Land-air dual-purpose solar cell four-rotor unmanned aerial vehicle

Abstract

The invention provides an air-ground dual-purpose solar cell four-rotor unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles. The four-rotor unmanned aerial vehicle comprises a vehicle body control bin in the middle and four flying mechanisms symmetrically distributed on the side face of the vehicle body control bin, and a crawling mechanism is connected to the bottom of the vehicle body control bin. The solar cell quadrotor unmanned aerial vehicle is based on a quadruped robot structure, can adapt to more complex terrain environments, and can make quick and accurate response to the maximum extent. The fuselage body is of a carbon fiber-honeycomb aluminum composite structure, joint components are made of titanium alloy, a solar cell panel covers the surface of the top of the fuselage, outdoor infinite endurance is supported, and solar energy is preferentially used for power supply. The mechanical-electrical integrated design significantly improves the environment adaptability, the operation efficiency and the energy utilization rate of the unmanned aerial vehicle, and has important application value in the fields of emergency rescue, geological exploration, equipment inspection and the like.

Description

Technical Field

[0001] The present invention relates to the technical field of drones, and particularly to a quadcopter drone with the ability to autonomously switch between flight and land walking modes and solar energy endurance. Background Art

[0002] Traditional quadcopter drones can usually only fly in the air and cannot move autonomously after landing, which limits their continuous operation ability in complex terrains. In the prior art, some drones have attempted to achieve ground movement through wheeled or fixed brackets, but there are the following problems:

[0003] 1. Bulky structure: The addition of a moving device causes the overall weight of the drone to exceed the standard, making it difficult to meet the portability requirements.

[0004] 2. Insufficient endurance: Relying on a single battery for power supply, it cannot support long-term lurking.

[0005] 3. Poor environmental adaptability: Lack of waterproof design, it is easily damaged in rainy or humid environments.

[0006] 4. Weak terrain adaptability: The wheeled structure cannot cross obstacles, and the leg-type structure has insufficient joint degrees of freedom. Therefore, how to provide a quadcopter drone that can autonomously switch between flight and land walking modes and has waterproof and solar energy endurance capabilities is one of the technical problems that need to be urgently solved in this field. Summary of the Invention

[0007] The purpose of the present invention is to provide a quadcopter drone with the ability to autonomously switch between flight and land walking modes and solar energy endurance, which is suitable for tasks such as reconnaissance, detection, and lurking in complex environments, and is particularly suitable for long-term outdoor covert operations.

[0008] To achieve the above-mentioned invention purpose, the present invention provides the following technical solutions:

[0009] The present invention provides a solar-powered quadcopter drone that can be used both on land and in the air, including a body control compartment in the middle and four flight mechanisms symmetrically distributed on the sides of the body control compartment. A crawling mechanism is connected to the bottom of the body control compartment.

[0010] Further, the flight mechanism includes an arm mounting base, a foldable arm, and a propeller. One end of the foldable arm is rotatably connected to the arm mounting base through a bearing. The other end of the foldable arm is provided with a propeller, and the propeller is driven by a servo motor at the bottom.

[0011] Further, the crawling mechanism includes a driving module. A first transmission rod is arranged on one side of the driving module, and a second transmission rod is arranged outside the first transmission rod.

[0012] Further, a connecting plate is arranged on the outer side of the second transmission rod, and a first driving rod is arranged on one side of the connecting plate.

[0013] Further, a second driving rod is internally connected to the first driving rod in a transmission manner. The number of the first driving rods is set to 4, and a claw part is fixedly connected to the bottom of the second driving rod.

[0014] Further, the crawling mechanism includes a first joint and a second joint. Motors are arranged inside the first joint and the second joint respectively, which are used to drive the first driving rod and the second driving rod.

[0015] Further, a solar panel is arranged on the top of the body control cabin, and the solar panel can provide power for the body.

[0016] Further, the body control cabin adopts a carbon fiber-aluminum honeycomb composite structure, and the first joint and the second joint adopt titanium alloy materials.

[0017] Advantages of the present invention:

[0018] In the present invention patent, a body control cabin, a flight mechanism and a crawling mechanism are designed. The main body of the fuselage adopts a carbon fiber-aluminum honeycomb composite structure, and the joint components use titanium alloy. Based on the dynamic gait algorithm of a quadruped robot, it can adapt to more complex terrain environments and can make quick and accurate responses to the greatest extent. The flexible solar panel covers the top surface of the fuselage, with a conversion efficiency of ≥23%, supports unlimited outdoor endurance, preferentially uses solar power supply, and enters the low-power standby mode when the battery power is <15%. The mechatronic design of the present invention significantly improves the environmental adaptability, operation efficiency and energy utilization rate of the unmanned aerial vehicle, and has important application values in the fields of emergency rescue, geological exploration, equipment inspection, etc. [[ID=2K]]Description of the Drawings

[0019] Figure 1 It is a schematic diagram of the overall structure of a solar-powered quadrotor unmanned aerial vehicle that can be used on land and in the air according to Embodiment 1 of the present invention;

[0020] Figure 2 It is a schematic diagram of the folding structure of the flight mechanism of a solar-powered quadrotor unmanned aerial vehicle that can be used on land and in the air according to Embodiment 1 of the present invention;

[0021] In the figure: 1-body control cabin, 2-flight mechanism, 3-crawling mechanism, 21-arm mounting seat, 22-foldable arm, 23-bearing, 24-propeller blade, 25-servo motor, 31-first joint, 32-second joint, 4-solar panel, 5-drive module, 6-first transmission rod, 7-second transmission rod, 8-claw part, 9-connecting plate, 10-first driving rod, 11-second driving rod. Detailed Embodiments

[0022] The present invention provides a solar cell quadcopter drone capable of both land and air use, including a body control compartment 1 in the middle and four flight mechanisms 2 symmetrically distributed on the sides of the body control compartment 1, and a crawling mechanism 3 is connected to the bottom of the body control compartment 1.

[0023] In the present invention, the flight mechanism 2 includes an arm mounting base 21, a foldable arm 2, and a propeller 24. One end of the foldable arm 22 is rotatably connected to the arm mounting base 21 through a bearing 23, and the other end of the foldable arm 22 is provided with a propeller 24, and the propeller 24 is driven by a servo motor 25 at the bottom.

[0024] In the present invention, the crawling mechanism 3 includes a driving module 5, a first transmission rod 6 is arranged on one side of the driving module 5, and a second transmission rod 7 is arranged on the outer side of the first transmission rod 6.

[0025] In the present invention, a connecting plate 9 is arranged on the outer side of the second transmission rod 6, and a first driving rod 10 is arranged on one side of the connecting plate 9.

[0026] In the present invention, a second driving rod 11 is internally connected to the first driving rod 10 in a transmission manner, the number of the first driving rods 10 is set to 4, and a claw part 8 is fixedly connected to the bottom of the second driving rod 11.

[0027] In the present invention, the crawling mechanism 3 includes a first joint 31 and a second joint 32. Motors are arranged inside the first joint 31 and the second joint 32 for driving the first driving rod 10 and the second driving rod 11.

[0028] In the present invention, a solar panel 4 is arranged on the top of the body control compartment 1 of the drone, and the solar panel 4 can provide power for the body. The battery is installed inside the body of the body control compartment 1. Installing the solar panel 4 can effectively reduce battery pollution and achieve the maximum endurance.

[0029] On the top of the body control compartment 1 of the quadcopter drone of the present invention, modular devices such as an infrared camera, a gas sensor, and a pickup can be carried.

[0030] In the present invention, the body control compartment 1 adopts a carbon fiber-aluminum honeycomb composite structure, and the first joint 31 and the second joint 32 adopt titanium alloy materials.

[0031] The technical solutions provided by the present invention will be described in detail below in conjunction with embodiments, but they cannot be construed as limiting the protection scope of the present invention.

[0032] Embodiment 1

[0033] A solar cell quadcopter that can be used both on land and in the air, including a body control compartment 1 in the middle and four flight mechanisms 2 symmetrically distributed on the sides of the body control compartment 1, and a crawling mechanism 3 is connected to the bottom of the body control compartment 1.

[0034] The flight mechanism 2 includes an arm mounting base 21, a foldable arm 2, and a propeller 24. One end of the foldable arm 22 is rotatably connected to the arm mounting base 21 through a bearing 23. The other end of the foldable arm 22 is provided with a propeller 24, and the propeller 24 is driven by a servo motor 25 at the bottom.

[0035] The crawling mechanism 3 includes a driving module 5. A first transmission rod 6 is arranged on one side of the driving module 5, and a second transmission rod 7 is arranged outside the first transmission rod 6.

[0036] A connecting plate 9 is arranged outside the second transmission rod 6, and a first driving rod 10 is arranged on one side of the connecting plate 9.

[0037] A second driving rod 11 is internally connected to the first driving rod 10. The number of the first driving rods 10 is set to 4, and a claw part 8 is fixedly connected to the bottom of the second driving rod 11.

[0038] The crawling mechanism 3 includes a first joint 31 and a second joint 32. Motors are arranged inside the first joint 31 and the second joint 32 for driving the first driving rod 10 and the second driving rod 11.

[0039] A solar panel 4 is provided on the top of the body control compartment 1 of the quadcopter, and the solar panel 4 can provide power for the body. The battery is installed inside the body of the body control compartment 1. Installing the solar panel 4 can effectively reduce battery pollution and achieve the maximum endurance.

[0040] Modular devices such as an infrared camera, a gas sensor, and a pickup can be carried on the top of the body control compartment 1 of the quadcopter.

[0041] The body control compartment 1 adopts a carbon fiber-aluminum honeycomb composite structure, and the first joint 31 and the second joint 32 adopt titanium alloy materials.

[0042] As can be seen from the above embodiments, the present invention provides an amphibious solar cell quadrotor UAV. The quadrotor UAV of the present invention includes a body control cabin in the middle and four flight mechanisms symmetrically distributed on the side of the body control cabin. A crawling mechanism is connected to the bottom of the body control cabin. The main body of the fuselage adopts a carbon fiber-aluminum honeycomb composite structure, and the joint components use titanium alloy; based on the dynamic gait algorithm of quadruped robots, it can adapt to more complex terrain environments and can make quick and accurate responses to the greatest extent. The flexible solar panel covers the top surface of the fuselage, with a conversion efficiency ≥ 23%, supports unlimited outdoor endurance, gives priority to solar power supply, and enters the low-power latent mode when the battery power < 15%. The mechatronic design of the present invention significantly improves the environmental adaptability, operation efficiency and energy utilization rate of the UAV, and has important application value in the fields of emergency rescue, geological exploration, equipment inspection, etc.

[0043] The above are only the preferred embodiments of the present invention. It should be noted that for those of ordinary skill in the art, without departing from the principle of the present invention, several improvements and refinements can be made, and these improvements and refinements should also be regarded as the protection scope of the present invention.

Claims

1. A solar cell quadcopter drone capable of both land and air use, characterized in that, It includes a body control cabin (1) in the middle and four flight mechanisms (2) symmetrically distributed on the sides of the body control cabin (1), and a crawling mechanism (3) is connected to the bottom of the body control cabin (1).

2. The quadrotor UAV according to claim 1, wherein The flight mechanism (2) includes an arm mounting base (21), a foldable arm (22), and a propeller (24). One end of the foldable arm (22) is rotatably connected to the arm mounting base (21) through a bearing (23). The other end of the foldable arm (22) is provided with a propeller (24), and the propeller (24) is driven by a servo motor (25) at the bottom.

3. The quadrotor UAV according to claim 1 or 2, characterized in that, The crawling mechanism (3) includes a driving module (5). A first transmission rod (6) is arranged on one side of the driving module (5), and a second transmission rod (7) is arranged outside the first transmission rod (6).

4. The quadrotor UAV according to claim 3, characterized in that, A connecting plate (9) is arranged outside the second transmission rod (6), and a first driving rod (10) is arranged on one side of the connecting plate (9).

5. The quadrotor UAV according to claim 4, wherein, A second driving rod (11) is internally connected to the first driving rod (10). The number of the first driving rods (10) is set to 4, and a claw part (8) is fixedly connected to the bottom of the second driving rod (11).

6. The quadrotor UAV according to claim 1, wherein The crawling mechanism (3) includes a first joint (31) and a second joint (32). Motors are arranged inside the first joint (31) and the second joint (32) to drive the first driving rod (10) and the second driving rod (11).

7. The quadrotor UAV according to claim 1, wherein A solar panel (4) is arranged on the top of the body control cabin (1), and the solar panel (4) can provide power for the body.

8. The quadrotor UAV according to claim 6, wherein The body control cabin (1) adopts a carbon fiber-aluminum honeycomb composite structure, and the first joint (31) and the second joint (32) adopt titanium alloy materials.

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