Design method and device for radiation shielding lightweight material of aerospace electronic component and readable storage medium

Abstract

The invention discloses a design method and equipment for a radiation shielding lightweight material of an aerospace electronic component, and a readable storage medium, and relates to the field of aerospace materials. The design method comprises the following steps: determining that the radiation shielding material is of a multi-layer composite structure; the total mass thickness of the radiation shielding material is designed to be lower than the equivalent mass thickness of an Al plate under the same shielding performance; designing a spacecraft equivalent model; gradually adjusting the number of layers of the designed radiation shielding material, the atomic number of each layer, the occupied mass thickness and the stacking sequence, and performing numerical simulation by adopting a Monte Carlo method; the average energy deposition of the silicon balls in the equivalent model of the spacecraft and the cumulative total dose of the total radiation quantity in 10 years are simulated and calculated, and then a radiation shielding material is selected according to the anti-radiation requirement. According to the shielding material designed through the method, the shielding efficiency is improved, and the quality of the shielding material is controlled; and electronic components in the spacecraft can be protected from being subjected to less accumulated dose in the on-orbit working time.

Description

Technical Field

[0001] The present invention relates to the field of aerospace materials, and particularly to a design method, device, and readable storage medium for a lightweight radiation shielding material for aerospace electronic components. Background Art

[0002] Spacecraft need to face strong radiation from solar wind, high-energy electrons, protons, and rays (GCRs). Electronic components and instruments in spacecraft are vulnerable to radiation, leading to malfunctions or performance degradation. It is statistically shown that 60 - 70% of satellite failures usually result from the influence of charged particle radiation. Efficient radiation shielding materials can reduce the radiation dose received by electronic devices and extend the in-orbit life of spacecraft. Although traditional radiation shielding materials (such as lead and thick aluminum plates) can effectively shield, the required weight is too high to meet the lightweight requirements of spacecraft. In addition, they will generate more bremsstrahlung radiation, causing additional radiation damage to electronic components. Summary of the Invention

[0003] In order to break through the limitations of traditional shielding materials and obtain a new lightweight shielding material with better performance and lower density, which helps to reduce the launch cost and improve the competitiveness of commercial aerospace. The present invention provides a design method, device, and readable storage medium for a radiation shielding material for aerospace electronic components.

[0004] The design method of the lightweight radiation shielding material for aerospace electronic components of the present invention is carried out according to the following steps:

[0005] Determine that the radiation shielding material is a multi-layer composite structure;

[0006] Design the total mass thickness of the radiation shielding material to be lower than the equivalent mass thickness of the Al plate under the same shielding performance;

[0007] Design an equivalent model of the spacecraft: Introduce the AE-8 electron energy spectrum in the geosynchronous orbit, use the total radiation dose of the omnipotent spectrum electrons in this orbit for 10 years as the incident electrons, use the designed radiation shielding material as the closed outer skin, and place a silicon sphere at the center of the above outer skin as the equivalent electronic component;

[0008] Gradually adjust the number of layers, atomic number, mass thickness occupied, and stacking order of the designed radiation shielding material, and perform numerical simulation using the Monte Carlo method; simulate and calculate the average energy deposition of the silicon sphere in the equivalent model of the spacecraft and the cumulative total dose of the total radiation dose for 10 years, and then select the radiation shielding material according to the anti-radiation requirements.

[0009] Further, the multi-layer composite structure is 2 layers or 3 layers.

[0010] Further, the anti-radiation requirement is that the cumulative dose that the equivalent electronic component can resist for 10 years is 10 - 100 Gy.

[0011] Further, the single-layer material in the multi-layer composite structure is a metal material, a polymer material, a ceramic material or a composite material.

[0012] Further, the multi-layer composite structure is composed of two layers, one layer being a low-Z element material and the other layer being a high-Z element material.

[0013] Among them, the high-Z element is an element with an atomic number Z exceeding 50; the low-Z element is an element with an atomic number Z lower than 30.

[0014] An electronic device according to the present invention includes:

[0015] A memory for storing a computer program;

[0016] A processor for executing the computer program to implement the method described in any one of the above.

[0017] A readable storage medium according to the present invention is used to store a computer program, wherein the computer program, when executed by a processor, implements the method described in any one of the above.

[0018] A radiation shielding material for spacecraft electronic components according to the present invention is a radiation shielding material obtained by using the method described in any one of the above.

[0019] The shielding material designed by the method of the present invention realizes the improvement of shielding efficiency and the control of the mass of the shielding material (that is, the shielding efficiency is improved without increasing the mass of the shielding material; or the mass of the shielding material is reduced without improving the shielding efficiency); it can protect the electronic components in the spacecraft from less cumulative dose during the on-orbit working time. The on-orbit service cycle of the spacecraft is generally 10 years. The shielding material designed by the present invention takes the equivalent mass thickness of a 2-mm aluminum plate as a reference. Without increasing the mass, under the geosynchronous orbit energy spectrum environment and the satellite equivalent model, it is sufficient to protect the electronic components in the satellite for 10 years of on-orbit working requirements. Description of the Drawings

[0020] Figure 1 It is the simulation model diagram in Embodiment 1;

[0021] Figure 2 It is the radiation shielding performance of the shielding material to be tested in Embodiment 1; Figure 2 In which (a) 1 MeV - single metal; (b) 2 MeV - single metal; (c) 1 MeV - bimetal; (d) 2 MeV - bimetal;

[0022] Figure 3 It is the satellite electronic component radiation shielding equivalent model diagram in Embodiment 2;

[0023] Figure 4 It is a curve showing the influence of the mass ratio of Ta in the Al / Ta radiation shielding material in Example 2 on the average energy deposition of silicon spheres and the cumulative total radiation dose within the silicon spheres over 10 years;

[0024] Figure 5 It is a relative shielding efficiency diagram of Al / Ta radiation shielding composite materials with different Ta mass fractions under the same mass thickness of an equivalent 2 mm Al plate in Example 2. Specific implementation manners

[0025] The technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without making creative efforts belong to the scope of protection of the present invention.

[0026] It should be noted that, without conflict, the embodiments in the present invention and the features in the embodiments can be combined with each other.

[0027] Specific implementation manner one: This implementation manner is used for the design method of a radiation shielding lightweight material for aerospace electronic components, and is carried out according to the following steps:

[0028] Determine that the radiation shielding material is a multi-layer composite structure;

[0029] Design the total mass thickness of the radiation shielding material to be lower than the equivalent mass thickness of the Al plate under the same shielding performance;

[0030] Design a spacecraft equivalent model: Introduce the AE-8 electron energy spectrum in the geosynchronous orbit, use the total radiation dose of the omnipotent spectrum electrons in this orbit over 10 years as the incident electrons, use the designed radiation shielding material as the closed outer skin, and place silicon spheres at the center of the above outer skin as equivalent electronic components;

[0031] Gradually adjust the number of layers, atomic numbers of each layer, mass thickness occupied, and stacking order of the designed radiation shielding material, and perform numerical simulation using the Monte Carlo method; Simulate and calculate the average energy deposition of the silicon spheres and the cumulative total dose of the total radiation dose over 10 years in the spacecraft equivalent model, and then select the radiation shielding material according to the anti-radiation requirements.

[0032] The anti-radiation requirements include: multi-objective constraint conditions such as shielding and lightweight determined by the service life of the spacecraft and the space radiation environment.

[0033] Specific implementation manner two: The difference between this implementation manner and specific implementation manner one is that: the multi-layer composite structure is more than 2 layers. Other steps and parameters are the same as those in specific implementation manner one.

[0034] Specific Embodiment 3: The difference between this embodiment and Specific Embodiment 1 or 2 is that the multi-layer composite structure is 2 or 3 layers. Other steps and parameters are the same as those in Specific Embodiment 1 or 2.

[0035] Specific Embodiment 4: The difference between this embodiment and any one of Specific Embodiments 1 to 3 is that the outer skin is spherical. Other steps and parameters are the same as those in any one of Specific Embodiments 1 to 3.

[0036] Specific Embodiment 5: The difference between this embodiment and any one of Specific Embodiments 1 to 4 is that the anti-radiation requirement is that the cumulative dose that the equivalent electronic components can resist in 10 years is 10 - 100 Gy. Other steps and parameters are the same as those in any one of Specific Embodiments 1 to 4.

[0037] Specific Embodiment 6: The difference between this embodiment and any one of Specific Embodiments 1 to 5 is that the single-layer material in the multi-layer composite structure is a metal material, a polymer material, a ceramic material or a composite material. Other steps and parameters are the same as those in any one of Specific Embodiments 1 to 5.

[0038] Specific Embodiment 7: The difference between this embodiment and any one of Specific Embodiments 1 to 6 is that the multi-layer composite structure is 2 layers, one layer is a low-Z element material, and the other layer is a high-Z element material. Other steps and parameters are the same as those in any one of Specific Embodiments 1 to 6.

[0039] Specific Embodiment 8: The difference between this embodiment and Specific Embodiment 7 is that the multi-layer composite structure is 2 layers, one layer is elemental aluminum, and the other layer is elemental high-Z metal. Other steps and parameters are the same as those in Specific Embodiment 7.

[0040] Specific Embodiment 9: The difference between this embodiment and Specific Embodiment 8 is that the multi-layer composite structure is 2 layers, one layer is elemental aluminum, and the other layer is elemental tantalum. Other steps and parameters are the same as those in Specific Embodiment 8.

[0041] Specific Embodiment 10: The difference between this embodiment and Specific Embodiment 9 is that the multi-layer composite structure is 2 layers, the outer layer is elemental aluminum, and the inner layer is elemental tantalum. Other steps and parameters are the same as those in Specific Embodiment 9.

[0042] Example 1

[0043] The quantification of the shielding performance of this example is obtained through the simulation of the particle transport software FLUKA.

[0044] Testing method: Monoenergetic electron sources of 1 MeV and 2 MeV are respectively selected as the particle sources, and they are incident linearly; the shielding material to be tested is a sphere with a radius of 2 cm and a total mass thickness of 0.54 g / cm 2in the shape of a round cake (the mass thickness is equivalent to that of a 2-mm aluminum plate), the electron incident ray perpendicularly passes through the center of the material, and the simulation model diagram is as Figure 1 shown.

[0045] The shielding materials to be tested include: Mg, Al, Ti, Fe, Ta, W, Pt, Au, Pb, Mg+Ta, Mg+W, Mg+Pb, Al+Ta, Al+W, Al+Au, Al+Pb, Ti+Ta, Ti+W, Ti+Pb.

[0046] Test results: By statistically calculating the total energy of all particles in the cross-section after passing through the material, the radiation shielding performance of the shielding materials to be tested is evaluated, and the results are as follows Figure 2 shown.

[0047] It can be seen from Figure 2 that the shielding performances of different shielding materials are completely opposite under the monoenergetic electron radiation sources of 1 MeV and 2 MeV. At 1 MeV, for the shielding material with a mass thickness of 0.54 g / cm 2 , the smaller the atomic number, the better the radiation shielding performance; while at 2 MeV, the larger the atomic number, the better the radiation shielding performance. The bimetallic composite plates with a low-Z + high-Z combination show better radiation shielding performance than pure low-Z and pure high-Z at 1 MeV, and show radiation shielding performance between the two at 2 MeV. It can be seen that replacing a single metal plate with a bimetallic composite plate with a low-Z + high-Z combination can achieve better comprehensive radiation shielding performance without increasing the mass.

[0048] Example 2

[0049] The design method of the lightweight material for radiation shielding of aerospace electronic components is carried out according to the following steps:

[0050] Determine that the radiation shielding material is a two-layer composite structure, where the outer layer is a single aluminum and the inner layer is a bimetallic composite plate of single tantalum;

[0051] Design the total mass thickness of the radiation shielding material to be 0.54 g / cm 2 ;

[0052] Design the satellite equivalent model (as Figure 3 shown): Introduce the AE-8 electron energy spectrum in the geosynchronous orbit, use the total radiation dose of the omnipotent spectrum electrons in this orbit for 10 years as the incident electrons, use the designed radiation shielding material as the closed outer skin, and place a silicon sphere at the center of the above outer skin as the equivalent electronic component;

[0053] Gradually adjust the mass fraction of tantalum plates in the designed radiation shielding material, and take 11 nodes from 0 - 100% for sequential testing. Use the Monte Carlo method for numerical simulation, and input into the FLUKA software to simulate and calculate the average energy deposition of the silicon sphere and the cumulative total dose of the total radiation dose over 10 years in the satellite equivalent model.

[0054] The test results are as Figure 4 shown. From Figure 4 it can be seen that when the mass fraction of Ta is between 30% - 90%, the total mass thickness is 0.54 g / cm 2 The aluminum-tantalum bimetallic composite plate can meet the 10-year cumulative dose requirement of satellite electronic components. Among them, the composite plate with the best radiation shielding performance has a Ta mass fraction of 59.259%, that is, this double-layer composite plate is composed of a 0.815-mm aluminum plate and a 0.192-mm tantalum plate.

[0055] Figure 4 The shape of the average energy deposition curve of the silicon sphere in

[0056]

[0057] n total = 1 / 2∫ E dφ·A Al ·t 10y

[0058] Among them, is the cumulative radiation dose in orbit for 10 years;

[0059] is the average energy deposition in the silicon sphere;

[0060] n tatol is the total number of electrons irradiated by the shielding material in orbit for 10 years;

[0061] E tatol is the cumulative energy deposition in the silicon sphere in orbit for 10 years;

[0062] m Si is the mass of the silicon sphere;

[0063] r Si is the radius of the silicon sphere;

[0064] ρ Si is the density of the silicon sphere;

[0065] dφ is the differential electron flux;

[0066] A Al is the surface area of the Al shielding shell;

[0067] t 10y is the cumulative irradiation time of 10 years.

[0068] In the satellite equivalent model, it can be found that traditional pure aluminum plates and pure tantalum plates with a mass thickness of 0.54 g / cm 2 cannot meet the cumulative dose requirements of satellite electronic components. If these pure plates are used, the thickness of the shielding case or skin must be increased, which will cause an increase in the mass of the satellite. By choosing an aluminum-tantalum bimetal composite plate and controlling the mass fraction of tantalum between 30% and 90%, this requirement can be met.

[0069] Taking a 0.2 cm thick aluminum plate as a reference, the relative shielding efficiency of Al / Ta radiation shielding composite materials with different Ta mass fractions under the same mass thickness is as Figure 5 shown.

[0070] The calculation formula for the relative shielding efficiency is:

[0071] η relative = E Al in Si / E x in Si

[0072] where E Al in Si is the energy deposition in the silicon sphere when using Al shielding material, and E x in Si is the energy deposition in the silicon sphere when using the target plate for protection. As Figure 5 can be seen, under the incidence of non-monochromatic electrons in orbit, the addition of tantalum improves the radiation shielding performance compared to pure aluminum. Without increasing the mass, the shielding efficiency is increased by up to 82.4%. Therefore, it can be seen that the shielding material designed by the method of the present invention realizes the improvement of the shielding efficiency and the control of the mass of the shielding material.

[0073] At the same time, various comparisons were also made in terms of the spatial arrangement of the materials, such as three-layer materials, more-layer materials, etc. Finally, a double-layer material with aluminum in the front and tantalum in the back was selected according to the comprehensive radiation shielding performance. Therefore, the research on anti-radiation materials for other equivalent thicknesses, other different element combinations, and other multi-layer materials in the space of electronic components carried out by the method described in this patent is also included in the scope of protection of this patent.

Claims

1. A design method for lightweight materials for radiation shielding of aerospace electronic components, characterized in that, The method is carried out according to the following steps: Determine that the radiation shielding material is a multi-layer composite structure; The total mass thickness is lower than the equivalent mass thickness of the Al plate under the same shielding performance; Design a satellite equivalent model: introduce the AE-8 electron energy spectrum in the geosynchronous orbit, use the total radiation dose of the omnipotent spectrum electrons in this orbit for 10 years as the incident electrons, use the designed radiation shielding material as the closed outer skin, and place a silicon sphere at the center of the above outer skin as the equivalent electronic component; Gradually adjust the number of layers of the designed radiation shielding material, the atomic number of each layer, the mass thickness occupied, and the stacking order, and use the Monte Carlo method for numerical simulation; Simulate and calculate the average energy deposition of the silicon sphere in the spacecraft equivalent model and the cumulative total dose of the total radiation dose for 10 years, and then select the radiation shielding material according to the anti-radiation requirements.

2. The design method of the lightweight material for radiation shielding of aerospace electronic components according to claim 1, characterized in that, The multi-layer composite structure is 2 layers or 3 layers.

3. The design method of the lightweight material for radiation shielding of aerospace electronic components according to claim 1, wherein, The anti-radiation requirement is that the cumulative dose that the equivalent electronic component can resist for 10 years is 10 - 100 Gy.

4. The design method of the lightweight material for radiation shielding of aerospace electronic components according to claim 2, characterized in that, The single-layer material in the multi-layer composite structure is a metal material, a polymer material, a ceramic material or a composite material.

5. The design method of the lightweight material for radiation shielding of aerospace electronic components according to claim 2, wherein, The multi-layer composite structure is 2 layers, one of which is elemental aluminum and the other is elemental high-Z metal.

6. The design method of the lightweight material for radiation shielding of aerospace electronic components according to claim 2, characterized in that, The multi-layer composite structure is 2 layers, one of which is elemental aluminum and the other is elemental tantalum.

7. The design method of the lightweight material for radiation shielding of aerospace electronic components according to claim 2 or 6, characterized in that The multi-layer composite structure is 2 layers, one of which is a low-Z element material and the other is a high-Z element material.

8. An electronic device, characterized in that, Including: A memory for storing a computer program; A processor for executing the computer program to implement the method according to any one of claims 1 to 7.

9. A readable storage medium, characterized in that, For saving a computer program, wherein the computer program, when executed by a processor, implements the method according to any one of claims 1 to 7.

10. A radiation shielding material for satellite electronic components, characterized in that, A radiation shielding material obtained by using the method according to any one of claims 1 to 7.

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