A vortex strong heat exchange system with embedded laser cells in a wing and a thermal management method

Abstract

The application provides a vortex strong heat exchange system with a laser cell embedded in a wing, comprising: a wing main body, an airflow channel extending along a wingspan direction being arranged in the wing main body; the airflow channel comprises a smooth connection air inlet section, a flat heat exchange section and an air outlet section; a laser cell is embedded in the wing main body, an energy conversion unit of the laser cell is used for receiving laser irradiation to generate electricity, a heat dissipation end of the laser cell is exposed to the flat heat exchange section, and an outer surface of the heat dissipation end of the laser cell is flush with a surface of the flat heat exchange section; and a vortex heat dissipation assembly is arranged in the airflow channel, the vortex heat dissipation assembly is fixedly arranged on the heat dissipation end of the laser cell, and the vortex heat dissipation assembly comprises at least one group of heat dissipation fins which are in thermal connection with the heat dissipation end of the laser cell. The laser cell is embedded in the wing, and the vortex heat dissipation assembly actively disturbs the laminar flow of the heat dissipation end of the laser cell into vortex flow, so that the heat exchange efficiency is improved.

Description

Technical Field

[0001] This invention belongs to the field of fixed-wing UAV endurance photoelectric conversion technology, and in particular relates to an eddy current heat exchange system and thermal management method for a laser battery embedded in the wing. Background Technology

[0002] Compared to solar power generation, laser power generation systems offer advantages such as high energy conversion efficiency, strong directionality, concentrated energy, high controllability, wide application scenarios, low energy loss, and high stability. At the same power density, laser power generation significantly improves energy conversion efficiency and maximum output power compared to sunlight irradiation. Furthermore, the irradiation time and angle of the laser can be artificially controlled, providing uninterrupted power to the target, thus solving problems such as increased weight, reduced payload, and insufficient flight time caused by excessive energy storage devices in aircraft. However, high-intensity laser irradiation generates waste heat in optoelectronic devices. This heat not only hinders the efficient utilization of incident photons but may also affect device performance due to increased operating temperature. Current technologies typically utilize airflow during flight to cool the battery, but airflow alone cannot achieve rapid heat dissipation for the laser battery. Moreover, when the temperature difference between the hot and cold ends of the thermoelectric device is small, the amount of electricity generated by the thermoelectric device is limited. Additionally, direct contact between the cold end of the thermoelectric device and the airflow increases wind resistance, affecting aircraft flight stability to some extent. Summary of the Invention

[0003] In view of this, the present invention aims to overcome the defects in the prior art and proposes an eddy current heat transfer system and method for embedding laser batteries in the wing.

[0004] To achieve the above objectives, the technical solution created by this invention is implemented as follows: A vortex heat transfer system with an embedded laser battery in the wing, comprising: The wing body has an internal airflow channel extending along the wingspan direction; the airflow channel includes a smoothly connected air intake section, a straight heat exchange section, and an air outlet section; A laser battery is embedded in the wing body. The energy conversion unit of the laser battery is used to receive laser irradiation to generate electricity. The heat dissipation end of the laser battery is exposed in the straight heat exchange section, and the outer surface of the heat dissipation end of the laser battery is flush with the surface of the straight heat exchange section. The vortex heat dissipation component is located in the airflow channel and is fixedly installed at the heat dissipation end of the laser battery. The vortex heat dissipation component includes at least one set of heat dissipation fins thermally connected to the heat dissipation end of the laser battery. Each set includes two heat dissipation fins. The two heat dissipation fins in the same set are arranged symmetrically in a figure-eight shape, and the blades of the two heat dissipation fins in the same set are opposite each other, so as to disturb the airflow flowing through the heat dissipation end, so as to change it from laminar flow to vortex flow, thereby improving the heat exchange efficiency.

[0005] Furthermore, the figure-eight structure formed by the two heat dissipation fins in the same group has its small opening facing the side of the air intake section.

[0006] Furthermore, the profiles of both the inlet section and the outlet section are smooth curves obtained based on the original airfoil profile.

[0007] Furthermore, the air profiles of the inlet and outlet sections are determined in the following way: based on the original airfoil profile, computational fluid dynamics is used to perform parametric modeling and iterative optimization of the air profile with the optimization objectives of smooth airflow transition and minimizing flow resistance, so as to obtain the final air profile.

[0008] Furthermore, the wing body is divided into an upper main wing and a lower secondary wing by the airflow channel, and the laser battery is disposed through the lower secondary wing, with its energy conversion unit exposed on the lower surface of the lower secondary wing.

[0009] Furthermore, the lower surface of the energy conversion unit is conformally configured with the lower surface of the secondary wing, forming a smoothly transitioned aerodynamic shape.

[0010] Furthermore, the heat dissipation fins are airfoil-shaped fins.

[0011] Furthermore, the laser battery uses a pure thermoelectric module. The hot end of the pure thermoelectric module receives the incident laser, while the cold end is exposed in a straight heat exchange section. The eddy current heat dissipation component is thermally connected to the cold end of the pure thermoelectric module. Alternatively, the laser battery uses a pure photovoltaic module, with the laser incident on the conductive glass end of the pure photovoltaic module, and the electrode exposed in a straight heat exchange section, with the eddy current heat dissipation component thermally connected to the electrode. Alternatively, the laser cell may employ a photovoltaic-thermoelectric tandem device, which includes a photovoltaic part and a thermoelectric part. The photovoltaic part is used to receive laser irradiation to generate electricity, and the hot end of the thermoelectric part is connected to the electrode of the photovoltaic part to receive the waste heat generated during the operation of the laser cell. The waste heat is directly absorbed by the thermoelectric part for thermoelectric conversion, and the cold end of the thermoelectric part is exposed in a flat heat exchange section.

[0012] A thermal management method for an eddy current heat transfer system with an embedded laser battery in an airfoil includes the following steps: Airflow channels are installed inside the main body of the wing, extending along the wingspan direction; The laser is continuously irradiated onto the laser battery on the wing of the UAV by ground or air laser emitting device, so that the energy conversion unit of the laser battery generates electrical energy, and the heat dissipation end of the laser battery is exposed to the airflow channel inside the wing; The air intake section at the leading edge of the wing guides the relative airflow generated during the flight of the UAV into the airflow channel, so that the airflow flows through the heat dissipation end of the laser battery; By actively disturbing the airflow passing through the heat dissipation end using the vortex heat dissipation component installed in the airflow channel, the laminar flow is transformed into vortex flow. The temperature of the heat dissipation end is reduced through forced convection heat transfer, thereby achieving heat dissipation for the energy conversion unit.

[0013] Furthermore, the vortex heat dissipation assembly includes at least one set of heat dissipation fins, each heat dissipation fin including two wing-shaped fins, the two wing-shaped fins in the same set are arranged symmetrically in a figure-eight shape, and the blades of the two wing-shaped fins in the same set are opposite each other.

[0014] Compared with existing technologies, the present invention has the following advantages: This invention embeds a laser battery inside the wing, providing a flow channel foundation for thermal management while maintaining the original airfoil's aerodynamic performance. The vortex cooling component actively transforms the laminar flow passing through the laser battery's heat dissipation end into vortices, significantly enhancing heat transfer efficiency and substantially reducing the temperature at the heat dissipation end. This increases the temperature difference between the heat dissipation end of the thermoelectric conversion and the heat-generating part of the energy conversion unit, improving waste heat power generation and effectively cooling the laser battery. The expansion shape of the airflow channel increases the pressure during gas flow, allowing the outflowing air to have higher pressure. This provides a higher-pressure airflow to the lower surface of the wing, increasing lift. Furthermore, the reaction force on the upper surface of the channel, where the airflow is deflected, also indirectly increases lift. Attached Figure Description

[0015] The accompanying drawings, which form part of this invention, are used to provide a further understanding of the invention. The illustrative embodiments and descriptions of the invention are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings: Figure 1 A schematic diagram of the wing with an embedded laser battery in this invention; Figure 2 for Figure 1 A schematic diagram showing the location of the airflow channel in the middle; Figure 3 This is a top view of the laser battery in the installed state during the invention process; Figure 4 This is a perspective view of the laser battery in the installed state during the invention process; Figure 5 A top view of the eddy current heat dissipation component in this invention; Figure 6 A top view of the airfoil-shaped fin portion created for this invention; Figure 7 This is a schematic diagram of a laser battery using a photovoltaic-thermoelectric stacked device in this invention. Figure 8 This is a schematic diagram of the laser battery in this invention using a pure photovoltaic module; Figure 9This is a schematic diagram of a laser battery using a pure thermoelectric module in the present invention. Figure 10 A cloud map showing the heat dissipation coefficient of a laser cell surface in ANSYS simulation; Figure 11 A cloud map showing the cross-sectional temperature of a laser cell simulated using ANSYS. Figure 12 This is a static pressure cloud diagram of the wing in the airflow channel area simulated by ANSYS. Detailed Implementation

[0016] It should be noted that, unless otherwise specified, the embodiments and features described in the present invention can be combined with each other.

[0017] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on this invention. Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, features defined with "first," "second," etc., may explicitly or implicitly include one or more of that feature. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0018] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art will understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0019] The invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0020] A vortex-driven high-intensity heat transfer system with laser batteries embedded in the wing, such as Figures 1 to 8 As shown, it includes: The wing body 1 has an airflow channel 2 extending along the wingspan inside it; the airflow channel includes a smoothly connected air intake section 3, a straight heat exchange section 4, and an air outlet section 5. A laser battery 6 is embedded in the wing body. The energy conversion unit of the laser battery is used to receive laser irradiation to generate electricity. The heat dissipation end of the laser battery is exposed in the straight heat exchange section, and the outer surface of the heat dissipation end of the laser battery is flush with the surface of the straight heat exchange section. The vortex heat dissipation component 7 is located in the airflow channel and is fixedly installed at the heat dissipation end of the laser battery. The vortex heat dissipation component includes at least one set of heat dissipation fins 8 that are thermally connected to the heat dissipation end of the laser battery. Each set includes two heat dissipation fins. The two heat dissipation fins in the same set are arranged symmetrically in a figure-eight shape, and the blades of the two heat dissipation fins in the same set are opposite each other, so as to disturb the airflow flowing through the heat dissipation end and change it from laminar flow to vortex flow to improve heat exchange efficiency.

[0021] For example, such as Figure 9 As shown, the laser battery of the present invention can use a pure thermoelectric module, which directly serves as an energy conversion unit. The pure thermoelectric module is integrated inside the wing. The hot end of the pure thermoelectric module receives the incident laser, while the cold end (as the heat dissipation end) is exposed in the straight heat exchange section, so that the vortex heat dissipation component is thermally connected to it to collect waste heat. The heat dissipation end of the pure electric module works in conjunction with the optimized airflow channel and the vortex heat dissipation component to achieve efficient thermal management and aerodynamic lift.

[0022] For example, such as Figure 8 As shown, the laser battery of the present invention can be a pure photovoltaic module, which directly serves as an energy conversion unit. The pure photovoltaic module is integrated into the wing. The laser is incident on the conductive glass end of the pure photovoltaic module, and the electrode end (as a heat dissipation end) is exposed in the straight heat exchange section. The vortex heat dissipation component is thermally connected to the electrode end to collect waste heat. Through the optimized airflow channel and the vortex heat dissipation component working together, efficient thermal management and aerodynamic lift are achieved.

[0023] For example, such as Figure 7 As shown, the laser battery of the present invention can employ a photovoltaic-thermoelectric tandem device, which includes a photovoltaic part 9 and a thermoelectric part 10. The photovoltaic part in the photovoltaic-thermoelectric tandem device serves as an energy conversion unit. The photovoltaic-thermoelectric tandem device is integrated inside the wing. The photovoltaic part is used to receive laser irradiation to generate electricity. The hot end of the thermoelectric part is connected to the electrode of the photovoltaic part to receive the waste heat generated during the operation of the laser battery. The waste heat is directly absorbed by the thermoelectric part for thermoelectric conversion. This structural layout makes full use of the internal space of the wing and realizes in-situ recovery and utilization of waste heat. The cold end of the thermoelectric part (as the heat dissipation end) is exposed in a straight heat exchange section, so that the vortex heat dissipation component is thermally connected to the cold end of the thermoelectric part to collect waste heat. The heat dissipation end of the photovoltaic-thermoelectric tandem device works in conjunction with the optimized airflow channel and the vortex heat dissipation component to achieve efficient thermal management and aerodynamic lift.

[0024] The airflow channels within the wing body, particularly the smooth connection design of the inlet section, the straight heat exchange section, and the outlet section, utilize the relative airflow during UAV flight to smoothly guide external air into the heat exchange area. This avoids flow losses caused by airflow separation and provides stable airflow conditions for subsequent heat exchange. The laser battery is embedded within the wing body, and its energy conversion unit receives laser irradiation to generate waste heat. The vortex cooling assembly is positioned close to the heat dissipation end of the laser battery, which is exposed in the straight heat exchange section, with its outer surface flush with the channel surface. This "embedded" arrangement ensures the streamlined integrity of the airflow channels, avoids interference from abrupt structures, and allows the heat dissipation end to directly contact the cooling airflow, creating conditions for enhanced heat exchange.

[0025] The vortex heat dissipation component is fixedly mounted at the heat dissipation end. Its symmetrically arranged, figure-eight-shaped airfoil fins with opposing blades actively disturb the flow field as airflow passes through, transforming the original laminar flow state into a vortex state. By enhancing the mixing effect of fluid micro-particles, it significantly improves the convective heat transfer coefficient of the heat dissipation end surface. This vortex-enhanced heat transfer mechanism effectively reduces the temperature of the laser battery's heat dissipation end. According to the Seebeck effect, the increased temperature difference between the heat dissipation end and the heat-generating part of the energy conversion unit directly improves the thermoelectric conversion efficiency. On the other hand, through forced convection heat transfer, it promptly removes the waste heat generated by the energy conversion unit, preventing the laser battery from experiencing efficiency degradation due to excessive temperature, thus achieving a dual heat dissipation effect.

[0026] For example, the heat dissipation fins are all airfoil fins. The airfoil fins are arranged symmetrically with "blade-face" configuration. While generating vortices, they can also form a local low-pressure area on the lower surface of the wing, generating additional lift effect and compensating for the aerodynamic losses caused by the slotting to a certain extent.

[0027] The figure-eight structure formed by the two heat dissipation fins in the same group, with the smaller opening facing the intake section, provides a gradually expanding flow channel for the cold airflow as it enters the heat exchange area. When the laminar airflow from the intake section comes into contact with this structure, its flow cross-section is gradually expanded, achieving deceleration and pressurization. Furthermore, this gradually expanding flow channel smoothly guides the airflow to the backs (i.e., the convex arc surfaces) of the two airfoil fins. Due to the streamlined characteristics of the airfoil backs, the airflow can flow close to the surface, but as it flows through the latter half of the fins, a controllable, slight flow separation occurs due to the boundary layer effect and pressure gradient. The opposing arrangement of the blades causes the airflow separated from the two fins to converge and shear near the central axis of the figure-eight structure, thereby inducing vortices.

[0028] It should be noted that the small opening faces the incoming flow, ensuring that the airflow enters the airflow channel without impact and with low loss, and is effectively organized to generate vortices. These vortices effectively enhance the mixing and disturbance of fluid particles on the surface of the laser battery's heat dissipation end, completely breaking the heat insulation effect of the laminar boundary layer. This allows the heat at the heat dissipation end to be rapidly carried away by the high-speed airflow, significantly improving the convective heat transfer coefficient. Since this efficient heat dissipation process directly increases the temperature difference between the heat-generating part of the laser battery and its heat dissipation end, according to the Seebeck effect, it can effectively improve the thermoelectric conversion efficiency and output power. Simultaneously, the generated vortex core region forms a local low-pressure area. This figure-eight structure ensures that this low-pressure area is stably attached to the lower surface of the wing (i.e., the upper wall of the straight heat exchange section). According to Bernoulli's principle, this local low pressure will generate an upward suction force on the wing, i.e., additional lift.

[0029] The air profiles ("profiles" specifically refer to the contour curves that form the walls of the air intake / exhaust ducts) of both the inlet and exhaust duct sections are smooth curves obtained based on the original airfoil profile ("original airfoil profile" refers to the inherent, aerodynamically optimized cross-sectional shape of the UAV wing itself before any slotting or modification). Designing the air profiles based on the original airfoil profile ensures that the slotted wing maintains its original lift-drag characteristics in terms of macroscopic aerodynamic shape, avoiding lift loss and drag surges caused by slotting. The smooth curve transitions between the inlet and exhaust duct sections improve the smoothness of external airflow entering and exiting the airflow channels, effectively suppressing unsteady flow phenomena such as flow separation and vortex shedding, minimizing flow losses. Simultaneously, the smooth profile transitions also reduce flow resistance within the airflow channels, reducing energy consumption during UAV flight and improving endurance. Therefore, while realizing the active heat exchange function, the invention also preserves the original aerodynamic quality of the wing to the greatest extent, solves the technical problem of the aerodynamic performance degradation of traditional slotted heat dissipation structures, and provides a reliable guarantee for the long-term stable flight of laser-powered UAVs.

[0030] The air profiles of the inlet and outlet sections are determined as follows: Using the original airfoil profile as a baseline, computational fluid dynamics (CFD) methods are employed to perform parametric modeling and iterative optimization of the air profile, with the optimization objectives of smooth airflow transition and minimizing flow drag, to obtain the final air profile. Parametric modeling based on the original airfoil profile ensures that the optimized air profile retains the excellent lift-drag characteristics of the original airfoil in its aerodynamic shape. Furthermore, iterative optimization using CFD methods accurately simulates the flow state of the airflow in the inlet and outlet sections. By capturing complex flow phenomena such as boundary layer development, pressure distribution, and flow separation, fine-tuning of key parameters such as air profile curvature and transition angle is achieved. By using "smooth airflow transition" and "minimizing flow resistance" as dual-objective optimization functions, the optimization process not only focuses on minimizing flow losses, ensuring that the airflow does not experience drastic velocity gradient changes or flow separation when entering and exiting the heat exchange section, thus avoiding energy dissipation caused by vortex shedding, this provides stable and uniform inflow conditions for subsequent heat exchange sections. Minimizing flow resistance directly reduces the energy consumption of the UAV during flight, improving its endurance. Therefore, through parametric modeling and iterative optimization, the final profile achieves an optimal balance between aerodynamic performance, flow efficiency, and manufacturing feasibility.

[0031] The wing body is divided into an upper main wing section 11 and a lower aileron section 12 by the airflow channel. The laser battery is disposed through the lower aileron section, and its energy conversion unit is exposed on the lower surface of the lower aileron section. Preferably, the lower surface of the energy conversion unit is conformally arranged with the lower surface of the lower aileron section, forming a smooth transition aerodynamic shape to reduce drag. This allows the upper main wing section to maintain a relatively complete aerodynamic shape, preserving the lift-drag characteristics of the original airfoil to the greatest extent, while the slot position of the airflow channel is selected in the lower aileron section, which has a relatively small impact on the overall aerodynamic performance of the wing. The lower aileron is located on the lower surface of the wing. Under normal flight attitude, it can directly receive laser irradiation from the ground or air, avoiding the irradiation angle deviation that may occur due to changes in wing attitude caused by the upper surface arrangement, thus ensuring the stability and continuity of laser energy reception. Secondly, the energy conversion unit is exposed on the lower surface, which can directly exchange heat with the external environment through radiation, providing auxiliary heat dissipation in non-flight or low-speed states, while avoiding thermal resistance caused by the encapsulation structure. Furthermore, the laser battery runs through the lower aileron, and the heat dissipation end is directly exposed in the airflow channel, resulting in a short heat transfer path, which is conducive to the rapid removal of waste heat and the improvement of thermoelectric conversion efficiency.

[0032] A thermal management method for an eddy current heat transfer system with an embedded laser battery in an airfoil includes the following steps: Airflow channels are installed inside the main body of the wing, extending along the wingspan direction; The laser is continuously irradiated onto the laser battery on the wing of the UAV by ground or air laser emitting device, so that the energy conversion unit of the laser battery generates electrical energy, and the heat dissipation end of the laser battery is exposed to the airflow channel inside the wing; The air intake section at the leading edge of the wing guides the relative airflow generated during the flight of the UAV into the airflow channel, so that the airflow flows through the heat dissipation end of the laser battery; relative airflow refers to the airflow generated by the relative motion between the wing and the surrounding air, that is, the airflow formed by the flight motion of the UAV itself.

[0033] By actively disturbing the airflow passing through the heat dissipation end using the vortex heat dissipation component installed in the airflow channel, the laminar flow is transformed into vortex flow. The temperature of the heat dissipation end is reduced through forced convection heat transfer, thereby achieving heat dissipation for the energy conversion unit.

[0034] It should be noted that when the laser cell uses a photovoltaic-thermoelectric tandem device, the waste heat generated during the power generation process is directly absorbed by the thermoelectric module that is in close contact with the photovoltaic module, and part of the waste heat is converted into thermoelectric energy. This converts the waste heat generated by the energy conversion unit into additional electrical energy, realizing in-situ recovery and utilization of waste heat and improving energy utilization efficiency. The waste heat that is not converted into thermoelectric energy and the waste heat generated during the thermoelectric conversion process will be forcibly cooled by the airflow in the airflow channel.

[0035] This invention incorporates an airflow channel within the wing, providing a structural foundation for the subsequent heat exchange process and enabling the effective introduction of external airflow. Power is generated by continuous laser irradiation of the energy conversion unit, supplying electricity to the drone. Waste heat generated during power generation is naturally introduced into the airflow channel using the dynamic pressure of the drone's flight, achieving passive-active heat exchange without the need for an additional power unit. As the airflow passes over the laser battery's heat dissipation end, a vortex cooling component within the channel actively agitates the airflow, transforming laminar flow into vortex flow. This step significantly improves the convective heat transfer coefficient of the heat dissipation end surface by enhancing the mixing effect of fluid micro-particles. According to the Seebeck effect, the decrease in heat dissipation end temperature directly increases the temperature difference between the laser battery's heat dissipation end and the heat-generating part of the energy conversion unit, thereby improving thermoelectric conversion efficiency. Simultaneously, forced convection heat exchange also promptly removes the waste heat generated by the energy conversion unit, preventing the laser battery from experiencing efficiency degradation due to excessive temperature, achieving a dual heat dissipation effect.

[0036] In particular, the local vortices generated by the airfoil fins can increase the local airflow velocity on the wing and reduce surface pressure according to Bernoulli's principle, thereby providing additional lift for the UAV. This step organically combines the heat dissipation process with aerodynamic performance improvement, partially compensating for the aerodynamic losses caused by the slotting. By realizing laser power generation, waste heat generation, thermoelectric conversion, airflow introduction, vortex-enhanced heat transfer, and additional lift through each step, energy conversion, thermal management, and aerodynamic effects are linked together, solving the heat dissipation problem of laser-powered UAVs during long-term flight, while improving the overall system efficiency and flight performance.

[0037] In an optional embodiment, the vortex heat dissipation component includes at least one set of heat dissipation fins, each set comprising two heat dissipation fins. The two heat dissipation fins in the same set are arranged symmetrically in a figure-eight shape, with their blades facing each other. This "blade-blade facing" arrangement allows the airflow separated from the two fins to converge and shear near the central axis of the figure-eight structure, thereby efficiently and stably inducing large-scale vortices. This vortex structure greatly enhances the mixing and disturbance of fluid microparticles on the surface of the laser battery's heat dissipation end, completely breaking the thermal insulation effect of the laminar boundary layer. This allows the heat at the heat dissipation end to be rapidly carried away by the high-speed airflow, significantly improving the convective heat transfer coefficient. According to the Seebeck effect, the decrease in the temperature at the heat dissipation end directly increases the temperature difference between the heat dissipation end of the laser battery and the heat-generating part of the energy conversion unit, thereby improving the thermoelectric conversion efficiency.

[0038] The symmetrically arranged "eight"-shaped airfoil fins form a gradually expanding air passage 16. As the airflow passes through, the speed decreases and the pressure increases. Therefore, the airflow speed at the outlet of the air passage is less than the airflow speed at the inlet of the air passage. The streamlined shape of this "eight"-shaped symmetrically arranged airfoil fins can effectively reduce pressure drag and avoid the problem of excessive additional drag caused by adding heat dissipation structures. Furthermore, the local vortices generated by the airfoil fins form a stable low-pressure area on the lower surface of the wing. According to Bernoulli's principle, this will generate additional lift, partially compensating for the aerodynamic losses caused by the slotting. In a further improved design, a functional slot 13 is formed on the sidewall of the airfoil fin. The inlet end 14 of the functional slot is approximately located in the middle of the airfoil fin blade basin, while the outlet end 15 is approximately located on the back of the airfoil fin near the outlet of the air passage. The width of the functional slot gradually decreases from the inlet end to the outlet end. When airflow passes through the air passage, some of the airflow entering the blade basin is discharged through the functional slot. Due to the contractile shape of the functional slot, the airflow is accelerated as it passes through it, effectively increasing the speed of the low-speed airflow near the blade basin. Furthermore, after the main airflow in the air passage is accelerated, the low-speed airflow near the blade basin is viscously dragged, and the concave surface of the blade basin guides the airflow, which also weakens the influence of vortices at the blade basin position on the airflow speed to a certain extent. In summary, by setting a functional slot at the blade basin, the airflow at the airfoil fin blade basin position is accelerated, effectively increasing the flow speed of the low-speed airflow near the blade basin and improving the local heat dissipation effect at the corresponding heat dissipation end of the blade basin.

[0039] Referring to the experimental data in the table below, the influence of the airflow channels and airfoil fins set in this invention on the wing performance can be intuitively seen. like Figure 10 The image shows a cloud map of the heat dissipation coefficient of a laser cell surface simulated using ANSYS. Part A is the heat dissipation coefficient cloud map without heat dissipation fins, and Part B is the heat dissipation coefficient cloud map with heat dissipation fins. The heat dissipation coefficient of the system has been optimized overall, the average value of the global heat dissipation coefficient has been improved, and prominent high heat dissipation areas are visible in some areas. The original weak heat dissipation dead corner areas have disappeared.

[0040] like Figure 11 The image shows the temperature cloud map of the laser cell cross section simulated using ANSYS. Part C is the temperature cloud map without heat sink fins, and part D is the temperature cloud map with heat sink fins. The temperature cloud map in part D shows that the overall temperature level is significantly reduced, and at the same time, the distribution range of the high temperature area is significantly reduced.

[0041] like Figure 12The diagram shows the static pressure cloud map of an airfoil simulated using ANSYS at the airflow channel location. Part D is the static pressure cloud map of a simulated airfoil without an airflow channel, while Part E is the static pressure cloud map of a simulated airfoil with an airflow channel, and Part G is the static pressure cloud map of a simulated airfoil with an airflow channel and airfoil fins. The static pressure cloud maps of the models with airflow channels and airflow channels and airfoil fins are compared with those without airflow channels. It shows that after setting the airflow channel, the static pressure difference between the upper and lower wing surfaces is significantly increased. This is mainly manifested in the more concentrated distribution of the high-pressure area on the lower wing surface and the increase in pressure value. The increased pressure difference is directly converted into a stronger lift effect, indicating that the optimization of adding channels and heat dissipation fins effectively improves the lift characteristics of the airfoil.

[0042] In this invention, the installation angle, spacing, and number of airfoil fins can be determined through computational fluid dynamics (CFD) simulation optimization, specifically including the following steps: Step 1: Establish a parametric model A three-dimensional parametric model is established, including the wing body, airflow channels, and vortex heat dissipation components. The installation angle α, spacing d, and number n of the airfoil fins are used as design variables and can be adjusted parametrically. The installation angle α is defined as the angle between the fin chord line and the airflow direction, ranging from -10° to +10°; the spacing d is defined as the vertical distance between the leading edges of adjacent fins, ranging from 0.5 to 2 times the fin chord length; and the number n is determined based on the length of the heat exchange section, ranging from 3 to 15 fins.

[0043] Step 2: Set optimization objectives and constraints The objective function is optimized into a multi-objective function, specifically including: Heat transfer efficiency target: Maximize the Nusselt number Nu or the convective heat transfer coefficient h; Aerodynamic performance target: While ensuring an increase in lift coefficient, control the increase in drag coefficient to not exceed 5% of the original airfoil; Lift enhancement target: To increase the overall lift coefficient of the wing by at least 1.5% through the additional lift generated by local vortices; The constraints include: Structural constraints: The fin spacing shall not be less than the minimum value allowed by the manufacturing process (e.g., 1 mm). Flow constraints: to prevent excessive flow separation that could lead to flow instability; Temperature constraint: The temperature of the laser battery heat dissipation end shall not exceed the set threshold (e.g., 50°C). Step 3: CFD simulation calculation Commercial CFD software (such as ANSYS Fluent, STAR-CCM+, etc.) was used for coupled flow and temperature field calculations. The calculation model included: Turbulence model: k-ε or SST k-ω model is used; Boundary conditions: The inlet is a velocity inlet, the outlet is a pressure outlet, and the wall uses no-slip boundary conditions; Mesh generation: A structured mesh is used, and the mesh is refined on the fin surface and near the wall area to ensure that the y+ value is less than 1; Convergence criterion: Residuals reduced to 10 -4 The following parameters will remain unchanged at the monitoring points; Step 4: Algorithm Optimization and Iteration Parameter optimization is performed using response surface methodology (RSM), genetic algorithm (GA), or multi-objective optimization algorithms. The specific process is as follows: Step 1: Select sample points within the design space for CFD calculation; Step 2: Establish a response surface model of the design variables and the objective function; Step 3: Find the optimal solution on the response surface using optimization algorithms; Step 4: Perform CFD verification on the optimal solution. If the preset threshold is met, output the result; otherwise, return to step 1.

[0044] Step 5: Determine and Verify Final Parameters Through the above optimization process, the optimal parameter combination is determined to achieve a lift enhancement effect that reaches a preset threshold (e.g., a 1.5% increase in the lift coefficient). Final verification requires CFD simulation to confirm that the heat exchange efficiency is improved and the lift enhancement effect is stable under UAV cruise conditions.

[0045] This invention embeds a laser battery inside the wing and designs a smooth airflow profile, providing a flow channel foundation for thermal management while maintaining the original airfoil's aerodynamic performance. The vortex cooling component uses symmetrically arranged "eight"-shaped airfoil fins to actively transform the laminar flow passing through the laser battery's heat dissipation end into vortices, greatly enhancing heat transfer efficiency and significantly reducing the temperature at the heat dissipation end. This increases the temperature difference between the heat dissipation end of the thermoelectric conversion and the heat-generating part of the energy conversion unit, improving waste heat power generation and effectively cooling the laser battery. The expanding shape of the airflow channel increases the pressure during gas flow, allowing the outflowing air to have higher pressure. This provides a higher-pressure airflow to the lower surface of the wing, increasing lift. Furthermore, the reaction force on the upper surface of the channel where the airflow deflects also indirectly increases lift.

[0046] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A high-intensity eddy current heat transfer system with an embedded laser battery in an airfoil, characterized in that, include: The wing body has an internal airflow channel extending along the wingspan direction; the airflow channel includes a smoothly connected air intake section, a straight heat exchange section, and an air outlet section; A laser battery is embedded in the wing body. The energy conversion unit of the laser battery is used to receive laser irradiation to generate electricity. The heat dissipation end of the laser battery is exposed in the straight heat exchange section, and the outer surface of the heat dissipation end of the laser battery is flush with the surface of the straight heat exchange section. The vortex heat dissipation component is located in the airflow channel and is fixedly installed on the heat dissipation end of the laser battery. The vortex heat dissipation component includes at least one set of heat dissipation fins that are thermally connected to the heat dissipation end of the laser battery. The two heat dissipation fins in the same set are arranged symmetrically in a figure-eight shape, and the blades of the two heat dissipation fins in the same set are opposite each other, so as to disturb the airflow flowing through the heat dissipation end, so that it changes from laminar flow to vortex flow, thereby improving the heat exchange efficiency.

2. The eddy current heat transfer system for an embedded laser battery in a wing according to claim 1, characterized in that: The two heat dissipation fins in the same group form an "eight"-shaped structure, with the small opening facing the side of the air intake section.

3. The eddy current heat transfer system for an embedded laser battery in a wing according to claim 1, characterized in that: The air intake section and the air outlet section both have smooth curves obtained based on the original airfoil profile.

4. The eddy current heat transfer system for an embedded laser battery in a wing according to claim 3, characterized in that, The air profiles of the inlet and outlet sections are determined as follows: using the original airfoil profile as a reference, computational fluid dynamics is employed to perform parametric modeling and iterative optimization of the air profile with the optimization objectives of smooth airflow transition and minimizing flow resistance, thereby obtaining the final air profile.

5. The eddy current heat transfer system for an embedded laser battery in a wing according to claim 1, characterized in that: The wing body is divided into an upper main wing and a lower secondary wing by the airflow channel. The laser battery is disposed through the lower secondary wing, and its energy conversion unit is exposed on the lower surface of the lower secondary wing.

6. The eddy current heat transfer system for an embedded laser battery in a wing according to claim 5, characterized in that: The lower surface of the energy conversion unit is conformally configured with the lower surface of the secondary wing, forming a smoothly transitioning aerodynamic shape.

7. A vortex heat transfer system for an embedded laser battery in a wing according to any one of claims 1 to 6, characterized in that: The laser battery uses a pure thermoelectric module. The hot end of the pure thermoelectric module receives the incident laser, while the cold end is exposed in a straight heat exchange section. The vortex heat dissipation component is thermally connected to the cold end of the pure thermoelectric module. Alternatively, the laser battery uses a pure photovoltaic module, with the laser incident on the conductive glass end of the pure photovoltaic module, and the electrode exposed in a straight heat exchange section, with the eddy current heat dissipation component thermally connected to the electrode. Alternatively, the laser cell may employ a photovoltaic-thermoelectric tandem device, which includes a photovoltaic part and a thermoelectric part. The photovoltaic part is used to receive laser irradiation to generate electricity, and the hot end of the thermoelectric part is connected to the electrode of the photovoltaic part to receive the waste heat generated during the operation of the laser cell. The waste heat is directly absorbed by the thermoelectric part for thermoelectric conversion, and the cold end of the thermoelectric part is exposed in a flat heat exchange section.

8. A thermal management method based on the system according to any one of claims 1 to 6, characterized in that, Includes the following steps: Airflow channels are installed inside the main body of the wing, extending along the wingspan direction; The laser is continuously irradiated onto the laser battery on the wing of the UAV by ground or air laser emitting device, so that the energy conversion unit of the laser battery generates electrical energy, and the heat dissipation end of the laser battery is exposed to the airflow channel inside the wing; The air intake section at the leading edge of the wing guides the relative airflow generated during the flight of the UAV into the airflow channel, so that the airflow flows through the heat dissipation end of the laser battery; By actively disturbing the airflow passing through the heat dissipation end using the vortex heat dissipation component installed in the airflow channel, the laminar flow is transformed into vortex flow. The temperature of the heat dissipation end is reduced through forced convection heat transfer, thereby achieving heat dissipation for the energy conversion unit.

9. The thermal management method for an eddy current heat transfer system with an embedded laser battery in a wing according to claim 8, characterized in that: The vortex heat dissipation assembly includes at least one set of heat dissipation fins, each heat dissipation fin including two wing-shaped fins. The two wing-shaped fins in the same set are arranged symmetrically in a figure-eight shape, and the blades of the two wing-shaped fins in the same set are opposite each other.

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