Flight control module for unmanned aerial vehicle

Abstract

The utility model discloses a flight control module for an unmanned aerial vehicle, which relates to the technical field of unmanned aerial vehicles and comprises an unmanned aerial vehicle body, a connecting plate is mounted at the bottom of the unmanned aerial vehicle body, an unmanned aerial vehicle height adjusting part is mounted at the bottom of the connecting plate, and supporting legs are slidably connected to four corners of the connecting plate. The two sides of the connecting plate are provided with camera shooting assemblies for assisting in shooting pictures. According to the flight control module for the unmanned aerial vehicle, the connecting plate and the battery electric control box adopt a detachable structure, so that maintenance of a power system is facilitated; the supporting legs achieve flexible switching between a soft landing buffering mode and a hard supporting mode through intelligent switching of electric push rods and buffering springs, and the aircraft body structure is effectively protected; the height adjusting assembly drives a screw mechanism through a servo motor, so that the unmanned aerial vehicle can accurately adjust the ground clearance according to the terrain, and the operation stability in the complex environment is enhanced.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a flight control module for UAVs. Background Technology

[0002] Drones are devices operated by radio remote control equipment and their own program control devices, or by onboard computers, either completely or intermittently autonomously. They include unmanned aerial vehicles, unmanned vehicles, and robotic dogs, and are widely used in fields such as aerial photography, agriculture, plant protection, miniature selfies, express delivery, disaster relief, wildlife observation, infectious disease monitoring, surveying, news reporting, power line inspection, disaster relief, film and television shooting, and creating romance.

[0003] Traditional drones mostly use fixed support legs, which cannot adjust their altitude according to complex terrain. This can easily cause the drone to tilt on uneven surfaces, affecting the quality of aerial photography. At the same time, their buffer mechanisms are simple, relying solely on springs for shock absorption. This makes it difficult to effectively disperse the impact force during emergency landings, resulting in a high risk of damage to the drone and precision instruments. Therefore, a flight control module for drones is provided to solve the above-mentioned problems. Utility Model Content

[0004] The purpose of this invention is to solve the problem in the prior art that it is difficult to effectively disperse the impact force during emergency landing, resulting in a high risk of damage to the aircraft body and precision instruments. Therefore, this invention proposes a flight control module for unmanned aerial vehicles (UAVs).

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] A flight control module for a drone includes a drone body, a connecting plate installed at the bottom of the drone body, a drone altitude adjustment component installed at the bottom of the connecting plate, and support legs slidably connected to the four corners of the connecting plate. Camera components for assisting in capturing images are installed on both sides of the connecting plate.

[0007] The bottom of the connecting plate is also equipped with two wind speed measuring components and two emergency support components.

[0008] Preferably, the drone body includes a fuselage, a battery control box is fixedly installed at the bottom of the fuselage, the fuselage is connected to a connecting plate through the battery control box, and multiple wings are installed on the fuselage.

[0009] Preferably, the support leg includes a main leg, a buffer spring is fixedly connected to the bottom of the main leg, an electric push rod is connected to the bottom of the buffer spring, a base is installed at the bottom of the electric push rod, the top end of the output rod of the electric push rod is in contact with the bottom end of the main leg, and the main leg is slidably connected to the connecting plate.

[0010] Preferably, the drone altitude adjustment component includes a micro servo motor, the output shaft of which is connected to a screw via a coupling, a threaded ring is threaded onto the screw, a support ring is fixedly connected to each of the main legs, and a support rod is fixedly connected between each of the support rings and the threaded ring.

[0011] Preferably, the emergency support includes a first support plate, on which a hinge shaft is mounted, and a second support plate is hinged to the bottom of the hinge shaft. Electromagnets that attract each other are mounted on both the first and second support plates.

[0012] Preferably, the camera assembly includes a camera support rod, on which a camera is rotatably connected.

[0013] Preferably, the wind speed measurement component includes a positioning block, on which two wind tunnels with arc-shaped surfaces are formed, and gas flow rate sensors are installed at the air outlets of the two wind tunnels.

[0014] Compared with the prior art, the advantages and positive effects of this utility model are as follows:

[0015] 1. The flight control module of this UAV adopts a detachable structure through the connecting plate and the battery control box, which facilitates the maintenance of the power system; the support legs realize the flexible conversion between soft landing buffer and hard support modes through intelligent switching of electric push rod and buffer spring, effectively protecting the airframe structure; the altitude adjustment component uses a servo motor to drive the screw mechanism, enabling the UAV to accurately adjust the ground clearance according to the terrain, enhancing the operational stability in complex environments.

[0016] 2. The UAV uses a flight control module that triggers the deployment of emergency support components through wind tunnel airflow analysis via a wind speed measurement component. This forms a multi-level buffer system with the main support legs to prevent damage from sudden crashes. The camera component and altitude adjustment system work together to ensure the quality of aerial footage. The entire mechanical structure design takes into account both routine operations and extreme working conditions, providing a highly reliable technical guarantee for surveying and mapping. Attached Figure Description

[0017] Figure 1 This is a three-dimensional structural diagram of the present invention from a first-person perspective;

[0018] Figure 2 This is a three-dimensional structural diagram of the present invention from a second perspective;

[0019] Figure 3 This is a three-dimensional structural diagram of the connection between the connecting plate and the supporting leg, the emergency support component, and the camera assembly in this utility model.

[0020] Figure 4 This is a three-dimensional exploded view of the supporting leg in this utility model;

[0021] Figure 5 This is a three-dimensional structural diagram of the wind speed measuring component in this utility model;

[0022] Figure 6 This is a partial cross-sectional structural diagram of the drone altitude adjustment component of this utility model.

[0023] Legend: 1. UAV body; 11. Fuselage; 12. Battery and control box; 13. Wing; 2. Connecting plate; 3. Support leg; 31. Main leg; 32. Buffer spring; 33. Electric push rod; 34. Base; 4. UAV altitude adjustment component; 41. Miniature servo motor; 42. Threaded ring; 43. Support rod; 44. Support ring; 45. Screw; 5. Emergency support component; 51. First support plate; 52. Second support plate; 53. Electromagnet; 54. Hinge shaft; 6. Camera assembly; 61. Camera support rod; 62. Camera; 7. Wind speed measurement component; 71. Positioning block; 72. Wind tunnel; 73. Gas flow rate sensor. Detailed Implementation

[0024] To better understand the above-mentioned objectives, features, and advantages of this utility model, the present utility model will be further described below with reference to the accompanying drawings and embodiments. It should be noted that, unless otherwise specified, the embodiments and features described in these embodiments can be combined with each other.

[0025] Many specific details are set forth in the following description in order to provide a full understanding of the present invention. However, the present invention may also be implemented in other ways different from those described herein. Therefore, the present invention is not limited to the specific embodiments disclosed in the following specification.

[0026] like Figure 1-6 As shown, this utility model provides a flight control module for a drone, including a drone body 1, a connecting plate 2 installed at the bottom of the drone body 1, a drone height adjustment component 4 installed at the bottom of the connecting plate 2, and support legs 3 slidably connected to the four corners of the connecting plate 2, and camera components 6 for assisting in shooting images installed on both sides of the connecting plate 2.

[0027] The bottom of the connecting plate 2 is also equipped with two wind speed measuring components 7 and two emergency support components 5.

[0028] In this embodiment, the drone body 1 includes a fuselage 11, a battery control box 12 is fixedly installed at the bottom of the fuselage 11, the fuselage 11 is connected to the connecting plate 2 through the battery control box 12, and multiple wings 13 are installed on the fuselage 11.

[0029] Inside the drone body 1, the fuselage 11 and the battery control box 12 serve as support, and the wings 13 enable take-off, landing and flight. The battery control box 12 and the connecting plate 2 are connected by screws or clips, which makes it easy to adjust the battery or other electrical components inside the battery control box 12 when maintenance is needed.

[0030] In this embodiment, the support leg 3 includes a main leg 31, a buffer spring 32 is fixedly connected to the bottom of the main leg 31, an electric push rod 33 is connected to the bottom of the buffer spring 32, a base 34 is installed at the bottom of the electric push rod 33, the top of the output rod of the electric push rod 33 is in contact with the bottom of the main leg 31, and the main leg 31 is slidably connected to the connecting plate 2.

[0031] In this embodiment, the drone altitude adjustment component 4 includes a micro servo motor 41. The output shaft of the micro servo motor 41 is connected to a screw 45 via a coupling. A threaded ring 42 is threaded onto the screw 45. Support rings 44 are fixedly connected to multiple main legs 31. Support rods 43 are fixedly connected between the multiple support rings 44 and the threaded rings 42.

[0032] Inside the support leg 3, the main leg 31 serves as the primary support component. Under normal landing conditions, the main leg 31 is connected to the electric push rod 33 and the base 34. When the telescopic rod of the electric push rod 33 is not retracted and is in contact with the main leg 31 by the buffer spring 32, it provides soft support. This provides a certain buffering effect during landing and can prevent damage to the UAV body 1 from landing too fast. When ground support or takeoff, the electric push rod 33 is activated to lift the main leg 31. At this time, the electric push rod 33 replaces the buffer spring 32 and directly connects to the main leg 31 to achieve a rigid connection, which can provide a certain support effect for takeoff or when on the ground.

[0033] Based on the support leg 3, the drone height adjustment component 4 can be added. By starting the micro servo motor 41, the screw 45 can be rotated. When the threaded ring 42 is threadedly connected to the screw 45 and the threaded ring 42 is connected to multiple support rings 44 through the support rod 43, a limit can be formed. At this time, the rotation of the screw 45 will cause the threaded ring 42 to drive multiple support legs 3 to rise and fall through multiple support rings 44, thereby adjusting the vertical height of the entire drone body 1 to adapt to different environments.

[0034] In this embodiment, the emergency support component 5 includes a first support plate 51, on which a hinge shaft 54 ​​is mounted, and a second support plate 52 is hinged to the bottom of the hinge shaft 54. Electromagnets 53 that attract each other are mounted on both the first support plate 51 and the second support plate 52. The wind speed measurement component 7 includes a positioning block 71, on which two wind tunnels 72 with arc-shaped surfaces are opened, and gas flow rate sensors 73 are installed at the air outlets of the two wind tunnels 72.

[0035] The emergency support component 5 and the wind speed measurement component 7 work together. When the UAV body 1 loses power and falls vertically, a large amount of airflow will enter through the wind tunnel 72 and pass through the gas flow sensor 73. When the gas flow sensor 73 detects an airflow speed different from that during normal flight, it will de-energize the electromagnet 53 and allow the second support plate 52 to unfold. This can work with multiple support legs 3 to assist in buffering and reduce damage to the UAV body 1.

[0036] In this embodiment, the camera assembly 6 includes a camera support rod 61, and a camera 62 is rotatably connected to the camera support rod 61.

[0037] Within the camera assembly 6, the camera 62 is supported by the camera support rod 61, ensuring that the shooting is not obstructed by other parts. The shooting angle can be adjusted as needed, making operation convenient and quick. The rotating parts of the camera support rod 61 and the camera 62 are equipped with damping blocks, which can be adjusted and positioned to the shooting position.

[0038] For further details, please refer to [link / reference]. Figure 3 A torsion spring is installed at the connection between the hinge shaft 54 ​​and the electromagnet 53. This torsion spring allows the second support plate 52 to spring open when the electromagnet 53 is de-energized. Figure 2 The position shown is the maximum position where the second support plate 52 can be deployed.

[0039] How to use and how to work this device:

[0040] When in use, the device adds a connecting plate 2 to the bottom of the drone body 1 as the main support, and adds support legs 3, drone altitude adjustment components 4, emergency support components 5, camera components 6, and wind speed measurement components 7 to achieve better optimization of conventional landing, ground support, and emergency landing based on aerial photography.

[0041] Inside the drone body 1, the fuselage 11 and the battery control box 12 serve as support, and the wings 13 enable take-off, landing and flight. The battery control box 12 and the connecting plate 2 are connected by screws or snap-fit, which makes it easy to adjust the battery or other electrical components inside the battery control box 12 when maintenance is needed.

[0042] Inside the support leg 3, the main leg 31 serves as the primary support component. Under normal landing conditions, the main leg 31 is connected to the electric push rod 33 and the base 34. When the telescopic rod of the electric push rod 33 is not retracted and is in contact with the main leg 31 by the buffer spring 32, it provides soft support. This provides a certain buffering effect during landing and can prevent damage to the UAV body 1 from landing too fast. When ground support or takeoff, the electric push rod 33 is activated to lift the main leg 31. At this time, the electric push rod 33 replaces the buffer spring 32 and directly connects to the main leg 31 to achieve a rigid connection, which can provide a certain support effect for takeoff or when on the ground.

[0043] Based on the support leg 3, the drone height adjustment component 4 can be added. The screw 45 can be rotated by starting the micro servo motor 41. When the threaded ring 42 is threadedly connected to the screw 45 and the threaded ring 42 is connected to multiple support rings 44 through the support rod 43, a limit can be formed. At this time, the rotation of the screw 45 will cause the threaded ring 42 to drive multiple support legs 3 to rise and fall through multiple support rings 44, thereby adjusting the vertical height of the entire drone body 1 to adapt to different environments.

[0044] The emergency support component 5 and the wind speed measurement component 7 work together. When the UAV body 1 loses power and falls vertically, a large amount of airflow will enter through the wind tunnel 72 and pass through the gas flow sensor 73. When the gas flow sensor 73 detects an airflow speed different from that during normal flight, it will de-energize the electromagnet 53 and allow the second support plate 52 to unfold. This can work with multiple support legs 3 to assist in buffering and reduce damage to the UAV body 1.

[0045] Within the camera assembly 6, the camera 62 is supported by the camera support rod 61, ensuring that the shooting is not obstructed by other parts. The shooting angle can be adjusted as needed, making operation convenient and quick. The rotating parts of the camera support rod 61 and the camera 62 are equipped with damping blocks, which can be adjusted and positioned to the shooting position.

[0046] The above are merely preferred embodiments of this utility model and are not intended to limit the utility model in any other way. Any person skilled in the art may make changes or modifications to the above-disclosed technical content to create equivalent embodiments for application in other fields. However, any simple modifications, equivalent changes, and modifications made to the above embodiments based on the technical essence of this utility model without departing from the technical solution of this utility model shall still fall within the protection scope of this utility model.

Claims

1. A flight control module for an unmanned aerial vehicle (UAV), characterized in that: Includes a drone body (1), a connecting plate (2) is installed at the bottom of the drone body (1), a drone height adjustment component (4) is installed at the bottom of the connecting plate (2), and support legs (3) are slidably connected to the four corners of the connecting plate (2). Camera components (6) for assisting in shooting images are installed on both sides of the connecting plate (2). The bottom of the connecting plate (2) is also equipped with two wind speed measuring components (7) and two emergency support components (5).

2. The flight control module for an unmanned aerial vehicle (UAV) according to claim 1, characterized in that: The UAV body (1) includes a fuselage (11), a battery control box (12) is fixedly installed at the bottom of the fuselage (11), the fuselage (11) is connected to the connecting plate (2) through the battery control box (12), and multiple wings (13) are installed on the fuselage (11).

3. The flight control module for a UAV according to claim 1, characterized in that: The support leg (3) includes a main leg (31), a buffer spring (32) is fixedly connected to the bottom of the main leg (31), an electric push rod (33) is connected to the bottom of the buffer spring (32), a base (34) is installed at the bottom of the electric push rod (33), the top of the output rod of the electric push rod (33) is in contact with the bottom of the main leg (31), and the main leg (31) is slidably connected to the connecting plate (2).

4. A flight control module for a drone according to claim 3, characterized in that: The drone altitude adjustment component (4) includes a micro servo motor (41), the output shaft of which is connected to a screw (45) via a coupling, a threaded ring (42) is threaded onto the screw (45), a support ring (44) is fixedly connected to each of the main legs (31), and a support rod (43) is fixedly connected between each of the support rings (44) and the threaded ring (42).

5. A flight control module for an unmanned aerial vehicle (UAV) according to claim 1, characterized in that: The emergency support (5) includes a first support plate (51), on which a hinge shaft (54) is mounted, and a second support plate (52) is hinged to the bottom of the hinge shaft (54). Electromagnets (53) that attract each other are mounted on both the first support plate (51) and the second support plate (52).

6. A flight control module for an unmanned aerial vehicle (UAV) according to claim 5, characterized in that: The camera assembly (6) includes a camera support rod (61), on which a camera (62) is rotatably connected.

7. A flight control module for an unmanned aerial vehicle (UAV) according to claim 6, characterized in that: The wind speed measurement component (7) includes a positioning block (71), on which two wind tunnels (72) with arc-shaped surfaces are opened, and gas flow rate sensors (73) are installed at the air outlets of the two wind tunnels (72).

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