Solar energy drag reduction and energy storage aircraft wing and drag reduction and energy storage method

Abstract

The application provides a solar energy drag reduction and energy storage aircraft wing and a drag reduction and energy storage method, and relates to the technical field of aircrafts.The wing body is internally provided with an angle control system and multiple solar panels.The angle control system comprises a control rod, a connecting rod and a control shaft, the middle part of each solar panel is provided with the control shaft, the two adjacent solar panels are hingedly connected through the connecting rod to form a whole solar panel, and the bottom of the solar panel at the head and tail is provided with the control rod.The control rod is used for adjusting the overall inclination angle of the whole solar panel, and the control shaft is used for adjusting the inclination angle of each solar panel.The multiple solar panels are connected to form a whole solar panel, the overall inclination angle adjustment and the accurate inclination angle adjustment are combined when the angle is adjusted, the solar energy is maximally absorbed, and good economic benefits are achieved, and a reflective coating is designed to reduce the flight resistance.

Description

Technical Field

[0001] This invention belongs to the field of aircraft technology, and particularly relates to an aircraft wing for solar drag reduction and energy storage, and a drag reduction and energy storage method. Background Technology

[0002] Existing biomimetic flapping-wing aircraft typically rely on mechanical motion to generate lift. However, the lift generated is low and is often limited by its own payload weight and battery energy storage, resulting in short flight time and failing to meet the needs of long-duration flight.

[0003] To address this issue, current aircraft employ various methods to absorb energy from the environment, such as using wind power to rotate propellers and solar panels. Furthermore, various technological explorations have been undertaken to reduce and manage the required power, thereby improving aerodynamic and mechanical efficiency and ultimately lowering electricity consumption.

[0004] For example, Chinese invention patent application CN 112208776 A discloses a high-altitude, long-endurance biplane unmanned aerial vehicle and its manufacturing method, which specifically discloses:

[0005] A servo motor I 14 is installed in the internal cavity of the base 11. The output shaft of the servo motor I 14 is connected to the rotating shaft 15 via a coupling. The rotating shaft 15 extends through the upper surface of the circular groove 12 and is fixedly connected to the rotating bracket 13. The servo motor I 14 drives the rotating bracket 13 to rotate within the circular groove 12 via the rotating shaft 15, adjusting the angle of the photovoltaic panel 20 in the vertical direction. Fan-shaped limiting grooves 18 are provided on both sides of the top of the rotating bracket 13. A rotating rod 19 is rotatably mounted inside the limiting groove 18. The limiting groove 18 limits the angle of the rotating rod 19. The photovoltaic panel 20 is fixedly mounted on the rotating rod 19. At the top, a driven gear 23 is mounted on one side surface of the rotating rod 19. A servo motor II 21 is mounted on the rotating bracket 13. The output shaft of the servo motor II 21 passes through the rotating bracket 13 and is connected to the driving gear 22. The driving gear 22 and the driven gear 23 mesh with each other. The servo motor II 21 drives the driven gear 23 to rotate through the driving gear 22. The driven gear 23 drives the rotating rod 19 and the photovoltaic panel 20 to rotate in the horizontal direction to adjust the angle. An angular displacement sensor 24 is mounted on the other side surface of the rotating rod 19 to detect the rotation angle of the rotating rod 19 and the photovoltaic panel 20 in the horizontal direction.

[0006] The inventors discovered that while the technical solution disclosed in the aforementioned patent can achieve angle adjustment of each photovoltaic panel in both the vertical and horizontal directions, the angle adjustment of each panel requires two motors and two sets of transmission devices, resulting in a relatively complex overall structure. Furthermore, each photovoltaic panel is separate and independent, possessing its own independent angle adjustment device. Since the daily variation in sunlight intensity is slow and continuous, the independent angle adjustment devices in the aforementioned solution, each driven by two sets of drive devices, are not the most economical way to achieve angle adjustment. Summary of the Invention

[0007] To overcome the shortcomings of the prior art, this invention provides an aircraft wing for solar drag reduction and energy storage, and a drag reduction and energy storage method. Multiple solar panels are connected into a whole solar panel. When adjusting the angle, a combination of overall tilt angle adjustment and precise tilt angle adjustment is used to maximize the absorption of solar energy while achieving better economic benefits. A reflective coating is also designed to reduce flight drag.

[0008] To achieve the above objectives, one or more embodiments of the present invention provide the following technical solutions:

[0009] The first aspect of the present invention provides a solar-powered drag-reducing and energy-storing aircraft wing.

[0010] A solar-powered drag-reduction and energy storage aircraft wing includes a wing body. An angle control system and multiple solar panels are internally installed within the wing body. The angle control system includes control rods, connecting rods, and control shafts. Each solar panel has a control shaft located in its center. Adjacent solar panels are hinged together via connecting rods to form a single solar panel. Control rods are located at the bottom of the front and rear solar panels. The control rods are used to adjust the tilt angle of the front and rear solar panels, as well as the overall tilt angle of the entire solar panel. The control shafts are used to adjust the tilt angle of each solar panel individually.

[0011] Optionally, the upper surface of the wing body is provided with a light-transmitting skin, and the solar panel is disposed under the light-transmitting skin.

[0012] Optionally, the angle adjustment system further includes a position sensor, which is mounted on the adjustment lever.

[0013] Optionally, it also includes a solar energy storage system, which includes multiple solar panels, energy storage batteries, and a light sensor. The light sensor is mounted on the solar panels, and each solar panel is electrically connected to the energy storage battery.

[0014] Optionally, the translucent skin includes a carbon fiber frame filled with a translucent material, which includes polycarbonate, transparent resin, and plexiglass.

[0015] Optionally, the lower surface of the wing is coated with a reflective coating, the reflective coating being white in color and made of composite ceramic nanomaterials.

[0016] Optionally, the number of control rods is set to multiple, and the control rod is a telescopic rod with telescopic function, including a hydraulic rod, a pneumatic cylinder and an electric cylinder.

[0017] Optionally, the angle adjustment system further includes a controller, which is connected to a light sensor, a position sensor, an adjustment lever, and an adjustment shaft.

[0018] The second aspect of the present invention provides a drag reduction and energy storage method for aircraft wings that utilizes solar energy for drag reduction and energy storage.

[0019] A drag reduction and energy storage method for an aircraft wing based on the solar drag reduction and energy storage described in the first aspect includes an energy storage method and a drag reduction method, wherein the energy storage method includes the following steps:

[0020] The controller calculates the optimal position information of the entire solar panel angle based on the sunlight parameter information collected by the light sensor;

[0021] The control lever extends and retracts based on the optimal position information of the entire solar panel angle, adjusting the tilt angle of the first and last solar panels, and thus adjusting the overall tilt angle of the entire solar panel.

[0022] The position sensor collects the adjusted position information of the control lever and feeds it back to the controller.

[0023] The control shaft on each solar panel is driven by an external drive transducer, which drives the corresponding solar panel to rotate, thereby precisely adjusting the tilt angle of each solar panel.

[0024] The precisely adjusted solar panels transfer the collected solar energy to the energy storage battery, completing the energy storage process.

[0025] Optionally, the drag reduction method includes the following steps:

[0026] The solar panels on the upper surface of the wing absorb solar energy, while the reflective coating on the lower surface reflects solar energy, creating a temperature difference between the upper and lower surfaces.

[0027] The temperature difference between the upper and lower surfaces causes thermal convection in the air near the upper and lower surfaces of the wing body, which changes the airflow around the wing body, making the airflow on the upper surface easier to flow downward, reducing airflow separation and turbulence on the upper surface, stabilizing the airflow, increasing the lift of the wing body, and reducing drag during flight.

[0028] The above one or more technical solutions have the following beneficial effects:

[0029] This invention provides a solar-powered drag reduction and energy storage method for an aircraft wing. It employs a combination of overall tilt angle adjustment and precise tilt angle adjustment. Multiple solar panels are connected into a single, continuous solar panel using linkages. Adjustment is only required on the front and rear solar panels, utilizing the hinged connections between adjacent panels to achieve overall tilt angle adjustment. An adjustment shaft is installed in the center of each solar panel, driving its rotation and thus precisely adjusting the tilt angle of each panel. The adjustable solar panels can autonomously adjust their angle based on the aircraft's operating status and the location of solar energy, maximizing solar energy absorption. This active utilization of solar energy extends the aircraft's endurance while reducing costs, achieving economic benefits.

[0030] The invention also designed a wing structure based on solar thermal performance, which uses the upper surface of the wing to absorb solar energy and the reflective coating on the lower surface to reflect solar energy, creating a temperature difference between the upper and lower surfaces of the wing. This structure not only improves the lift of the flapping wing, but also reduces drag during flight and increases the range of the flapping wing aircraft.

[0031] The solar-powered drag-reducing and energy-storing aircraft wing provided by this invention has a simple overall structure, improves the efficiency and performance of the aircraft, extends its endurance, and increases its practicality in complex environments.

[0032] Advantages of additional aspects of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0033] The accompanying drawings, which form part of this invention, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an improper limitation of the invention.

[0034] Figure 1 This is a schematic diagram of the overall structure of the wing body according to Embodiment 1 of the present invention.

[0035] Figure 2 This is a schematic diagram of the internal structure of the wing body according to Embodiment 1 of the present invention.

[0036] Figure 3 This is a schematic diagram of the solar panel angle adjustment according to Embodiment 1 of the present invention.

[0037] Figure 4 This is a flowchart of the illumination condition adaptive algorithm of Embodiment 1 of the present invention.

[0038] The attached diagram lists the components represented by each number as follows:

[0039] 1. Wing body, 2. Transparent skin, 3. Solar panel, 4. Light sensor, 5. Reflective coating, 6. Energy storage battery, 7. Control rod, 8. Control shaft, 9. Linkage, 10. Position sensor. Detailed Implementation

[0040] It should be noted that the following detailed descriptions are exemplary and intended to provide further illustration of the invention. Unless otherwise specified, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains.

[0041] It should be noted that the terminology used herein is for the purpose of describing particular implementations only and is not intended to limit the exemplary implementations of the present invention.

[0042] Where there is no conflict, the embodiments and features in the embodiments of the present invention can be combined with each other.

[0043] The overall concept proposed in this invention is as follows:

[0044] To address the problems mentioned in the background art, this invention, from an economic perspective, designs a novel solar-powered drag-reduction and energy storage aircraft wing. Instead of requiring vertical and horizontal adjustments to each individual solar panel, it employs a holistic adjustment concept. Multiple solar panels are hinged together via connecting rods to form a single solar panel, which supports and connects them. Each solar panel has an adjustment shaft for adjusting its horizontal tilt angle. For vertical angle adjustment, control rods are located at the bottom of the front and rear solar panels, allowing for adjustment of the tilt angles of the front and rear panels, as well as the overall tilt angle of the entire solar panel. This solution achieves economic benefits while ensuring sufficient precision in solar panel control.

[0045] Furthermore, natural aerodynamics such as birds and insects have provided inspiration for this invention. The varied wing colors of birds and insects suggest that wing color can significantly impact the aerodynamic performance of drones and can be a crucial factor in improving drone efficiency and endurance. For example, the tops of the wings of albatrosses flying over the sea are typically black, while the bottoms are white. This color difference results in different degrees of heat distribution on the upper and lower surfaces of the wings. When heat from sunlight or the sky reaches the wing surface, some heat is absorbed, some is reflected, and the remainder is transferred, creating a temperature difference between the upper and lower surfaces of the wing. This reduces air viscosity and density, thereby reducing drag.

[0046] Therefore, inspired by organisms in nature, this invention combines flight drag reduction and energy harvesting to provide a solar-powered aircraft wing with high lift, long endurance, and long service life. By reducing flight drag, it improves the efficiency and performance of flapping-wing aircraft. At the same time, by precisely adjusting the angle of the solar panels, the solar panels can obtain as much solar energy as possible, thereby extending the aircraft's endurance and improving its practicality in complex environments.

[0047] Example 1

[0048] This embodiment discloses an aircraft wing that uses solar energy for drag reduction and energy storage.

[0049] like Figure 1 As shown, a solar-powered drag-reduction and energy storage aircraft wing includes a wing body 1, a solar energy storage system, and an angle control system. An internal space is provided within the wing body 1, and the solar energy storage system and angle control system are housed within this space. To facilitate sunlight transmission, a light-transmitting skin 2 is provided on the upper surface of the wing body 1, allowing sunlight energy to be collected into the solar energy storage system.

[0050] The solar energy storage system includes a solar panel 3, a light sensor 4, and a solar energy storage battery 6. The solar panel 3 is installed inside the wing body 1 of the aircraft to absorb solar energy; the light sensor 4 is installed on the solar panel 3 to collect parameters such as the incident position and intensity of sunlight; the solar energy storage battery 6 is installed inside the wing and converts the absorbed solar energy into electrical energy through the photovoltaic effect, which is then stored through energy storage devices such as battery packs.

[0051] The energy storage battery 6 includes multiple solar cell units connected in series to form an energy storage battery group 6, which stores the electrical energy converted from the solar energy absorbed by the solar panel 3.

[0052] like Figure 2As shown, in order to achieve angle adjustment of multiple solar panels 3, the angle control system of this embodiment includes components such as a controller, control rod 7, connecting rod 9, control shaft 8, and position sensor 10.

[0053] The control rod 7 is installed below the solar panel 3 to adjust the angle of the solar panel 3 through mechanical movement; the control shaft 8 is installed on each solar panel 3 to adjust the angle of each solar panel 3 individually; the connecting rod 9 is used to support and fix the solar panel 3, connecting and fixing adjacent solar panels 3 at the beginning and end. It can be understood that the connecting rod 9 and the solar panel 3 are hinged to achieve different angle changes and adjustments; the position sensor 10 is installed to monitor the position and speed parameters of the control rod 7; the controller is used to monitor the light angle and intensity information, calculate the optimal position information of the solar panel 3 based on the data, and ensure that the position of the connecting rod 9 is adjusted to the correct angle through the feedback information of the position sensor 10.

[0054] Unlike existing technologies, in this embodiment, the control rod 7, control shaft 8, and connecting rod 9 connect multiple solar panels 3 into a single solar panel 3. Therefore, when adjusting the overall tilt angle (vertical height) of the solar panel 3, it is unnecessary to adjust each solar panel 3 individually; only the first and last solar panels 3 need to be adjusted. The overall tilt angle of the entire solar panel 3 is adjusted by utilizing the hinged connections between the first and last solar panels 3 and adjacent solar panels 3. Furthermore, to more precisely adjust the tilt angle of each individual solar panel 3, this embodiment retains the function of adjusting the tilt angle of each individual solar panel 3. A control shaft 8 is installed in the middle of each solar panel 3. This control shaft 8 is connected to an external drive device, which drives the corresponding solar panel 3 to rotate, thereby precisely adjusting the tilt angle of each solar panel 3.

[0055] Specifically, such as Figure 2 and Figure 3 As shown, there are a total of 4 control rods 7, which are installed below the first and last solar panels 3. Two rods are installed at the bottom of the first solar panel 3 and two rods are installed at the bottom of the last solar panel 3. The 4 control rods 7 extend or retract through mechanical movement, thereby adjusting the overall angle of the entire solar panel 3.

[0056] The specific control methods of the angle control system are as follows: Figure 3 As shown:

[0057] Among them, the control rod 7 is located at each corner of the entire solar panel 3 (i.e. at the beginning and end of the solar panel 3). The controller controls each control rod 7 to raise and lower at different heights, so that the overall tilt angle of the solar panel 3 reaches the preset tilt angle, thus completing the overall angle adjustment of the solar panel 3.

[0058] The control shaft 8 on the sub-solar panel 3 (i.e., each solar panel 3) rotates at the corresponding angle according to the command, adjusting the tilt angle of the sub-solar panel 3, thereby achieving precise angle control of the entire solar panel 3 and maximizing the absorption of solar energy.

[0059] As a specific technical solution, the control rod 7 may be made of components including but not limited to lightweight hydraulic rods, lightweight cylinders, etc.

[0060] As a further technical solution, the light-transmitting skin 2 in the middle of the upper surface of the wing allows light to pass through and illuminate the solar panel 3; the light-transmitting skin 2 is made of carbon fiber frame and filled with light-transmitting material, which includes, but is not limited to, polycarbonate, transparent resin, plexiglass and other materials with high light transmittance.

[0061] The second improvement in this embodiment is that a reflective coating 5 is applied to the lower surface of the wing body 1. The reflective coating 5 on the lower surface of the wing body 1 is a white composite ceramic nano-reflective coating 5 with high solar reflectivity and radiative cooling rate, which makes the temperature of the lower surface of the wing lower than the ambient temperature, thereby reducing flight drag and achieving the technical effect of drag reduction.

[0062] The working principle of reflective coating 5 in reducing flight drag is as follows:

[0063] The solar panel 3 on the upper surface of the wing body 1 absorbs solar energy, while the lower surface reflects solar energy, creating a temperature difference between the upper and lower surfaces. This causes thermal convection in the air near the upper and lower surfaces of the wing body 1, altering the airflow around the wing. This makes the airflow on the upper surface of the wing flow downwards more easily, reducing airflow separation and turbulence on the upper surface of the wing, stabilizing the airflow, thereby increasing the lift of the wing and reducing flight drag.

[0064] As a more detailed technical solution:

[0065] The reflective coating 5 is made of ceramic particles with high reflectivity, such as titanium dioxide particles; a polymer resin with corrosion resistance and wear resistance is selected as the base material; and suitable solvents and additives are selected to adjust the viscosity, rheology, and drying speed of the coating.

[0066] Optimize the formulation ratio and composition of the coating to ensure that the coating has good reflective properties, weather resistance and abrasion resistance;

[0067] The raw materials, such as ceramic particles, polymer resin, solvent and additives, are thoroughly mixed to form a stable coating solution, removing particles and impurities to ensure coating quality and surface smoothness.

[0068] The coating method combines spraying and brushing to apply the paint to the lower surface of the wing. Professional spraying equipment is used to control the spraying thickness and speed, and the paint is sprayed evenly on the lower surface of the wing. Multiple coats are applied to the surface as needed using brushes or rollers to ensure uniform coating and achieve the required coating thickness.

[0069] After the painting is completed, the coating is cured to form a strong protective layer on the wing surface.

[0070] It can be understood that the controller is connected to the light sensor 4, the position sensor 10, the control lever 7 and the control shaft 8 respectively. Based on the sunlight angle and intensity information collected by the light sensor 4, the controller calculates the optimal position information of the solar panel 3 angle according to the data, and monitors and adjusts the position of the control lever 7 by using the feedback information from the position sensor 10 and the feedback control algorithm to ensure that each control lever 7 is adjusted to the correct height to achieve the angle adjustment of the solar panel 3.

[0071] Furthermore, in this embodiment, the controller combines the Maximum Power Point Tracking (MPPT) algorithm and the fuzzy logic control algorithm to form an adaptive adjustment algorithm for illumination conditions, optimizing the three-angle adjustment of the solar panel. The specific process is as follows: Figure 4 As shown:

[0072] The light intensity and incident angle are monitored by the light sensor 4;

[0073] Monitor the output voltage and current of solar panel 3;

[0074] Based on the current illumination conditions, the maximum power point is calculated using the MPPT algorithm. Based on the information of the maximum power point, the ideal angle of solar panel 3 is determined.

[0075] Based on the current light intensity and incident angle, the degree of adjustment of the angle of solar panel 3 is determined by the fuzzy logic control algorithm. Fuzzy rules are set: if the light intensity is high and the incident angle is small, the angle of solar panel 3 is increased; if the light intensity is low and the incident angle is large, the angle of solar panel 3 is decreased.

[0076] Based on the fuzzy rules and the input lighting conditions, the fuzzy logic control algorithm generates a fuzzy output with an adjusted angle.

[0077] The optimal angle calculated by the MPPT algorithm is combined with the adjustment angle generated by the fuzzy logic control algorithm to obtain the final solar energy adjustment angle. The angle control system is then used to adjust the angle of the solar panel 3.

[0078] The output power of solar panel 3 is continuously monitored, and adjustments and optimizations are implemented based on changes in the actual output power. If the actual output power deviates from the expectation, the optimal angle is recalculated and adjusted based on feedback information.

[0079] In other embodiments, other methods may be used to find the optimal solar panel angle 3, and this embodiment does not impose any limitations on this.

[0080] This embodiment features a solar-powered drag reduction and energy storage aircraft wing system. The solar energy storage system utilizes solar panels 3 to absorb solar energy and convert it into electrical energy through the photovoltaic effect for storage. An angle control system adjusts the angle of the automatic solar panels 3 to maximize solar energy absorption. The lower surface coating of the wing employs a white composite ceramic nano-reflective coating 5 with high solar reflectivity and radiative cooling rate, ensuring the lower surface temperature of the wing is lower than the ambient temperature, thereby reducing drag. This embodiment has a simple overall structure, reduces flight drag, increases endurance, improves aircraft efficiency and performance, and enhances practicality in complex environments.

[0081] Example 2

[0082] This embodiment discloses a drag reduction and energy storage method for an aircraft wing that utilizes solar energy for drag reduction and energy storage.

[0083] A drag reduction and energy storage method for an aircraft wing based on solar drag reduction and energy storage as described in Embodiment 1 includes an energy storage method and a drag reduction method, wherein the energy storage method includes the following steps:

[0084] The controller calculates the optimal position information of the entire solar panel 3 based on the sunlight parameter information collected by the light sensor 4.

[0085] The control lever 7 extends and retracts according to the optimal position information of the entire solar panel 3, adjusts the tilt angle of the first and last solar panels 3, and then adjusts the overall tilt angle of the entire solar panel 3.

[0086] Position sensor 10 collects the adjusted position information of control lever 7 and feeds it back to the controller;

[0087] The control shaft 8 on each solar panel 3 is driven by an external drive to rotate the corresponding solar panel 3, thereby precisely adjusting the tilt angle of each solar panel 3.

[0088] The precisely adjusted solar panel 3 transfers the collected solar energy to the energy storage battery 6, completing the energy storage process.

[0089] In practice, the control axis on each solar panel generates an angle adjustment amount based on local illumination and position information through the control system. This adjustment is then driven by an external drive to rotate the corresponding solar panel, thereby precisely adjusting the tilt angle of each solar panel.

[0090] Furthermore, the drag reduction method includes the following steps:

[0091] The solar panel 3 on the upper surface of the wing body 1 absorbs solar energy, and the reflective coating 5 on the lower surface reflects solar energy, creating a temperature difference between the upper and lower surfaces.

[0092] The temperature difference between the upper and lower surfaces causes thermal convection in the air near the upper and lower surfaces of the wing body 1, which changes the airflow around the wing body 1, making the airflow on the upper surface easier to flow downward, reducing airflow separation and turbulence on the upper surface, stabilizing the airflow, increasing the lift of the wing body 1, and reducing drag during flight.

[0093] While the specific embodiments of the present invention have been described above in conjunction with the accompanying drawings, this is not intended to limit the scope of protection of the present invention. Those skilled in the art should understand that various modifications or variations that can be made by those skilled in the art without creative effort based on the technical solutions of the present invention are still within the scope of protection of the present invention.

Claims

1. A solar-powered drag-reducing and energy-storing aircraft wing, characterized in that, The system includes a wing body, inside which is installed an angle control system and multiple solar panels. The angle control system includes control rods, connecting rods, and control shafts. Each solar panel has a control shaft in its center. Adjacent solar panels are hinged together by connecting rods to form a single solar panel. Control rods are installed at the bottom of the solar panels at the front and rear. The control rods are used to adjust the tilt angle of the solar panels at the front and rear, as well as the overall tilt angle of the entire solar panel. The control shafts are used to adjust the tilt angle of each solar panel individually. The lower surface of the wing body is coated with a reflective coating, which is white in color and made of composite ceramic nanomaterials. The solar panels on the upper surface of the wing absorb solar energy, while the reflective coating on the lower surface reflects solar energy, creating a temperature difference between the upper and lower surfaces. The temperature difference between the upper and lower surfaces causes thermal convection in the air near the upper and lower surfaces of the wing body, which changes the airflow around the wing body, making the airflow on the upper surface easier to flow downward, reducing airflow separation and turbulence on the upper surface, stabilizing the airflow, increasing the lift of the wing body, and reducing drag during flight.

2. The solar-powered drag reduction and energy storage aircraft wing as described in claim 1, characterized in that, The upper surface of the wing body is provided with a light-transmitting skin, and the solar panel is located at the lower part of the light-transmitting skin.

3. The solar-powered drag reduction and energy storage aircraft wing as described in claim 1, characterized in that, The angle adjustment system also includes a position sensor, which is mounted on the adjustment lever.

4. The solar-powered drag reduction and energy storage aircraft wing as described in claim 3, characterized in that, It also includes a solar energy storage system, which comprises multiple solar panels, energy storage batteries, and a light sensor. The light sensor is mounted on the solar panels, and each solar panel is electrically connected to the energy storage battery.

5. The solar-powered drag reduction and energy storage aircraft wing as described in claim 2, characterized in that, The translucent skin includes a carbon fiber frame, which is filled with a translucent material, including polycarbonate, transparent resin and plexiglass.

6. The solar-powered drag reduction and energy storage aircraft wing as described in claim 1, characterized in that, The number of control rods is set to multiple, and each control rod is a telescopic rod with telescopic function. Each control rod includes a hydraulic rod, a pneumatic cylinder, and an electric cylinder.

7. The solar-powered drag reduction and energy storage aircraft wing as described in claim 4, characterized in that, The angle adjustment system also includes a controller, which is connected to a light sensor, a position sensor, an adjustment lever, and an adjustment shaft.

8. A drag reduction and energy storage method for an aircraft wing based on the solar drag reduction and energy storage described in any one of claims 1-7, characterized in that, This includes energy storage methods and drag reduction methods, wherein the energy storage method includes the following steps: The controller calculates the optimal position information of the entire solar panel angle based on the sunlight parameter information collected by the light sensor; The control lever extends and retracts based on the optimal position information of the entire solar panel angle, adjusting the tilt angle of the first and last solar panels, and thus adjusting the overall tilt angle of the entire solar panel. The position sensor collects the adjusted position information of the control lever and feeds it back to the controller. The control shaft on each solar panel is driven by an external drive transducer, which drives the corresponding solar panel to rotate, thereby precisely adjusting the tilt angle of each solar panel. The precisely adjusted solar panels transfer the collected solar energy to the energy storage battery, completing the energy storage process; The drag reduction method includes the following steps: The solar panels on the upper surface of the wing absorb solar energy, while the reflective coating on the lower surface reflects solar energy, creating a temperature difference between the upper and lower surfaces. The temperature difference between the upper and lower surfaces causes thermal convection in the air near the upper and lower surfaces of the wing body, which changes the airflow around the wing body, making the airflow on the upper surface easier to flow downward, reducing airflow separation and turbulence on the upper surface, stabilizing the airflow, increasing the lift of the wing body, and reducing drag during flight.

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