Power supply heat-dissipation air-cooling casing of unmanned aerial vehicle

Abstract

The utility model discloses a power supply heat dissipation air cooling casing of an unmanned aerial vehicle, which relates to the technical field of unmanned aerial vehicles and comprises a cyclone ring channel groove, a paddle support, a wing rod, an outer casing and an air flow channel casing groove. A worker assembles a cyclone ring channel groove on a paddle support to be matched with a wing rod frame to be protected on the two sides of the outer shell, and then a Tesla valve channel is connected in series front and back through an air inlet pipeline and an exhaust pipeline of an air flow channel shell groove, so that the Tesla valve channel and the surface of the air flow channel groove form an air cooling ventilation flight heat dissipation effect on the top of a power supply end; then the corrugated flow channel is connected in series with the outer cyclone channel, the middle cyclone channel and the inner cyclone channel to form an air cooling heat dissipation operation effect of transitional discharge of inner and outer concave cyclone and middle-partition concave-convex fluctuating cyclone, so that overheating caused by continuous increase of power supply electricity load due to addition of a radiator is avoided; the area division of single blade motor heat dissipation and power supply heat dissipation is improved, targeted machine shell ventilation is achieved, and the flight air cooling heat dissipation effect is achieved.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a power supply heat dissipation air-cooling casing of an unmanned aerial vehicle. Background Art

[0002] Aircraft refers to aircraft that can fly in the atmosphere. Any aircraft must generate a lift greater than its own weight in order to rise into the air. Based on the principle of generating lift, aircraft can be divided into two categories: lighter-than-air aircraft and heavier-than-air aircraft. The former relies on the static buoyancy of air to rise into the air; the latter relies on aerodynamic force to overcome its own gravity to rise into the air. Aircraft is a large category of aircraft, and refers to any machine that obtains aerodynamic force to rise into the air through the relative movement of the fuselage and the air, that is, not the reaction of air to the ground. Including balloons, airships, airplanes, gliders, gyroplanes, helicopters, flapping-wing aircraft, tilt-rotor aircraft, etc., and unmanned aerial vehicles are also a relatively special category of aircraft.

[0003] The wing motors of unmanned aerial vehicles are prone to overheating due to the continuous rotation of the propellers, and the internal power pack of the cabin itself and the circuit board will also continue to heat up. In order to avoid spontaneous combustion and explosion of the unmanned aerial vehicle during flight, it is necessary to control the heat dissipation operation of the aircraft power supply and motor source. Often, the radiator is added to increase the power load of the secondary power supply. The radiator itself also overheats during the heat dissipation process, resulting in poor heat dissipation effect. Utility Model Content

[0004] In view of the deficiencies in the prior art, the utility model provides a power heat dissipation air-cooled casing for an unmanned aerial vehicle to solve the problem that the wing motor of the unmanned aerial vehicle is prone to overheating due to the continuous rotation of the propeller, and the internal power supply group in the cabin itself The circuit board will also continue to increase heat. In order to avoid spontaneous combustion and explosion of the unmanned aerial vehicle during flight, it is necessary to control the heat dissipation operation of the aircraft power supply and motor source. The radiator is often superimposed to increase the power load of the secondary power supply. The radiator itself also overheats during the heat dissipation process, resulting in poor heat dissipation.

[0005] To achieve the above objectives, the utility model is implemented through the following technical solutions: a power heat dissipation air-cooling casing of an unmanned aerial vehicle, comprising a cyclone ring channel groove, a blade support, a wing rod, an outer shell, and an airflow channel shell groove, the cyclone ring channel groove is nested on the top of the blade support, the blade support and the wing rod are inserted together, four wing rods are provided and are respectively inserted on the left and right sides of the outer shell, the airflow channel shell groove is installed inside the outer shell, the cyclone ring channel groove is provided with a corrugated flow channel, an outer cyclone channel, a middle cyclone channel, and an inner cyclone channel, the inner cyclone channel is nested on the inner side of the middle cyclone channel, the outer cyclone channel is nested on the outer side of the middle cyclone channel, the corrugated flow channel is provided with four and are all inserted together around the center of the outer cyclone channel, the middle cyclone channel, and the inner cyclone channel, the airflow channel shell groove is provided with an intake pipe, a Tesla valve channel, and an exhaust pipe, the intake pipe is obliquely inserted on the top of the rear side of the Tesla valve channel, the exhaust pipe is inserted on the front side of the Tesla valve channel, and the Tesla valve channel is installed inside the outer shell.

[0006] Preferably, the Tesla valve channel is provided with a Tesla valve body and an air flow channel groove surface, the Tesla valve body is installed inside the air flow channel groove surface, and the Tesla valve body and the air flow channel groove surface are fixed together.

[0007] Preferably, the corrugated flow channel is in the form of a slot frame structure with concave surfaces at the top and bottom and a convex surface in the middle, which facilitates the external discharge of air from the air gap when the cyclone climbs and efficiently adapts to air cooling operations.

[0008] Preferably, the outer cyclone channel and the inner cyclone channel are both grooves that are connected in series with the corrugated flow channel slots for ventilation through the grooves in the middle cyclone channel, so as to facilitate the cyclone climbing operation under the aircraft blades by forming layer-by-layer air waves.

[0009] Preferably, the intake duct oblique frame intake and the exhaust duct horizontal exhaust are combined into an airflow duct for ventilation, which facilitates the transverse airflow to form a high-level airflow to the low-level airflow to carry out heat dissipation and air cooling operations on the aircraft power supply end.

[0010] Preferably, the Tesla valve body is a short-range double-corrugated valve port unidirectional Tesla valve structure, which facilitates the unidirectional Tesla valve to stabilize the air wave consistency and efficiently exhaust, balance the stratospheric airflow stability of the aircraft in the air and the auxiliary air cooling efficient air intake and exhaust operation effect.

[0011] The utility model provides a power supply heat dissipation air-cooling casing for an unmanned aerial vehicle, which has the following beneficial effects:

[0012] In the power heat dissipation air-cooled casing of an unmanned aerial vehicle, workers assemble a cyclone ring channel groove on the blade support and match it with the wing rod frame to protect it on both sides of the outer shell, and then connect the Tesla valve channel in series through the air intake pipe and the exhaust pipe of the air flow channel casing groove, so that the Tesla valve body and the air flow channel groove surface form an air-cooled ventilation flight heat dissipation effect at the top of the power supply end, and then connect the outer cyclone channel, the middle cyclone channel, and the inner cyclone channel in series through the corrugated flow channel to form an inner and outer concave cyclone and a middle cyclone with uneven transition and external discharge of the air-cooled heat dissipation operation effect, so as to avoid the installation of a radiator to increase the power supply power load and continuously increase overheating, improve the area division of the heat dissipation of the single blade motor and the power supply heat dissipation, and realize the flight air-cooled heat dissipation effect through targeted casing ventilation. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 This is a three-dimensional perspective structural diagram of a power supply heat dissipation air-cooling casing of an unmanned aerial vehicle according to the utility model;

[0014] Figure 2 This is a schematic diagram of the top view of the cyclone annular channel structure of the utility model;

[0015] Figure 3 This is a three-dimensional perspective structural diagram of the airflow channel shell groove of the utility model;

[0016] Figure 4 This is a schematic diagram of the Tesla valve channel structure from a top view of the present utility model.

[0017] In the figure: cyclone ring channel groove 1, blade support 2, wing rod 3, outer shell 4, airflow channel shell groove 5, corrugated flow channel 11, outer cyclone channel 12, middle cyclone channel 13, inner cyclone channel 14, air intake pipe 51, Tesla valve channel 52, exhaust pipe 53, Tesla valve body 521, airflow channel groove surface 522. DETAILED DESCRIPTION

[0018] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0019] See also Figure 1-Figure 4 The utility model provides a power heat dissipation air-cooling casing of an unmanned aerial vehicle, comprising a cyclone ring channel groove 1, a blade support 2, a wing rod 3, an outer shell 4, and an airflow channel shell groove 5. The cyclone ring channel groove 1 is nested on the top of the blade support 2, the blade support 2 and the wing rod 3 are inserted together, four wing rods 3 are provided and are respectively inserted on the left and right sides of the outer shell 4, and the airflow channel shell groove 5 is installed inside the outer shell 4.

[0020] Since the wing motors of unmanned aerial vehicles are prone to overheating due to the continuous rotation of the propellers, and the internal power pack of the cabin itself and the circuit board will also continue to heat up, in order to avoid spontaneous combustion and explosion of the unmanned aerial vehicle during flight, it is necessary to control the heat dissipation operation of the aircraft power supply and motor source. Often, the radiator is added to increase the power load of the secondary power supply. The radiator itself also overheats during the heat dissipation process, resulting in poor heat dissipation.

[0021] The cyclone annular channel groove 1 is provided with a corrugated flow channel 11, an outer cyclone channel 12, a middle cyclone channel 13, and an inner cyclone channel 14. The inner cyclone channel 14 is nested on the inner side of the middle cyclone channel 13, and the outer cyclone channel 12 is nested on the outer side of the middle cyclone channel 13. There are four corrugated flow channels 11 and they are all inserted together around the center of the outer cyclone channel 12, the middle cyclone channel 13, and the inner cyclone channel 14. The corrugated flow channel 11 is a slot frame structure with concave surfaces on the upper and lower sides and convex surfaces in the middle, which is convenient for the air gap to discharge and unload when the cyclone climbs and efficiently adapt to the wind cooling operation. The outer cyclone channel 12 and the inner cyclone channel 14 are both grooves that are connected in series with the corrugated flow channel 11 slots for ventilation through the grooves in the middle cyclone channel 13, which is convenient for the cyclone climbing operation under the blades of the aircraft to form layer-by-layer air waves.

[0022] The airflow channel shell groove 5 is provided with an air intake duct 51, a Tesla valve channel 52, and an exhaust duct 53. The air intake duct 51 is obliquely inserted on the top of the rear side of the Tesla valve channel 52, and the exhaust duct 53 is inserted on the front side of the Tesla valve channel 52. The Tesla valve channel 52 is installed inside the outer shell 4. The air intake duct 51 is inclined to intake and the exhaust duct 53 is horizontally exhausted to form an airflow duct for ventilation, which is convenient for the horizontal airflow to form a high-level airflow to the low-level airflow to undertake the heat dissipation and air cooling operation of the aircraft power supply end.

[0023] The Tesla valve channel 52 is provided with a Tesla valve body 521 and an airflow channel groove surface 522. The Tesla valve body 521 is installed inside the airflow channel groove surface 522. The Tesla valve body 521 and the airflow channel groove surface 522 are fixed together. The Tesla valve body 521 is a short-range double-corrugated channel valve port unidirectional Tesla valve structure, which is convenient for the unidirectional Tesla valve to have stable air wave consistency and efficient exhaust, balance the stratospheric airflow stability of the aircraft in the air and assist air cooling and efficient air intake and exhaust operation effects.

[0024] The staff assembled the cyclone ring channel groove 1 on the blade support 2 and matched it with the wing rod 3 to protect it on both sides of the outer shell 4, and then connected the Tesla valve channel 52 in series through the air intake duct 51 and the exhaust duct 53 of the air flow channel shell groove 5, so that the Tesla valve body 521 and the air flow channel groove surface 522 form a wind-cooled ventilation and flight heat dissipation effect at the top of the power supply end, and then connected the outer cyclone channel 12, the middle cyclone channel 13, and the inner cyclone channel 14 in series through the corrugated flow channel 11 to form an inner and outer concave cyclone and a cyclone with an undulating middle partition to transition to the outside of the wind-cooled heat dissipation operation effect, so as to avoid the installation of a radiator to increase the power supply power load and continuously increase overheating, and improve the area division of single blade motor heat dissipation and power supply heat dissipation to achieve flight wind-cooled heat dissipation effect.

[0025] The above description is only a specific implementation manner of the present application, but the protection scope of the present application is not limited thereto. Any technician familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed in the present application, which should be included in the protection scope of the present application.

Claims

1. A power heat dissipation air-cooling housing for an unmanned aerial vehicle, characterized in that: The invention comprises a cyclone ring channel groove (1), a blade support (2), a wing rod (3), an outer shell (4), and an airflow channel shell groove (5), wherein the cyclone ring channel groove (1) is nested on the top of the blade support (2), the blade support (2) and the wing rod (3) are inserted together, four wing rods (3) are provided and are respectively inserted on the left and right sides of the outer shell (4), and the airflow channel shell groove (5) is installed inside the outer shell (4); The cyclone annular channel groove (1) is provided with a corrugated flow channel (11), an outer cyclone channel (12), a middle cyclone channel (13), and an inner cyclone channel (14); the inner cyclone channel (14) is nested inside the middle cyclone channel (13), and the outer cyclone channel (12) is nested outside the middle cyclone channel (13); the corrugated flow channels (11) are provided with four and are all inserted and embedded together around the center of the outer cyclone channel (12), the middle cyclone channel (13), and the inner cyclone channel (14); The air flow channel housing groove (5) is provided with an air intake pipe (51), a Tesla valve channel (52), and an exhaust pipe (53). The air intake pipe (51) is obliquely inserted on the top of the rear side of the Tesla valve channel (52), and the exhaust pipe (53) is inserted on the front side of the Tesla valve channel (52). The Tesla valve channel (52) is installed inside the outer shell (4).

2. The power heat dissipation air-cooling housing of an unmanned aerial vehicle according to claim 1, characterized in that: The Tesla valve channel (52) is provided with a Tesla valve body (521) and an air flow channel groove surface (522). The Tesla valve body (521) is installed inside the air flow channel groove surface (522). The Tesla valve body (521) and the air flow channel groove surface (522) are fixed together.

3. The power heat dissipation air-cooling housing of an unmanned aerial vehicle according to claim 1, characterized in that: The corrugated flow channel (11) is in the form of a slot frame structure with concave surfaces at the top and bottom and a convex surface in the middle.

4. The power heat dissipation air-cooling housing of an unmanned aerial vehicle according to claim 1, characterized in that: The outer cyclone channel (12) and the inner cyclone channel (14) are both grooves that are connected in series with the grooves of the corrugated flow channel (11) through the grooves in the middle cyclone channel (13) for ventilation.

5. The power heat dissipation air-cooling housing of an unmanned aerial vehicle according to claim 1, characterized in that: The inlet duct (51) is inclined for inlet and the exhaust duct (53) is horizontal for exhaust, which is combined into an airflow duct for ventilation.

6. The power heat dissipation air-cooling housing of an unmanned aerial vehicle according to claim 2, characterized in that: The Tesla valve body (521) is a Tesla valve structure with a short-range double-corrugated valve port and a one-way conduction.

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