Radiation resistant glass for low earth orbit spacecraft and methods of making and using the same
By using a specific ratio of raw materials and processes to prepare radiation-resistant glass for low-Earth orbit spacecraft, the problem of insufficient radiation resistance of glass with a thickness of ≤1mm was solved, and the radiation resistance and impact resistance of low-Earth orbit spacecraft were improved, ensuring the stable operation of the spacecraft.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- QINHUANGDAO XINGJIAN SPECIAL GLASS
- Filing Date
- 2026-04-16
- Publication Date
- 2026-07-14
AI Technical Summary
Existing glass for low Earth orbit spacecraft has insufficient radiation resistance, especially ultra-thin glass with a thickness of ≤1mm, which cannot effectively block space radiation, resulting in rapid degradation of optical and mechanical properties, and failing to meet the long-term stable service requirements of low Earth orbit spacecraft.
Radiation-resistant glass for low-orbit spacecraft is prepared by using raw materials such as quartz sand, aluminum hydroxide, boric acid, carbonate, cerium oxide, gallium trioxide, lead oxide, tetrabutyl titanate, and kerosene in specific proportions through melting, forming, and annealing processes. The combination of cerium dioxide, gallium trioxide, lead oxide, and tetrabutyl titanate enhances the network structure of the glass, absorbs and scatters radiation energy, and improves its radiation resistance.
The prepared radiation-resistant glass for low-Earth orbit spacecraft, with a thickness of ≤1mm, significantly improves radiation resistance and impact resistance, meeting the usage requirements of low-Earth orbit spacecraft and ensuring the stable operation and data transmission capabilities of the spacecraft.
Smart Images
Figure SMS_1
Abstract
Description
Technical Field
[0001] This invention relates to the field of radiation-resistant glass technology, specifically to radiation-resistant glass for low Earth orbit spacecraft, its preparation method, and its application. Background Technology
[0002] Low Earth Orbit (LEO) spacecraft glass is a special type of glass material primarily used to protect the internal components of satellites and other spacecraft from damage caused by cosmic radiation. It effectively protects optical instruments, electronic equipment, and other sensitive components within the spacecraft in the harsh radiation environment of LEO. This glass absorbs or scatters high-energy particles, such as protons, electrons, and heavy ions, thereby reducing their impact and potential damage to internal equipment. In this way, LEO spacecraft glass ensures the stable operation and data transmission capabilities of spacecraft during long-term space missions.
[0003] However, the low Earth orbit (LEO) space environment contains a large number of high-energy charged particles and ionizing radiation, posing more stringent requirements for the radiation resistance of glass used in spacecraft. Currently, the radiation resistance of existing glass materials is insufficient for LEO applications. Furthermore, due to the limitations of lightweight and miniaturized spacecraft design, ultra-thin glass with a thickness of ≤1mm is the mainstream choice. However, this type of ultra-thin glass has significant shortcomings in radiation resistance; it not only fails to effectively block space radiation but also suffers rapid degradation of its optical and mechanical properties due to radiation damage, weakening its protective function for spacecraft.
[0004] Therefore, developing a glass for low-Earth orbit spacecraft that can achieve a breakthrough in radiation resistance with a thickness of ≤1mm is of vital importance for filling the technological gap in the industry and ensuring the long-term stable service of low-Earth orbit spacecraft. Summary of the Invention
[0005] This invention proposes radiation-resistant glass for low-Earth orbit spacecraft, its preparation method, and its application, solving the problem of insufficient radiation resistance of glass for low-Earth orbit spacecraft in related technologies.
[0006] The technical solution of the present invention is as follows: This invention proposes radiation-resistant glass for low-orbit spacecraft, comprising the following raw materials in parts by weight: 45.5-68 parts of quartz sand, 8.41-10.25 parts of aluminum hydroxide, 8.86-24.62 parts of boric acid, 24-43.69 parts of carbonate, 0.6-2.1 parts of cerium dioxide, 0.2-1.2 parts of gallium trioxide, 0.5-1 part of antimony trioxide, 2-4.6 parts of nitrate, 0.5-1.4 parts of molybdenum dioxide, 0.8-2.2 parts of lead oxide, 3.4-12.75 parts of tetrabutyl titanate, and 0.2-0.8 parts of kerosene.
[0007] The radiation-resistant glass for low-orbit spacecraft of this invention can protect materials from the impact of space particles, has a certain degree of light transmittance, is easy to machine, and can meet the usage requirements of complex working conditions such as irregular structures.
[0008] As a further technical solution, the thickness of the radiation-resistant glass used in the low-orbit spacecraft is ≤1mm.
[0009] As a further technical solution, the carbonate comprises the following components in parts by weight: Barium carbonate 10.30~16.22 parts, lithium carbonate 0.49~7.65 parts, potassium carbonate 13.21~19.82 parts; The nitrates include sodium nitrate.
[0010] As a further technical solution, the mass ratio of lead oxide, molybdenum dioxide, tetrabutyl titanate and kerosene is 1~1.8:0.5:3.4:0.2.
[0011] In the radiation-resistant glass for low-Earth orbit spacecraft of the present invention, the mass ratio of the raw materials lead oxide, molybdenum dioxide, tetrabutyl titanate and kerosene is specified as 1~1.8:0.5:3.4:0.2, which further improves the radiation resistance performance of the glass for low-Earth orbit spacecraft.
[0012] As a further technical solution, the mass ratio of cerium dioxide, gallium trioxide, lead oxide and tetrabutyl titanate is 1:1:1:3.4.
[0013] In the radiation-resistant glass for low-Earth orbit spacecraft of the present invention, the mass ratio of the raw materials cerium dioxide, gallium trioxide, lead oxide and tetrabutyl titanate is further defined as 1:1:1:3.4. While ensuring the radiation resistance performance of the glass for low-Earth orbit spacecraft, the impact performance of the glass for low-Earth orbit spacecraft is also improved.
[0014] This invention also proposes a method for preparing radiation-resistant glass for low-Earth orbit spacecraft, comprising the following steps: S1. Mix quartz sand, aluminum hydroxide, boric acid, carbonate, cerium dioxide, gallium trioxide, antimony trioxide, nitrate, molybdenum dioxide, and lead oxide evenly to obtain a mixture; S2. Melt the mixture, add tetrabutyl titanate and kerosene and mix to obtain molten glass; S3. The molten glass is shaped to obtain a semi-finished glass product; S4. Demold and anneal the glass semi-finished product to obtain the radiation-resistant glass for low-orbit spacecraft.
[0015] In the radiation-resistant glass for low-Earth orbit spacecraft of this invention, antimony trioxide (Sb₂O₃) and sodium nitrate (NaNO₃) can play a clarifying and homogenizing role. Sb₂O₃ can also supplement the network in the glass structure. After decomposition, NaNO₃ forms Na₂O, which enters the glass as an external network component. During the glass chemical strengthening process, Na₂O and Li₂O react with K₂ in the molten salt. + For chemical ion exchange, K, with its larger radius, + with Na + Li + After the exchange, a compressive stress layer will be formed on the glass surface to ensure the strength, Vickers hardness and other properties of the radiation-resistant glass surface used in low-orbit spacecraft.
[0016] As a further technical solution, the radiation-resistant glass for low-orbit spacecraft is composed of the following components by mass percentage: Al2O3: 5.5%~6.7%, B2O3: 5%~13.9%, BaO: 8%~12.6%, Li2O: 0.2%~3.1%, K2O: 9%~13.5%, CeO2: 0.6%~2.1%, TiO2: 0.8%~3%, Ga2O3: 0.2%~1.2%, MoO2: 0.5%~1.4%, PbO: 0.8%~2.2%, Sb2O3: 0.5%~1%, Na2O: 0.73%~1.68%, with the balance being SiO2 and other unavoidable impurities.
[0017] The radiation-resistant glass for low-Earth orbit spacecraft of this invention contains BaO and K2O. The combined effect of BaO and K2O ensures the optical performance of the radiation-resistant glass for low-Earth orbit spacecraft.
[0018] As a further technical solution, the melting temperature is 1430~1480℃ and the time is 1~2h; In step S2, the mixing temperature is 1450~1520℃, the rotation speed is 60~100rpm, and the time is 15~25min.
[0019] As a further technical solution, the demolding temperature is 1050~1100℃.
[0020] As a further technical solution, the annealing temperature is 580~635℃ and the time is 1~3h.
[0021] The present invention also proposes the application of the radiation-resistant glass for low-Earth orbit spacecraft described herein, or the radiation-resistant glass for low-Earth orbit spacecraft prepared by the aforementioned method, in low-Earth orbit spacecraft.
[0022] The working principle and beneficial effects of this invention are as follows: In this invention, the glass raw material contains cerium dioxide, gallium trioxide, lead oxide, tetrabutyl titanate, molybdenum dioxide, and kerosene, which improves the radiation resistance of glass for low-orbit spacecraft.
[0023] Gallium trioxide has a high refractive index and large dispersion, and its application in low Earth orbit will not cause glass deformation, meeting the re-orbit operation requirements of low Earth orbit spacecraft. Tetrabutyl titanate is added in liquid form during the glass manufacturing process and can react chemically with kerosene to promote the removal of bubbles in the glass melt, improve the uniformity of the glass, prevent phase separation and crystallization, and accelerate the clarification process of the glass melt. Furthermore, the Ti element enters the glass structure, which not only supplements the network structure and reduces defects, but also absorbs harmful particles in sunlight to play a role in radiation resistance. Lead oxide can absorb space radiation particles and reduce the glass melting temperature, reducing energy consumption during the glass melting process. In addition, Pb element can strengthen the network structure and improve the stability of the glass structure, thereby ensuring the stability of radiation resistance performance. Therefore, the above-mentioned raw materials work together to strengthen the network structure of glass, reduce internal defects, absorb and scatter radiation energy, and synergistically improve the radiation resistance of glass for low-Earth orbit spacecraft. This solves the industry problem of high radiation resistance for low-Earth orbit spacecraft glass with a thickness of ≤1mm, which is more easily penetrated by radiation particles due to its thinness. Detailed Implementation
[0024] The technical solutions of the present invention will be clearly and completely described below with reference to the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.
[0025] Example 1 A method for preparing radiation-resistant glass for low-Earth orbit spacecraft includes the following steps: S1. By weight, 68 parts of quartz sand, 10.25 parts of aluminum hydroxide, 8.86 parts of boric acid, 10.30 parts of barium carbonate, 0.49 parts of lithium carbonate, 13.21 parts of potassium carbonate, 0.6 parts of cerium dioxide, 0.2 parts of gallium trioxide, 0.5 parts of antimony trioxide, 2 parts of sodium nitrate, 0.5 parts of molybdenum dioxide, and 0.8 parts of lead oxide are mixed evenly to obtain a mixture. S2. Add the mixture to the crucible and heat it in the furnace to 1480℃ for 2 hours. Then heat it to 1520℃ and add 3.4 parts of tetrabutyl titanate and 0.2 parts of kerosene while mechanically stirring (the tetrabutyl titanate and kerosene are added by high-temperature atomization). The mechanical stirring speed is 60 rpm and the time is 25 minutes to obtain glass melt. S3. Pour the molten glass into the forming mold for overflow forming to obtain a glass semi-finished product; S4. The glass semi-finished product is cooled to 1100℃, shrinks, and then separates from the mold. It is then placed in a muffle furnace for annealing at 635℃ for 3 hours. After annealing, it is cut, polished, and a 0.16mm thick radiation-resistant glass for low-Earth orbit spacecraft is obtained (composed of the following components by mass percentage: Al2O3: 6.7%, B2O3: 5%, BaO: 8%, Li2O: 0.2%, K2O: 9%, CeO2: 0.6%, TiO2: 0.8%, Ga2O3: 0.2%, MoO2: 0.5%, PbO: 0.8%, Sb2O3: 0.5%, Na2O: 0.73%, with the balance being SiO2 and other unavoidable impurities).
[0026] Example 2 The method for preparing radiation-resistant glass for low-Earth orbit spacecraft includes the following steps: S1. By weight, 45.5 parts of quartz sand, 8.41 parts of aluminum hydroxide, 16.12 parts of boric acid, 16.22 parts of barium carbonate, 7.65 parts of lithium carbonate, 19.82 parts of potassium carbonate, 2.1 parts of cerium dioxide, 1.2 parts of gallium trioxide, 1 part of antimony trioxide, 4.6 parts of sodium nitrate, 1.4 parts of molybdenum dioxide, and 2.2 parts of lead oxide are mixed evenly to obtain a mixture. S2. Add the mixture to the crucible and heat it in the furnace to 1430℃ for 1 hour. Then heat it to 1450℃ and add 12.75 parts of tetrabutyl titanate and 0.8 parts of kerosene while mechanically stirring (the tetrabutyl titanate and kerosene are added by high-temperature atomization). The mechanical stirring speed is 100 rpm and the time is 15 minutes to obtain glass melt. S3. Pour the molten glass into the forming mold for overflow forming to obtain a glass semi-finished product; S4. The glass semi-finished product is cooled to 1050℃, shrinks, and then separated from the mold. It is then placed in a muffle furnace for annealing at 580℃ for 1 hour. After annealing, it is cut, polished, and a 0.16mm thick radiation-resistant glass for low-orbit spacecraft is obtained (composed of the following components by mass percentage: Al2O3: 5.5%, B2O3: 9.1%, BaO: 12.6%, Li2O: 3.1%, K2O: 13.5%, CeO2: 2.1%, TiO2: 3%, Ga2O3: 1.2%, MoO2: 1.4%, PbO: 2.2%, Sb2O3: 1%, Na2O: 1.68%, with the balance being SiO2 and other unavoidable impurities).
[0027] Example 3 The method for preparing radiation-resistant glass for low-Earth orbit spacecraft includes the following steps: S1. By weight, 48.37 parts of quartz sand, 9.17 parts of aluminum hydroxide, 24.62 parts of boric acid, 12.88 parts of barium carbonate, 7.4 parts of lithium carbonate, 14.68 parts of potassium carbonate, 2 parts of cerium dioxide, 1 part of gallium trioxide, 1 part of antimony trioxide, 2 parts of sodium nitrate, 1 part of molybdenum dioxide, and 2 parts of lead oxide are mixed evenly to obtain a mixture. S2. Add the mixture to the crucible and heat it in the furnace to 1450℃ for 1 hour. Then heat it to 1480℃ and add 4.25 parts of tetrabutyl titanate and 0.3 parts of kerosene while mechanically stirring (the tetrabutyl titanate and kerosene are added by high-temperature atomization). The mechanical stirring speed is 70 rpm and the time is 20 minutes to obtain glass melt. S3. Pour the molten glass into the forming mold for overflow forming to obtain a glass semi-finished product; S4. The glass semi-finished product is cooled to 1060℃, shrinks, and then separates from the mold. It is then placed in a muffle furnace for annealing at 595℃ for 2 hours. After annealing, it is cut, polished, and a 0.16mm thick radiation-resistant glass for low-orbit spacecraft is obtained (composed of the following components by mass percentage: Al2O3: 6%, B2O3: 13.9%, BaO: 10%, Li2O: 3%, K2O: 10%, CeO2: 2%, TiO2: 1%, Ga2O3: 1%, MoO2: 1%, PbO: 2%, Sb2O3: 1%, Na2O: 0.73%, with the balance being SiO2 and other unavoidable impurities).
[0028] Example 4 The method for preparing radiation-resistant glass for low-Earth orbit spacecraft includes the following steps: S1. By weight, 54.15 parts of quartz sand, 8.87 parts of aluminum hydroxide, 15.59 parts of boric acid, 12.36 parts of barium carbonate, 4.44 parts of lithium carbonate, 15.86 parts of potassium carbonate, 1.6 parts of cerium dioxide, 0.8 parts of gallium trioxide, 0.8 parts of antimony trioxide, 3.5 parts of sodium nitrate, 0.9 parts of molybdenum dioxide, and 1.6 parts of lead oxide are mixed evenly to obtain a mixture. S2. Add the mixture to the crucible and heat it in the furnace to 1460℃ for 1.5 hours. Then heat it to 1490℃ and add 8.08 parts of tetrabutyl titanate and 0.5 parts of kerosene while mechanically stirring (the tetrabutyl titanate and kerosene are added by high-temperature atomization). The mechanical stirring speed is 80 rpm and the time is 15 minutes to obtain glass melt. S3. Pour the molten glass into the forming mold for overflow forming to obtain a glass semi-finished product; S4. The glass semi-finished product is cooled to 1055℃, shrinks, and then separates from the mold. It is then placed in a muffle furnace for annealing at 605℃ for 2 hours. After annealing, it is cut, polished, and a 0.16mm thick radiation-resistant glass for low-Earth orbit spacecraft is obtained (composed of the following components by mass percentage: Al2O3: 5.8%, B2O3: 8.8%, BaO: 9.6%, Li2O: 1.8%, K2O: 10.8%, CeO2: 1.6%, TiO2: 1.9%, Ga2O3: 0.8%, MoO2: 0.9%, PbO: 1.6%, Sb2O3: 0.8%, Na2O: 1.45%, with the balance being SiO2 and other unavoidable impurities).
[0029] Example 5 The method for preparing radiation-resistant glass for low-Earth orbit spacecraft includes the following steps: S1. By weight, 60.28 parts of quartz sand, 9.02 parts of aluminum hydroxide, 12.22 parts of boric acid, 10.94 parts of barium carbonate, 3.21 parts of lithium carbonate, 14.97 parts of potassium carbonate, 1.6 parts of cerium dioxide, 0.4 parts of gallium trioxide, 0.7 parts of antimony trioxide, 3.2 parts of sodium nitrate, 0.7 parts of molybdenum dioxide, and 1 part of lead oxide are mixed evenly to obtain a mixture. S2. Add the mixture to the crucible and heat it in the furnace to 1470℃ for 2 hours. Then heat it to 1505℃ and add 5.1 parts of tetrabutyl titanate and 0.4 parts of kerosene while mechanically stirring (the tetrabutyl titanate and kerosene are added by high-temperature atomization). The mechanical stirring speed is 90 rpm and the time is 23 minutes to obtain glass melt. S3. Pour the molten glass into the forming mold for overflow forming to obtain a glass semi-finished product; S4. The glass semi-finished product is cooled to 1090℃, shrinks, and then separates from the mold. It is then placed in a muffle furnace for annealing at 615℃ for 2.5 hours. After annealing, it is cut, polished, and a 0.16mm thick radiation-resistant glass for low-orbit spacecraft is obtained (composed of the following components by mass percentage: Al2O3: 5.9%, B2O3: 6.9%, BaO: 8.5%, Li2O: 1.3%, K2O: 10.2%, CeO2: 1.6%, TiO2: 1.2%, Ga2O3: 0.4%, MoO2: 0.7%, PbO: 1%, Sb2O3: 0.7%, Na2O: 1.32%, with the balance being SiO2 and other unavoidable impurities).
[0030] Example 6 The only difference between this embodiment and Embodiment 1 is that the amount of lead oxide added during the preparation of the radiation-resistant glass for low-orbit spacecraft is 1 part.
[0031] Example 7 The only difference between this embodiment and Embodiment 1 is that 1.8 parts of lead oxide are added during the preparation of radiation-resistant glass for low-orbit spacecraft.
[0032] Example 8 The only difference between this embodiment and Embodiment 1 is that 1.9 parts of lead oxide are added during the preparation of radiation-resistant glass for low-orbit spacecraft.
[0033] Example 9 The only difference between this embodiment and Embodiment 6 is that 1 part of cerium dioxide and 1 part of gallium trioxide are added during the preparation of radiation-resistant glass for low-orbit spacecraft.
[0034] Example 10 The only difference between this embodiment and Embodiment 6 is that 1.4 parts of cerium dioxide and 1.2 parts of gallium trioxide are added during the preparation of radiation-resistant glass for low-orbit spacecraft.
[0035] Comparative Example 1 The method for preparing radiation-resistant glass for low-Earth orbit spacecraft includes the following steps: S1. By weight, 68.46 parts of quartz sand, 14.38 parts of aluminum hydroxide, 5.31 parts of boric acid, 3.86 parts of barium carbonate, 0.25 parts of lithium carbonate, 11.74 parts of potassium carbonate, 1 part of cerium dioxide, 1 part of gallium trioxide, 0.8 parts of antimony trioxide, 3 parts of sodium nitrate, 1 part of molybdenum dioxide, and 2 parts of lead oxide are mixed evenly to obtain a mixture. S2. Add the mixture to the crucible and heat it in the furnace to 1480℃ for 2 hours. Then heat it to 1520℃ and add 4.25 parts of tetrabutyl titanate and 0.38 parts of kerosene (tetrabutyl titanate and kerosene are added by high-temperature atomization) while mechanically stirring. The mechanical stirring speed is 60 rpm and the time is 25 minutes to obtain glass melt. S3. Pour the molten glass into the forming mold for overflow forming to obtain a glass semi-finished product; S4. The glass semi-finished product is cooled to 1100℃, shrinks, and then separates from the mold. It is then placed in a muffle furnace for annealing at 635℃ for 3 hours. After annealing, it is cut, polished, and a 0.16mm thick radiation-resistant glass for low-orbit spacecraft is obtained (composed of the following components by mass percentage: Al2O3: 9.4%, B2O3: 3%, BaO: 3%, Li2O: 0.1%, K2O: 8%, CeO2: 1%, TiO2: 1%, Ga2O3: 1%, MoO2: 1%, PbO: 2%, Sb2O3: 0.8%, Na2O: 1.24%, with the balance being SiO2 and other unavoidable impurities).
[0036] Comparative Example 2 The method for preparing radiation-resistant glass for low-Earth orbit spacecraft includes the following steps: S1. By weight, 38.96 parts of quartz sand, 6.12 parts of aluminum hydroxide, 29.94 parts of boric acid, 19.31 parts of barium carbonate, 9.87 parts of lithium carbonate, 22.02 parts of potassium carbonate, 3.5 parts of cerium dioxide, 0.1 parts of gallium trioxide, 0.4 parts of antimony trioxide, 1.8 parts of sodium nitrate, 0.4 parts of molybdenum dioxide, and 0.5 parts of lead oxide are mixed evenly to obtain a mixture. S2. Add the mixture to the crucible and heat it in the furnace to 1480℃ for 2 hours. Then heat it to 1520℃ and add 2.13 parts of tetrabutyl titanate and 0.1 parts of kerosene while mechanically stirring (the tetrabutyl titanate and kerosene are added by high-temperature atomization). The mechanical stirring speed is 60 rpm and the time is 25 minutes to obtain glass melt. S3. Pour the molten glass into the forming mold for overflow forming to obtain a glass semi-finished product; S4. The glass semi-finished product is cooled to 1100℃, shrinks, and then separates from the mold. It is then placed in a muffle furnace for annealing at 635℃ for 3 hours. After annealing, it is cut, polished, and a 0.16mm thick radiation-resistant glass for low-Earth orbit spacecraft is obtained (composed of the following components by mass percentage: Al2O3: 4%, B2O3: 16.9%, BaO: 15%, Li2O: 4%, K2O: 15%, CeO2: 3.5%, TiO2: 0.5%, Ga2O3: 0.1%, MoO2: 0.4%, PbO: 0.5%, Sb2O3: 0.4%, Na2O: 0.74%, with the balance being SiO2 and other unavoidable impurities).
[0037] Comparative Example 3 The only difference between this comparative example and Example 1 is that tetrabutyl titanate and kerosene are not added during the preparation of the radiation-resistant glass for low-Earth orbit spacecraft.
[0038] Comparative Example 4 The only difference between this comparative example and Example 1 is that molybdenum dioxide is replaced with lead oxide in the preparation of radiation-resistant glass for low-Earth orbit spacecraft.
[0039] Comparative Example 5 The only difference between this comparative example and Example 1 is that, in the preparation of radiation-resistant glass for low-Earth orbit spacecraft, lead oxide is replaced with molybdenum dioxide.
[0040] Comparative Example 6 The only difference between this comparative example and Example 1 is that lead oxide is replaced with cerium dioxide in the preparation of radiation-resistant glass for low-Earth orbit spacecraft.
[0041] Comparative Example 7 The only difference between this comparative example and Example 1 is that lead oxide is replaced with gallium trioxide in the preparation of radiation-resistant glass for low-Earth orbit spacecraft.
[0042] Experimental Example The radiation-resistant glass for low-orbit spacecraft prepared in Examples 1-10 and Comparative Examples 1-7 was tested for transmittance attenuation rate after irradiation at different wavelengths according to the method in GJB1976A-2021 "Specification for Radiation-Resistant Glass Covers for Space" to reflect its resistance to electron radiation, with 500nm≤λ≤2000nm; the impact performance was tested according to the method specified in GB / T 36259-2018 "High-Aluminosilicate Glass for Touch Screen Covers", and the test results are shown in Table 1 (in Table 1, "-" indicates that the data was not tested).
[0043] Table 1. Test results of resistance to electron radiation and impact performance
[0044] As shown in Table 1, the radiation-resistant glass for low-Earth orbit spacecraft prepared in the embodiments of the present invention has an electron radiation resistance of less than 1%. Therefore, the glass raw materials of the present invention contain cerium dioxide, gallium trioxide, lead oxide, tetrabutyl titanate, molybdenum dioxide and kerosene, which improves the radiation resistance of the glass for low-Earth orbit spacecraft.
[0045] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.
Claims
1. Radiation-resistant glass for low-Earth orbit spacecraft, characterized in that, The raw materials include the following parts by weight: quartz sand 45.5~68 parts, aluminum hydroxide 8.41~10.25 parts, boric acid 8.86~24.62 parts, carbonate 24~43.69 parts, cerium dioxide 0.6~2.1 parts, gallium trioxide 0.2~1.2 parts, antimony trioxide 0.5~1 parts, nitrate 2~4.6 parts, molybdenum dioxide 0.5~1.4 parts, lead oxide 0.8~2.2 parts, tetrabutyl titanate 3.4~12.75 parts, and kerosene 0.2~0.8 parts.
2. The radiation-resistant glass for low-orbit spacecraft according to claim 1, characterized in that, The thickness of the radiation-resistant glass used in the low-orbit spacecraft is ≤1mm.
3. The radiation-resistant glass for low-Earth orbit spacecraft according to claim 1, characterized in that, The carbonate comprises the following components in parts by weight: Barium carbonate 10.30~16.22 parts, lithium carbonate 0.49~7.65 parts, potassium carbonate 13.21~19.82 parts; The nitrates include sodium nitrate.
4. The radiation-resistant glass for low-orbit spacecraft according to claim 1, characterized in that, The mass ratio of lead oxide, molybdenum dioxide, tetrabutyl titanate, and kerosene is 1~1.8:0.5:3.4:0.
2.
5. The radiation-resistant glass for low-orbit spacecraft according to claim 4, characterized in that, The mass ratio of cerium dioxide, gallium trioxide, lead oxide, and tetrabutyl titanate is 1:1:1:3.
4.
6. A method for preparing radiation-resistant glass for low-Earth orbit spacecraft, used to prepare the radiation-resistant glass for low-Earth orbit spacecraft as described in any one of claims 1 to 5, characterized in that, Includes the following steps: S1. Mix quartz sand, aluminum hydroxide, boric acid, carbonate, cerium dioxide, gallium trioxide, antimony trioxide, nitrate, molybdenum dioxide, and lead oxide evenly to obtain a mixture; S2. Melt the mixture, add tetrabutyl titanate and kerosene and mix to obtain molten glass; S3. The molten glass is shaped to obtain a semi-finished glass product; S4. Demold and anneal the glass semi-finished product to obtain the radiation-resistant glass for low-orbit spacecraft.
7. The method for preparing radiation-resistant glass for low-Earth orbit spacecraft according to claim 6, characterized in that, The radiation-resistant glass for low-Earth orbit spacecraft is composed of the following components by mass percentage: Al2O3: 5.5%~6.7%, B2O3: 5%~13.9%, BaO: 8%~12.6%, Li2O: 0.2%~3.1%, K2O: 9%~13.5%, CeO2: 0.6%~2.1%, TiO2: 0.8%~3%, Ga2O3: 0.2%~1.2%, MoO2: 0.5%~1.4%, PbO: 0.8%~2.2%, Sb2O3: 0.5%~1%, Na2O: 0.73%~1.68%, with the balance being SiO2 and other unavoidable impurities.
8. The method for preparing radiation-resistant glass for low-Earth orbit spacecraft according to claim 6, characterized in that, The melting temperature is 1430~1480℃, and the melting time is 1~2 hours; In step S2, the mixing temperature is 1450~1520℃, the rotation speed is 60~100rpm, and the time is 15~25min.
9. The method for preparing radiation-resistant glass for low-Earth orbit spacecraft according to claim 6, characterized in that, The demolding temperature is 1050~1100℃; The annealing temperature is 580~635℃, and the time is 1~3h.
10. The application of the radiation-resistant glass for low-Earth orbit spacecraft according to any one of claims 1 to 5, or the radiation-resistant glass for low-Earth orbit spacecraft prepared by the preparation method according to any one of claims 6 to 9, in low-Earth orbit spacecraft.