Solar spectrum total reflection surface and pasting method of reflection layer

Abstract

The invention discloses a solar spectrum total reflection surface and a pasting method of a reflection layer, which can be used in the technical field of solar energy utilization, and the solar spectrum total reflection surface comprises a main body frame and a reflection layer, the main body frame is made of an aeronautical aluminum alloy material; the reflecting layer is composed of N multi-layer composite glass reflecting mirrors, the whole reflecting layer is of a paraboloid or spherical surface structure, the reflecting layer is arranged on the reflecting surface substrate of the main body frame, total reflection of a solar spectrum ranging from 0.3 micrometer to 3.0 micrometers is achieved, and the reflectivity of the reflecting layer is not lower than 94%; n is a positive integer. Therefore, the high-reflectivity reflecting layer with a paraboloid or spherical structure is designed while an aviation aluminum alloy material is selected as a main body frame material, so that the utilization efficiency of solar energy is improved while the structural stability of the reflecting surface is ensured.

Description

Technical Field

[0001] The present application relates to the technical field of solar energy utilization, and in particular to a solar spectrum total reflection surface and a method for pasting a reflection layer. Background Art

[0002] Solar energy, a renewable resource, refers to the sun's thermal radiation energy, primarily manifested in sunlight. In the efficient utilization and research of solar energy, large reflectors are the core components for achieving high-powered solar concentration.

[0003] Existing solar reflectors are small in size, making them inadequate for large-scale solar energy collection. Even larger reflectors often suffer from structural design and material selection issues, preventing them from fully reflecting the solar spectrum. This leads to structural instability and insufficient solar energy utilization efficiency.

[0004] Therefore, how to improve the utilization efficiency of solar energy while ensuring the structural stability of the reflective surface is a problem that those skilled in the art urgently need to solve. Summary of the Invention

[0005] Based on the above problems, the present application provides a solar spectrum total reflection surface and a method for pasting a reflection layer. While selecting aviation aluminum alloy material as the main frame material, a reflection layer with high reflectivity, parabolic or spherical structure is designed, thereby improving the utilization efficiency of solar energy while ensuring the stability of the reflection surface structure.

[0006] In a first aspect, an embodiment of the present application provides a solar spectrum total reflection surface, comprising: a main frame and a reflection layer;

[0007] The main frame is made of aviation aluminum alloy;

[0008] The reflective layer is composed of N multi-layer composite glass reflectors, which have a parabolic structure or a spherical structure as a whole. It is arranged on the reflective surface base of the main frame to achieve total reflection of the solar spectrum between 0.3μm and 3.0μm, and the reflectivity of the reflective layer is not less than 94%; N is a positive integer.

[0009] Optionally, the diameter of the reflective layer is 10m;

[0010] The focal length of the parabolic structure corresponding to the reflective layer is 15m;

[0011] The curvature equation of the parabolic structure is x 2 +y 2 =60z.

[0012] Optionally, the aviation aluminum alloy material used for the main frame has a yield strength of not less than 300 MPa and a tensile strength of not less than 400 MPa.

[0013] Optionally, the multi-layer composite glass reflector comprises: a glass mirror layer, a silver film layer, a dielectric film layer and a nano-scale silicon dioxide-organic silicon composite protective film layer;

[0014] The glass mirror layer is made of high-transmittance optical glass, and the transmittance of the optical glass is not less than 92%;

[0015] The silver film layer, the dielectric film layer and the nano-scale silicon dioxide-organic silicon composite protective film layer are sequentially arranged on one side of the glass mirror layer;

[0016] The dielectric film layer is made of silicon dioxide and titanium dioxide.

[0017] Optionally, the parabolic structure is preset with N unit surfaces;

[0018] Each multi-layer composite glass reflector is designed by CNC machining equipment corresponding to a unit surface on the parabolic structure;

[0019] The shape error between the multi-layer composite glass reflector and the corresponding unit surface is within 0.1mm.

[0020] Optionally, the reflective layer is adhered to the reflective surface substrate by structural adhesive;

[0021] The tensile strength of the structural adhesive is not less than 15 MPa, and the shear strength is not less than 10 MPa.

[0022] Optionally, the main frame is anodized, and an oxide film with a thickness of 10 μm to 15 μm exists on the outer surface.

[0023] Optionally, the silver film layer, the dielectric film layer and the nano-scale silicon dioxide-organic silicon composite protective film layer are prepared by magnetron sputtering coating technology.

[0024] Optionally, the focus position error of the parabolic structure corresponding to the reflective layer is within ±20 mm.

[0025] In a second aspect, an embodiment of the present application provides a method for pasting a reflective layer, the method being used for pasting the reflective layer and the main frame, the method comprising:

[0026] The reflective surface base of the main frame is sequentially subjected to sandblasting, chemical cleaning and drying;

[0027] The reflective layer is bonded to the reflective surface substrate using structural adhesive by dispensing or scraping with a laser aligner, and a pressure of 0.1 MPa to 0.2 MPa is applied to the reflective layer to control the adhesive layer thickness to be between 0.2 mm and 0.3 mm. The ratio of the main agent to the curing agent in the structural adhesive is between 10:1 and 15:1.

[0028] Determining whether the surface flatness of the reflective layer is within ±0.05 mm;

[0029] If so, the structural adhesive is cured for 24 to 48 hours in an environment with a temperature between 20° C. and 25° C. and a humidity between 40% and 60%.

[0030] It can be seen from the above technical solutions that compared with the existing technology, this application has the following advantages:

[0031] The solar spectrum total reflection surface provided in this application comprises: a main frame and a reflective layer; the main frame is made of aviation aluminum alloy; the reflective layer is composed of N multi-layer composite glass reflectors, with an overall parabolic or spherical structure, arranged on the reflective surface base of the main frame, achieving total reflection of the solar spectrum between 0.3μm and 2.5μm, with a reflectivity of no less than 94%; N is a positive integer. Thus, while aviation aluminum alloy is used as the main frame material, a high-reflectivity, parabolic or spherical reflective layer is designed, thereby ensuring the structural stability of the reflective surface while improving the efficiency of solar energy utilization. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0033] Figure 1 A schematic structural diagram of a solar spectrum total reflection surface provided in an embodiment of the present application;

[0034] Figure 2 A schematic diagram of a parabola curvature equation provided in an embodiment of the present application;

[0035] Figure 3 A schematic structural diagram of a multi-layer composite glass reflector provided in an embodiment of the present application;

[0036] Figure 4 A schematic diagram of laminating a reflective layer and a reflective surface substrate provided in an embodiment of the present application;

[0037] Figure 5 A flowchart of a method for pasting a reflective layer provided in an embodiment of the present application. DETAILED DESCRIPTION

[0038] As previously mentioned, existing solar spectrum reflectors suffer from structural stability and insufficient solar energy utilization efficiency. Specifically, existing large-scale reflectors are made of materials with low reflectivity, preventing them from fully reflecting the solar spectrum. Furthermore, their non-parabolic structure prevents them from accurately focusing sunlight, leading to insufficient solar energy utilization efficiency. Furthermore, these structural deficiencies affect the reflector's structural stability, reducing its reflective effectiveness and service life.

[0039] To solve the above problems, an embodiment of the present application provides a total solar spectrum reflection surface, which includes: a main frame and a reflection layer; the main frame is made of aviation aluminum alloy material; the reflection layer is composed of N multi-layer composite glass reflectors, which have a parabolic structure or a spherical structure as a whole and are arranged on the reflection surface base of the main frame to achieve total reflection of the solar spectrum between 0.3μm and 2.5μm, and the reflectivity of the reflection layer is not less than 94%; N is a positive integer.

[0040] In this way, while selecting aviation aluminum alloy material as the main frame material, a reflective layer with high reflectivity, parabolic or spherical structure is designed, thereby improving the utilization efficiency of solar energy while ensuring the stability of the reflective surface structure.

[0041] It should be noted that the solar spectrum total reflection surface and the method for attaching a reflective layer provided in this application can be applied to the field of solar energy utilization technology. The above is only an example and does not limit the application field of the solar spectrum total reflection surface and the method for attaching a reflective layer provided in this application.

[0042] In order to make the purpose, technical solutions and advantages of the embodiments of the present application more clear, the technical solutions in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the embodiments described are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of this application.

[0043] Figure 1 This is a schematic diagram of the structure of a solar spectrum total reflection surface provided in an embodiment of the present application. Figure 1 As shown, the solar spectrum total reflection surface includes: a main frame 100 and a reflection layer 200;

[0044] The main frame 100 is made of aviation aluminum alloy;

[0045] The reflective layer 200 is composed of N multi-layer composite glass reflectors, which have a parabolic structure or a spherical structure as a whole. It is arranged on the reflective surface base of the main frame 100 to achieve total reflection of the solar spectrum between 0.3μm and 2.5μm, and the reflectivity of the reflective layer 200 is not less than 94%; N is a positive integer.

[0046] Specifically, high-strength, lightweight aviation aluminum alloy material can be used as the main frame 100, which can ensure the structural stability of the reflective surface during long-term use, thereby increasing service life and reducing maintenance costs. Aviation aluminum alloy material is an ultra-high-strength deformed aluminum alloy widely used in the aerospace industry. The main types include Al-Cu and Al-Zn alloys, which have the advantages of low density, high strength, and good corrosion resistance. While ensuring the structural strength of the reflective surface, it can reduce the overall weight and facilitate installation and maintenance. Figure 1 As shown, the main frame 100 may include a supporting fin structure and a reflective surface base. The supporting fin structure is connected to the reflective surface base to support the reflective surface base toward the sunlight, and the reflective surface base is used to support the reflective layer 200 toward the sunlight. In addition, Figure 1 Only a convex mirror function is given in the figure. It is understandable that the reflective surface can also have a concave mirror function. Figure 1 Not drawn in the figure. The reflective layer 200 uses a multi-layer composite glass reflector. By optimizing the coating structure and material selection, it achieves total reflection of the solar spectrum. Compared with traditional reflective surface materials, it greatly improves the efficiency of solar energy collection and provides a strong guarantee for the efficient use of solar energy. In addition, due to the high difficulty of preparing large multi-layer composite glass reflectors using existing technology, for this reason, the embodiment of the present application uses N small-area multi-layer composite glass reflectors to form a reflective layer 200 with a parabolic structure or a spherical structure. The reflectivity of the reflective layer 200 is not less than 94%, and it can achieve total reflection of the solar spectrum between 0.3μm and 2.5μm.

[0047] As an embodiment, regarding how to design the structure of the reflective layer 200, the diameter of the reflective layer 200 is 10m;

[0048] The focal length of the parabolic structure corresponding to the reflective layer 200 is 15m;

[0049] The curvature equation of the parabolic structure is x 2 +y 2 =60z.

[0050] Specifically, the reflective layer 200 provided in the embodiment of the present application is a parabolic structure. Figure 2 A schematic diagram of a parabola curvature equation provided in an embodiment of the present application. Figure 2 As shown, a three-dimensional rectangular coordinate system is established with the vertex of the (parabola) structure of the reflective layer 200 as the origin, wherein the axis of symmetry of the parabola is the z-axis, and the plane perpendicular to the axis of symmetry is the xy plane. Combined with the definition of a parabola, for a parabola rotating around the z-axis, its parabola equation on the xz plane or the yz plane is x2=4fz. Furthermore, since the diameter of its reflective layer 200 is 10m (large-scale design, meeting the needs of large-scale utilization of solar energy), and in order to achieve efficient concentration, after a large number of optical simulations and actual tests, it is determined that its corresponding parabola structure is better when the focal length f=15m. Thus, the expression of a parabola with a diameter of 10m on the xz plane or the yz plane is x2=4fz. 2 =60z, and the curvature equation of the three-dimensional paraboloid structure after rotation along the z-axis can be expressed as x 2 +y 2 =60z.

[0051] As an embodiment, regarding how to design the main frame 100, the aviation aluminum alloy material used in the main frame 100 has a yield strength of not less than 300 MPa and a tensile strength of not less than 400 MPa.

[0052] Specifically, the aviation aluminum alloy material used in the main frame 100 is required to have a yield strength of not less than 300 MPa and a tensile strength of not less than 400 MPa, so that the main frame 100 can withstand various external forces to which the large reflective surface is subjected during use, such as stress caused by wind, gravity, and temperature changes.

[0053] As an embodiment, regarding how to design a multi-layer composite glass reflector, the multi-layer composite glass reflector includes: a glass mirror layer 210, a silver film layer 220, a dielectric film layer 230 and a nano-scale silicon dioxide-organic silicon composite protective film layer 240;

[0054] The glass mirror layer 210 is made of high-transmittance optical glass, and the transmittance of the optical glass is not less than 92%;

[0055] The silver film layer 220, the dielectric film layer 230 and the nano-scale silicon dioxide-organic silicon composite protective film layer 240 are sequentially arranged on one side of the glass mirror layer 210;

[0056] The dielectric film layer 230 is made of silicon dioxide and titanium dioxide.

[0057] Figure 3 A schematic diagram of the structure of a multi-layer composite glass reflector provided in an embodiment of the present application. Figure 3As shown, the glass mirror layer 210 is made of high-transmittance optical glass, with a transmittance of no less than 92%, thereby reducing light absorption and scattering within the glass. Furthermore, one side of the glass mirror layer 210 is coated with multiple layers of metal-dielectric composite films. The bottom layer is a silver (Ag) film 220 with extremely high visible and near-infrared reflectivity, effectively reflecting the two main energy components of the solar spectrum. The middle layer is a dielectric film layer 230 composed of silicon dioxide (SiO2) and titanium dioxide (TiO2). By precisely controlling the thickness and number of dielectric film layers, an optical interference effect is created, further improving reflectivity and broadening the reflected spectral range, achieving total reflection of the solar spectrum (wavelength range of approximately 0.3-2.5μm). Finally, the top layer is a wear-resistant and anti-fouling nano-scale silicon dioxide-organic silicon composite protective film 240, which effectively protects the reflective surface from environmental factors such as dust, rain, and wind. It also improves surface wear resistance and extends the service life of the reflective surface.

[0058] As an implementation method, regarding how to design each multi-layer composite glass reflector, the parabolic structure is preset with N unit surfaces;

[0059] Each multi-layer composite glass reflector is designed by CNC machining equipment corresponding to a unit surface on the parabolic structure;

[0060] The shape error between the multi-layer composite glass reflector and the corresponding unit surface is within 0.2mm.

[0061] Specifically, because the reflective layer 200 needs to be composed of multiple multi-layer composite glass reflectors, in order to ensure the accuracy of the parabola structure during the actual processing of the multi-layer composite glass reflector, the parabola can be divided into multiple tiny unit surfaces, and then, according to the size, shape and processing accuracy requirements of each unit surface, the curvature equation "x 2 +y 2 =60z", the shape of the multi-layer composite glass reflector corresponding to each unit surface is precisely processed, so that the shape error of the entire reflective surface is controlled within ±0.2mm, to ensure that the sunlight can be accurately focused at the focal position. In other words, if the parabolic structure is preset to be divided into N unit surfaces, then the multi-layer composite glass reflector corresponding to each unit surface will be processed separately using CNC machining equipment according to the processing requirements of each unit surface, thereby obtaining N multi-layer composite glass reflectors that can be assembled into a complete reflective layer 200, and the shape error between each multi-layer composite glass reflector and its corresponding unit surface is within 0.1mm, thereby being able to accurately focus the sunlight to the focal position, and the focusing accuracy is improved by more than 30% compared with the existing technology, effectively improving the performance of systems such as solar concentrating power generation and high-temperature heat utilization.

[0062] As an embodiment, regarding how to design the structural adhesive 300, the reflective layer 200 is adhered to the reflective surface substrate by the structural adhesive 300;

[0063] The tensile strength of the structural adhesive 300 is not less than 15 MPa, and the shear strength is not less than 10 MPa.

[0064] Specifically, the embodiment of the present application uses structural adhesive 300 to connect the reflective layer 200 to the reflective surface substrate. The structural adhesive 300 is a high-strength structural adhesive with a tensile strength of no less than 15 MPa and a shear strength of no less than 10 MPa, ensuring a secure bond between the reflective layer 200 and the reflective surface substrate while maintaining light transmission. Figure 4 A schematic diagram of a reflective layer and a reflective surface substrate provided in an embodiment of the present application. Figure 4 As shown, the reflection layer 200 is bonded to the reflection surface substrate 110 by bonding the back surface of N multi-layer composite glass reflectors (the outermost film of the multi-layer metal-dielectric composite film, i.e., the nano-scale silicon dioxide-organic silicon composite protective film layer 240) to the reflection surface substrate 110 through an adhesive (structural adhesive 300).

[0065] As an embodiment, regarding how to design the main frame 100, the main frame 100 is subjected to anodizing treatment, and an oxide film with a thickness of 10 μm to 15 μm exists on the outer surface.

[0066] Specifically, the main frame 100 needs to be processed by cutting, bending, welding and other processing techniques on aviation aluminum alloy plates using CNC processing equipment according to the design size and shape of the reflective surface to produce the main frame 100 of the reflective surface. During the processing, the dimensional accuracy of the main structure needs to be strictly controlled to ensure that the diameter error of the frame is controlled within ±5mm and the connection angle error of each component is controlled within ±0.5°. Furthermore, the main frame 100 needs to be surface treated, including anodizing, to form an oxide film with a thickness of 10-15μm on the outer surface of the main frame 100, thereby improving the corrosion resistance and wear resistance of the main frame 100.

[0067] As an embodiment, with respect to how to prepare a multi-layer composite coating, the silver film layer 220 , the dielectric film layer 230 and the nano-scale silicon dioxide-organic silicon composite protective film layer 240 are prepared by magnetron sputtering coating technology.

[0068] Specifically, during the preparation of the reflective layer 200, high-transmittance optical glass is first cut into N small pieces of appropriate size and shape, which can be assembled into the complete reflective layer 200 and conform to the required parabolic structure of the reflective surface. Next, a multilayer metal-dielectric composite film is deposited on the optical glass surface using magnetron sputtering technology. Specifically, the optical glass is first heated to 150-200°C in a vacuum environment. Then, a silver film layer 220, a dielectric film layer 230, and a nano-scale silica-organic silicon composite protective film layer 240 are sequentially sputtered onto the surface. By precisely controlling parameters such as sputtering time, sputtering power, and gas flow, the thickness of each film layer is controlled, ultimately forming a multilayer composite film with total reflection performance. After coating, each multilayer composite glass reflector undergoes quality inspection, including reflectivity and film thickness testing, to ensure that the reflectivity and film thickness meet design requirements.

[0069] As an implementation manner, with respect to how to design the reflective layer 200 , the focus position error of the parabolic structure corresponding to the reflective layer 200 is within ±20 mm.

[0070] Specifically, the optical performance of the solar spectrum total reflection surface must meet the requirement of an average reflectivity of no less than 94% across the solar spectrum, and the error between the actual focal position of the parabolic structure of the reflective layer 200 and the ideal focal position must be controlled within ±20mm. The overall structural performance of the solar spectrum total reflection surface must ensure that the stress in each part does not exceed the allowable stress of the material, and the tensile strength of the glass mirror at the bonding point to the substrate must be no less than 15MPa, and the shear strength must be no less than 10MPa.

[0071] In summary, the solar spectrum total reflection surface provided in this application comprises: a main frame and a reflective layer; the main frame is made of aviation aluminum alloy; the reflective layer is composed of N multi-layer composite glass reflectors, with an overall parabolic or spherical structure, disposed on the reflective surface base of the main frame, achieving total reflection of the solar spectrum between 0.3μm and 2.5μm, with a reflectivity of no less than 94%; N is a positive integer. Thus, while aviation aluminum alloy is used as the main frame material, a high-reflectivity, parabolic or spherical reflective layer is designed, thereby improving solar energy utilization efficiency while ensuring the structural stability of the reflective surface.

[0072] Figure 5 This is a flow chart of a method for pasting a reflective layer provided in an embodiment of the present application. Figure 5 As shown, the method is used for pasting the above-mentioned reflective layer and the main frame, and the method includes:

[0073] S1: performing sandblasting, chemical cleaning and drying on the reflective surface base of the main frame in sequence.

[0074] In actual application, the reflective surface base in the main frame needs to be surface treated before pasting the glass mirror. Specifically, it is first sandblasted. Aluminum oxide sand particles with a particle size between 0.1-0.3mm are used to sandblast the surface of the reflective surface base at a pressure of 0.3-0.5MPa to remove surface oil, oxide layer and other impurities, while increasing the surface roughness and improving the pasting effect. The reflective surface base is then chemically cleaned by soaking it in a mixed solution containing sodium hydroxide and sodium phosphate at a temperature of 50-60°C for 10-15 minutes to further remove residual impurities on the surface. Finally, it is rinsed with deionized water and dried at a temperature of 100-120°C for 30-40 minutes to make the surface of the reflective surface base dry and clean, laying the foundation for the subsequent pasting of the glass mirror.

[0075] S2: Combined with a laser positioning instrument, the reflective layer is bonded to the reflective surface base using structural adhesive by dispensing or scraping, and a pressure of 0.1 MPa to 0.2 MPa is applied to the reflective layer to control the thickness of the adhesive layer to be between 0.2 mm and 0.3 mm; the ratio of the main agent to the curing agent in the structural adhesive is between 10:1 and 15:1.

[0076] In actual application, N processed multi-layer composite glass reflectors are placed on the reflective surface substrate according to the designed arrangement. A high-precision positioning device, such as a laser positioning device, is used to ensure the accurate position of each multi-layer composite glass reflector, and the gap between adjacent multi-layer composite glass reflectors is controlled to be 0.5-1mm. Furthermore, the prepared structural adhesive is evenly applied to the back of the multi-layer composite glass reflector and the surface of the reflective surface substrate by dispensing or scraping, and the thickness of the adhesive layer is controlled to be 0.2-0.3mm. The multi-layer composite glass reflector and the reflective surface substrate are quickly bonded and a certain pressure (pressure range is 0.1-0.2MPa) is applied to ensure that the adhesive fully fills the gap between the multi-layer composite glass reflector and the reflective surface substrate and eliminates air bubbles. The structural adhesive needs to be pre-mixed with the main agent and curing agent in a certain ratio according to the instructions, generally between 10:1 and 15:1, and then fully stirred (stirring time is not less than 5 minutes) to ensure that the adhesive components are evenly mixed.

[0077] S3: Determine whether the surface flatness of the reflective layer is within ±0.05 mm.

[0078] In actual applications, during the pasting process, each multi-layer composite glass reflector needs to be pasted using a flatness detection device, such as an interferometer, to detect in real time whether the flatness of the multi-layer composite glass reflector surface is within ±0.05mm. If not, the pressure and thickness of the adhesive layer are adjusted to ensure that the flatness error of the multi-layer composite glass reflector surface is controlled within ±0.05mm.

[0079] S4: If yes, curing the structural adhesive in an environment with a temperature between 20° C. and 25° C. and a humidity between 40% and 60% for 24 to 48 hours.

[0080] In practical applications, if the flatness of the multi-layer composite glass reflector surface detected by interferometer is within ±0.05mm, it means that the bonding is complete. The bonded reflective surface is placed in an environment with a temperature of 20-25℃ and a humidity of 40-60% for 24-48 hours to fully cure the structural adhesive and form a firm bonding connection.

[0081] Furthermore, the prepared reflective surface was tested for spectral reflectivity using a spectral reflectivity meter. The reflectivity was measured at multiple points within the solar spectrum (0.3-2.5μm) to ensure an average reflectivity of no less than 94%. A laser collimator was also used to test the reflective surface's focusing effect. A laser beam simulating sunlight was directed onto the reflective surface, and the convergence of the light to the focal point was observed. The deviation in the focal position was measured to ensure that the focus position error was within ±10mm.

[0082] Furthermore, the structural strength of the reflective surface can be tested by applying simulated external forces such as wind and gravity to the reflective surface to detect deformation and structural stability. Stress sensors are used to measure the stress distribution of the reflective surface during the stress process, ensuring that the stress in each part does not exceed the allowable stress of the material. At the same time, the adhesion between the multi-layer composite glass reflector and the reflective surface substrate is checked. The strength of the adhesion is tested through tensile and shear tests to ensure that it meets design requirements. After testing and debugging, any non-compliant parts are adjusted and repaired until the optical and structural performance of the reflective surface fully meets the design standards and is ready for use.

[0083] In summary, the method for pasting the reflective layer provided in the present application is to first perform sandblasting, chemical cleaning and drying on the reflective surface base of the main frame in sequence. Then, in combination with a laser positioning instrument, the reflective layer is bonded to the reflective surface base using structural adhesive by dispensing or scraping, and a pressure of 0.1MPa to 0.2MPa is applied to the reflective layer to control the thickness of the adhesive layer to be between 0.2mm and 0.3mm. Among them, the ratio of the main agent to the curing agent in the structural adhesive is between 10:1 and 15:1. Finally, determine whether the surface flatness of the reflective layer is within ±0.05mm. If so, cure the structural adhesive for 24 to 48 hours in an environment with a temperature between 20℃ and 25℃ and a humidity between 40% and 60%. In this way, through innovative material selection and a scientific reflective surface pasting method, efficient total reflection of the solar spectrum is achieved, thereby improving the utilization efficiency of solar energy while ensuring the stability of the reflective surface structure.

[0084] The above description of the disclosed embodiments is intended to enable one skilled in the art to implement or use the present application. Various modifications to these embodiments will be readily apparent to one skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, the present application is not limited to the embodiments shown herein, but is intended to conform to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A solar spectrum total reflection surface, characterized in that: The solar spectrum total reflection surface comprises: a main frame and a reflection layer; The main frame is made of aviation aluminum alloy; The reflective layer is composed of N multi-layer composite glass reflectors, which have a parabolic structure or a spherical structure as a whole. It is arranged on the reflective surface base of the main frame to achieve total reflection of the solar spectrum between 0.3μm and 2.5μm, and the reflectivity of the reflective layer is not less than 94%; N is a positive integer.

2. The solar spectrum total reflection surface according to claim 1, characterized in that: The diameter of the reflective layer is 10m; The focal length of the parabolic structure corresponding to the reflective layer is 15m; The curvature equation of the parabolic structure is x 2 +y 2 =60z.

3. The solar spectrum total reflection surface according to claim 1, characterized in that: The aviation aluminum alloy material used in the main frame has a yield strength of not less than 300 MPa and a tensile strength of not less than 400 MPa.

4. The solar spectrum total reflection surface according to claim 1, characterized in that: The multi-layer composite glass reflector comprises: a glass mirror layer, a silver film layer, a dielectric film layer and a nano-scale silicon dioxide-organic silicon composite protective film layer; The glass mirror layer is made of high-transmittance optical glass, and the transmittance of the optical glass is not less than 92%; The silver film layer, the dielectric film layer and the nano-scale silicon dioxide-organic silicon composite protective film layer are sequentially arranged on one side of the glass mirror layer; The dielectric film layer is made of silicon dioxide and titanium dioxide.

5. The solar spectrum total reflection surface according to claim 2, characterized in that: The parabolic structure is preset with N unit surfaces; Each multi-layer composite glass reflector is designed by CNC machining equipment corresponding to a unit surface on the parabolic structure; The shape error between the multi-layer composite glass reflector and the corresponding unit surface is within 0.1mm.

6. The solar spectrum total reflection surface according to claim 1, characterized in that: The reflective layer is adhered to the reflective surface substrate by structural adhesive; The tensile strength of the structural adhesive is not less than 15 MPa, and the shear strength is not less than 10 MPa.

7. The solar spectrum total reflection surface according to claim 1, characterized in that: The main frame is anodized, and an oxide film with a thickness of 10 μm to 15 μm exists on the outer surface.

8. The solar spectrum total reflection surface according to claim 4, characterized in that: The silver film layer, the dielectric film layer and the nano-scale silicon dioxide-organic silicon composite protective film layer are prepared by adopting magnetron sputtering coating technology.

9. The solar spectrum total reflection surface according to claim 2, characterized in that: The focus position error of the parabolic structure corresponding to the reflective layer is within ±20 mm.

10. A method for pasting a reflective layer, characterized in that: The method is used for pasting the reflective layer and the main frame according to any one of claims 1 to 9, and the method comprises: The reflective surface base of the main frame is sequentially subjected to sandblasting, chemical cleaning and drying; The reflective layer is bonded to the reflective surface substrate using structural adhesive by dispensing or scraping with a laser aligner, and a pressure of 0.1 MPa to 0.2 MPa is applied to the reflective layer to control the adhesive layer thickness to be between 0.2 mm and 0.3 mm. The ratio of the main agent to the curing agent in the structural adhesive is between 10:1 and 15:

1. Determining whether the surface flatness of the reflective layer is within ±0.05 mm; If so, the structural adhesive is cured for 24 to 48 hours in an environment with a temperature between 20° C. and 25° C. and a humidity between 40% and 60%.

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