A UAV fuselage structure with conveniently foldable rotors

Abstract

This invention discloses a rotor-folding drone fuselage structure, relating to the field of drone fuselage structure technology. The structure includes a fuselage frame, with an upper cover and a lower shell mounted at its upper and lower ends, respectively. The upper cover has heat dissipation vents on its side walls, and the lower shell has filter vents on its side walls. A cleaning mechanism is located on the exterior of the lower shell. During drone flight, the cleaning mechanism utilizes wind power to purify the gas entering the containment cavity, resulting in purer gas entering the drone through the filter vents. This improves the safety of the drone's internal electronic components, achieving energy conservation and environmental protection, and reducing maintenance costs.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicle (UAV) fuselage structures, and in particular to an unmanned aerial vehicle (UAV) fuselage structure with conveniently foldable rotors. Background Art

[0002] As an important part of modern aviation technology, drone technology has developed rapidly in recent years. During the continuous operation of drones, as the flight time and speed increase, the electronic components, batteries, motors and other components inside the fuselage will generate a lot of heat. In order to maintain the normal operating temperature of these key components and ensure the stable operation of the drone, the existing technology generally adopts the method of opening heat dissipation vents on the outside of the fuselage. These heat dissipation structures promote the exchange of air inside and outside the fuselage to form an effective airflow circulation, thereby taking away the accumulated heat inside the fuselage and achieving the purpose of heat dissipation.

[0003] During the flight, especially under complex and changeable environmental conditions, external impurities such as dust and particles can easily enter the fuselage through the heat dissipation vents, causing pollution and damage to precision electronic components, thereby affecting the overall performance and reliability of the drone.

[0004] At present, as the flight time increases, especially in harsh environments, dust and particles on the filter will gradually accumulate, resulting in a decrease in the effective mesh area of ​​the filter, which in turn affects the air circulation efficiency and ultimately weakens the heat dissipation effect of the drone. Since the filter is usually installed on the inside of the fuselage, once dust accumulates to a certain extent, the fuselage needs to be opened for disassembly and cleaning, which is not only cumbersome, but may also damage the overall structure of the drone and increase maintenance costs.

[0005] Therefore, it is necessary to provide a UAV fuselage structure with conveniently foldable rotors to solve the problems raised in the above background technology. Summary of the invention

[0006] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a drone fuselage structure with conveniently foldable rotors, comprising a fuselage, the fuselage comprising a fuselage plate frame, an upper shell cover and a lower shell are respectively installed at the upper and lower ends of the fuselage plate frame, a side shell wall of the upper shell cover is provided with a heat dissipation port, a side shell wall of the lower shell is provided with a filter air hole, a cleaning mechanism is provided on the outside of the lower shell, the cleaning mechanism comprises a rotating shell cover rotatably installed on the lower shell, a radial straight plate is installed at the center of the outer wall of the bottom end of the rotating shell cover, and the rotating shell cover is provided with a plurality of radial straight plates. A gear ring is fixed on the side shell wall, and an inner shell ring is also installed on the lower shell body. The inner shell ring is located outside the side wall of the rotating shell cover, and a rotating rod is rotatably installed on the shell wall of the inner shell ring. The rotating rod radially penetrates the shell wall of the inner shell ring, and a gear meshing with the gear ring is installed on the end of the rotating rod close to the rotating shell cover, and a cleaning brush is installed on the end of the rotating rod away from the rotating shell cover. An outer rotating shell ring is rotatably installed outside the side wall of the inner shell ring, and an air cavity 2 is formed between the outer rotating shell ring and the inner shell ring. A filter air port cooperating with the cleaning brush is provided on the shell wall of the outer rotating shell ring.

[0007] Further, as a preference, the rotating rod includes a column sleeve rotatably mounted with the inner shell ring, the column sleeve has a gear fixedly sleeved on one end close to the rotating shell cover, the column sleeve has a column cavity provided on one end away from the rotating shell cover, a column rod is slidably connected to the column cavity, the column rod and the column sleeve are connected by a spring, and the end of the column rod away from the column cavity is fixedly connected to a cleaning brush.

[0008] Further, as a preference, the filter air ports are distributed on the side walls and bottom wall of the outer rotating shell ring.

[0009] Furthermore, preferably, the cleaning brush has a spherical structure.

[0010] Furthermore, as a preference, a cleaning brush 2 cooperating with the filtering air holes is also provided on the shell wall of the outer rotating shell ring.

[0011] Furthermore, as a preference, a guide cover is installed in the upper shell cover, the guide cover and the upper shell cavity in the upper shell cover form an air cavity covering the heat dissipation port, a guide port is opened in the center of the guide cover, a forward and reverse motor is installed on the upper shell cover, and the output end of the forward and reverse motor is connected to a guide fan located in the guide port.

[0012] Furthermore, as a preference, a filter ring covering the heat dissipation opening is also provided on the fuselage panel frame.

[0013] Furthermore, preferably, the lower shell is also provided with a particle sensor for monitoring the concentration of particles in the second air cavity.

[0014] Further, as a preference, connecting frames are respectively installed at the four corner ends of the fuselage panel frame, a horizontally folding folding frame is installed on the connecting frame, and a rotor is installed on the folding frame.

[0015] Further, preferably, a buffer drop frame is installed at the lower end of the connecting frame.

[0016] Compared with the prior art, the present invention provides a UAV fuselage structure with conveniently foldable rotors, which has the following beneficial effects:

[0017] Through the structural design of the cleaning mechanism in the present invention, during the flight of the UAV, the flow of air can play the effect of pushing the straight plate, so that the straight plate will drive the rotating shell cover to rotate back and forth or unidirectionally with the fluctuation of the air flow, so that the gear ring can drive the gear to rotate, the gear drives the rotating rod to rotate, and the rotating rod drives the cleaning brush to rotate, so as to clean the filter air port in real time, avoid the accumulation of dust, particulate matter, etc. on the filter air port, and timely filter the particles and dust stuck on the air port in a sweeping manner from the inside to the outside, so as to maintain the cleanliness of the filter air port, thereby ensuring the filtering effect of the filter air port. That is to say, when the UAV is running and flying, the cleaning mechanism can use wind energy to purify the gas entering the accommodating cavity, thereby achieving energy saving and green environmental protection effects, and reducing maintenance costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0019] Figure 2 It is a structural schematic diagram of the buffer drop frame in the present invention;

[0020] Figure 3 It is a schematic diagram of the cross-sectional structure of the fuselage of the UAV in the present invention;

[0021] Figure 4 It is a structural schematic diagram of the cleaning mechanism in the present invention;

[0022] Figure 5 It is a structural schematic diagram of the transfer rod of the present invention;

[0023] In the figure: 1. fuselage; 2. connecting frame; 3. folding frame; 4. rotor; 5. buffer landing frame; 6. cleaning mechanism; 11. fuselage plate frame; 12. upper shell cover; 13. guide cover; 14. air cavity one; 15. filter ring; 16. lower shell; 121. heat dissipation port; 122. forward and reverse motor; 123. guide fan; 131. guide port; 161. filter air hole; 61. rotating shell cover; 62. straight plate; 63. gear ring; 64. inner shell ring; 65. rotating rod; 66. gear; 67. cleaning brush one; 68. outer rotating shell ring; 69. air cavity two; 610. particle sensor; 651. column sleeve; 652. column rod; 653. spring; 6511. column cavity; 681. filter air port; 682. cleaning brush two. DETAILED DESCRIPTION

[0024] Reference Figure 1-Figure 5The present invention provides a technical solution: a fuselage structure of a drone with conveniently foldable rotors, comprising a fuselage 1, wherein the fuselage 1 comprises a fuselage plate frame 11, wherein an upper shell cover 12 and a lower shell 16 are respectively installed at the upper and lower ends of the fuselage plate frame 11, wherein a side shell wall of the upper shell cover 12 is provided with a heat dissipation port 121, and a side shell wall of the lower shell 16 is provided with a filter air hole 161, and a cleaning mechanism 6 is provided on the outside of the lower shell 16, wherein the cleaning mechanism 6 comprises a rotating shell cover 61 rotatably installed on the lower shell 16, wherein a straight plate 62 in a radial direction is installed at the center of the outer wall of the bottom end of the rotating shell cover 61, and a gear ring 63 is fixedly sleeved on the side shell wall of the rotating shell cover 61, and an inner shell ring 64 is also installed on the lower shell 16, wherein the inner shell ring 64 is located at a position On the outside of the side wall of the rotating shell cover 61, a rotating rod 65 is rotatably installed on the shell wall of the inner shell ring 64, and the rotating rod 65 radially penetrates the shell wall of the inner shell ring 64. A gear 66 meshing with the gear ring 63 is installed on the end of the rotating rod 65 close to the rotating shell cover 61, and a cleaning brush 67 is installed on the end of the rotating rod 65 away from the rotating shell cover 61. An outer rotating shell ring 68 is rotatably installed on the outside of the side wall of the inner shell ring 64, and an air cavity 69 is formed between the outer rotating shell ring 68 and the inner shell ring 64. A filter air port 681 that cooperates with the cleaning brush 67 is provided on the shell wall of the outer rotating shell ring 68; wherein, a accommodating cavity is formed between the upper shell cover 12 and the lower shell 16, and the accommodating cavity is used to install the electronic devices required for the drone. When air enters the accommodating cavity through the filter air hole 161 The air in the accommodating cavity is taken away, and enters the air cavity 14 through the guide port 131, and then is discharged to the outside through the heat dissipation port 121 to dissipate heat from the accommodating cavity; through the setting of the cleaning mechanism 6, the air entering the accommodating cavity can be purified to ensure the purity of the gas entering the accommodating cavity, thereby preventing dust, particles and other pollutants in the air from contaminating the electronic devices in the accommodating cavity, avoiding affecting the normal operation of the drone, and improving the safety of use and service life of the drone; wherein, the lower shell 16 is fixedly assembled with the inner shell ring 64, and the center of the straight plate 62 coincides with the axis of the lower shell 16. When the drone is in flight, the flow of air can push the straight plate 62, which will make the straight plate The plate 62 drives the rotating shell 61 to rotate back and forth or unidirectionally as the air flow fluctuates, so that the gear ring 63 can drive the gear 66 to rotate, and the gear 66 drives the rotating rod 65 to rotate, and the rotating rod 65 drives the cleaning brush 67 to rotate, so as to clean the filter air port 681 in real time to avoid the accumulation of dust, particulate matter, etc. on the filter air port 681, and timely filter the particles and dust stuck on the air port 681 by sweeping from the inside to the outside, so as to maintain the cleanliness of the filter air port 681, thereby ensuring the filtering effect of the filter air port 681. That is to say, when the UAV is running and flying, the cleaning mechanism 6 can use wind energy to purify the gas entering the accommodating cavity, thereby realizing energy saving and green environmental protection effects.

[0025] In this embodiment, the rotating rod 65 includes a column sleeve 651 rotatably mounted with the inner shell ring 64, and a gear 66 is fixedly sleeved on one end of the column sleeve 651 close to the rotating shell cover 61, and a column cavity 6511 is provided on the end of the column sleeve 651 away from the rotating shell cover 61, and a column rod 652 is slidably connected to the column cavity 6511. The column rod 652 is connected to the column sleeve 651 by a spring 653, and the end of the column rod 652 away from the column cavity 6511 is fixedly connected to the cleaning brush 67; so that the rotating rod 65 has retractability, and through the elastic action of the spring 653, the cleaning brush 67 can fully push against the filter air port 681, thereby improving the cleaning strength of the filter air port 681.

[0026] In this embodiment, the filter air ports 681 are distributed on the side walls and bottom walls of the outer rotating shell ring 68 so that dust, particles, etc. in the air cavity 2 69 can be swept out by the cleaning brush 1 67 in a timely manner.

[0027] In this embodiment, the cleaning brush 67 is in a spherical structure so as to sweep the filter air port 681 upward and drive the outer rotating shell ring 68 to rotate.

[0028] In this embodiment, a cleaning brush 2 682 cooperating with the filter air hole 161 is also provided on the shell wall of the outer rotating shell ring 68; when the rotating rod 65 drives the cleaning brush 1 67 to rotate and sweep and clean the filter air port 681, at the same time, the cleaning brush 1 67 can drive the outer rotating shell ring 68 to rotate, and can drive the cleaning brush 2 682 to clean the filter air hole 161.

[0029] In this embodiment, a guide cover 13 is installed in the upper shell cover 12, and the guide cover 13 and the upper shell cavity in the upper shell cover 12 form an air cavity 14 covering the heat dissipation port 121. A guide port 131 is opened in the center of the guide cover 13, and a forward and reverse motor 122 is installed on the upper shell cover 12. The output end of the forward and reverse motor 122 is connected to a guide fan 123 located in the guide port 131; that is, by driving the guide fan 123 to rotate forward and reversely through the forward and reverse motor 122, the guide direction of the gas in the guide port 131 can be changed, and the guide direction can be divided into a guide direction one and a guide direction two, that is, the guide direction one is that the guide fan 123 guides the airflow in the accommodating cavity into the air cavity 14, and the airflow in the air cavity 14 The air is discharged through the heat dissipation port 121. At this time, the external gas enters the second air cavity 69 through the filter air port 681, and enters the accommodating cavity through the filter air hole 161, thereby forming a heat dissipation treatment for the heat in the accommodating cavity; the second flow direction is that the guide fan 123 guides the airflow in the air cavity 14 to enter the accommodating cavity, and the airflow in the accommodating cavity enters the second air cavity 69 through the filter air port 681, and the airflow in the second air cavity 69 is discharged through the filter air port 681. At this time, the external gas is filtered by the filter ring 15 and enters the air cavity 14 through the heat dissipation port 121, which is conducive to cooperating with the cleaning brush 1 67 to remove the dust and particulate matter in the second air cavity 69 through the filter air port 681. At the same time, the heat in the accommodating cavity can also be temporarily dissipated.

[0030] In this embodiment, a filter ring 15 covering the heat dissipation opening 121 is further provided on the fuselage plate frame 11 so as to perform a short filtering and purification process on the external air when the external air flows in through the heat dissipation opening 121 .

[0031] In this embodiment, the lower shell 16 is also provided with a particle sensor 610 for monitoring the concentration of particulate matter in the second air cavity 69; wherein, the particle sensor 610 monitors the concentration of particulate matter in the second air cavity 69, and when the warning value is reached, feedback is given to the forward and reverse motor 122 to start the second flow diversion direction program, that is, the first flow diversion direction program serves as the main heat dissipation treatment method for the heat of the accommodating cavity, and the second flow diversion direction program serves as the exchange of gas in the second air cavity 69 and the cleaning treatment of the filter air port 681.

[0032] In this embodiment, connecting frames 2 are respectively installed at the four corner ends of the fuselage panel frame 11, and a horizontally folding frame 3 is installed on the connecting frame 2, and a rotor 4 is installed on the folding frame 3, so that the folding of the rotor 4 is more convenient.

[0033] In this embodiment, a buffer landing frame 5 is installed at the lower end of the connecting frame 2 so that the landing of the UAV is safer.

[0034] In the specific implementation, the warning value of the particle sensor 610 that monitors the particle concentration is set, and the folding frame 3 is opened to start the drone. During the flight of the drone, the airflow in the air automatically triggers the cleaning mechanism 6 to ensure the purity of the gas when the electronic devices in the drone are cooled. When the warning value of the particle sensor 610 is triggered, it is fed back to the forward and reverse motors 122 to start the second diversion direction program until the monitoring value of the particle sensor 610 falls back to the range of the lowest stable fluctuation, and then it is fed back to the forward and reverse motors 122 again to start the first diversion direction program to dissipate the heat of the accommodating cavity. When the flight of the drone ends, the drone is safely landed through the buffer landing frame 5.

[0035] The above description is only a preferred specific implementation manner of the invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical scheme and inventive concept of the present invention within the technical scope disclosed by the invention, which should be covered by the protection scope of the present invention.

Claims

1. A drone fuselage structure with conveniently foldable rotors, comprising a fuselage (1), characterized in that: The fuselage (1) comprises a fuselage plate frame (11), an upper shell cover (12) and a lower shell (16) are respectively mounted on the upper and lower ends of the fuselage plate frame (11), a side shell wall of the upper shell cover (12) is provided with a heat dissipation port (121), a side shell wall of the lower shell (16) is provided with a filter air hole (161), a cleaning mechanism (6) is provided on the outside of the lower shell (16), the cleaning mechanism (6) comprises a rotating shell cover (61) rotatably mounted on the lower shell (16), a radial straight plate (62) is mounted at the center of the outer wall at the bottom end of the rotating shell cover (61), a toothed ring (63) is fixedly sleeved on the side shell wall of the rotating shell cover (61), and an inner shell ring (64) is also mounted on the lower shell (16). The inner shell ring (64) is located outside the side wall of the rotating shell cover (61), and a rotating rod (65) is rotatably mounted on the shell wall of the inner shell ring (64). The rotating rod (65) radially penetrates the shell wall of the inner shell ring (64), and a gear (66) meshing with the gear ring (63) is mounted on one end of the rotating rod (65) close to the rotating shell cover (61), and a cleaning brush (67) is mounted on one end of the rotating rod (65) away from the rotating shell cover (61). An outer rotating shell ring (68) is rotatably mounted outside the side wall of the inner shell ring (64), and an air cavity (69) is formed between the outer rotating shell ring (68) and the inner shell ring (64). A filter air port (681) cooperating with the cleaning brush (67) is provided on the shell wall of the outer rotating shell ring (68).

2. The UAV fuselage structure with conveniently foldable rotors according to claim 1 is characterized in that: The rotating rod (65) comprises a column sleeve (651) rotatably mounted with the inner shell ring (64); a gear (66) is fixedly mounted on one end of the column sleeve (651) close to the rotating shell cover (61); a column cavity (6511) is provided on one end of the column sleeve (651) away from the rotating shell cover (61); a column rod (652) is slidably connected to the column cavity (6511); the column rod (652) is connected to the column sleeve (651) via a spring (653); and one end of the column rod (652) away from the column cavity (6511) is fixedly connected to a cleaning brush (67).

3. The UAV fuselage structure with conveniently foldable rotors according to claim 1, characterized in that: The filter air ports (681) are distributed on the side wall and the bottom wall of the outer rotating shell ring (68).

4. The UAV fuselage structure with conveniently foldable rotors according to claim 1, characterized in that: The cleaning brush 1 (67) is spherical in structure.

5. The UAV fuselage structure with conveniently foldable rotors according to claim 1, characterized in that: A second cleaning brush (682) cooperating with the filtering air hole (161) is also provided on the shell wall of the outer rotating shell ring (68).

6. The UAV fuselage structure with conveniently foldable rotors according to claim 1, characterized in that: A guide cover (13) is installed in the upper shell cover (12); the guide cover (13) and the upper shell cavity in the upper shell cover (12) form an air cavity (14) covering the heat dissipation port (121); a guide port (131) is opened at the center of the guide cover (13); a forward and reverse motor (122) is installed on the upper shell cover (12); and the output end of the forward and reverse motor (122) is connected to a guide fan (123) located in the guide port (131).

7. The UAV fuselage structure with conveniently foldable rotors according to claim 1, characterized in that: The fuselage plate frame (11) is also provided with a filter ring (15) covering the heat dissipation opening (121).

8. The UAV fuselage structure with conveniently foldable rotors according to claim 1, characterized in that: The lower housing (16) is also provided with a particle sensor (610) for monitoring the concentration of particles in the second air cavity (69).

9. The UAV fuselage structure with conveniently foldable rotors according to claim 1, characterized in that: The four corner ends of the fuselage plate frame (11) are respectively installed with connecting frames (2), a horizontally foldable folding frame (3) is installed on the connecting frame (2), and a rotor (4) is installed on the folding frame (3).

10. The UAV fuselage structure with conveniently foldable rotors according to claim 9, characterized in that: A buffer drop frame (5) is installed at the lower end of the connecting frame (2).

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