An unmanned aerial vehicle

Abstract

This invention discloses a drone, including a buffer mechanism disposed at the lower part of the wing mechanism and partially overlapping with the wing mechanism. The buffer mechanism includes an arched buffer plate, with a predetermined distance between the two ends of the buffer plate and the two ends of the wing mechanism, and a buffer element is disposed between the buffer mechanism and the wing mechanism. This invention, by providing a shock-absorbing and buffering mechanism at the lower part of the drone, avoids violent collisions between the drone and the ground during descent, greatly reducing vibration during landing. The arched buffer mechanism at the lower part of the drone has shock-absorbing springs at both ends. When the drone lands, the initial force is absorbed and offset by the arched buffer mechanism. The offset force is then further offset by spring compression and damping rods, ultimately completely canceling out the vibration force and preventing vibration of the entire drone body, thus avoiding damage to the internal components and shell.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicles (UAVs), and particularly to a UAV. Background Technology

[0002] Multi-rotor drones are unmanned aerial vehicles with three or more rotor axes. Due to their advantages such as small size, light weight, hovering ability, and ease of control, multi-rotor drones have seen rapid development in the field of aerial photography in recent years. To extend the operational time of multi-rotor drones in the air while maintaining the same video imaging quality, using lighter and smaller payloads has become the preferred choice for drone manufacturers. However, most multi-rotor drones still suffer from the following problems.

[0003] (1) The lack of shock absorption structure causes damage to the components of the drone during descent.

[0004] (2) Independently distributed wire harnesses can be flexibly wired according to the user's wishes. However, the wiring of independently distributed wire harnesses is complicated and intertwined, which is very unsightly. Furthermore, independently distributed wire harnesses are prone to damage and misconnection. When the space between the terminal block and the mounting base becomes narrow after the terminal block is fixed, the wire harness connector cannot be connected to it. Summary of the Invention

[0005] One object of the present invention is to provide a drone that at least solves any of the above-mentioned technical problems.

[0006] A further objective of this invention is to prevent drones from generating [something] when they land on the ground.

[0007] Another further objective of this invention is to improve the efficiency of wire harness wiring and facilitate the rational use of space.

[0008] In particular, the present invention provides a drone, including a main body having a teardrop-shaped shell and a mounting base, the shell covering the upper part of the mounting base;

[0009] A wing mechanism is fixedly mounted on the bottom of the mounting base and is perpendicular to the mounting base.

[0010] A control mechanism is disposed on the upper part of the mounting base and covered by the housing;

[0011] A buffer mechanism is provided at the lower part of the wing mechanism and partially overlaps with the wing mechanism. The buffer mechanism includes an arched buffer plate. The two ends of the buffer plate are provided at a preset distance from the two ends of the wing mechanism, and a buffer element is provided between the buffer mechanism and the wing mechanism.

[0012] Furthermore, the main body also includes a battery pack, which is disposed at one end near the housing. The housing is provided with an access hole for monitoring the activity of the device and a mounting hole for mounting an antenna.

[0013] Furthermore, the wing mechanism includes support frames extending to both sides of the shell, with a drive motor and a propeller at the end of the support frame, and a cable routing channel communicating with the interior of the shell in the middle of the support frame.

[0014] Furthermore, the buffer plate has a long groove in the middle, and a screw for fixing the buffer member is provided in the groove. One end of the buffer member is located in the upper part of the groove, and the buffer member can move radially along the groove.

[0015] Furthermore, the buffer is a shock-absorbing spring, and a damping rod is provided in the middle of the shock-absorbing spring, and the damping rod is fixedly connected to both ends of the spring.

[0016] Furthermore, the buffer plate has elastic ends.

[0017] Furthermore, the control mechanism includes multiple processing boards arranged in parallel and an integrated wiring harness. The processing boards transmit signals to the drive motor, the sensor head, and the camera adjustment mechanism through the integrated wiring harness.

[0018] Furthermore, the integrated wiring harness includes an outer sheath and a connector, the sheath having a movable groove for receiving the connector, the connector being movably connected to the outer sheath.

[0019] Furthermore, the movable groove is provided with an arc-shaped groove, which is positioned directly opposite the connector.

[0020] The technical effects and advantages of this invention are as follows:

[0021] 1. This invention provides a shock-absorbing and buffering mechanism at the lower part of the drone to prevent the drone from colliding violently with the ground during descent, thus greatly reducing vibration during landing. Specifically, an arched buffer mechanism is provided at the lower part of the drone, and shock-absorbing springs are provided at both ends of the buffer mechanism. When the drone lands, the force generated is initially absorbed and offset by the arched buffer mechanism. The offset force is then further offset by spring compression and damping rods, ultimately completely offsetting the vibration force and preventing the entire drone body from vibrating and damaging the internal components of the drone body and shell.

[0022] 2. In this invention, an integrated wire harness is used to connect various control components. The integrated wire harness includes an outer sheath, and a rotatable connector is provided inside the outer sheath. The connector is connected to the connecting wire. In order to avoid the situation where the connector is too large to be installed, the connector is first connected to the wire board, so that the outer sheath rotates relative to the connector, thereby avoiding the situation where the connector cannot be installed and making the integrated wire harness connector flexible to use. Attached Figure Description

[0023] The following sections will describe some specific embodiments of the invention in detail by way of example and not limitation, with reference to the accompanying drawings. The same reference numerals in the drawings denote the same or similar parts or portions. Those skilled in the art should understand that these drawings are not necessarily drawn to scale. In the drawings:

[0024] Figure 1 This is a schematic diagram of the structure of the present invention.

[0025] Figure 2 This is a top view of the structure of the present invention.

[0026] Figure 3 For the present invention Figure 2 Schematic diagram of the cross-sectional structure along the AA direction.

[0027] Figure 4 This is a schematic diagram of the bottom structure of the UAV of the present invention.

[0028] Figure 5 For the present invention Figure 3 A magnified schematic diagram of the structure of C.

[0029] Figure 6 This is a schematic diagram of the integrated wire harness connector structure of the present invention.

[0030] Figure 7 This is a top view of the integrated wire harness connector of the present invention.

[0031] Figure 8 For the present invention Figure 7 Schematic diagram of the cross-sectional structure in the middle BB direction.

[0032] In the diagram: 100, main body; 101, shell; 102, battery pack; 103, camera; 104, antenna; 105, movable hole; 106, sensor mounting port; 107, heat dissipation hole; 200, wing mechanism; 201, support rod; 202, propeller blade; 203, drive motor; 300, buffer mechanism; 301, groove; 400, control mechanism; 401, charging interface; 402, processing board; 403, integrated wiring harness; 4031, outer shell; 4032, connector; 4033, arc groove; 4034, connecting wire; 4035, movable groove; 404, sensor head; 405, camera adjustment mechanism; 500, shock absorption spring. Detailed Implementation

[0033] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0034] Figure 1 This is a schematic diagram of the structure of the present invention. Figure 2 This is a top view of the structure of the present invention. Figure 3 For the present invention Figure 2 Schematic diagram of the cross-sectional structure along the AA direction. Figure 4 This is a schematic diagram of the bottom structure of the UAV of the present invention. Figure 5 For the present invention Figure 3 A magnified schematic diagram of the structure of C. Figure 6 This is a schematic diagram of the integrated wire harness connector structure of the present invention. Figure 7 This is a top view of the integrated wire harness connector of the present invention. Figure 8 For the present invention Figure 7 Schematic diagram of the cross-sectional structure in the middle BB direction.

[0035] The solution in this embodiment, such as Figure 1 As shown, a drone is provided, including a main body 100, a buffer mechanism 300, a control mechanism 400, and a wing mechanism 200. The main body 100 has a teardrop-shaped shell 101 and a mounting base, with the shell 101 covering the upper part of the mounting base. The wing mechanism 200 is fixedly disposed at the bottom of the mounting base, wherein the mounting base is located at the lower part of the shell 101. A charging interface 401 extending to the outside is provided inside the mounting base. A heat dissipation hole 107 is also provided at the lower part of the mounting base. This structure is existing and is not shown in the figure. The support rod 201 is arranged perpendicularly to the mounting base. The control mechanism 400 is disposed on the upper part of the mounting base and is contained within the shell. 101 Cover; The buffer mechanism 300 is disposed at the lower part of the wing mechanism 200 and partially overlaps with the wing mechanism 200. The buffer mechanism 300 includes an arched buffer plate. The two ends of the buffer plate are provided with a preset distance from the two ends of the wing mechanism 200. A buffer component is provided between the buffer mechanism 300 and the wing mechanism 200. The buffer component is a shock-absorbing spring 500. A damping rod is provided in the middle of the shock-absorbing spring 500. The damping rod is fixedly connected to the two ends of the spring. The shock-absorbing spring 500 and the damping rod work together to cancel and reduce the vibration generated by the UAV. At the same time, the arched buffer plate first dampens and cancels the generated vibration force.

[0036] It should be further explained that the main body 100 also includes a battery pack 102, which is disposed at one end near the housing 101. The housing 101 is provided with an activity hole 105 for monitoring the movement of the device and a mounting hole for mounting an antenna 104. The monitoring device is an offset camera 103.

[0037] It should be further explained that the wing mechanism 200 includes two support frames extending to both sides of the housing 101. The two support frames are arranged in parallel. The end of the support frame is provided with a drive motor 203 and a propeller 202. The middle of the support frame is provided with a cable channel communicating with the inside of the housing 101.

[0038] It should be further explained that the buffer plate has a long strip-shaped groove 301 in the middle, and a screw for fixing the buffer is provided in the groove 301. One end of the buffer is located at the upper part of the groove 301, and the buffer can move radially along the groove 301. The position of the shock-absorbing spring 500 can be moved as needed. The closer the spring is to the center, the greater the spring force. When the drone is heavier, the shock-absorbing spring 500 and the damping force can be moved to the center to enhance the shock absorption effect.

[0039] It should be further noted that the two ends of the buffer plate are elastic to counteract vertical forces.

[0040] It needs to be further explained that, such as Figure 3 As shown, the control mechanism 400 includes an integrated wiring harness 403 and a plurality of parallel processing boards 402. The processing boards 402 transmit signals to the drive motor 203, the sensor head 404 and the camera adjustment mechanism 405 through the integrated wiring harness 403. The sensor head 404 is disposed in the sensor mounting port 106.

[0041] It needs to be further explained that, such as Figures 5 to 8 The integrated wire harness 403 described herein includes an outer sheath 4031 and a connector 4032. The sheath has a movable groove 4035 for accommodating the connector 4032. The connector 4032 is movably connected to the outer sheath 4031. The two ends of the connector 4032 are provided with rotating shafts, which enable rotation within the outer sheath 4031.

[0042] It should be further explained that an arc-shaped groove 4033 is provided in the movable groove 4035. The arc-shaped groove 4033 is directly opposite to the connector 4032, which facilitates the connection line 4034 to bend better when the connector 4032 rotates, preventing the connector 4032 from being bent hard. At the same time, the outer shell 4031 can protect the connection line 4034 at the connector 4032.

[0043] Working principle of this invention:

[0044] During use, a shock-absorbing mechanism is installed at the lower part of the drone to prevent the drone from colliding violently with the ground during descent, greatly reducing vibration during landing. Specifically, an arched buffer mechanism 300 is installed at the lower part of the drone, and shock-absorbing springs 500 are installed at both ends of the buffer mechanism 300. When the drone lands, the initial force is counteracted by the arched buffer mechanism 300. The counteracted force is then further counteracted by the spring compression and damping rod, ultimately completely canceling out the vibration force and preventing vibration of the entire drone body 100. This could damage the entire internal components and parts within the housing 101. During connection, an integrated wiring harness 403 is used to connect the various control components. The integrated wiring harness 403 includes an outer housing 4031, within which a rotatable connector 4032 is installed. The connector 4032 is connected to the connecting wire 4034. To prevent the connector 4032 from being too large to install, it is first connected to the wiring board, allowing the outer housing 4031 to rotate relative to the connector 4032. This ensures the connector 4032 can be used flexibly.

[0045] Finally, it should be noted that the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A drone, characterized in that, include, The main body (100) has a teardrop-shaped shell (101) and a mounting base, the shell (101) covering the upper part of the mounting base; A wing mechanism (200) is fixedly disposed at the bottom of the mounting base and is disposed perpendicularly to the mounting base; A control mechanism (400) is disposed on the upper part of the mounting base and covered by the housing (101); A buffer mechanism (300) is provided at the lower part of the wing mechanism (200) and partially overlaps with the wing mechanism (200). The buffer mechanism (300) includes an arched buffer plate. The two ends of the buffer plate are provided at a preset distance from the two ends of the wing mechanism (200), and a buffer member is provided between the buffer mechanism (300) and the wing mechanism (200). The buffer plate has a long groove (301) in the middle, and a screw for fixing the buffer is provided in the groove (301). One end of the buffer is located in the upper part of the groove (301), and the buffer can move radially along the groove (301). The buffer is a shock-absorbing spring (500), and a damping rod is provided in the middle of the shock-absorbing spring (500). The damping rod is fixedly connected to both ends of the spring.

2. The unmanned aerial vehicle (UAV) according to claim 1, characterized in that, The main body (100) also includes a battery pack (102), which is disposed at one end near the housing (101). The housing (101) is provided with an activity hole (105) for monitoring the activity of the device and a mounting hole for mounting an antenna (104).

3. The unmanned aerial vehicle (UAV) according to claim 1, characterized in that, The wing mechanism (200) includes a support frame extending to both sides of the housing (101), with a drive motor (203) and a propeller (202) at the end of the support frame, and a cable channel communicating with the inside of the housing (101) in the middle of the support frame.

4. The unmanned aerial vehicle (UAV) according to claim 1, characterized in that, The buffer plate has elastic ends.

5. The unmanned aerial vehicle (UAV) according to claim 1, characterized in that, The control mechanism (400) includes multiple parallel processing boards (402) and an integrated wiring harness (403). The processing boards (402) transmit signals to the drive motor (203), the sensor head (404), and the camera adjustment mechanism (405) through the integrated wiring harness (403).

6. The unmanned aerial vehicle (UAV) according to claim 5, characterized in that, The integrated wiring harness (403) includes an outer sheath (4031) and a connector (4032). The sheath has a movable groove (4035) for receiving the connector (4032), and the connector (4032) is movably connected to the outer sheath (4031).

7. The unmanned aerial vehicle (UAV) according to claim 6, characterized in that, An arc-shaped groove (4033) is provided inside the movable groove (4035), and the arc-shaped groove (4033) is positioned opposite to the connector (4032).

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