A dual-rotor drone

Abstract

This utility model discloses a dual-rotor drone, relating to the field of drones. It includes a casing, with an upper rotor rotatably mounted on the top of the casing and a lower rotor rotatably mounted on the bottom of the casing. The upper and lower rotors are arranged coaxially at the top and bottom of the casing, respectively, thus driving the drone to fly using a dual-rotor configuration. The upper and lower rotors are controlled independently, which facilitates the control of the drone and simplifies the dual-rotor structure, enabling the dual-rotor drone to be miniaturized and applied to more complex and varied environments.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicles (UAVs), specifically a dual-rotor UAV. Background Technology

[0002] Unmanned aerial vehicles (UAVs), also known as drones, are unmanned aircraft controlled by radio remote control equipment and onboard program control devices, or operated autonomously, either completely or intermittently, by an onboard computer. UAVs are widely used in agricultural plant protection, environmental monitoring, and military reconnaissance. Traditional dual-rotor UAVs mostly employ a coaxial dual-rotor structure, where the upper and lower rotors are mounted on the same mechanical shaft. Stable flight is achieved by counteracting torque through the counter-rotation of the two rotors. However, this structure has certain limitations: the transmission mechanism and control system of coaxial dual-rotors are complex, and steering requires adjusting the rotor blade angle of attack, resulting in larger and heavier UAVs. This makes them difficult to operate flexibly in narrow and complex spaces, such as dense jungles or confined spaces inside buildings, severely limiting their application and hindering miniaturization and portability. Furthermore, the complex structure increases production costs and maintenance difficulty, hindering large-scale deployment.

[0003] Furthermore, during prolonged operation, drones generate significant heat from components such as motors. Some drones have inadequate heat dissipation designs, relying solely on simple ventilation holes, which fails to effectively reduce internal temperatures. This can lead to decreased motor performance, shortened lifespan of electronic components, and even malfunctions, impacting the drone's reliability and stability. Utility Model Content

[0004] The purpose of this invention is to overcome the shortcomings of the existing technology and provide a dual-rotor drone to address the deficiencies of the existing technology.

[0005] The purpose of this utility model is achieved through the following technical solution: a dual-rotor unmanned aerial vehicle (UAV) including a casing, an upper rotor rotatably disposed on the top of the casing, and a lower rotor rotatably disposed on the bottom of the casing.

[0006] Furthermore, a first motor is provided inside the housing, the output shaft of the first motor is connected to the upper rotor, and the housing of the first motor is mounted on the housing via a two-axis four-way bracket.

[0007] Furthermore, the two-axis four-way support includes an inner ring and an outer ring arranged coaxially. The inner ring is sleeved on the housing of the first motor. The housing of the first motor is symmetrically connected to two first rotating shafts, both of which are rotatably connected to the inner ring. The outer ring of the inner ring is symmetrically connected to two second rotating shafts, both of which are rotatably connected to the outer ring. The outer ring is fixedly connected to the housing. The rotation axes of the first and second rotating shafts are both arranged horizontally, and the rotation axis of the first rotating shaft is orthogonal to the rotation axis of the second rotating shaft.

[0008] Furthermore, a lever is fixed to the tail of the first motor, and an electromagnetic direction control assembly is provided inside the housing. The electromagnetic direction control assembly includes a mounting plate, a guide frame, an electromagnet armature, and an electromagnet. Two guide frames are spaced apart along the axial direction of the lever, and the two guide frames are perpendicular to each other. Electromagnets are provided on both sides of the guide frame in the width direction. The electromagnets are mounted on the mounting plate, and an electromagnet armature slides through the electromagnet. One end of the electromagnet armature is connected to the guide frame, and the lever passes through the two guide frames.

[0009] Furthermore, a shooting window is provided on the side wall of the housing, and an information acquisition device is installed inside the shooting window.

[0010] Furthermore, the bottom circumference of the housing is provided with three feet, one of which is an antenna for signal reception, and the other two feet serve as the positive and negative terminals for charging.

[0011] Furthermore, the top and bottom of the housing are provided with multiple heat dissipation holes, which are connected to the inner cavity of the housing.

[0012] Furthermore, the diameter of the casing gradually decreases along the direction approaching the upper rotor.

[0013] Furthermore, a second motor is installed inside the housing, and the output shaft of the second motor is connected to the lower rotor.

[0014] The beneficial effects of this utility model are:

[0015] 1. The upper and lower rotors are arranged on opposite axes at the top and bottom of the fuselage, respectively. This means that the drone is driven by independent dual rotors. The upper and lower rotors are controlled separately. The upper rotor mainly controls the drone's vertical ascent and descent, while the lower rotor mainly controls the drone's horizontal rotation. This design facilitates the control of the drone and simplifies the dual rotor structure, enabling the dual-rotor drone to be miniaturized and applied to more complex and variable environments.

[0016] 2. By controlling the translational motion of the upper rotor in four directions on the horizontal plane through four sets of evenly distributed electromagnets, the upper rotor is driven to rotate around the two-axis four-way support as the fulcrum, thereby realizing the flight direction adjustment of the UAV and making the flight direction adjustment of the UAV simpler.

[0017] 3. The overall casing is teardrop-shaped or spindle-shaped, which reduces air resistance when the drone ascends and makes the lift generation more efficient.

[0018] 4. Ventilation holes are provided on the top and bottom of the casing to allow cold air from the outside to enter the casing, which enhances airflow and provides excellent heat dissipation for the drone.

[0019] 5. The dual rotor structure makes the drone's flight process discontinuous and difficult to lock onto, making it applicable to agricultural scenarios with complex and harsh terrain or military reconnaissance fields. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the structure of a dual-rotor unmanned aerial vehicle according to the present invention. Figure 1 ;

[0021] Figure 2 This is a top view of a dual-rotor unmanned aerial vehicle according to the present invention;

[0022] Figure 3 This is a schematic diagram of the internal structure of a dual-rotor unmanned aerial vehicle according to the present invention;

[0023] Figure 4 This is a schematic diagram of the electromagnetic direction control component in a dual-rotor unmanned aerial vehicle (UAV) according to this utility model. Figure 1 ;

[0024] Figure 5 This is a schematic diagram of the electromagnetic direction control component in a dual-rotor unmanned aerial vehicle (UAV) according to this utility model. Figure 2 ;

[0025] Figure 6 This is a schematic diagram of the structure of a dual-rotor unmanned aerial vehicle according to the present invention. Figure 2 ;

[0026] In the diagram, 1-casing, 2-upper rotor, 3-lower rotor, 4-first motor, 5-inner ring, 6-outer ring, 7-first shaft, 8-second shaft, 9-mounting plate, 10-electromagnet, 11-guide frame, 12-information acquisition device, 13-foot, 14-heat dissipation hole, 15-second motor, 16-armature, 17-lever, 18-reset spring, 19-guide shaft. Detailed Implementation

[0027] Example 1

[0028] like Figures 1 to 6As shown, a dual-rotor unmanned aerial vehicle (UAV) includes a housing 1. An upper rotor 2 is rotatably mounted on the top of the housing 1, and a lower rotor 3 is rotatably mounted on the bottom of the housing 1. The upper rotor 2 and lower rotor 3 are not mounted on the same mechanical axis, allowing them to operate independently. A first motor 4 is installed inside the housing 1, and the output shaft of the first motor 4 is connected to the upper rotor 2. The housing of the first motor 4 is mounted to the housing 1 via a two-axis four-way bracket. A second motor 15 is installed inside the housing 1, and the output shaft of the second motor 15 is connected to the lower rotor 3. The first motor 4 drives the upper rotor 2 to rotate, and the second motor 15 drives the lower rotor 3 to rotate. The upper rotor 2 and lower rotor 3 are not on the same axis but are arranged on the same axis. The upper rotor 2 and the lower rotor 3 are controlled independently, which facilitates the control of the UAV and simplifies the dual-rotor structure. This allows the dual-rotor UAV to be miniaturized and applied to more complex and variable environments. In practice, the blade angle of attack of the upper rotor 2 remains unchanged, and its lift is controlled by the rotation speed of the upper rotor 2. The lower rotor 3 is used to adjust and neutralize the torque difference generated by the upper rotor 2, thereby adjusting the flight direction of the UAV. Secondly, although the control precision of the upper and lower dual-rotor structure is not as high as that of the coaxial dual-rotor, it is an advantage in some specific fields of UAVs. That is, the flight process of the UAV is discontinuous and it is not easy to be locked, which can be applied to agricultural scenarios with complex and harsh terrain or military reconnaissance fields.

[0029] Furthermore, a shooting window is provided on the side wall of the housing 1, and an information acquisition device 12 is installed inside the shooting window. A power supply is provided inside the housing 1, and information is collected through the information acquisition device 12, or military reconnaissance is carried out.

[0030] Example 2

[0031] Based on Embodiment 1, the diameter of the casing 1 gradually decreases along the direction close to the upper rotor 2, and the casing 1 is generally teardrop-shaped or spindle-shaped, which reduces the air resistance when the drone ascends and makes the efficiency of generating lift higher.

[0032] Example 3

[0033] Based on Example 2, such as Figures 1 to 3As shown, the two-axis four-way support includes an inner ring 5 and an outer ring 6 arranged coaxially. The inner ring 5 is fitted onto the housing of the first motor 4. The housing of the first motor 4 is symmetrically connected to two first rotating shafts 7, both of which are rotatably connected to the inner ring 5. The outer ring of the inner ring 5 is symmetrically connected to two second rotating shafts 8, both of which are rotatably connected to the outer ring 6. The outer ring 6 is fixedly connected to the housing 1. The rotation axes of the first rotating shafts 7 and the second rotating shafts 8 are both horizontally arranged, and the rotation axes of the first rotating shafts 7 are orthogonal to the rotation axes of the second rotating shafts 8. The second rotating shafts 8 drive the inner ring 5 to deflect, and the inner ring 5 drives the first motor 4 to deflect through the first rotating shafts 7. The first motor 4 drives the upper rotor 2 to deflect, and the first rotating shafts 7 drive the first motor 4 to deflect, so that the first motor 4 drives the upper rotor 2 to deflect, thereby enabling the upper rotor 2 to deflect in different directions. Through the cooperation of the first rotating shafts 7 and the second rotating shafts 8, the deflection direction of the upper rotor 2 is controlled, thereby realizing the flight direction adjustment of the UAV.

[0034] Example 4

[0035] Based on Example 3, such as Figures 1 to 6As shown, a lever 17 is fixed to the tail of the first motor 4. An electromagnetic direction control assembly is installed inside the housing 1. The electromagnetic direction control assembly includes a mounting plate 9, guide frames 11, an electromagnet armature, and an electromagnet 10. Two guide frames 11 are spaced apart along the axial direction of the lever 17, and the two guide frames 11 are perpendicular to each other. An electromagnet 10 is installed on both sides of the guide frame 11 in the width direction. The electromagnet 10 is mounted on the mounting plate 9, and an electromagnet armature slides through the electromagnet 10. One end of the electromagnet armature is connected to the guide frame 11, and the lever 17 passes through the two guide frames. 11. A rectangular slot is provided through the guide frame 11, and the lever 17 passes through the rectangular slot. The length of the rectangular slot is greater than the diameter of the lever. Each guide frame 11 is provided with two electromagnets 10. The electromagnets 10 and their armatures form an electromagnet mechanism. The four sets of electromagnet mechanisms are evenly distributed in a circle around the axis of the lever 17. The electromagnet armature includes an armature 16, a spring 18, and a guide shaft 19. One end of the guide shaft 19 is connected to the armature 16, and the other end moves through the electromagnet 10. The armature 16 is connected to the guide frame 11, and the spring 18 is fitted onto the guide shaft. On 19, when one of the electromagnets 10 is energized, it attracts the corresponding armature 16 to move. The armature 16 compresses the spring 18, causing the armature 16 to move the guide frame 11 connected to it. The guide frame 11 then moves the lever 17 in the same direction. At this time, the lever 17 moves along the length of the rectangular slot within the other guide frame 11, ensuring that the lever 17 does not interfere with the other guide frame 11. Under the torque of the lever 17, the first motor 4 is driven to deflect around the first rotating shaft 7 or around the second rotating shaft 8, thereby driving... The upper rotor 2 deflects around the first axis 7 or the second axis 8. When the electromagnet 10 is de-energized, the armature 16 drives the corresponding guide frame 11 to reset under the reaction force of the spring 18. When a single axial electromagnet 10 is energized, the drone can move in the four directions of east, south, west, and north. When two adjacent electromagnets 10 are energized, the upper rotor 2 can move in the four directions of southeast, southwest, northwest, and northeast. By controlling the current of the electromagnets 10, the drone can fly in any direction, making the adjustment of the drone's flight direction simpler.

[0036] Example 5

[0037] Based on Embodiment 4, three legs 13 are arranged around the bottom circumference of the housing 1. One leg 13 is an antenna for signal reception, and the other two legs 13 serve as positive and negative terminals for charging the power supply inside the drone.

[0038] Example 6

[0039] Based on Example 5, such as Figure 1 and Figure 6As shown, multiple heat dissipation holes 14 are provided on the top and bottom of the housing 1. The heat dissipation holes 14 are connected to the inner cavity of the housing 1, allowing cold air from the outside to enter the housing 1, which enhances the air flow and can effectively dissipate heat from the drone.

Claims

1. A dual-rotor unmanned aerial vehicle (UAV), comprising a casing (1), characterized in that, The top of the housing (1) is rotatably equipped with an upper rotor (2), and the bottom of the housing (1) is rotatably equipped with a lower rotor (3). A first motor (4) is installed inside the housing (1). The output shaft of the first motor (4) is connected to the upper rotor (2). The housing of the first motor (4) is mounted on the housing (1) via a two-axis four-way bracket. The two-axis four-way bracket includes an inner ring (5) and an outer ring (6) arranged coaxially. The inner ring (5) is sleeved on the housing of the first motor (4). The housing of the first motor (4) is symmetrically connected to two first rotating shafts (7). Both first rotating shafts (7) are rotatably connected to the inner ring (5). The outer ring of the inner ring (5) is symmetrically connected to two second rotating shafts (8). Both second rotating shafts (8) are rotatably connected to the outer ring (6). The outer ring (6) is fixedly connected to the housing (1). The rotation axis of the shaft (7) and the rotation axis of the second shaft (8) are both arranged horizontally, and the rotation axis of the first shaft (7) is orthogonal to the rotation axis of the second shaft (8). The tail of the first motor (4) is fixed with a lever (17). An electromagnetic direction control assembly is provided inside the housing (1). The electromagnetic direction control assembly includes a mounting plate (9), a guide frame (11), an electromagnet armature, and an electromagnet (10). Two guide frames (11) are spaced apart along the axial direction of the lever (17), and the two guide frames (11) are arranged vertically. Electromagnets (10) are provided on both sides of the width direction of the guide frame (11). The electromagnets (10) are mounted on the mounting plate (9). An electromagnet armature slides through the electromagnet (10). One end of the electromagnet armature is connected to the guide frame (11). The lever (17) passes through the two guide frames (11).

2. A dual-rotor unmanned aerial vehicle according to claim 1, characterized in that, The side wall of the housing (1) is provided with a shooting window, and an information acquisition device (12) is installed in the shooting window.

3. A dual-rotor unmanned aerial vehicle according to claim 1, characterized in that, The bottom circumference of the housing (1) is provided with three feet (13), one of which is an antenna for signal reception, and the other two feet (13) serve as the positive and negative terminals for charging.

4. A dual-rotor unmanned aerial vehicle according to claim 1, characterized in that, The top and bottom of the housing (1) are provided with multiple heat dissipation holes (14), which are connected to the inner cavity of the housing (1).

5. A dual-rotor unmanned aerial vehicle according to claim 1, characterized in that, The diameter of the casing (1) gradually decreases along the direction close to the upper rotor (2).

6. A dual-rotor unmanned aerial vehicle according to claim 1, characterized in that, A second motor (15) is installed inside the housing (1), and the output shaft of the second motor (15) is connected to the lower rotor (3).

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