A portable exploration drone

Abstract

The utility model relates to the technical field of unmanned plane, belong to a kind of portable exploration unmanned plane, including body, the body includes body shell and body bottom shell, the body shell is connected on body bottom shell, installation bottom plate is equipped on the body bottom shell, the installation bottom plate is composed of central mainboard and several connecting ends connected on central mainboard, control feeling component, power execution component and energy component are equipped on the installation bottom plate, control feeling component and energy component are connected on central mainboard, power execution component is connected in connecting end, control feeling component includes airborne computer, the airborne computer is set in body shell, and it is close to body shell top setting. The utility model integrates laser radar, airborne computer, flight control, electrically controlled tuning and other various functional components in a micro unmanned plane body, realizes the high integration of system, reduces the overall volume and weight of unmanned plane, improves the reliability and maintainability of system.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, specifically a portable exploration UAV. Background Technology

[0002] Portable exploration drones are designed for outdoor reconnaissance, confined space exploration, and mobile missions, combining a lightweight structure with high-performance sensors to enable rapid deployment and flexible operation.

[0003] In existing technologies, many drones' airframes only provide basic structural support, lacking comprehensive collision protection design. The propellers, in particular, are prone to damage from collisions with obstacles during flight, and their protection devices are often inadequate or incomplete. Damage to the propellers or airframe results in high repair costs and complex processes, requiring specialized tools and technicians, leading to extended downtime and reduced efficiency. Most drones employ isolated rotor designs, requiring more energy to generate the same thrust, resulting in lower energy efficiency. This limits the drone's endurance and payload capacity. Furthermore, isolated rotors are susceptible to airflow interference during flight, leading to relatively poor stability and impacting flight performance. Some drones have complex battery installation methods, requiring the disassembly of multiple components for battery replacement, which is time-consuming. This reduces efficiency when frequent battery changes are needed to ensure continuous operation. Some drones may use a single sensor for obstacle avoidance, such as ultrasonic or infrared sensors. These sensors have limited detection range and accuracy, failing to achieve omnidirectional perception and prone to blind spots in complex environments, leading to collisions. In addition, even if some drones use lidar, their field of view is small, making it difficult for them to fully perceive the surrounding environment and limiting their autonomous flight capabilities in complex scenarios. Utility Model Content

[0004] To address the aforementioned technical problems, this utility model provides a portable exploration drone.

[0005] To achieve the above objectives, this utility model provides the following technical solution:

[0006] This application provides a portable exploration drone, including a body. The body includes an outer shell and a bottom shell. The outer shell is connected to the bottom shell. The bottom shell has a mounting plate, which consists of a central main board and several connecting ends connected to the central main board. The mounting plate has a sensing component, a power execution component, and an energy component. The sensing component and the energy component are connected to the central main board, and the power execution component is connected to the connecting ends. The sensing component includes an onboard computer, which is disposed inside the outer shell and close to the top of the outer shell.

[0007] Preferably, the control and sensing components also include a lidar and a matching flight controller. The lidar is mounted on a radar base and protrudes from the top surface of the fuselage. The radar base is connected to a mounting plate, and the matching flight controller is located on the bottom surface of the mounting plate. The lidar and the matching flight controller are electrically connected to the onboard computer.

[0008] Preferably, the onboard computer is equipped with a heat sink, which has a cooling fan and cooling fins. The cooling fan is located in the middle of the cooling fins, and the top of the casing has a heat dissipation hole through which the cooling fan and cooling fins are connected to the outside.

[0009] Preferably, the power actuation component includes an electronic speed controller (ESC), several motors, and several sets of rotors. The ESC is connected to the bottom surface of the mounting base plate, and the motors are connected to the mounting base plate one-to-one at their respective ends. The rotors are correspondingly mounted on the motor output shafts, and the ESC is electrically connected to the motors and the matching flight controller.

[0010] Preferably, the bottom shell of the fuselage is connected to several protective covers around its periphery. The protective covers are hollow rings and are arranged correspondingly to the rotor, and surround the rotor.

[0011] Preferably, the energy component includes a battery socket and a battery compartment for integrated battery installation. The battery socket is connected to the central main board of the mounting base plate, and the battery compartment is connected to the battery socket. The battery compartment has a battery docking plate on its inward side, and the battery docking plate integrates multiple interfaces. The battery compartment is electrically connected to the ESC.

[0012] Preferably, the battery compartment is connected to the outer shell of the machine body on the side away from the battery docking plate, and the side of the battery compartment is provided with a buckle guide groove, in which a buckle is slidably connected, and the outer shell of the machine body is provided with a corresponding engagement groove, and the buckle is connected to the engagement groove.

[0013] Compared with existing technologies, this utility model provides a portable exploration drone, which has the following advantages:

[0014] 1. By integrating multiple functional components such as lidar, onboard computer, flight control, and electronic speed controller into a miniature UAV body, and through reasonable layout and connection methods, a high degree of system integration is achieved, reducing the overall size and weight of the UAV and improving the system's reliability and maintainability.

[0015] 2. The protective shield of the fuselage is a hollow ring, forming a ducted structure. This innovative design not only improves the safety of the drone but also enhances its flight performance. The propeller protection ring structure effectively prevents damage to the propeller blades in collisions, extending their service life. The ducted structure optimizes airflow, increasing rotor thrust, allowing the drone to carry more payload or fly farther with the same power consumption.

[0016] 3. The battery features a quick-replacement design, allowing users to replace the battery quickly and improving the drone's efficiency, especially suitable for applications requiring frequent flights.

[0017] The features and advantages of this utility model will be described in detail through embodiments and accompanying drawings. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0019] Figure 2 This is a schematic diagram of the internal structure of the present invention;

[0020] Figure 3 This is a side view of the internal structure of the present invention.

[0021] Figure 4 This is a schematic diagram of the connection structure between the source component and the body of this utility model;

[0022] Figure 5 This is a schematic diagram of the electrical connections between the various components of this utility model.

[0023] In the diagram: 1. Airframe; 2. Mounting base plate; 3. Sensor components; 4. Power actuator components; 5. Energy components; 11. Airframe outer shell; 12. Airframe bottom shell; 13. Protective cover; 21. Central mainboard; 22. Connecting end; 31. LiDAR; 32. Onboard computer; 33. Matching flight controller; 321. Heat sink; 322. Cooling fan; 323. Heat sink fins; 41. Electronic speed controller; 42. Motor; 43. Rotor; 51. Battery holder; 52. Battery compartment; 53. Battery docking plate; 531. Clip guide groove; 532. Clip; 533. Engagement groove. Detailed Implementation

[0024] To make the objectives, technical solutions, and advantages of this utility model clearer, the present utility model will be further described in detail below with reference to the accompanying drawings and embodiments. However, it should be understood that the specific embodiments described herein are merely illustrative of the present utility model and are not intended to limit its scope. Furthermore, in the following description, descriptions of well-known structures and technologies are omitted to avoid unnecessarily obscuring the concepts of this utility model.

[0025] See Figures 1-5 This application provides a portable exploration drone, including a body 1. The body 1 includes an outer shell 11 and a bottom shell 12. The outer shell 11 is connected to the bottom shell 12. The connection can be made by screws or magnetic connectors, which facilitates quick disassembly, replacement and maintenance. The bottom shell 12 is provided with a mounting plate 2. The mounting plate 2 consists of a central main board 21 and several connecting ends 22 connected to the central main board. The mounting plate 2 is provided with a control sensor component 3, a power execution component 4 and an energy component 5. The control sensor component 3 and the energy component 5 are connected to the central main board 21. The power execution component 4 is connected to the connecting ends 22. The control sensor component 3 includes an onboard computer 32. The onboard computer 32 is disposed inside the outer shell 11 and is disposed close to the top of the outer shell 11, thereby facilitating heat dissipation of the onboard computer 32.

[0026] Specifically, the control and sensing component 3 also includes a lidar 31 and a matching flight controller 33. The lidar 31 is mounted on a radar base 34 and protrudes from the top surface of the fuselage shell 11. The radar base 34 is connected to a mounting base plate 2. The matching flight controller 33 is located on the bottom surface of the mounting base plate 2. The lidar 31 and the matching flight controller 33 are electrically connected to the onboard computer 32. The lidar 31 quickly transmits the scanned point cloud data to the onboard computer 32 for processing. The onboard computer 32 sends flight control commands to the matching flight controller 33 via a data bus. The matching flight controller 33 receives the control commands from the onboard computer 32 and precisely controls the UAV's flight attitude, speed, altitude, etc. The onboard computer can be an Orin NX or an NVIDIA Jetson Nano, and the lidar 31 can be a wide-field-of-view MID360 lidar.

[0027] Specifically, the onboard computer 32 is equipped with a heat sink 321, on which a cooling fan 322 and cooling fins 323 are provided. The cooling fan 322 is located in the middle of the cooling fins 323. A heat dissipation hole 111 is provided on the top of the casing 11. The cooling fan 322 and the cooling fins 323 are connected to the outside through the heat dissipation hole 111, thereby improving the heat dissipation capacity.

[0028] Specifically, the power execution component 4 includes an electronic speed controller (ESC) 41, several motors 42, and several sets of rotors 43. The ESC 41 is connected to the bottom surface of the mounting base plate 2. The motors 42 are connected one-to-one with the connecting ends 22 of the mounting base plate 2. The rotors 43 are correspondingly mounted on the output shafts of the motors 42. The ESC 41 is electrically connected to the motors 42 and the matching flight controller 33. The ESC 41 precisely adjusts the speed of the motors 42 according to the signal transmitted from the matching flight controller 33, thereby controlling the flight state of the UAV.

[0029] Specifically, the bottom shell 12 of the fuselage is connected to several protective covers 13 around its periphery. The protective covers 13 are hollow rings and are correspondingly arranged with the rotor 43. The protective covers 13 surround the rotor 43. The hollow ring-shaped protective covers 13 can better protect the rotor 43 while forming a duct structure. Under the same power consumption, it can generate greater thrust than an isolated rotor of the same diameter.

[0030] Specifically, the energy component 5 includes a battery holder 51 and a battery compartment 52 for integrating and installing batteries. The battery holder 51 is connected to the central main board 21 of the mounting base plate 2, and the battery compartment 52 is connected to the battery holder 51. The battery compartment 52 has a battery docking plate 53 on its inward side, and the battery docking plate 53 integrates multiple interfaces. The battery compartment 52 is electrically connected to the ESC 41, thereby the battery provides power to the entire UAV system.

[0031] Specifically, the battery compartment 52 is connected to the outer casing 11 on the side away from the battery docking plate 53, and the side of the battery compartment 52 is provided with a buckle guide groove 531. A buckle 532 is slidably connected in the buckle guide groove 531. The outer casing 11 is provided with a corresponding engagement groove 533. The buckle 532 is connected to the engagement groove 533. Through the buckle connection, the battery compartment 52 can be quickly disassembled.

[0032] The working principle of this utility model:

[0033] During use, the battery compartment 52 is electrically connected to the electronic speed controller (ESC) 41 to provide power to the entire UAV system. The lidar 31 is responsible for scanning the surrounding environment in all directions in real time to obtain high-precision three-dimensional spatial information. It quickly transmits the point cloud data obtained from the scan to the onboard computer 32 for processing. The onboard computer 32 receives the data from the lidar and runs complex algorithms to perform environmental perception, path planning, and flight control command generation. It sends the flight control commands to the matching flight controller 33 through the data bus. The matching flight controller 33 receives the control commands from the onboard computer 32 and sends the motor 42 speed control signal to the ESC 41. The ESC 41 precisely adjusts the speed of the motor 42 according to the signal from the matching flight controller 33, thereby controlling the flight status of the UAV and precisely controlling the flight attitude, speed, altitude, etc. The motor 42 drives the rotor 43 to rotate rapidly, generating lift.

[0034] The above description is only a preferred embodiment of this utility model and is not intended to limit this utility model. Any modifications, equivalent substitutions or improvements made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. A portable exploration drone, characterized in that: The system includes a body (1), which includes a body shell (11) and a body bottom shell (12). The body shell (11) is connected to the body bottom shell (12). The body bottom shell (12) is provided with a mounting base plate (2). The mounting base plate (2) consists of a central main board (21) and several connecting ends (22) connected to the central main board. The mounting base plate (2) is provided with a control sensing component (3), a power execution component (4) and an energy component (5). The control sensing component (3) and the energy component (5) are connected to the central main board (21). The power execution component (4) is connected to the connecting ends (22). The control sensing component (3) includes an onboard computer (32). The onboard computer (32) is located inside the body shell (11) and is located close to the top of the body shell (11).

2. A portable exploration drone as described in claim 1, characterized in that: The control and sensing component (3) also includes a lidar (31) and a matching flight controller (33). The lidar (31) is mounted on a radar base (34) and protrudes from the top surface of the fuselage shell (11). The radar base (34) is connected to the mounting base plate (2). The matching flight controller (33) is located on the bottom surface of the mounting base plate (2). The lidar (31) and the matching flight controller (33) are electrically connected to the onboard computer (32).

3. A portable exploration drone as described in claim 2, characterized in that: The onboard computer (32) is equipped with a heat sink (321), on which a cooling fan (322) and heat sink fins (323) are provided. The cooling fan (322) is located in the middle of the heat sink fins (323). A heat dissipation hole (111) is provided on the top of the casing (11). The cooling fan (322) and heat sink fins (323) are connected to the outside through the heat dissipation hole (111).

4. A portable exploration drone as described in claim 2, characterized in that: The power execution component (4) includes an electronic speed controller (41), several motors (42) and several sets of rotors (43). The electronic speed controller (41) is connected to the bottom surface of the mounting base plate (2). The motors (42) are connected one-to-one with the connecting ends (22) of the mounting base plate (2). The rotors (43) are correspondingly set on the output shaft of the motors (42). The electronic speed controller (41) is electrically connected to the motors (42) and the matching flight controller (33) respectively.

5. A portable exploration drone as described in claim 4, characterized in that: The bottom shell (12) of the fuselage is connected to several protective covers (13) around its periphery. The protective covers (13) are hollow rings. The protective covers (13) are correspondingly arranged with the rotor (43) and the protective covers (13) surround the rotor (43).

6. A portable exploration drone as described in claim 4, characterized in that: The energy component (5) includes a battery holder (51) and a battery compartment (52) for integrating and installing batteries. The battery holder (51) is connected to the central main board (21) of the mounting base plate (2). The battery compartment (52) is connected to the battery holder (51). The battery compartment (52) has a battery docking plate (53) on one side. The battery docking plate (53) integrates multiple interfaces. The battery compartment (52) is electrically connected to the ESC (41).

7. A portable exploration drone as described in claim 6, characterized in that: The battery compartment (52) is connected to the outer shell (11) on the side away from the battery docking plate (53), and the side of the battery compartment (52) is provided with a buckle guide groove (531). A buckle (532) is slidably connected in the buckle guide groove (531), and the outer shell (11) is provided with a corresponding engagement groove (533). The buckle (532) is connected to the engagement groove (533).

Images