Novel solar cell system and method suitable for airship

Abstract

The invention discloses a novel solar cell system and method suitable for an airship. The system comprises an electrochromic layer used for changing light transmittance, a solar cell array integrated on the airship and a voltage control module. Wherein the electrochromic layer is physically connected with the solar cell array, the electrochromic layer covers the surface of the solar cell array, and the voltage control module is electrically connected with the electrochromic layer. Therefore, by adopting the embodiment of the invention, the problems of overheat and overpressure of the capsule body can be reduced, meanwhile, the power generation efficiency of the solar cell is improved, damage to a skin material of the capsule body of the airship is avoided, and the service life of the airship is prolonged.

Description

Technical Field

[0001] This application relates to the field of near-space airship technology, and in particular to a novel solar cell system and method suitable for airships, which can be used in a data security exchange and sharing platform. Background Technology

[0002] In near-space missions, stratospheric airships, as important floating platforms, face complex thermal environment challenges. Due to diurnal periodic solar radiation and localized weather variations, the temperature and pressure within the airship's envelope experience periodic or temporary fluctuations.

[0003] Currently, the solar cell system on airships is a crucial energy supply device. However, existing solar cells generate excess electricity under high summer radiation conditions, which cannot be effectively utilized and ultimately becomes waste heat. This waste heat acts on the airship's envelope through conduction and radiation, exacerbating overheating and overpressure problems. Furthermore, the waste heat not only reduces the power generation efficiency of the solar cells but also damages the airship's skin material, shortening the airship's lifespan. Summary of the Invention

[0004] This application provides a novel solar cell system suitable for airships. To provide a basic understanding of some aspects of the disclosed embodiments, a brief summary is given below. This summary is not intended as a general commentary, nor is it intended to identify key / important components or to describe the scope of protection of these embodiments. Its sole purpose is to present some concepts in a simple form as a prelude to the detailed description that follows.

[0005] In a first aspect, embodiments of this application provide a novel solar cell system suitable for airships, the system comprising:

[0006] An electrochromic layer used to change light transmittance, a solar cell array integrated into the airship, and a voltage control module; among them,

[0007] The electrochromic layer is physically connected to the solar cell array and covers the surface of the solar cell array. The voltage control module is electrically connected to the electrochromic layer.

[0008] Optionally, the system may also include:

[0009] Composite insulation layer, airship skin; among them,

[0010] One surface of the composite heat insulation layer is physically connected to the surface of the airship skin, and the other surface of the composite heat insulation layer is physically connected to one surface of the solar cell array; the other surface of the solar cell array is covered by an electrochromic layer.

[0011] Optionally, the electrochromic layer includes an upper conductive electrode of the electrochromic film, an electrochromic active layer, an electrolyte layer, an ion storage layer, and a lower conductive electrode of the electrochromic film; wherein,

[0012] The electrochromic active layer, electrolyte layer, and ion storage layer are located between the upper conductive electrode and the lower conductive electrode of the electrochromic film.

[0013] Optionally, the solar cell array includes a transparent conductive layer, a photoactive layer, a hole transport layer, and a back electrode of the solar cell; wherein,

[0014] The photoelectric active layer and hole transport layer are located between the transparent conductive layer and the back electrode of the solar cell.

[0015] Optionally, one surface of the transparent conductive layer on the solar cell is physically connected to the conductive electrode under the electrochromic film; the other surface of the transparent conductive layer on the solar cell is physically connected to one surface of the photoactive layer.

[0016] One surface of the back electrode of the solar cell is physically connected to one surface of the hole transport layer, and the other surface of the back electrode of the solar cell is physically connected to one surface of the composite heat insulation layer.

[0017] Optionally, the voltage control module is electrically connected to the upper conductive electrode and the lower conductive electrode of the electrochromic film of the electrochromic layer via wires.

[0018] Optionally, the electrochromic layer is deposited on the surface of the solar cell array using magnetron sputtering.

[0019] Secondly, a novel solar cell method suitable for airships, the method comprising:

[0020] The voltage control module determines the current illumination data in real time; based on the illumination data, it adjusts the voltage applied to the electrochromic layer.

[0021] The electrochromic layer adjusts its color and transparency according to the applied voltage to change the light transmittance reaching the solar cell array.

[0022] Optionally, the voltage applied to the electrochromic layer can be adjusted based on illumination data, including:

[0023] Calculate the light intensity at the current moment based on the light data;

[0024] When the light intensity is less than or equal to the preset low light intensity threshold, it is determined to be a low light condition; or when the light intensity is greater than or equal to the preset high light intensity threshold, it is determined to be a high light condition.

[0025] The voltage applied to the electrochromic layer is adjusted based on whether the illumination is low or high.

[0026] Optionally, the voltage applied to the electrochromic layer can be adjusted based on low or high illumination conditions, including:

[0027] Under low light conditions, increase the voltage applied to the electrochromic layer;

[0028] Alternatively, under high light conditions, reduce the voltage applied to the electrochromic layer.

[0029] In this embodiment, by adding an electrochromic layer to the surface of the solar cell array, and by using a voltage control module to monitor the illumination data in real time and dynamically adjust the voltage applied to the electrochromic layer according to the illumination intensity, the transmittance of the electrochromic layer can be reduced under high irradiation conditions. This reduces the amount of light entering the solar cell, thereby reducing the heat generated by the solar cell and reducing waste heat generation. As waste heat generation is reduced, the heat acting on the airship capsule is reduced, thereby effectively reducing the temperature and pressure of the capsule, avoiding overheating and overpressure phenomena, and ensuring the structural safety of the airship.

[0030] It should be understood that the above general description and the following detailed description are exemplary and explanatory only, and do not limit this application. Attached Figure Description

[0031] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this application and, together with the description, serve to explain the principles of this application.

[0032] Figure 1 This is a schematic diagram of the system structure of a novel solar cell system suitable for airships provided in an embodiment of this application;

[0033] Figure 2 This is a schematic diagram of the internal structure of an electrochromic layer and a solar cell array provided in an embodiment of this application;

[0034] Figure 3 This is a schematic flowchart illustrating a novel solar cell method for airships provided in an embodiment of this application. Detailed Implementation

[0035] The following description and accompanying drawings fully illustrate specific embodiments of this application to enable those skilled in the art to practice them.

[0036] It should be understood that the described embodiments are merely some, not all, of the embodiments in this application. All other embodiments obtained by those skilled in the art based on the embodiments in this application without inventive effort are within the scope of protection of this application.

[0037] In the following description, when referring to the accompanying drawings, the same numbers in different drawings denote the same or similar elements unless otherwise indicated. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with this application. Rather, they are merely examples of systems and methods consistent with some aspects of this application as detailed in the appended claims.

[0038] In the description of this application, it should be understood that the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances. Furthermore, in the description of this application, unless otherwise stated, "multiple" refers to two or more. "And / or" describes the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent: A existing alone, A and B existing simultaneously, or B existing alone. The character " / " generally indicates that the preceding and following related objects are in an "or" relationship.

[0039] This application provides a novel solar cell system suitable for airships. In this embodiment, by adding an electrochromic layer to the surface of the solar cell array, and by using a voltage control module to monitor illumination data in real time and dynamically adjust the voltage applied to the electrochromic layer according to the illumination intensity, the transmittance of the electrochromic layer can be reduced under high irradiation conditions, thereby reducing the amount of light entering the solar cell, thus reducing the heat generation of the solar cell and reducing waste heat generation. As waste heat generation is reduced, the heat acting on the airship body is reduced, thereby effectively reducing the temperature and pressure of the body, avoiding overheating and overpressure phenomena, and ensuring the structural safety of the airship. The following is a detailed description using exemplary embodiments.

[0040] Please see Figure 1 , Figure 1 This is a schematic diagram of a novel solar cell system suitable for airships provided in an embodiment of this application. The system includes: an electrochromic layer for changing light transmittance, a solar cell array integrated into the airship, and a voltage control module; wherein, the electrochromic layer is physically connected to the solar cell array and covers the surface of the solar cell array, and the voltage control module is electrically connected to the electrochromic layer.

[0041] Electrochromism is a phenomenon in which the optical properties (reflectivity, transmittance, absorptivity, etc.) of a material undergo stable and reversible color changes under the influence of an applied electric field. This manifests as reversible changes in color and transparency. Materials exhibiting electrochromic properties are called electrochromic materials, and devices made from electrochromic materials are called electrochromic layers.

[0042] In some embodiments of this application, for example Figure 1 As shown, the system also includes: a composite heat insulation layer and the airship skin; wherein, one surface of the composite heat insulation layer is physically connected to the surface of the airship skin, and the other surface of the composite heat insulation layer is physically connected to one surface of the solar cell array; the other surface of the solar cell array is covered by an electrochromic layer.

[0043] In some embodiments of this application, for example Figure 2 As shown, the electrochromic layer includes an upper conductive electrode (1), an electrochromic active layer (2), an electrolyte layer (3), an ion storage layer (4), and a lower conductive electrode (5) of the electrochromic film; wherein the electrochromic active layer (2), the electrolyte layer (3), and the ion storage layer (4) are located between the upper conductive electrode (1) and the lower conductive electrode (5) of the electrochromic film.

[0044] The upper conductive electrode (1) of the electrochromic film serves as the upper electrode of the electrochromic layer, responsible for transmitting the voltage signal from the external circuit to the electrochromic active layer. Transparent conductive materials, such as indium tin oxide (ITO) or fluorine tin oxide (FTO), are used. These materials possess excellent conductivity and optical transparency, ensuring that light can pass through smoothly and reach the electrochromic active layer. During the electrochromic process, the upper conductive electrode applies voltage to the electrochromic active layer, causing a redox reaction that alters the color and transparency.

[0045] The electrochromic active layer (2) is the core component of the electrochromic layer, responsible for realizing the electrochromic function. The material is composed of electrochromic materials such as tungsten oxide (WO9), iridium oxide (IrO), and nickel oxide (NiO). These materials undergo redox reactions under an electric field, causing changes in their optical properties (such as color and transparency). When a voltage is applied, the materials in the electrochromic active layer undergo redox reactions, thereby changing their color and transparency. For example, tungsten oxide is transparent in its reduced state and appears deep blue or black in its oxidized state. This change can dynamically adjust the transmittance, controlling the intensity of light entering the solar cell.

[0046] The electrolyte layer (3) is an important component of the electrochromic layer, responsible for conducting ions and enabling the electrochromic reaction to proceed smoothly. The material is typically composed of solid electrolyte materials, such as lithium-ion-doped silicate glass or polymer electrolytes. These materials have good ion conductivity and can rapidly transfer ions. During the electrochromic process, the electrolyte layer allows ions to move between the electrochromic active layer and the ion storage layer. When a voltage is applied, ions move from the ion storage layer to the electrochromic active layer, or from the electrochromic active layer to the ion storage layer, thus achieving the reversibility of the electrochromic reaction.

[0047] The ion storage layer (4) stores ions to maintain the reversibility of the electrochromic reaction. The material is composed of materials capable of reversibly storing and releasing ions, such as lithium-ion-doped oxides (e.g., Li). x MnO (or polymers). During electrochromism, the ion storage layer can reversibly store and release ions. When the electrochromic active layer needs ions, the ion storage layer releases ions; when the electrochromic active layer releases ions, the ion storage layer absorbs ions. This mechanism ensures the reversibility and stability of the electrochromic reaction.

[0048] The lower conductive electrode (5) of the electrochromic film serves as the lower electrode of the electrochromic layer, responsible for transmitting the voltage signal from the external circuit to the electrochromic active layer. The material used is a transparent conductive material, such as indium tin oxide (ITO) or fluorine tin oxide (FTO). These materials possess excellent conductivity and optical transparency, ensuring that light can pass through smoothly and reach the electrochromic active layer. During the electrochromic process, the lower conductive electrode applies voltage to the electrochromic active layer, causing a redox reaction that alters the color and transparency. Simultaneously, the lower conductive electrode also supports and protects the electrochromic active layer.

[0049] In some embodiments of this application, for example Figure 2 As shown, the solar cell array includes a transparent conductive layer (6) on the solar cell, a photoelectric active layer (7), a hole transport layer (8), and a solar cell back electrode (9); wherein the photoelectric active layer (7) and the hole transport layer (8) are located between the transparent conductive layer (6) on the solar cell and the solar cell back electrode (9).

[0050] Specifically, one surface of the transparent conductive layer (6) on the solar cell is physically connected to the lower conductive electrode (5) of the electrochromic film; the other surface of the transparent conductive layer (6) on the solar cell is physically connected to one surface of the photoelectric active layer (7); one surface of the back electrode (9) of the solar cell is physically connected to one surface of the hole transport layer (8); and the other surface of the back electrode (9) of the solar cell is physically connected to one surface of the composite heat insulation layer (10).

[0051] The transparent conductive layer (6) on the solar cell serves as the upper electrode, responsible for collecting and transmitting photogenerated carriers (electrons and holes) to the external circuit. The material used is a transparent conductive material, such as indium tin oxide (ITO), fluorine tin oxide (FTO), or doped zinc oxide (ZnO). These materials possess excellent conductivity and optical transparency, ensuring that light can pass smoothly through and reach the photoactive layer. The transparent conductive layer not only allows light to penetrate to the photoactive layer but also efficiently collects photogenerated electrons generated in the photoactive layer and transmits them to the external circuit, thereby achieving electrical energy output.

[0052] The photoelectric active layer (7) is the core component of the solar cell, responsible for absorbing photons and converting them into photogenerated charge carriers (electrons and holes). The material is composed of semiconductor materials, such as silicon (Si), perovskite materials (e.g., CH4NHPbI4), and organic photovoltaic materials (e.g., P3HT:PCBM). These materials have suitable band gaps, enabling them to absorb sunlight and generate electron-hole pairs. When light shines on the photoelectric active layer, the energy of the photons is absorbed, exciting electrons to transition from the valence band to the conduction band, leaving holes. These photogenerated charge carriers are then separated and transported to the electrodes, forming a current.

[0053] The hole transport layer (8) is responsible for transporting holes generated in the photoelectric active layer to the back electrode of the solar cell. The material is composed of materials with high hole mobility, such as polytriphenylamine (PTAA), organic materials like 2,2',7,7'-tetratetra[N,N-di(4-methoxyphenyl)amino]-9,9'-spirodifluorene (Spiro-OMeTAD), or doped nickel oxide (NiO). x Inorganic materials such as [list of materials]. The hole transport layer effectively transports holes from the photoelectric active layer to the back electrode while preventing the reverse transport of electrons, thereby improving the efficiency and stability of the solar cell. It also protects the photoelectric active layer from oxidation or other chemical damage.

[0054] The back electrode (9) of the solar cell serves as the lower electrode, responsible for collecting holes and transmitting them to the external circuit. It is typically made of metals such as gold (Au), silver (Ag), and aluminum (Al). These materials have excellent conductivity, enabling efficient hole collection and transmission. The back electrode not only collects holes but also supports the entire solar cell structure. It transmits holes to the external circuit, forming a complete current loop, thereby enabling electrical energy output.

[0055] Specifically, for example Figure 2 As shown, one side of the airship skin (11) is physically connected to the other surface of the composite insulation layer (10).

[0056] In some embodiments of this application, the voltage control module is electrically connected to the upper conductive electrode and the lower conductive electrode of the electrochromic film of the electrochromic layer via wires.

[0057] In some embodiments of this application, the electrochromic layer is deposited on the surface of the solar cell array using magnetron sputtering. The multilayer structure fabricated using magnetron sputtering technology exhibits excellent response speed and reversibility; combined with matrix voltage control, it enables zoned management and dynamic reconfiguration of the solar cell array, further enhancing the modularity of thermal management.

[0058] In this embodiment, an electrochromic layer is integrated on the surface of the solar cell array to achieve dynamic control of light transmittance. This system effectively addresses the overheating and overpressure problems of the airship caused by seasonal changes in solar irradiance. Especially under high irradiance, it can actively reduce incident energy, decrease waste heat generation, and protect the airship structure.

[0059] In this embodiment, by adding an electrochromic layer to the surface of the solar cell array, and by using a voltage control module to monitor the illumination data in real time and dynamically adjust the voltage applied to the electrochromic layer according to the illumination intensity, the transmittance of the electrochromic layer can be reduced under high irradiation conditions. This reduces the amount of light entering the solar cell, thereby reducing the heat generated by the solar cell and reducing waste heat generation. As waste heat generation is reduced, the heat acting on the airship capsule is reduced, thereby effectively reducing the temperature and pressure of the capsule, avoiding overheating and overpressure phenomena, and ensuring the structural safety of the airship.

[0060] Please see Figure 3 This is a flowchart illustrating a novel solar cell method suitable for airships, as provided in this application embodiment. Figure 3 As shown, the detection method in this application embodiment may include the following steps:

[0061] S101, the voltage control module determines the current illumination data in real time; based on the illumination data, it adjusts the voltage applied to the electrochromic layer.

[0062] In some embodiments of this application, the specific process of adjusting the voltage applied to the electrochromic layer based on illumination data includes: calculating the illumination intensity at the current moment based on illumination data; determining a low illumination condition when the illumination intensity is less than or equal to a preset low illumination intensity threshold; or determining a high illumination condition when the illumination intensity is greater than or equal to a preset high illumination intensity threshold; and adjusting the voltage applied to the electrochromic layer based on the low illumination condition or the high illumination condition.

[0063] Specifically, the process of adjusting the voltage applied to the electrochromic layer based on low or high light conditions includes: increasing the voltage applied to the electrochromic layer under low light conditions; or decreasing the voltage applied to the electrochromic layer under high light conditions.

[0064] In one possible implementation, assume the airship's solar array is equipped with four light sensors, located in the four directions of the array (east, south, west, and north). Each sensor monitors the light intensity in its direction in real time and transmits the data to the voltage control module. At a certain moment, the light intensity data collected by the light sensors is as follows: East direction: 800 W / m 2 South direction: 1200W / m 2 West direction: 700W / m 2 North direction: 300W / m 2 The voltage control module calculated the average illuminance to be 700 W / m². 2 Based on the preset threshold (low light threshold is 300W / m²), 2 The high light threshold is 1000W / m 2 The voltage control module determines that the current lighting conditions are moderate. Based on an average light intensity of 700W / m², the voltage control module... 2 The voltage applied to the electrochromic layer is dynamically adjusted. Assuming calculations show that the voltage should be adjusted to 2.5V to make the light transmittance of the electrochromic layer approximately 45%.

[0065] S102, the electrochromic layer adjusts its color and transparency according to the applied voltage value to change the light transmittance reaching the solar cell array.

[0066] For example, when the electrochromic layer receives a voltage of 2.5V, its color and transparency change, and the light transmittance is adjusted to 45%. At this time, the intensity of light entering the solar cell is controlled at a moderate level, which ensures sufficient power generation efficiency while avoiding excessive heat generation.

[0067] In this embodiment, by adding an electrochromic layer to the surface of the solar cell array, and by using a voltage control module to monitor the illumination data in real time and dynamically adjust the voltage applied to the electrochromic layer according to the illumination intensity, the transmittance of the electrochromic layer can be reduced under high irradiation conditions. This reduces the amount of light entering the solar cell, thereby reducing the heat generated by the solar cell and reducing waste heat generation. As waste heat generation is reduced, the heat acting on the airship capsule is reduced, thereby effectively reducing the temperature and pressure of the capsule, avoiding overheating and overpressure phenomena, and ensuring the structural safety of the airship.

[0068] Those skilled in the art will understand that all or part of the processes in the above embodiments can be implemented by a computer program instructing related hardware. The program for the novel solar cell suitable for airships can be stored in a computer-readable storage medium. When executed, the program can include the processes of the embodiments of the above methods. The storage medium for the program of the novel solar cell suitable for airships can be a magnetic disk, optical disk, read-only memory, or random access memory, etc.

[0069] The above-disclosed embodiments are merely preferred embodiments of this application and should not be construed as limiting the scope of this application. Therefore, any equivalent variations made in accordance with the claims of this application shall still fall within the scope of this application.

[0070] Those skilled in the art will understand that all or part of the processes in the above embodiments can be implemented by a computer program instructing related hardware. The program for the novel solar cell suitable for airships can be stored in a computer-readable storage medium. When executed, the program can include the processes of the embodiments of the above methods. The storage medium for the novel solar cell suitable for airships can be a magnetic disk, optical disk, read-only memory, or random access memory, etc.

[0071] The above-disclosed embodiments are merely preferred embodiments of this application and should not be construed as limiting the scope of this application. Therefore, any equivalent variations made in accordance with the claims of this application shall still fall within the scope of this application.

Claims

1. A novel solar cell system suitable for airships, characterized in that, The system includes: An electrochromic layer used to change light transmittance, a solar cell array integrated into the airship, and a voltage control module; among them, The electrochromic layer is physically connected to the solar cell array and covers the surface of the solar cell array. The voltage control module is electrically connected to the electrochromic layer.

2. The system according to claim 1, characterized in that, The system also includes: Composite insulation layer, airship skin; among them, One surface of the composite heat insulation layer is physically connected to the surface of the airship skin, and the other surface of the composite heat insulation layer is physically connected to one surface of the solar cell array; the other surface of the solar cell array is covered by the electrochromic layer.

3. The system according to claim 2, characterized in that, The electrochromic layer includes an upper conductive electrode of the electrochromic film, an electrochromic active layer, an electrolyte layer, an ion storage layer, and a lower conductive electrode of the electrochromic film; wherein... The electrochromic active layer, electrolyte layer, and ion storage layer are located between the upper conductive electrode and the lower conductive electrode of the electrochromic film.

4. The system according to claim 3, characterized in that, The solar cell array includes a transparent conductive layer, a photoactive layer, a hole transport layer, and a back electrode for the solar cell; wherein... The photoelectric active layer and hole transport layer are located between the transparent conductive layer and the back electrode of the solar cell.

5. The system according to claim 4, characterized in that, One surface of the transparent conductive layer on the solar cell is physically connected to the conductive electrode under the electrochromic film; the other surface of the transparent conductive layer on the solar cell is physically connected to one surface of the photoactive layer. One surface of the back electrode of the solar cell is physically connected to one surface of the hole transport layer, and the other surface of the back electrode of the solar cell is physically connected to one surface of the composite heat insulation layer.

6. The system according to claim 4, characterized in that, The voltage control module is electrically connected to the upper conductive electrode and the lower conductive electrode of the electrochromic film of the electrochromic layer via wires.

7. The system according to claim 1, characterized in that, The electrochromic layer is deposited on the surface of the solar cell array using magnetron sputtering.

8. A novel solar cell method suitable for airships, implemented using the method according to any one of claims 1-7, characterized in that, The method includes: The voltage control module determines the current illumination data in real time; and adjusts the voltage applied to the electrochromic layer according to the illumination data. The electrochromic layer adjusts its color and transparency according to the applied voltage value to change the light transmittance reaching the solar cell array.

9. The method according to claim 8, characterized in that, The step of adjusting the voltage applied to the electrochromic layer according to the illumination data includes: Calculate the light intensity at the current moment based on the light data; When the light intensity is less than or equal to a preset low light intensity threshold, it is determined to be a low light condition; or when the light intensity is greater than or equal to a preset high light intensity threshold, it is determined to be a high light condition. The voltage applied to the electrochromic layer is adjusted based on the low light conditions or the high light conditions.

10. The method according to claim 9, characterized in that, Adjusting the voltage applied to the electrochromic layer based on the low illumination conditions or the high illumination conditions includes: Under the low light conditions, the voltage applied to the electrochromic layer is increased; Alternatively, under the high light conditions, the voltage applied to the electrochromic layer can be reduced.

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