during transportation. At this time, the arm is in a folded state.

Claims

1. A folding arm structure of a drone, characterized in that: The invention comprises a machine body fixed end (1), a sliding handle (2), an aluminum alloy rotating shaft (3), an aluminum alloy fixed connecting rod (4), a machine arm rotating end (5), a fixed stop rod (6), a machine arm clamping block (7), a machine arm (8), a spring (9), a hexagonal head bolt (10), a nut (11) and a slide groove (12), wherein the machine body fixed end (1) is provided with two identical threaded holes (13) at the upper and lower parts, and a slide groove (12) is provided on the right side of the machine body fixed end (1), and the upper limit of the slide groove (12) is provided with a screw threaded with the aluminum alloy. The aluminum alloy fixed link (4) is parallel to the sliding handle (2), a spring (9) is arranged in the middle of the aluminum alloy fixed link (4), one end of the spring (9) is placed in the mounting groove of the aluminum alloy fixed link (4), and the other end is placed in the mounting groove of the sliding handle (2), the aluminum alloy rotating shaft (3) penetrates the fixed end (1) of the fuselage and the rotating end (5) of the arm, the arm (8) penetrates the rotating end (5) of the arm through a hexagonal bolt (10), and the arm clamping block (7) cooperates with a nut (11) to clamp the arm (8).

2. The folding arm structure of a drone according to claim 1, characterized in that: The aluminum alloy rotating shaft (3) passes through the fixed end (1) of the fuselage and the rotating end (5) of the arm.

3. The folding arm structure of a drone according to claim 1, characterized in that: The sliding handle (2) cooperates with the sliding groove (12) on the fixed end (1) of the fuselage.

4. The folding arm structure of a drone according to claim 1, characterized in that: The fixed blocking rod (6) passes through the fixed end (1) of the fuselage.

5. The folding arm structure of a drone according to claim 1, characterized in that: The lower side of the arm rotating end (5) is provided with a groove.

6. The folding arm structure of a drone according to claim 1, characterized in that: The side surface of the machine arm clamping block (7) is provided with two circular holes.

7. The folding arm structure of a drone according to claim 1, characterized in that: The sliding handle (2) has a pressing portion (14).

8. The folding arm structure of a drone according to claim 1, characterized in that: The left side of the fixed end (1) of the fuselage is arc-shaped.

9. The folding arm structure of a drone according to claim 1, characterized in that: The aluminum alloy fixing connecting rod (4) passes through the fixed end (1) of the fuselage.

10. The folding arm structure of a drone according to claim 1, characterized in that: The machine arm rotating end (5), the machine arm clamping block (7) and the machine arm (8) are made of carbon fiber composite materials.

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