A simulation method for radiation shielding protection against dynamically changing structures

Abstract

The present invention provides a simulation method for radiation shielding protection against a dynamically changing structure, including: combining the actual operating state of a spacecraft to obtain the dynamic change law of the geometric structure of the spacecraft and the material properties; performing dynamic geometric modeling to construct a structure model corresponding to the geometric structure of the spacecraft at any moment, and endowing the structure model with the corresponding material properties of the spacecraft; based on the Monte Carlo method, under different irradiation parameter conditions, calculating the irradiation effect on the geometric structure of the spacecraft at any moment to characterize the radiation shielding protection of the devices inside the geometric structure of the spacecraft; analyzing the change law of the radiation shielding protection of the electronic components inside the spacecraft over time. By analyzing the irradiation effect on the dynamically changing geometric structure of the spacecraft, the present invention can greatly improve the simulation accuracy of the radiation shielding protection of the geometric structure of the spacecraft in the actual operating state, providing a basis for the optimization of the spacecraft structure and materials.

Description

Technical Field

[0001] The present invention relates to the technical field of space environment effects. Specifically, it relates to a simulation method for radiation shielding protection of a dynamically changing structure. Background Art

[0002] With the rapid development of the space industry, higher requirements are also put forward for the radiation protection technology of spacecraft. During the in-orbit flight of a spacecraft, it will interact with various types of particles. These particles can cause ionization radiation effects, displacement radiation effects, single-event effects, etc., thereby significantly affecting the performance of electronic components in the spacecraft, easily leading to abnormalities or malfunctions of the electronic components, and even ultimately causing catastrophic accidents to the spacecraft. Therefore, the research on radiation protection of electronic components in spacecraft is of great significance.

[0003] For electronic components of spacecraft in the space radiation environment, mass shielding methods are mainly used for shielding. A certain thickness of material can shield particle radiation in a certain energy range and reduce the energy of penetrating particles. Through radiation shielding simulation, it is possible to effectively estimate the radiation shielding protection of key electronic components in the spacecraft. However, the currently commonly used radiation shielding simulation methods are mainly for radiation protection materials with fixed shapes. In actual situations, the structure of the spacecraft is constantly changing dynamically. One typical situation is that the solar wings of the spacecraft are constantly rotating, and the dynamic changes in the spacecraft structure will affect the radiation shielding effect of its internal key devices. Therefore, there is an urgent need for a simulation method that can achieve radiation shielding protection for a dynamically changing spacecraft structure, conform to the operating conditions in the actual application scenario of the spacecraft, select more suitable protection materials and geometric structures, and provide an important theoretical basis for the optimization design of the spacecraft. Summary of the Invention

[0004] The problem solved by the present invention is how to provide a radiation shielding simulation method for a dynamically changing spacecraft structure, which conforms to the actual application scenario of the spacecraft and provides theoretical support for spacecraft optimization.

[0005] To solve at least one aspect of the above problems, the present invention provides a simulation method for radiation shielding protection of a dynamically changing structure, including the following steps:

[0006] Step S1: Combine the actual operating state of the spacecraft, obtain the dynamic change law of the geometric structure of the spacecraft, and confirm the material properties of the geometric structure of the spacecraft;

[0007] Step S2: Perform dynamic geometric modeling, construct a structure model corresponding to the geometric structure of the spacecraft at any moment, and endow the structure model with the corresponding material properties of the spacecraft;

[0008] Step S3: Based on the Monte Carlo method, calculate the irradiation effects on the geometric structure of the spacecraft at any moment under different irradiation parameters, and characterize the radiation shielding protection for the devices inside the spacecraft geometric structure.

[0009] Step S4: Analyze the variation law of the radiation shielding protection for the electronic components inside the spacecraft over time.

[0010] Preferably, in the step S1, the spacecraft geometric structure includes the spacecraft solar wing, the TT&C structure, the thermal control structure, the navigation and positioning structure, the battery structure or the antenna structure.

[0011] Preferably, in the step S2, when performing dynamic geometric modeling, the spacecraft geometric structure is simplified into a flat plate structure with a certain thickness.

[0012] Preferably, in the step S3, the irradiation parameters include the radiation particle type, the radiation particle energy spectrum and the radiation particle incident angle.

[0013] Preferably, the radiation particle type includes electrons, protons, neutrons or heavy ions.

[0014] Preferably, in the step S3, the radiation effects include the ionization absorbed dose and the displacement absorbed dose.

[0015] Preferably, the step S3 further includes that when irradiating the spacecraft geometric structure at any moment, automatically adding a shielding layer on the irradiated side of the spacecraft geometric structure, and comparing the calculation results of the irradiation effects on the spacecraft geometric structure before and after adding the shielding layer.

[0016] Preferably, the material of the shielding layer is aluminum, polyethylene, polyimide or Teflon.

[0017] In the present invention, by obtaining the dynamic change law of the spacecraft geometric structure according to the actual operating state of the spacecraft, constructing the structure model and material properties corresponding to the spacecraft geometric structure at any moment, irradiating the structure model at any moment by a radiation source, and using the Monte Carlo method to simulate and calculate the irradiation effects on the spacecraft geometric structure, it is possible to realize the irradiation effects on the spacecraft at any moment under the actual operating state, and characterize in real time the radiation protection state of the devices in the spacecraft geometric structure; by analyzing the irradiation effects on the dynamically changing spacecraft geometric structure, the simulation accuracy of the radiation shielding protection for the spacecraft geometric structure under the actual operating state can be greatly improved, providing a basis for the optimization of the spacecraft structure and materials. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a flowchart of the simulation method for radiation shielding protection for a dynamically changing structure in an embodiment of the present invention.

[0019] Figure 2 This is a schematic diagram of the dynamic change of the spacecraft solar wing in the embodiment of the present invention;

[0020] Figure 3 This is a schematic diagram of the simplified structural model of the spacecraft solar wing in the embodiment of the present invention;

[0021] Figure 4 This is an analysis diagram of the ionization absorption dose and displacement absorption dose of the spacecraft solar wing after 20 MeV proton irradiation in the embodiment of the present invention;

[0022] Figure 5 This is a trend diagram of the ionization absorption dose and displacement absorption dose of the spacecraft solar wing changing with time after AE-8 electron irradiation in the embodiment of the present invention. Detailed implementation manners

[0023] To make the above objects, features, and advantages of the present invention more obvious and understandable, the following detailed description of the specific embodiments of the present invention is provided.

[0024] It should be noted that, without conflict, the features in the embodiments of the present invention can be combined with each other. The meanings of the terms "include", "comprise", "contain", and "have" are non-restrictive, that is, other steps and other components that do not affect the result can be added. The above terms cover the terms "consisting of" and "consisting essentially of". Unless otherwise specified, materials, equipment, and reagents are commercially available.

[0025] The embodiment of the present invention provides a simulation method for radiation shielding protection against a dynamically changing structure, as Figure 1 shown, including the following steps:

[0026] Step S1: Combine the actual operating state of the spacecraft, obtain the dynamic change law of the geometric structure of the spacecraft, and confirm the material properties of the geometric structure of the spacecraft;

[0027] Step S2: Perform dynamic geometric modeling, construct a structural model corresponding to the geometric structure of the spacecraft at any time, and endow the structural model with the corresponding material properties of the spacecraft;

[0028] Step S3: Based on the Monte Carlo method, under different irradiation parameter conditions, calculate the irradiation effect received by the geometric structure of the spacecraft at any time, and characterize the radiation shielding protection of the devices inside the geometric structure of the spacecraft;

[0029] Step S4: Analyze the change law of the radiation shielding protection received by the electronic components inside the spacecraft with time.

[0030] Among them, in step S1, by analyzing the state of the spacecraft during actual operation, the dynamic change law of the spacecraft's geometric structure is obtained, so that the structural states of the spacecraft's geometric structure at different times can be collected, and dynamic modeling can be carried out to confirm that the material properties of the spacecraft can improve the simulation accuracy.

[0031] Exemplarily, the geometric structure of the spacecraft includes the spacecraft's solar wing, TT&C structure, thermal control structure, navigation and positioning structure, battery structure or antenna structure. During the on-orbit flight of the spacecraft, the solar wing rotates continuously, and the geometric structure changes constantly at different times.

[0032] In step S2, based on the dynamic change law of the spacecraft's geometric structure and the material properties obtained in step S1, dynamic geometric modeling is carried out. To simplify the calculation process, when carrying out dynamic geometric modeling, the spacecraft's geometric structure is simplified into a flat plate structure with a certain thickness.

[0033] In step S3, based on the Monte Carlo method, under different irradiation parameter conditions, the spacecraft's geometric structure at any time constructed in step S2 is irradiated, and the irradiation effect received by the spacecraft's geometric structure is calculated, so as to characterize the radiation shielding protection received by the devices inside the spacecraft's geometric structure.

[0034] Specifically, the irradiation parameters include the irradiation particle type, irradiation particle energy spectrum and irradiation particle incident angle. Among them, the irradiation particle type includes electrons, protons, neutrons or heavy ions; the irradiation effect includes ionization absorption dose and displacement absorption dose, that is, after calculating the irradiation of the irradiation particles, the ionization absorption dose and displacement absorption dose of the spacecraft's geometric structure are calculated, so as to characterize the radiation shielding protection received by the devices inside the spacecraft's geometric structure.

[0035] In addition, in order to verify the shielding protection effect of the shielding layer, when irradiating the spacecraft structure at any time, a shielding layer is automatically added to the side of the spacecraft that is irradiated, and the calculation results of the irradiation effects received by the spacecraft before and after adding the shielding layer are compared, so as to provide a basis for the addition of the shielding layer.

[0036] Exemplarily, the material of the shielding layer can be aluminum, polyethylene, polyimide or Teflon. When the shielding layer is aluminum, the thickness is 0 - 1.8 mm. When the shielding layer is polyethylene, the thickness is 0 - 3.5 mm. When the shielding layer is other materials, the thickness is 0 - 2.8 mm.

[0037] By obtaining the dynamic change law of the spacecraft's geometric structure according to the actual operating state of the spacecraft, constructing the structure model and material properties corresponding to the spacecraft's geometric structure at any time, irradiating the structure model at any time with a radiation source, and simulating and calculating the irradiation effect received by the spacecraft's geometric structure through the Monte Carlo method, it is possible to realize the irradiation effect received by the spacecraft at any time under the actual operating state, and real-time characterize the radiation protection state of the devices in the spacecraft's geometric structure; by analyzing the irradiation effect of the dynamically changing spacecraft's geometric structure, the simulation accuracy of the radiation shielding protection of the spacecraft's geometric structure under the actual operating state can be greatly improved, providing a basis for the optimization of the spacecraft's structure and materials.

[0038] The following further elaborates the present invention in conjunction with specific embodiments. It should be understood that these embodiments are only used to illustrate the present invention and not to limit the scope of the present invention. The experimental methods without specific conditions noted in the following embodiments are generally in accordance with the conditions recommended by the manufacturer.

[0039] Embodiment 1

[0040] This embodiment provides a simulation method for radiation shielding protection of a dynamically changing structure, including:

[0041] 1.1. Combining the actual operating state of the spacecraft, obtaining the dynamic change law of the spacecraft's solar wing, and confirming that the material property of the spacecraft's solar wing is an aluminum honeycomb sandwich structure with a graphite fiber composite material as the panel;

[0042] 1.2. Using the gdml structure for dynamic geometry modeling, constructing the structure model corresponding to the spacecraft's solar wing at any time, and endowing the structure model with the corresponding material properties of the spacecraft, where the structure model is simplified to a flat plate structure as shown in Figure 3 shown.

[0043] 1.3. Selecting a 20 MeV proton source to irradiate the solar wing structure model at one moment from the front, and when irradiating the structure model, automatically adding an aluminum shielding layer with a thickness of 1.8 mm on the irradiated side of the solar wing, and using the Monte Carlo method to calculate the TID (total ionizing dose) and NID (non-ionizing displacement dose) generated before and after adding the aluminum shielding layer respectively;

[0044] As shown in Figure 2 shown, Figure 2 where a) in is the normal state of the spacecraft's solar wing, while Figure 2 where b) in is the state of the spacecraft's solar wing when receiving proton irradiation, and an aluminum shielding layer is automatically added on the irradiated side of the solar wing;

[0045] As shown in Figure 4 shown, Figure 4In a), the TID (Total Ionizing Dose) results after 20 MeV irradiation are shown, Figure 4 In b), the NID (Non-Ionizing Displacement Dose) results after 20 MeV irradiation are shown. In the figure, TID_shielding and NID_shielding respectively represent the calculation results under the condition of adding an aluminum shielding layer, while TID_unprotected and NID_unprotected respectively represent the calculation results without adding an aluminum shielding layer.

[0046] Example 2

[0047] 2.1. Combining with the actual operating state of the spacecraft, obtain the dynamic change law of the spacecraft's solar wing between 14:00 on January 3, 2017 and 2:00 on January 5, 2017. Record the structural state of the spacecraft's solar wing every 4 hours, and confirm that the material property of the spacecraft's solar wing is a graphite fiber composite material as the frame, covered with a polyester amide film;

[0048] 2.2. Use the gdml structure for dynamic geometry modeling to construct a structural model corresponding to the structural state of the spacecraft's solar wing in step 2.1, and endow the structural model with the corresponding material properties of the spacecraft. The structural model is simplified to a flat plate structure;

[0049] 2.3. Select the electron source of AE-8 to irradiate the dynamic structural model of the solar wing constructed in step 2.2 from the front. When irradiating the structural model, automatically add an aluminum shielding layer with a thickness of 1.8 mm on the irradiated side of the solar wing, and use the Monte Carlo method to calculate the TID (Total Ionizing Dose) and NID (Non-Ionizing Displacement Dose) generated under the structural states of the spacecraft's solar wing at different times respectively;

[0050] As Figure 5 shown, Figure 5 in a), the trend of TID (Total Ionizing Dose) changing with time is shown, while Figure 5 in b), the trend of NID (Non-Ionizing Displacement Dose) changing with time is shown. It can be seen from the figure that the radiation damage values at different times change with time, so it has a certain impact on the spacecraft's solar wing during operation. The thickness of the corresponding protective layer can be set according to the simulation at each moment, and appropriate protective layer materials and thicknesses can be added for each area.

[0051] Although the present disclosure is disclosed as above, the protection scope of the present disclosure is not limited thereto. Those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present disclosure, and these changes and modifications will all fall within the protection scope of the present invention.

Claims

1. A simulation method for radiation shielding protection against dynamically changing structures, characterized in that, It includes the following steps: Step S1: Combine the actual operating state of the spacecraft, obtain the dynamic change law of the geometric structure of the spacecraft, and confirm the material properties of the geometric structure of the spacecraft; Step S2: Conduct dynamic geometric modeling, construct a structural model corresponding to the geometric structure of the spacecraft at any time, and endow the structural model with the corresponding material properties of the spacecraft; Step S3: Based on the Monte Carlo method, calculate the irradiation effect on the geometric structure of the spacecraft at any time under different irradiation parameter conditions, and characterize the radiation shielding protection of the devices inside the geometric structure of the spacecraft; Step S4: Analyze the variation law of the radiation shielding protection of the electronic components inside the spacecraft with time.

2. The simulation method for radiation shielding protection against dynamically changing structures according to claim 1, characterized in that In the said Step S1, the geometric structure of the spacecraft includes the solar wing of the spacecraft, the TT&C structure, the thermal control structure, the navigation and positioning structure, the battery structure or the antenna structure.

3. The simulation method for radiation shielding protection against dynamically changing structures according to claim 1, characterized in that In the said Step S2, when conducting dynamic geometric modeling, the geometric structure of the spacecraft is simplified into a flat plate structure with a certain thickness.

4. The simulation method for radiation shielding protection against dynamically changing structures according to claim 1, characterized in that, In the said Step S3, the irradiation parameters include the type of radiation particles, the energy spectrum of radiation particles and the incident angle of radiation particles.

5. The simulation method for radiation shielding protection against a dynamically changing structure according to claim 4, characterized in that, The said type of radiation particles includes electrons, protons, neutrons or heavy ions.

6. The simulation method for radiation shielding protection against dynamically changing structures according to claim 1, characterized in that In the said Step S3, the irradiation effect includes ionization absorbed dose and displacement absorbed dose.

7. The simulation method for radiation shielding protection against dynamically changing structures according to claim 1, characterized in that, The said Step S3 further includes that when irradiating the geometric structure of the spacecraft at any time, a shielding layer is automatically added to the irradiated side of the geometric structure of the spacecraft, and the calculation results of the irradiation effect on the geometric structure of the spacecraft before and after adding the shielding layer are compared.

8. The simulation method for radiation shielding protection against dynamically changing structures according to claim 7, characterized in that, The material of the said shielding layer is aluminum, polyethylene, polyimide or Teflon.

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