Cooling structure for plasma unmanned aerial vehicle propeller

Abstract

The invention provides a cooling structure for a plasma unmanned aerial vehicle propeller, and relates to the technical field of plasma unmanned aerial vehicles. According to the cooling structure for the plasma unmanned aerial vehicle propeller, by designing the mounting plate, the propeller supporting frame, the heat conduction pieces, the supporting base, the supporting column and the fan blades, when an unmanned aerial vehicle flies, heat generated by the propeller of the unmanned aerial vehicle can be upwards transmitted to the supporting column and the fan blades through the heat conduction pieces; furthermore, the outer surface of the fan blade is coated with a high-emissivity coating to radiate heat outwards, the heat is dissipated outwards, the heat loss process is accelerated through the rotation process of the fan blade, the heat dissipation and cooling effects are improved, and the service life of the fan blade is prolonged. And the fluid cooling system with the internal cooling channel can further transfer heat of the plasma generating device to fluid, and is combined with radiation cooling, so that a flexible, efficient and relatively reliable heat dissipation solution is provided for the plasma unmanned aerial vehicle propeller, the propeller is ensured to work within a safe temperature range, and the service life of the propeller is prolonged. The efficiency and service life are improved.

Description

Technical Field

[0001] This invention relates to the field of plasma drone technology, specifically a cooling structure for a plasma drone propulsion system. Background Technology

[0002] Plasma propulsion is an electric propulsion technology that uses an electromagnetic field to ionize propellant gas, generating plasma and accelerating charged particles to create thrust. The flight principle of plasma drones utilizes an asymmetric high-voltage electrode array to ionize air through corona discharge, and then accelerates the ions through a high-voltage electric field. These ions exchange momentum with air molecules, generating an ion wind that produces thrust for flight or lift for vertical takeoff and landing. Compared to traditional drones, plasma-propelled drones require no additional rotating parts and have a simple thrust structure. They generate propulsion directly by consuming electrical energy, providing power for flight. Plasma drones offer advantages such as lower mechanical fatigue, lower flight noise, and higher energy efficiency. As a novel concept aircraft, the ultra-quiet nature of plasma drones means they will be suitable for future urban inspections, freight transportation, and other tasks, reducing urban noise. Their lack of moving mechanical parts suggests they are likely to replace flight control surfaces in the future, further simplifying aircraft structure, extending service life, and reducing maintenance costs.

[0003] Plasma drone propulsion systems (typically referring to electric propulsion systems such as Hall thrusters and ion thrusters) generate significant heat during operation, primarily from ionized gas and electrode / grid losses. Ionizing neutral gas into plasma requires energy, a process that itself generates heat. Furthermore, collisions between electrons and ions and electrodes or grids result in energy loss, also converted into heat. To ensure the thruster operates within a safe temperature range and to improve efficiency and lifespan, an effective cooling structure must be designed.

[0004] To address this, we have developed a new cooling structure for plasma drone propulsion. Summary of the Invention

[0005] (1) Technical problems solved

[0006] To address the shortcomings of existing technologies, this invention provides a cooling structure for plasma drone propulsion systems. This structure solves the problem of existing plasma drone propulsion systems (typically referring to electric propulsion systems such as Hall thrusters and ion thrusters) generating significant heat during operation. This heat primarily originates from ionized gas and electrode / grid losses. Ionizing neutral gas into plasma requires energy, a process that itself generates heat. Furthermore, collisions between electrons and ions and electrodes or grids result in energy loss, also converted into heat. To ensure the propulsion system operates within a safe temperature range and improve efficiency and lifespan, an effective cooling structure must be designed.

[0007] (2) Technical solution

[0008] To achieve the above objectives, the present invention provides a cooling structure for a plasma drone propulsion system, comprising: a shell, the shell being fixedly connected to the upper surface of the drone body, and an energy storage battery and a high-voltage power converter being fixedly installed inside the shell.

[0009] Mounting plate, fixedly connected to one end of the wing, with a thruster support frame fixedly connected to the upper surface of the mounting plate, a plasma generator installed inside the thruster support frame, and heat-conducting plates symmetrically fixedly connected to the top of the thruster support frame. A support base is fixedly connected to the opposite side of the two heat-conducting plates, and a support column is rotatably connected to the upper surface of the support base. Fan blades are symmetrically fixedly connected to the top of the support column.

[0010] Pipelines are laid and fixedly connected to the upper surface of the wing. The pipelines contain wires and liquid supply pipes.

[0011] Preferably, the thruster support frame includes a frame body, which is fixedly connected to the upper surface of the mounting plate. The frame body has a hollow circular annular structure, and multiple microchannels are fixedly connected to the outer surface of the frame body. Corresponding conduits are fixedly connected to each other in sequence among the multiple microchannels.

[0012] Preferably, the heat-conducting sheet includes a main rod, which is fixedly connected to the upper surface of the thruster support frame. One end of the main rod is fixedly connected to a connecting rod, and one end of the connecting rod is fixedly connected to the outer surface of the support base. Thermal grease is applied between the main rod and the thruster support frame.

[0013] Preferably, the plasma generating device includes a first support ring and a second support ring fixedly connected to the inner wall of the frame, the inner wall of the first support ring being fixedly connected to a plurality of first connecting rods, the inner wall of the second support ring being fixedly connected to a plurality of second connecting rods, the upper surface of the plurality of first connecting rods being fixedly connected to an emitting electrode, and the upper surface of the plurality of second connecting rods being fixedly connected to a collecting electrode.

[0014] Preferably, each of the opposite sides of the plurality of first links and the opposite sides of the plurality of second links is fixedly connected to a support block.

[0015] Preferably, the emitting electrode is connected to the positive terminal of the energy storage battery via a wire, and the collecting electrode is connected to the negative terminal of the energy storage battery.

[0016] Preferably, the outer surfaces of the thruster support frame, heat-conducting plate, support base, support column and fan blade are all coated with a high emissivity coating.

[0017] Preferably, a cover is fixedly connected to the top of the outer shell, and mounting holes are provided around the upper surface of the cover.

[0018] Beneficial effects

[0019] This invention provides a cooling structure for a plasma drone propulsion system. It offers the following advantages:

[0020] 1. The cooling structure for plasma drone thrusters, through the design of mounting plates, thruster support frames, heat-conducting plates, support seats, support columns, and fan blades, allows the heat generated by the thrusters during drone flight to be transferred upwards to the support columns and fan blades via the heat-conducting plates. The heat is then radiated outwards through the high emissivity coating on the outer surface, dissipating heat. Furthermore, the rotation of the fan blades further accelerates this heat loss process, improving the heat dissipation and cooling effect.

[0021] 2. The cooling structure for plasma drone propulsion, through the design of the frame, conduits, microchannels, and pipeline laying, and the fluid cooling system with internal cooling channels, can further transfer the heat of the plasma generator to the fluid. Fluid cooling can quickly respond to peak heat loads, effectively control local high temperatures, and, combined with radiation cooling, provide a flexible, efficient, and relatively reliable heat dissipation solution for plasma drone propulsion. It is especially suitable for scenarios with slightly higher power or stricter temperature control requirements, ensuring that the propulsion operates within a safe temperature range, improving efficiency and lifespan. Attached Figure Description

[0022] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0023] Figure 2 This is a first-view structural schematic diagram of the propeller support frame of the present invention;

[0024] Figure 3 This is a second-view structural schematic diagram of the propeller support frame of the present invention;

[0025] Figure 4 This is a schematic diagram of the plasma generating device of the present invention;

[0026] Figure 5 This is a schematic diagram of the connection structure between the heat-conducting sheet and the support base of the present invention;

[0027] Figure 6 This is a perspective view of the outer casing of the present invention.

[0028] The components are as follows: 1. Fuselage; 2. Outer shell; 3. Shell cover; 4. Wing; 5. Mounting plate; 6. Laying pipeline; 7. Energy storage battery; 8. High-voltage power converter; 9. Thruster support frame; 901. Frame; 902. Microchannel; 903. Conduit; 10. Heat-conducting plate; 1001. Main rod; 1002. Connecting rod; 1003. Thermal grease; 11. Support base; 12. Support column; 13. Fan blade; 14. First support ring; 15. Second support ring; 16. First connecting rod; 17. Second connecting rod; 18. Emitter electrode; 19. Collector electrode; 20. Support block. Detailed Implementation

[0029] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0030] Examples, such as Figure 1 - Figure 6 As shown, this embodiment of the invention provides a cooling structure for a plasma drone propulsion system, comprising: a shell 2, which is fixedly connected to the upper surface of the fuselage 1, and an energy storage battery 7 and a high-voltage power converter 8 are fixedly installed inside the shell 2.

[0031] Mounting plate 5 is fixedly connected to one end of wing 4. A thruster support frame 9 is fixedly connected to the upper surface of mounting plate 5. A plasma generator is installed inside the thruster support frame 9. Heat conduction plates 10 are symmetrically fixedly connected to the top of the thruster support frame 9. A support base 11 is fixedly connected to the opposite side of the two heat conduction plates 10. A support column 12 is rotatably connected to the upper surface of the support base 11. Fan blades 13 are symmetrically fixedly connected to the top of the support column 12. As the UAV moves up and down, the wind can drive the support column 12 and the fan blades to rotate, further accelerating the outward dissipation of heat.

[0032] Pipeline 6 is laid and fixedly connected to the upper surface of wing 4. Inside pipeline 6, wires and liquid supply pipes are installed.

[0033] The thruster support frame 9 includes a frame 901, which is fixedly connected to the upper surface of the mounting plate 5. The frame 901 has a hollow circular structure. Multiple microchannels 902 are fixedly connected to the outer surface of the frame 901. Corresponding conduits 903 are fixedly connected to the multiple microchannels 902 in sequence. The conduits 903 connect the multiple microchannels 902. The interior of the microchannels 902 is filled with cooling fluid. One side of the outer surface of the lowest microchannel 902 is connected to the liquid supply pipe inside the laying pipeline 6. One end of the liquid supply pipe is connected to the interior of the outer shell 2. The interior of the outer shell 2 is also equipped with a closed loop and a corresponding radiator, thereby realizing the circulation process of the cooling fluid.

[0034] Accordingly, a small, lightweight, and high-efficiency pump should be installed in the entire circulation loop to drive the coolant to circulate in the closed loop. Lightweight, high-temperature resistant, and corrosion-resistant flexible or rigid pipes should be used to connect the propeller, radiator, and pump. Valves should also be included for flow regulation or system isolation, adjusting the flow rate by controlling the pump speed or valve opening to achieve closed-loop temperature control.

[0035] The heat-conducting plate 10 includes a main rod 1001, which is fixedly connected to the upper surface of the thruster support frame 9. One end of the main rod 1001 is fixedly connected to a connecting rod 1002, and one end of the connecting rod 1002 is fixedly connected to the outer surface of the support base 11. Thermal grease 1003 is applied between the main rod 1001 and the thruster support frame 9. The thermal grease 1003 can transfer the heat of the thruster support frame 9 upwards. It fills the microscopic gaps between the main rod 1001 and the thruster support frame 9, improving the heat conduction efficiency and thus improving the heat dissipation effect of the entire heat-conducting plate.

[0036] The plasma generating device includes a first support ring 14 and a second support ring 15 fixedly connected to the inner wall of the frame 901. The inner wall of the first support ring 14 is fixedly connected to a plurality of first connecting rods 16, and the inner wall of the second support ring 15 is fixedly connected to a plurality of second connecting rods 17. Correspondingly, a support block 20 is fixedly connected to each of the opposite sides of the plurality of first connecting rods 16 and the opposite sides of the plurality of second connecting rods 17. An emitting electrode 18 is fixedly connected to the upper surface of the plurality of first connecting rods 16, and a collecting electrode 19 is fixedly connected to the upper surface of the plurality of second connecting rods 17.

[0037] The upper emitting electrode 18 and the lower collecting electrode 19 are staggered. This staggered arrangement can effectively improve the aerodynamic characteristics of the ion wind and reduce the viscous resistance acting on the collecting electrode 19.

[0038] Furthermore, the emitting electrode 18 is connected to the positive terminal of the energy storage battery 7 via a wire, and the collecting electrode 19 is connected to the negative terminal of the energy storage battery 7. Since the emitting electrode 18 is positively charged and the collecting electrode 19 is negatively charged, corona discharge occurs between the electrodes, generating an ion wind pointing from the emitting electrode 18 to the collecting electrode 19, thereby generating thrust in the opposite direction, thus providing flight power for the UAV.

[0039] The fuselage 1 is made of fiberglass material through mold lamination. The mounting structures of the transmitting electrode 18 and the collecting electrode 19—the first support ring 14, the second support ring 15, the first connecting rod 16 and the second connecting rod 17—are all made of balsa wood profiles. This effectively reduces the structural weight while meeting the requirements of structural rigidity and strength, thus achieving a lightweight design for the UAV.

[0040] Furthermore, the outer surfaces of the thruster support frame 9, heat-conducting plate 10, support base 11, support column 12, and fan blade 13 are all coated with a high emissivity coating. This ensures that the thruster's outer shell material combines structural strength, high temperature resistance, and a certain degree of thermal conductivity, achieving a radiative heat dissipation effect—the heat generated inside the thruster is conducted to a larger heat dissipation area through the high thermal conductivity material, and then dissipated through radiation or other means.

[0041] The top of the outer shell 2 is fixedly connected to the shell cover 3. The upper surface of the shell cover 3 is provided with mounting holes around the perimeter. The interior of the mounting holes can be used to install bolts, thereby achieving the fixation between the shell cover 3 and the outer shell 2.

[0042] A cooling structure for a plasma drone thruster is used in such a way that the emitting electrode 18 inside the thruster support frame 9 and the collecting electrode 19 below it are staggered. This staggered arrangement can effectively improve the aerodynamic characteristics of the ion wind and reduce the viscous drag acting on the collecting electrode 19. The emitting electrode 18 is connected to positive electricity and the collecting electrode 19 is connected to negative electricity. Corona discharge occurs between the electrodes, generating an ion wind from the emitting electrode 18 to the collecting electrode 19, thereby generating thrust in the opposite direction, thus providing flight power for the drone.

[0043] When the drone is in flight, the heat generated by its thrusters can be transferred to the thruster support frame 9 through the first support ring 14 and the second support ring 15. Then, the heat of the thruster support frame 9 is transferred upward through the thermal grease 1003, which fills the micro gap between the main rod 1001 and the thruster support frame 9, improving the heat conduction efficiency and thus improving the heat dissipation effect of the entire heat-conducting plate 10. The heat-conducting plate 10 transfers the heat upward to the support column 12 and the fan blade 13, and then radiates heat outward through the high emissivity coating on its outer surface, dissipating the heat outward.

[0044] Furthermore, as the drone moves up and down, the wind can drive the support column 12 and the fan blade 13 to rotate, further accelerating the outward dissipation of heat. The rotation of the fan blade 13 itself further accelerates this heat loss process, improving the heat dissipation and cooling effect.

[0045] Meanwhile, the fluid cooling system with internal cooling channels can further transfer the heat of the plasma generator to the fluid. Fluid cooling can quickly respond to peak heat loads, effectively control local high temperatures, and, combined with radiation cooling, provide a flexible, efficient and relatively reliable heat dissipation solution for plasma drone thrusters. It is especially suitable for scenarios with slightly higher power or stricter temperature control requirements, ensuring that the thruster operates within a safe temperature range, improving efficiency and lifespan.

[0046] While embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions, and variations may be made to these embodiments without departing from the principles and spirit of the invention, and that the scope of the invention is defined by the appended claims and their equivalents.

Claims

1. A cooling structure for a plasma unmanned aerial vehicle (UAV) propulsion system, characterized in that, include: The outer shell (2) is fixedly connected to the upper surface of the body (1), and the energy storage battery (7) and the high voltage power converter (8) are fixedly installed inside the outer shell (2); Mounting plate (5), which is fixedly connected to one end of wing (4), and a thruster support frame (9) is fixedly connected to the upper surface of the mounting plate (5). A plasma generator is installed inside the thruster support frame (9), and heat-conducting plates (10) are symmetrically fixedly connected to the top of the thruster support frame (9). A support base (11) is fixedly connected to the opposite side of the two heat-conducting plates (10). A support column (12) is rotatably connected to the upper surface of the support base (11), and fan blades (13) are symmetrically fixedly connected to the top of the support column (12). A pipeline (6) is laid, which is fixedly connected to the upper surface of the wing (4). The pipeline (6) contains wires and a liquid supply pipe.

2. The cooling structure for a plasma drone propulsion system according to claim 1, characterized in that: The thruster support frame (9) includes a frame (901), which is fixedly connected to the upper surface of the mounting plate (5). The frame (901) has a hollow circular structure. Multiple microchannels (902) are fixedly connected to the outer surface of the frame (901), and corresponding conduits (903) are fixedly connected to each other in sequence.

3. The cooling structure for a plasma drone propulsion system according to claim 1, characterized in that: The heat-conducting plate (10) includes a main rod (1001), which is fixedly connected to the upper surface of the thruster support frame (9). One end of the main rod (1001) is fixedly connected to a connecting rod (1002), and one end of the connecting rod (1002) is fixedly connected to the outer surface of the support base (11). Thermal grease (1003) is applied between the main rod (1001) and the thruster support frame (9).

4. A cooling structure for a plasma drone propulsion system according to claim 1, characterized in that: The plasma generating device includes a first support ring (14) and a second support ring (15) fixedly connected to the inner wall of the frame (901). The inner wall of the first support ring (14) is fixedly connected to a plurality of first connecting rods (16), and the inner wall of the second support ring (15) is fixedly connected to a plurality of second connecting rods (17). The upper surface of the plurality of first connecting rods (16) is fixedly connected to an emission electrode (18), and the upper surface of the plurality of second connecting rods (17) is fixedly connected to a collection electrode (19).

5. A cooling structure for a plasma drone propulsion system according to claim 4, characterized in that: Each of the opposite sides of the plurality of first links (16) and the opposite sides of the plurality of second links (17) is fixedly connected to a support block (20).

6. A cooling structure for a plasma drone propulsion system according to claim 4, characterized in that: The emitting electrode (18) is connected to the positive terminal of the energy storage battery (7) via a wire, and the collecting electrode (19) is connected to the negative terminal of the energy storage battery (7).

7. A cooling structure for a plasma drone propulsion system according to claim 1, characterized in that: The outer surfaces of the thruster support frame (9), heat-conducting plate (10), support base (11), support column (12) and fan blade (13) are all coated with a high emissivity coating.

8. A cooling structure for a plasma drone propulsion system according to claim 1, characterized in that: The top of the outer shell (2) is fixedly connected to a cover (3), and mounting holes are provided around the upper surface of the cover (3).

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