Packaging material for satellite solar wing capable of assisting defect detection and preparation method thereof

Abstract

The application discloses a satellite solar wing encapsulating material capable of assisting in defect detection and a preparation method thereof, and belongs to the technical field of encapsulating materials. The encapsulating material comprises an A component and a B component, wherein the A component and the B component are mixed and solidified according to a mass ratio of (0.8-1.2):1 during use; the A component comprises phenyl vinyl silicone oil, phenyl vinyl MQ resin, a defoaming agent, a leveling agent and a platinum catalyst; and the B component comprises phenyl vinyl silicone oil, phenyl hydrogen-containing silicone oil, phenyl vinyl MQ resin, fluorescent tracer nanoparticles, an anti-ultraviolet additive, a tackifier and an inhibitor. The satellite solar wing encapsulating material capable of assisting in defect detection prepared by the application has good transparency, tensile strength, ultraviolet aging resistance and defect assisting detection capability.

Description

Technical Field

[0001] This invention relates to the field of packaging materials technology, specifically to a packaging material for satellite solar panels that can assist in defect detection and its preparation method. Background Technology

[0002] As satellites evolve towards higher power, longer lifespan, and higher reliability, solar panels, as key components of satellite energy systems, typically require encapsulation materials for bonding, fixing, and environmental protection between their cells, glass covers, metal substrates, and insulating layers. Existing encapsulation adhesives for satellite solar panels mostly use silicone-based materials, which possess certain resistance to high and low temperatures, radiation, and low gas release. However, to improve mechanical strength, adhesion, or environmental resistance, reinforcing fillers or functional additives are often introduced into the system, easily leading to a semi-transparent or opaque adhesive layer. Due to the reduced transparency, defects such as bubbles, voids, localized coating omissions, interface debonding, cracks, and cell breakage formed during the encapsulation process are not easily observed or identified directly and in a timely manner. Furthermore, after solar panel components undergo environmental tests such as vibration, thermal shock, or UV aging, if abnormal output or structural failure occurs, it is usually necessary to locate the defect by disassembling the encapsulation layer, cross-sectional analysis, or other destructive testing methods. This not only has a long testing cycle and low efficiency but may also further damage the cells, glass covers, or interlayer bonding structures. Therefore, developing a satellite solar panel encapsulation material that combines high transparency, UV radiation resistance, and good adhesion, and can assist in identifying encapsulation defects through fluorescence tracing, is of great significance for improving the efficiency of solar panel encapsulation quality inspection and service reliability. Summary of the Invention

[0003] To address the shortcomings of existing technologies, the purpose of this invention is to provide a satellite solar panel encapsulation material that can assist in defect detection and its preparation method.

[0004] A satellite solar panel encapsulation material that can assist in defect detection includes component A and component B. When used, component A and component B are mixed and cured at a mass ratio of (0.8-1.2):1. Component A includes phenyl vinyl silicone oil, phenyl vinyl MQ resin, defoamer, leveling agent, and platinum catalyst; Component B includes phenyl vinyl silicone oil, phenyl hydrogen silicone oil, phenyl vinyl MQ resin, fluorescent tracer nanoparticles, UV stabilizers, thickeners, and inhibitors. The fluorescent tracer nanoparticles were prepared by the following method: Europium nitrate hexahydrate, dibenzoylmethane, and o-phenanthroline react to generate a europium complex dispersion; then tetraethyl orthosilicate is added to react and a europium complex / silica composite nanoparticle dispersion is obtained. After surface modification with 7-octenyltrimethoxysilane and phenyltrimethoxysilane, fluorescent tracer nanoparticles are obtained.

[0005] In component A, the mass ratio of the phenyl vinyl silicone oil, phenyl vinyl MQ resin, defoamer, leveling agent and platinum catalyst is 100:(20-30):(0.05-0.3):(0.05-0.3):(0.05-0.2).

[0006] In component B, the mass ratio of the phenyl vinyl silicone oil, phenyl hydrogen silicone oil, phenyl vinyl MQ resin, fluorescent tracer nanoparticles, UV-resistant additive, thickener and inhibitor is 100:(10-30):(15-30):(0.3-0.5):(0.2-0.6):(2-4):(0.05-0.1).

[0007] The UV-resistant additive is prepared by hydrolysis and condensation of 2-hydroxy-4-(3-triethoxysilylpropoxy)benzophenone, 1-naphthyltrimethoxysilane and vinyltriethoxysilane.

[0008] The mass ratio of europium nitrate hexahydrate, dibenzoylmethane, o-phenanthroline, tetraethyl orthosilicate, 7-octenyltrimethoxysilane and phenyltrimethoxysilane is 1:(1.5-2.0):(0.4-0.7):(3.0-5.0):(0.4-0.8):(0.4-0.8).

[0009] The thickener is γ-glycidoxypropyltrimethoxysilane.

[0010] The defoamer is an organosilicone defoamer.

[0011] The leveling agent is one of polyether-modified polysiloxane or polyester-modified polysiloxane.

[0012] The inhibitor is 1-ethynylcyclohexanol.

[0013] A method for preparing a satellite solar panel encapsulation material that can assist in defect detection includes the following steps: (1) Stir and mix phenyl vinyl silicone oil and phenyl vinyl MQ resin, add defoamer and leveling agent, disperse evenly, add platinum catalyst, stir, disperse, defoam and filter to obtain component A; (2) Stir and mix phenyl vinyl silicone oil and phenyl vinyl MQ resin, add phenyl hydrogen silicone oil, fluorescent tracer nanoparticles, anti-ultraviolet additive, thickener and inhibitor, stir to disperse, degas and filter to obtain component B; (3) When using, mix components A and B, degas under vacuum, and then coat the part of the satellite solar panel to be encapsulated. After curing, the product is ready.

[0014] Due to the adoption of the above technical solutions, the beneficial effects of the present invention include: The encapsulation material prepared by this invention exhibits excellent transparency, flexibility, resistance to high and low temperatures, and low vacuum gas release performance. The phenyl vinyl MQ resin improves the strength and dimensional stability of the adhesive layer. Fluorescent tracer nanoparticles form a uniform fluorescent background under ultraviolet light, causing bubble defects to appear as fluorescent dark areas or boundary anomalies, enabling non-destructive identification. The UV-resistant additive absorbs ultraviolet energy, reducing yellowing and fluorescence decay of the adhesive layer. Furthermore, its silane and vinyl structures facilitate its bonding with the organosilicon network, thereby reducing the risks of migration, precipitation, and volatilization, and improving the long-term stability and encapsulation reliability of the material in solar panel encapsulation scenarios. Attached Figure Description

[0015] Figure 1 The image shows a transmission electron microscope (TEM) image of the fluorescent tracer nanoparticles prepared in Example 1.

[0016] Figure 2 The image shows the X-ray diffraction (XRD) pattern of the fluorescent tracer nanoparticles prepared in Example 1.

[0017] Figure 3 The fluorescence emission spectrum of the fluorescent tracer nanoparticles prepared in Example 1 is shown.

[0018] Figure 4 Fourier transform infrared spectrum of the UV-resistant additive prepared in Example 3. Detailed Implementation

[0019] Example 1: Preparation of fluorescent tracer nanoparticles Add 100 mL of anhydrous ethanol, 1.0 g of europium nitrate hexahydrate, 1.5 g of dibenzoylmethane, and 0.4 g of o-phenanthroline to a reaction flask. Stir at room temperature for 30 min under light-protected conditions. Add 1.0 mL of triethylamine dropwise, and react at 60 °C under light-protected conditions for 3 h to obtain a europium complex dispersion. Add 80 mL of anhydrous ethanol, 20 mL of deionized water, and 3 mL of 25 wt% ammonia to the europium complex dispersion. Stir at 400 rpm for 20 min, and slowly add 20 mL of anhydrous ethanol solution containing 3.0 g of tetraethyl orthosilicate dropwise over 30 min. React at room temperature for 6 h to obtain a europium complex / silica composite nanoparticle dispersion. Add 0.4 g of... 7-Octenyltrimethoxysilane and 0.4 g phenyltrimethoxysilane were added to 10 mL anhydrous ethanol and 1 mL deionized water, and 0.03 g glacial acetic acid was added. The mixture was pre-hydrolyzed at room temperature for 30 min to obtain a silane pre-hydrolyzed solution. The silane pre-hydrolyzed solution was slowly added dropwise to a europium complex / silica composite nanoparticle dispersion. The addition was completed in 20 min. After reacting at 45 °C for 4 h, the mixture was cooled to room temperature, centrifuged at 8000 rpm for 15 min, the supernatant was discarded, and the precipitate was collected. The precipitate was washed twice with anhydrous ethanol (50 mL each time), twice with deionized water (50 mL each time), and twice with anhydrous ethanol (50 mL each time). Then, it was vacuum dried at 60 °C for 10 h to obtain fluorescent tracer nanoparticles.

[0020] Figure 1 The image shows a transmission electron microscope (TEM) image of the fluorescent tracer nanoparticles. As can be seen, the prepared fluorescent tracer nanoparticles exhibit a near-spherical morphology with relatively clear particle boundaries and a relatively uniform particle size distribution. While some particles show slight contact, the overall dispersion is good, and no severe large-scale aggregation is observed. The particles exhibit deep internal contrast, while a relatively shallow shell structure can be observed on the outer layer, indicating that the europium complex, after being coated with a silica network, forms a composite nanoparticle structure.

[0021] Figure 2 The XRD pattern of the fluorescent tracer nanoparticles shows a broad, diffuse diffraction peak around 2θ≈22°. No sharp crystalline diffraction peaks were observed, indicating that the prepared fluorescent tracer nanoparticles are primarily amorphous. This broad peak can be attributed to the amorphous Si-O-Si network formed after the hydrolysis and condensation of tetraethyl orthosilicate. Furthermore, the absence of obvious crystal diffraction peaks for the pin complex indicates that the pin complex is highly dispersed within the silica network, which is beneficial for improving the stability and uniformity of the fluorescent tracer component within the nanoparticles.

[0022] Figure 3 The figure shows the fluorescence emission spectrum of the fluorescent tracer nanoparticles. As can be seen, Eu appears at approximately 579 nm, 592 nm, 615 nm, 650 nm, and 699 nm. 3+The characteristic emission peaks are found, with the highest intensity near 615 nm, corresponding to Eu. 3 + of 5 D0→ 7 The F2 electric dipole transition indicates that the sample exhibits significant red fluorescence emission characteristics; the emission peak near 592 nm corresponds to Eu. 3+ of 5 D0→ 7 The F1 magnetic dipole transition, with emission peaks near 650 nm and 699 nm, are attributed to Eu. 3+ of 5 D0→ 7 F3 and 5 D0→ 7 F4 transition. The intensity of the 615nm main peak is significantly higher than other emission peaks, indicating that Eu... 3+ In a low-symmetry coordination environment, the absorbed ultraviolet energy is transferred to the Eu³⁺ luminescent centers. Overall, the europium complex retains a clear Eu luminescence even after silica coating and surface organosilanes modification. 3+ The characteristic emission indicates that the coating and modification process did not significantly damage its luminescent structure, and the resulting fluorescent tracer nanoparticles can generate obvious fluorescent signals under ultraviolet light excitation.

[0023] Example 2 Preparation of fluorescent tracer nanoparticles Add 100 mL of anhydrous ethanol, 1.0 g of europium nitrate hexahydrate, 1.8 g of dibenzoylmethane, and 0.6 g of o-phenanthroline to a reaction flask. Stir at room temperature for 30 min under light-protected conditions. Add 1.0 mL of triethylamine dropwise, and react at 65 °C under light-protected conditions for 2.5 h to obtain a europium complex dispersion. Add 80 mL of anhydrous ethanol, 20 mL of deionized water, and 3 mL of 25 wt% ammonia to the europium complex dispersion. Stir at 400 rpm for 20 min, and slowly add 20 mL of anhydrous ethanol solution containing 4.0 g of tetraethyl orthosilicate dropwise over 30 min. React at room temperature for 6 h to obtain a europium complex / silica composite nanoparticle dispersion. Add 0.6 g of... 7-Octenyltrimethoxysilane and 0.6 g phenyltrimethoxysilane were added to 10 mL anhydrous ethanol and 1 mL deionized water, and 0.03 g glacial acetic acid was added. The mixture was pre-hydrolyzed at room temperature for 30 min to obtain a silane pre-hydrolyzed solution. The silane pre-hydrolyzed solution was slowly added dropwise to a europium complex / silica composite nanoparticle dispersion. The addition was completed in 20 min. After reacting at 50 °C for 3 h, the mixture was cooled to room temperature and centrifuged at 8000 rpm for 15 min. The supernatant was discarded, and the precipitate was collected. The precipitate was washed twice with anhydrous ethanol (50 mL each time), twice with deionized water (50 mL each time), and twice with anhydrous ethanol (50 mL each time). Then, it was vacuum dried at 60 °C for 10 h to obtain fluorescent tracer nanoparticles.

[0024] Example 3 Preparation of fluorescent tracer nanoparticles Add 100 mL of anhydrous ethanol, 1.0 g of europium nitrate hexahydrate, 2.0 g of dibenzoylmethane, and 0.7 g of o-phenanthroline to a reaction flask. Stir at room temperature for 30 min under light-protected conditions. Add 1.0 mL of triethylamine dropwise, and react at 70 °C under light-protected conditions for 2 h to obtain a europium complex dispersion. Add 80 mL of anhydrous ethanol, 20 mL of deionized water, and 3 mL of 25 wt% ammonia to the europium complex dispersion. Stir at 400 rpm for 20 min, and slowly add 20 mL of anhydrous ethanol solution containing 5.0 g of tetraethyl orthosilicate dropwise over 30 min. React at room temperature for 6 h to obtain a europium complex / silica composite nanoparticle dispersion. Add 0.8 g of... 7-Octenyltrimethoxysilane and 0.8 g phenyltrimethoxysilane were added to 10 mL anhydrous ethanol and 1 mL deionized water, and 0.03 g glacial acetic acid was added. The mixture was pre-hydrolyzed at room temperature for 30 min to obtain a silane pre-hydrolyzed solution. The silane pre-hydrolyzed solution was slowly added dropwise to a europium complex / silica composite nanoparticle dispersion. The addition was completed in 20 min. After reacting at 55 °C for 2 h, the mixture was cooled to room temperature and centrifuged at 8000 rpm for 15 min. The supernatant was discarded, and the precipitate was collected. The precipitate was washed twice with anhydrous ethanol (50 mL each time), twice with deionized water (50 mL each time), and twice with anhydrous ethanol (50 mL each time). Then, it was vacuum dried at 60 °C for 10 h to obtain fluorescent tracer nanoparticles.

[0025] Example 4 Preparation of UV-resistant additives Under nitrogen protection, 40 mL of anhydrous ethanol and 5 mL of deionized water were added to the reaction flask, followed by 0.2 g of 10 wt% acetic acid aqueous solution. After stirring evenly, 2.0 g of 2-hydroxy-4-(3-triethoxysilylpropoxy)benzophenone, 0.8 g of 1-naphthyltrimethoxysilane, and 0.6 g of vinyltriethoxysilane were added. The mixture was stirred and pre-hydrolyzed at room temperature for 30 min. Subsequently, the temperature was raised to 45 °C, and the reaction was carried out for 4 h. The mixture was then rotary evaporated at 50 °C to constant weight and vacuum dried at 60 °C for 2 h to obtain the UV-resistant additive.

[0026] Figure 4 The Fourier transform infrared spectrum of the UV-resistant additive shows that at 3430 cm⁻¹... -1 A broad absorption peak appears nearby, mainly attributed to the OH stretching vibration; 2972 ​​cm⁻¹ -1 and 2853cm -1 The nearby absorption peak is attributed to the alkyl CH stretching vibration, indicating that the product contains an organosilanes with side chains; 1638 cm⁻¹ -1 The nearby absorption peaks can be attributed to conjugate C=O stretching vibrations and aromatic ring skeletal vibrations; 1510 cm⁻¹ -1 The nearby absorption peak is mainly attributed to the aromatic ring skeletal vibration, 748 cm⁻¹.-1 The nearby absorption peaks are mainly attributed to the out-of-plane bending vibrations of the aromatic ring CH, indicating the presence of carbonyl and aromatic ring-related groups in the product; 1262 cm⁻¹ -1 The nearby absorption peak can be attributed to the stretching vibrations of CO, COC, or Si-OC; 1086 cm⁻¹ -1 and 803cm -1 The nearby absorption peaks correspond to the asymmetric and symmetric stretching vibrations of Si-O-Si, respectively, indicating that the silane group underwent hydrolysis and condensation to form a siloxane structure; 958 cm⁻¹ -1 The nearby absorption peaks are related to Si-OH and Si-OC vibrations, indicating that there are a small number of incompletely condensed silanol or vinyl-related groups in the system.

[0027] Example 5: Preparation of Encapsulation Material for Satellite Solar Array that Can Aid Defect Detection (1) Weigh 100g of phenyl vinyl silicone oil, 20g of phenyl vinyl MQ resin, 0.05g of defoamer (organic silicone defoamer), 0.05g of leveling agent (polyether modified polysiloxane) and 0.05g of platinum catalyst; Phenyl vinyl silicone oil and phenyl vinyl MQ resin were added to a planetary power mixer and premixed at 500 rpm for 20 min. Then, the vacuum system was turned on with a gauge pressure of -0.09 MPa, the temperature was raised to 110℃, and the mixture was vacuum dispersed at 1000 rpm for 2 h. After that, the temperature was lowered to 45℃. Defoamer and leveling agent were added, and the mixture was dispersed at 2000 rpm for 30 min. After that, the temperature was lowered to 30℃, platinum catalyst was added, and the mixture was stirred at 500 rpm for 20 min. The mixture was then vacuum degassed for 15 min under a gauge pressure of -0.09 MPa to obtain component A.

[0028] (2) Weigh 100g of phenyl vinyl silicone oil, 10g of phenyl hydrogen silicone oil, 15g of phenyl vinyl MQ resin, 0.3g of fluorescent tracer nanoparticles (prepared in Example 1), 0.2g of UV-resistant additive (prepared in Example 4), 2g of tackifier (γ-glycidyl oxypropyltrimethoxysilane) and 0.05g of inhibitor (1-ethynylcyclohexanol); Phenyl vinyl silicone oil and phenyl vinyl MQ resin were added to a planetary power mixer and premixed at 500 rpm for 20 min. Then, the vacuum system was turned on with a gauge pressure of -0.09 MPa, the temperature was raised to 110 °C, and the mixture was vacuum dispersed at 800 rpm for 2 h. After that, the temperature was lowered to 45 °C. Phenyl hydrogen silicone oil, fluorescent tracer nanoparticles, UV stabilizer, thickener and inhibitor were added and dispersed at 800 rpm for 30 min. The mixture was then vacuum degassed for 15 min under a gauge pressure of -0.09 MPa to obtain component B.

[0029] (3) When using, mix component A and component B at a mass ratio of 0.8:1, stir at 400 rpm for 5 min, then degas under vacuum for 10 min at a gauge pressure of -0.09 MPa, apply the degassed mixed adhesive to the part of the satellite solar wing to be encapsulated, and control the adhesive layer thickness to be 0.3 mm; after coating, level at room temperature for 20 min, and cure at 25°C and 50% relative humidity for 10 days to obtain the encapsulation material.

[0030] Example 6: Preparation of Encapsulation Material for Satellite Solar Array that Can Aid Defect Detection (1) Weigh 100g of phenyl vinyl silicone oil, 25g of phenyl vinyl MQ resin, 0.15g of defoamer (organosilicon defoamer), 0.15g of leveling agent (polyether modified polysiloxane) and 0.12g of platinum catalyst; Phenyl vinyl silicone oil and phenyl vinyl MQ resin were added to a planetary power mixer and premixed at 500 rpm for 20 min. Then, the vacuum system was turned on with a gauge pressure of -0.09 MPa, the temperature was raised to 110℃, and the mixture was vacuum dispersed at 1000 rpm for 2 h. After that, the temperature was lowered to 45℃. Defoamer and leveling agent were added, and the mixture was dispersed at 2000 rpm for 30 min. After that, the temperature was lowered to 30℃, platinum catalyst was added, and the mixture was stirred at 500 rpm for 20 min. The mixture was then vacuum degassed for 15 min under a gauge pressure of -0.09 MPa to obtain component A.

[0031] (2) Weigh 100g of phenyl vinyl silicone oil, 20g of phenyl hydrogen silicone oil, 24g of phenyl vinyl MQ resin, 0.4g of fluorescent tracer nanoparticles (prepared in Example 2), 0.4g of UV-resistant additive (prepared in Example 4), 3g of tackifier (γ-glycidyl etheroxypropyltrimethoxysilane) and 0.08g of inhibitor (1-ethynylcyclohexanol); Phenyl vinyl silicone oil and phenyl vinyl MQ resin were added to a planetary power mixer and premixed at 500 rpm for 20 min. Then, the vacuum system was turned on with a gauge pressure of -0.09 MPa, the temperature was raised to 110 °C, and the mixture was vacuum dispersed at 800 rpm for 2 h. After that, the temperature was lowered to 45 °C. Phenyl hydrogen silicone oil, fluorescent tracer nanoparticles, UV stabilizer, thickener and inhibitor were added and dispersed at 800 rpm for 30 min. The mixture was then vacuum degassed for 15 min under a gauge pressure of -0.09 MPa to obtain component B.

[0032] (3) When using, mix component A and component B at a mass ratio of 1:1 and stir at 400 rpm for 5 min. Then, degas under vacuum for 10 min at a gauge pressure of -0.09 MPa. Apply the degassed mixed adhesive to the part of the satellite solar wing to be encapsulated, and control the adhesive layer thickness to be 0.3 mm. After coating, level at room temperature for 20 min and cure at 25°C and 50% relative humidity for 10 days to obtain the encapsulation material.

[0033] Example 7: Preparation of Encapsulation Material for Satellite Solar Array that Can Aid Defect Detection (1) Weigh 100g of phenyl vinyl silicone oil, 30g of phenyl vinyl MQ resin, 0.3g of defoamer (organosilicon defoamer), 0.3g of leveling agent (polyester modified polysiloxane) and 0.2g of platinum catalyst; Phenyl vinyl silicone oil and phenyl vinyl MQ resin were added to a planetary power mixer and premixed at 500 rpm for 20 min. Then, the vacuum system was turned on with a gauge pressure of -0.09 MPa, the temperature was raised to 110℃, and the mixture was vacuum dispersed at 1000 rpm for 2 h. After that, the temperature was lowered to 45℃. Defoamer and leveling agent were added, and the mixture was dispersed at 2000 rpm for 30 min. After that, the temperature was lowered to 30℃, platinum catalyst was added, and the mixture was stirred at 500 rpm for 20 min. The mixture was then vacuum degassed for 15 min under a gauge pressure of -0.09 MPa to obtain component A.

[0034] (2) Weigh 100g of phenyl vinyl silicone oil, 30g of phenyl hydrogen silicone oil, 30g of phenyl vinyl MQ resin, 0.5g of fluorescent tracer nanoparticles (prepared in Example 3), 0.6g of UV-resistant additive (prepared in Example 4), 4g of tackifier (γ-glycidyl etheroxypropyltrimethoxysilane) and 0.1g of inhibitor (1-ethynylcyclohexanol); Phenyl vinyl silicone oil and phenyl vinyl MQ resin were added to a planetary power mixer and premixed at 500 rpm for 20 min. Then, the vacuum system was turned on with a gauge pressure of -0.09 MPa, the temperature was raised to 110 °C, and the mixture was vacuum dispersed at 800 rpm for 2 h. After that, the temperature was lowered to 45 °C. Phenyl hydrogen silicone oil, fluorescent tracer nanoparticles, UV stabilizer, thickener and inhibitor were added and dispersed at 800 rpm for 30 min. The mixture was then vacuum degassed for 15 min under a gauge pressure of -0.09 MPa to obtain component B.

[0035] (3) When using, mix component A and component B at a mass ratio of 1.2:1, stir at 400 rpm for 5 min, then degas under vacuum for 10 min at a gauge pressure of -0.09 MPa, apply the degassed mixed adhesive to the part of the satellite solar wing to be encapsulated, and control the adhesive layer thickness to be 0.3 mm; after coating, level at room temperature for 20 min, and cure at 25°C and 50% relative humidity for 10 days to obtain the encapsulation material.

[0036] Comparative Example 1 The preparation method of the encapsulation material for satellite solar panels that can assist in defect detection is basically the same as in Example 6, except that the fluorescent tracer nanoparticles are replaced with an equal weight of fluorescent tracer nanoparticles prepared by the following method: The preparation method of the fluorescent tracer nanoparticles is basically the same as that in Example 2, except that 7-octenyltrimethoxysilane is replaced with an equal weight of vinyltriethoxysilane.

[0037] Comparative Example 2 The preparation method of the encapsulation material for satellite solar panels that can assist in defect detection is basically the same as in Example 6, except that the fluorescent tracer nanoparticles are replaced with an equal weight of fluorescent tracer nanoparticles prepared by the following method: The preparation method of the fluorescent tracer nanoparticles is basically the same as that in Example 2, except that 7-octenyltrimethoxysilane is replaced with an equal weight of n-octyltrimethoxysilane.

[0038] Comparative Example 3 The preparation method of the encapsulation material for satellite solar panels that can assist in defect detection is basically the same as in Example 6, except that the fluorescent tracer nanoparticles are replaced with an equal weight of fluorescent tracer nanoparticles prepared by the following method: The preparation method of fluorescent tracer nanoparticles is basically the same as that in Example 2, except that phenyltrimethoxysilane is replaced with an equal weight of methyltriethoxysilane.

[0039] Comparative Example 4 The preparation method of the encapsulation material for satellite solar panels that can assist in defect detection is basically the same as in Example 6, except that the fluorescent tracer nanoparticles are replaced with an equal weight of fluorescent tracer nanoparticles prepared by the following method: The preparation method of the fluorescent tracer nanoparticles is basically the same as that in Example 2, except that 0.2g of phenyltrimethoxysilane is added in the preparation of the fluorescent tracer nanoparticles.

[0040] Comparative Example 5 The preparation method of the encapsulation material for satellite solar panels that can assist in defect detection is basically the same as in Example 6, except that the fluorescent tracer nanoparticles are replaced with an equal weight of fluorescent tracer nanoparticles prepared by the following method: The preparation method of fluorescent tracer nanoparticles is basically the same as that in Example 2, except that dibenzoylmethane is replaced with an equal weight of acetylacetone.

[0041] Comparative Example 6 The preparation method of the encapsulation material for satellite solar panels that can assist in defect detection is basically the same as in Example 6, except that the fluorescent tracer nanoparticles are replaced with an equal weight of fluorescent tracer nanoparticles prepared by the following method: The preparation method of the fluorescent tracer nanoparticles is basically the same as that in Example 2, except that o-phenanthroline is replaced with an equal weight of 2,2'-bipyridine.

[0042] Comparative Example 7 The preparation method of the satellite solar panel encapsulation material that can assist in defect detection is basically the same as that in Example 6, except that the UV-resistant agent is replaced with an equal weight of 2-hydroxy-4-(3-triethoxysilylpropoxy)benzophenone.

[0043] Comparative Example 8 The preparation method of the encapsulation material for satellite solar panels that can assist in defect detection is basically the same as in Example 6, except that the UV-resistant agent is replaced with an equal weight of UV-resistant agent prepared by the following method: The preparation method of the UV-resistant additive is basically the same as that in Example 4, except that 2-hydroxy-4-(3-triethoxysilylpropoxy)benzophenone is replaced with an equimolar amount of 2-hydroxy-4-methoxybenzophenone.

[0044] Comparative Example 9 The preparation method of the encapsulation material for satellite solar panels that can assist in defect detection is basically the same as in Example 6, except that the UV-resistant agent is replaced with an equal weight of UV-resistant agent prepared by the following method: The preparation method of the UV-resistant additive is basically the same as that in Example 4, except that 1-naphthyltrimethoxysilane is replaced with an equimolar amount of phenyltrimethoxysilane.

[0045] The phenyl vinyl silicone oil used in the embodiments and comparative examples of this application is model RH-510V-5000, with a vinyl content of 0.10 wt%, and is produced by Ningbo Runhe High-Tech Materials Technology Co., Ltd.; the phenyl vinyl MQ resin is model LR-MQP-171, with a vinyl content of 5.35 wt%; the phenyl hydrogen silicone oil is model SiSiB® HF2080, with a phenyl content of 25 wt% and a hydrogen content of 0.5 wt%; the polyether-modified polysiloxane is model BYK-333; the polyester-modified polysiloxane is model BYK-310; the silicone defoamer is model BYK-066N; and the platinum catalyst contains 2 wt% platinum.

[0046] The satellite solar array encapsulation materials prepared in the examples and comparative examples for assisting defect detection were tested for light transmittance, tensile strength, shear strength, defect identification ability, vacuum release, and UV aging resistance. The test results are shown in Table 1.

[0047] Sample preparation: Take components A and B obtained from the examples and comparative examples, and place them in an environment of 23±2℃ and 50±5% relative humidity for 2 hours. Before use, weigh components A and B at a mass ratio of 1:1 and place them in a clean and dry polytetrafluoroethylene beaker. Stir at 400 rpm for 5 minutes. After mixing, place the mixed adhesive in a vacuum degassing tank and degas under vacuum for 10 minutes at a gauge pressure of -0.09 MPa to obtain the mixed adhesive to be tested.

[0048] 1.1 Preparation of colloidal test pieces The mixed adhesive to be tested was slowly poured into a polytetrafluoroethylene (PTFE) mold with dimensions of 120mm × 120mm × 2mm. Pouring was done continuously from one side of the mold, allowing the adhesive to spread naturally and avoiding air trapping within the adhesive layer. After pouring, a scraper was used to gently smooth the upper surface of the mold, controlling the adhesive layer thickness to 2.0 ± 0.1mm. The mold was then placed back into a vacuum degassing chamber for 3 minutes at a gauge pressure of -0.09MPa. After degassing, the mold was allowed to level at room temperature for 20 minutes, then cured for 10 days at 25℃ and 50% relative humidity, followed by 24 hours at 23 ± 2℃ and 50 ± 5% relative humidity. After curing, the adhesive sheet was removed from the mold, and uneven areas at the edges were trimmed to obtain a colloidal specimen with uniform thickness, a smooth surface, and no obvious bubbles or impurities. This colloidal specimen was used for transmittance, tensile properties, vacuum degassing, and UV aging resistance tests.

[0049] 1.2 Preparation of shear specimens The substrate used for the sheared test pieces was an aluminum alloy sheet, which was cut into strips of 100mm × 25mm × 2mm. The overlap length was 12.5mm, the overlap width was 25mm, and the adhesive layer thickness was controlled at 0.3±0.05mm. The overlap area was first sanded unidirectionally with 800-grit sandpaper, and then wiped with anhydrous ethanol and isopropanol in sequence to remove surface oil, dust, and loose particles. After wiping, it was dried at 60℃ for 30 minutes and then cooled to room temperature for later use. The mixed adhesive to be tested was evenly applied to the overlap area of ​​one aluminum alloy sheet; then another aluminum alloy sheet was placed over the coated area to form an aluminum-aluminum overlap structure. After overlapping, the sheets were gently pressed together to spread the adhesive evenly, and excess adhesive at the edges was removed. The assembled shear test specimen was fixed with clamps to prevent displacement or warping during curing. It was then cured according to the same curing regime as the colloidal test specimen: leveling at room temperature for 20 minutes, curing for 10 days at 25°C and 50% relative humidity, and then placing it in an environment of 23±2°C and 50±5% relative humidity for 24 hours to obtain the aluminum-aluminum lap shear test specimen. This shear test specimen is used to test the shear strength of the encapsulation material against the aluminum alloy substrate.

[0050] 1.3 Sample Preparation for Defect Detection Defect detection samples were prepared using simulated solar panel components. The aluminum alloy substrate, polyimide insulating film, simulated solar cell, and transparent glass cover were cut into dimensions of 80mm×80mm×2mm, 75mm×75mm×0.05mm, 60mm×60mm×0.2mm, and 65mm×65mm×1mm, respectively. The surfaces were cleaned sequentially with anhydrous ethanol and isopropanol, and then dried before use. First, the polyimide insulating film was laid on the surface of the aluminum alloy substrate, and then the simulated solar cell was placed on the polyimide insulating film. Next, the mixed adhesive to be tested was applied to the simulated solar cell and its surrounding area, controlling the adhesive layer thickness to be 0.5mm. Finally, the transparent glass cover was placed over the sample, allowing the adhesive to spread evenly between the glass cover and the simulated solar cell, forming a simulated encapsulation structure. Bubble defects were used as a representative defect to evaluate the defect-aided detection capability of the encapsulation material. During sample preparation, air bubbles were locally introduced into the adhesive layer between the glass cover and the simulated solar cell using a micro-injector, forming bubble defects with diameters of approximately 0.2 mm, 0.5 mm, and 1.0 mm. Three bubble defects were designed for each size, resulting in a total of nine bubble defects per sample. The designed location and size of the bubble defects were recorded. After assembly, the samples were cured according to the same curing regime as in the example: leveling at room temperature for 20 minutes, followed by curing at 25°C and 50% relative humidity for 10 days, yielding the simulated solar wing packaged sample. This simulated solar wing packaged sample was used to test defect identification capability. Three parallel samples were tested in each group, and the average value was taken.

[0051] Transmittance test: The transmittance of the colloidal sample at 550 nm was measured using a UV-Vis spectrophotometer. Five parallel samples were tested for each group of samples, and the average value was taken.

[0052] Tensile property test: Cut the colloidal specimen into type 1 dumbbell-shaped specimens and test the tensile strength of the colloidal specimens according to GB / T 528-2009. The tensile speed is 500 mm / min. Five parallel samples are tested for each group of samples, and the average value is taken.

[0053] Shear strength test: The shear strength of aluminum-aluminum lap joints was tested according to GB / T 7124-2008. The tensile speed was 5 mm / min. The maximum failure load was recorded. The shear strength was calculated as the ratio of the maximum failure load to the lap area. Five parallel samples were tested for each group of samples, and the average value was taken.

[0054] Defect recognition capability test: The simulated solar panel packaging sample containing artificial defects was placed under a 365nm ultraviolet lamp for observation, and the bubble recognition results were statistically analyzed. If the defective area exhibits a dark fluorescence area, fluorescence interruption, fluorescence boundary enhancement, or abnormal fluorescence intensity under ultraviolet light, the defect is considered identifiable. The defect recognition rate is calculated using the following formula: Defect recognition rate = Number of identifiable defects / Total number of artificially created defects × 100%.

[0055] Vacuum release test: Test the vacuum release performance of the cured colloidal specimens according to ASTM E595, and record the total mass loss (TML) and condensable volatile matter (CVCM).

[0056] UV aging test: The samples were placed in a UV aging chamber for aging treatment. The UV light source was a UVA-340 lamp, and the irradiance at 340nm was controlled at 0.68W / m. 2 The sample surface temperature was controlled at 60±2℃, and the sample was continuously irradiated for 500 hours. After aging, the sample was taken out and placed in an environment of 23±2℃ and 50±5% relative humidity for 24 hours. Then, it was placed on a white background plate and the appearance changes of the sample were observed under the same light source conditions to evaluate whether yellowing, fogging, or cracking occurred.

[0057] Table 1. Test data of packaging material performance As can be seen from the data in Table 1, the satellite solar panel encapsulation material prepared by this invention, which can assist in defect detection, has good transparency, tensile strength, UV aging resistance, and defect-assisted detection capability. This is mainly due to the synergistic effect between the phenyl addition-type organosilicon network, fluorescent tracer nanoparticles, and UV-resistant additives. Phenyl vinyl silicone oil and phenyl hydrogen-containing silicone oil undergo a hydrosilylation reaction under the action of a platinum catalyst to form a flexible, high- and low-temperature resistant, and low-gas-release cross-linked silicone rubber network. Phenyl vinyl MQ resin has good compatibility with phenyl silicone oil and can serve as a rigid siloxane reinforcing phase, improving the tensile strength and dimensional stability of the encapsulation material. In addition, the phenyl structure is beneficial to improving its compatibility and refractive index matching with the phenyl organosilicon system, reducing interfacial light scattering, and making the fluorescence distribution more uniform. Europium complexes in fluorescent tracer nanoparticles can generate fluorescence responses under ultraviolet light. The silica coating layer can isolate and protect the europium complexes, reducing the migration, aggregation, and environmental quenching of fluorescent components. The 7-octenyl structure introduced on the surface can participate in hydrosilylation reactions, immobilizing the fluorescent tracer nanoparticles in the organosilicon cross-linked network and reducing their migration risk during curing and aging. When air bubbles are present in the encapsulation material, the defective areas will disrupt the continuous fluorescence background, manifesting as dark fluorescence areas, fluorescence interruptions, or boundary enhancement, thereby achieving non-destructive visual identification. The benzophenone structure in the UV-resistant additive can absorb ultraviolet energy, the naphthyl structure helps improve the compatibility and refractive index matching between the additive and the phenyl organosilicon matrix, and the vinyl structure enables it to integrate into the organosilicon cross-linked network, reducing the risk of migration and precipitation. Therefore, the encapsulation material prepared by this invention can simultaneously achieve transparent encapsulation, low gas release, UV resistance and low yellowing, and defect fluorescence development.

[0058] In Comparative Example 1, the short-chain vinyl silane's wetting and dispersing effect on fluorescent particles was insufficient, leading to a decrease in fluorescence distribution uniformity. In Comparative Example 2, although n-octylsilane had some hydrophobic compatibility, it did not contain double bonds that could participate in hydrosilylation, making it difficult for fluorescent tracer nanoparticles to integrate into the organosilicon crosslinking network via reaction. This resulted in greater migration, localized enrichment, or fluorescence attenuation during curing and UV aging, leading to a decrease in defect recognition ability. In Comparative Example 3, the replacement of phenylsilane with methylsilane reduced the aromatic structure on the surface of the fluorescent tracer nanoparticles, decreasing their compatibility and refractive index matching with the phenyl organosilicon matrix, increasing interfacial scattering, and worsening fluorescence background uniformity. In Comparative Example 4, reducing the amount of phenyltrimethoxysilane from 0.6 g to 0.2 g resulted in insufficient phenyl modification on the surface of the fluorescent tracer nanoparticles. Since the encapsulation system mainly consists of phenyl vinyl silicone oil and phenyl vinyl MQ resin, insufficient phenyl modification reduces the compatibility between the nanoparticles and the matrix, making the particles more prone to aggregation and uneven dispersion, thereby increasing light scattering and reducing transmittance. Simultaneously, the interfacial bonding between the particles and the organosilicon matrix weakens, leading to a decrease in tensile and shear strength. Uneven distribution of fluorescent particles also reduces the fluorescence contrast in defect areas, resulting in a decrease in defect recognition ability. In Comparative Example 5, replacing dibenzoylmethane with acetylacetone resulted in lower conjugation and weaker UV absorption and energy transfer efficiency compared to dibenzoylmethane, leading to insufficient Eu... 3+ The characteristic red light emission intensity decreased, and the fluorescent tracer signal in the encapsulation material weakened, thus significantly reducing the defect recognition ability. In Comparative Example 6, o-phenanthroline was replaced with 2,2'-bipyridine. Although 2,2'-bipyridine can also participate in coordination as a bidentate ligand, its molecular rigidity and planarity are weaker than o-phenanthroline, leading to a decrease in the luminescence stability of the europium complex, thereby reducing the defect recognition ability. Comparative Example 7 used only a single silanized benzophenone to replace the composite UV absorber. Although it has a certain UV absorption effect and contains a hydrolyzable silane group, it lacks the synergistic effect of the naphthyl structure on aromatic conjugation, compatibility, and refractive index regulation. Therefore, the binding stability of the UV absorber in the cured network is reduced, and slight yellowing occurs after UV aging. Comparative Example 8 used a benzophenone-based UV absorber without silane groups, which is difficult to integrate into the siloxane structure, easily migrates and precipitates, and increases vacuum gas release. In Comparative Example 9, the substitution of the naphthyl structure with the phenyl structure weakened the aromatic conjugation and refractive index regulation effects, resulting in lower levels of yellowing and defect recognition after UV aging compared to the Examples.

[0059] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. However, any modifications, alterations, and variations made by those skilled in the art without departing from the scope of the present invention based on the disclosed technical content are equivalent embodiments of the present invention. Furthermore, any modifications, alterations, and variations made to the above embodiments based on the essential technology of the present invention are still within the protection scope of the present invention.

Claims

1. A packaging material for satellite solar panels that can assist in defect detection, characterized in that, It includes component A and component B. When using it, mix component A and component B at a mass ratio of (0.8-1.2):1 and cure. Component A includes phenyl vinyl silicone oil, phenyl vinyl MQ resin, defoamer, leveling agent, and platinum catalyst; Component B includes phenyl vinyl silicone oil, phenyl hydrogen silicone oil, phenyl vinyl MQ resin, fluorescent tracer nanoparticles, UV stabilizers, thickeners, and inhibitors. The fluorescent tracer nanoparticles were prepared by the following method: Europium nitrate hexahydrate, dibenzoylmethane, and o-phenanthroline react to generate a europium complex dispersion; then tetraethyl orthosilicate is added to react and a europium complex / silica composite nanoparticle dispersion is obtained. After surface modification with 7-octenyltrimethoxysilane and phenyltrimethoxysilane, fluorescent tracer nanoparticles are obtained.

2. The satellite solar panel encapsulation material for assisting defect detection according to claim 1, characterized in that, In component A, the mass ratio of the phenyl vinyl silicone oil, phenyl vinyl MQ resin, defoamer, leveling agent and platinum catalyst is 100:(20-30):(0.05-0.3):(0.05-0.3):(0.05-0.2).

3. The satellite solar panel encapsulation material for assisting defect detection according to claim 1, characterized in that, In component B, the mass ratio of the phenyl vinyl silicone oil, phenyl hydrogen silicone oil, phenyl vinyl MQ resin, fluorescent tracer nanoparticles, UV-resistant additive, thickener and inhibitor is 100:(10-30):(15-30):(0.3-0.5):(0.2-0.6):(2-4):(0.05-0.1).

4. The satellite solar panel encapsulation material for assisting defect detection according to claim 1, characterized in that, The UV-resistant additive is prepared by hydrolysis and condensation of 2-hydroxy-4-(3-triethoxysilylpropoxy)benzophenone, 1-naphthyltrimethoxysilane and vinyltriethoxysilane.

5. The satellite solar panel encapsulation material for assisting defect detection according to claim 1, characterized in that, The mass ratio of europium nitrate hexahydrate, dibenzoylmethane, o-phenanthroline, tetraethyl orthosilicate, 7-octenyltrimethoxysilane and phenyltrimethoxysilane is 1:(1.5-2.0):(0.4-0.7):(3.0-5.0):(0.4-0.8):(0.4-0.8).

6. The satellite solar panel encapsulation material for assisting defect detection according to claim 1, characterized in that, The thickener is γ-glycidoxypropyltrimethoxysilane.

7. The satellite solar panel encapsulation material for assisting defect detection according to claim 1, characterized in that, The defoamer is an organosilicone defoamer.

8. The satellite solar panel encapsulation material for assisting defect detection according to claim 1, characterized in that, The leveling agent is one of polyether-modified polysiloxane or polyester-modified polysiloxane.

9. The satellite solar panel encapsulation material for assisting defect detection according to claim 1, characterized in that, The inhibitor is 1-ethynylcyclohexanol.

10. A method for preparing a satellite solar panel encapsulation material capable of assisting in defect detection as described in any one of claims 1-9, characterized in that, Includes the following steps: (1) Stir and mix phenyl vinyl silicone oil and phenyl vinyl MQ resin, add defoamer and leveling agent, disperse evenly, add platinum catalyst, stir, disperse, defoam and filter to obtain component A; (2) Stir and mix phenyl vinyl silicone oil and phenyl vinyl MQ resin, add phenyl hydrogen silicone oil, fluorescent tracer nanoparticles, anti-ultraviolet additive, thickener and inhibitor, stir to disperse, degas and filter to obtain component B; (3) When using, mix components A and B, degas under vacuum, and then coat the part of the satellite solar panel to be encapsulated. After curing, the product is ready.

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