Progressive ionizing radiation shielding for planetary exploration

Abstract

The application provides a planetary exploration strong radiation environment progressive ionizing radiation shielding protection method, which comprises the following steps: according to a planetary exploration task, carrying out space radiation environment analysis, forming an ionizing total dose depth curve table, and formulating a space environment protection design requirement; collating total single machine anti-total dose capacity indexes, and forming a single machine anti-ionizing radiation capacity statistics table; confirming a protection level of matching of each single machine and the space environment protection design requirement; forming a strong radiation environment progressive shielding protection single machine list; evaluating an effect of the progressive ionizing radiation shielding protection strategy; formulating a progressive ionizing radiation shielding protection implementation scheme, and clearly defining single machine protection levels, shielding protection strategies, platform layouts and guarantee conditions, and forming an engineering implementation scheme. The application provides a strong radiation environment protection method for the ionizing radiation protection requirement of the planetary exploration task, and can be applied to engineering and implementation.

Description

Technical Field

[0001] This invention belongs to the field of radiation shielding and protection for spacecraft engineering in planetary exploration missions, and specifically relates to a progressive ionizing radiation shielding and protection method for planetary exploration. Background Technology

[0002] Planetary exploration refers to the exploration activities conducted by man-made spacecraft on planets within the solar system and in interstellar space. With the development of human space activities, planetary exploration targets have expanded from Earth to Venus, Mars, Mercury, Jupiter, and Saturn, and even more distant planets. Compared to Earth's Van Allen radiation belts, similar radiation belt phenomena have been discovered on other planets and moons, among which Jupiter's radiation belts are the most energetic and largest in the solar system.

[0003] It is generally believed that the highest energy of electrons in Earth's orbit is <10 MeV, while the highest energy of electrons in Jupiter's orbit can reach 1 GeV, and the highest energy of protons is several GeV. Comparing the energy spectra of high-energy particles at the geosynchronous orbit (GEO) and Jupiter's equatorial plane at 4Rj (Rj = 71492 km, the radius of Jupiter), the flux of high-energy protons and electrons in Jupiter's orbit is more than two orders of magnitude greater than that of Earth, and the maximum energy is also two orders of magnitude higher. The outer edge of Earth's radiation belts is 7Re (Re = 6371 km, the radius of Earth), while the boundary of Jupiter's main radiation belts can reach 17Rj.

[0004] Therefore, when conducting orbital exploration of Jupiter and its system, the total ionizing dose level encountered by spacecraft far exceeds that encountered by satellites in high Earth orbit. How to do a good job of radiation shielding protection in a strong radiation environment is an important prerequisite for ensuring the success of planetary exploration missions.

[0005] In spacecraft radiation shielding design, measures such as increasing the thickness of shielding materials (e.g., aluminum) or using high atomic number materials (e.g., tantalum, tungsten, lead) to locally shield weak components are mainly employed, requiring significant redundant mass. However, deep-space exploration missions like those targeting Jupiter, due to their great distance from Earth and limited launch capabilities, typically face extremely stringent constraints on mass and energy costs in order to maximize the carrying of scientific payloads. Therefore, achieving the best radiation shielding effect with minimal resource consumption while meeting electromechanical and thermal performance requirements throughout the mission is a major challenge in the design of protection against strong radiation environments for planetary exploration missions.

[0006] Search of existing technologies:

[0007] (1) Patent document CN115169109A discloses a simulation method for radiation shielding protection of dynamically changing structures. The method proposed in this patent includes: obtaining the dynamic change law and material properties of the spacecraft's geometry based on the actual operating state of the spacecraft; performing dynamic geometric modeling to construct a structural model corresponding to the spacecraft's geometry at any given time, and assigning the structural model the corresponding material properties of the spacecraft; calculating the irradiation effect on the spacecraft's geometry at any given time under different irradiation parameters using the Monte Carlo method, characterizing the radiation shielding protection of devices within the spacecraft's geometry; and analyzing the change law of radiation shielding protection of electronic components within the spacecraft over time. This invention solves the problem of simulating radiation shielding protection of dynamically changing spacecraft structures.

[0008] (2) Patent document CN115146385A discloses a guiding method for radiation shielding hardening of spacecraft. The method proposed in this patent includes constructing a three-dimensional structural model of the spacecraft; performing ray tracing calculations on multiple detectors in the structural model to obtain data; inputting the range on the coordinate axes to determine a rectangular box region and dividing it into uniform grid regions; inputting the desired total dose upper limit and the dose data of each detector point; sequentially using the dose data of each detector point from largest to smallest as the maximum reference dose, until the sum of the doses of all detector points with the maximum reference dose as the upper limit is less than the total dose upper limit, thus obtaining the hardening area; emitting a ray from the grid region to the detector point requiring hardening, calculating the direction vector, and determining whether the angle is within the hardening area. This invention solves the problem of simultaneously calculating the dose of multiple detector points on a spacecraft and balancing the radiation shielding hardening area.

[0009] (3) In their article "Spacecraft Space Radiation Protection Materials and Structures" published in the 2020 Issue 2 of *Aerospace Materials and Processes*, Shen Zicai et al. from the Beijing Satellite Environmental Engineering Research Institute introduced mass shielding materials, electrostatic protection materials, radiation-resistant functional materials, and space radiation protection structures from three different dimensions: materials, subsystems (or components), and spacecraft, addressing the needs of space radiation protection. To achieve uniform distribution of mass shielding protection within the spacecraft, the layout of instruments, equipment, fuel, and other materials inside the cabin is optimized to obtain a relatively uniform mass shielding thickness for sensitive devices or the astronaut cabin. However, for sensitive devices, components, or astronauts and their sensitive areas, local shielding methods are adopted, such as adding separate shielding layers, shielding cabins, or emergency shielding rooms (for astronauts) to achieve radiation shielding in transient high-intensity environments or for more sensitive devices.

[0010] (4) In their article "Particle Radiation Environment Effects and Key Protection Technologies in the Jupiter System," published in the 2018 issue of Spacecraft Environmental Engineering, Wang Jianzhao et al. from the Beijing Spacecraft Overall Design Department analyzed radiation effects, including total ionization dose, internal charge, single-event effects, and displacement damage, based on Jupiter's unique high-radiation, low-light, and ultra-low-temperature environment. They also focused on the challenges in studying radiation environment effects. In Jupiter system exploration missions, existing methods should be integrated, optimized, and innovated to adapt to Jupiter's unique radiation environment, developing new and refined methods. For the total ionization dose effect, the uncertainty of device failure dose and radiation environment, as well as the design of composite shielding materials and shielding boxes, should be comprehensively considered. Furthermore, the total dose contribution during the long orbital transfer phase should also be considered. For the internal charge effect, specific shielding materials and orbital design should be considered, along with the impact of low temperature on dielectric resistivity. For the single-event effect, the influence of the low-temperature environment and total dose effect should be considered, and the single-event effect caused by high-energy electrons should be studied. For the displacement damage effect, the impact of low temperature and low-light environments should be emphasized.

[0011] (5) In the article “Juno Radiation Design and Implementation” published in IEEE Transactions on Nucleear Science, Volume 66, Issue 10, 2019, Sammy Kayali et al. from the JPL (Jet Propulsion Laboratory) in the United States analyzed the proton and electron flux distribution and the total ionization dose of the mission based on the Juno ring-Juno probe mission. In order to ensure the survival and performance of Juno in a strong radiation environment, the project team proposed to encapsulate the electronic equipment and instrumentation electronics in a rectangular titanium structure (Vault), and detailed the work on material selection, structural optimization design, radiation testing and analysis.

[0012] The two patents cited above both use numerical simulation to evaluate the total ionization dose effect of spacecraft. The latter three papers, in conjunction with the application background, propose the radiation effects and difficulties that need to be addressed in strong radiation environments, and provide some explanation of local shielding protection measures.

[0013] In addition, patent document CN107677898A discloses a method for determining the total dose resistance of a device by combining ground and on-orbit environments, which only involves the total dose resistance of the device.

[0014] However, in deep space exploration missions, mass and energy constraints are limited by launch vehicle capacity and communication capabilities with Earth. Therefore, conventional local shielding protection methods are no longer applicable, and there is an urgent need for a systematic radiation shielding protection method that achieves the best radiation shielding effect with minimal resource consumption. Summary of the Invention

[0015] To address the shortcomings of existing technologies, the purpose of this invention is to provide a progressive ionizing radiation shielding and protection method for planetary exploration.

[0016] According to the progressive ionizing radiation shielding protection method for planetary exploration provided by the present invention, based on the analysis of space radiation environment, a matching analysis of the ionizing radiation resistance capability of spacecraft components and the space environment protection design requirements is conducted to determine the protection level of each component and formulate a progressive radiation shielding protection implementation plan.

[0017] Preferably, during the design phase of a planetary exploration mission, a space radiation environment analysis is conducted in conjunction with the entire flight process.

[0018] Preferably, a single-unit radiation sensitivity assessment is adopted to analyze and confirm the radiation shielding protection level of a single unit on the spacecraft, and different protection strategies are adopted according to the protection level of the single unit to meet the requirements of the total anti-ionization dose index.

[0019] Preferably, a tabular approach is used for process management. By analyzing the total ionization dose depth curve table, space environment protection design requirements, and individual unit anti-ionization radiation capability statistics table, a progressive shielding protection individual unit list is formed.

[0020] Preferably, it includes:

[0021] Step S1: Based on the flight process of the planetary orbit exploration mission and in conjunction with the orbital scheme, conduct a space radiation environment analysis, generate a total ionization dose depth curve table, and propose space environment protection design requirements;

[0022] Step S2: Based on the product matching of each subsystem of the spacecraft, compile the total dose resistance index of the single unit and form a statistical table of the ionizing radiation resistance of the single unit;

[0023] Step S3: Conduct individual unit radiation sensitivity assessments and confirm the protection level of each individual unit in accordance with the space environment protection design requirements; determine the corresponding protection strategies based on the protection level met by different individual units.

[0024] Step S4: Compile the selected individual units' radiation resistance capabilities and corresponding shielding protection measures to form a progressive shielding protection list for strong radiation environments.

[0025] Preferably, in step S3:

[0026] For individual units that meet protection level I, the structural dimensions and total dose resistance of sensitive units are analyzed, and the protection strategy of using a centralized shielded chamber is determined based on the total ionization dose depth curve table.

[0027] For single units that meet protection level II, the structural dimensions and total dose resistance of the subsensitive units are analyzed, and the protection strategy of using load-bearing structures to shield is determined based on the total ionization dose depth curve table.

[0028] For individual units that meet protection level III, the total dose resistance capabilities of insensitive units, the total dose resistance capabilities of units with special installation requirements, and weak components are analyzed. Based on the total ionization dose depth curve table, a local radiation shielding protection strategy is adopted for units with special installation requirements.

[0029] Preferably, the total ionization dose depth profile is configured to record: material shielding thickness and total dose;

[0030] The space environment protection design requirements are in tabular form and are configured to record: single unit, total dose radiation resistance, and shielding protection level.

[0031] Preferably, the single-unit anti-ionizing radiation capability statistics table is configured to record: component name, component model, and component total dose resistance capability;

[0032] The list of individual units for progressive shielding protection in strong radiation environments is configured to record: shielding protection level and unit name.

[0033] Preferably, it further includes:

[0034] Step S5: Utilize analytical methods such as 3D modeling and radiation shielding simulation calculations to evaluate the effectiveness of the progressive ionizing radiation shielding method.

[0035] Preferably, it further includes:

[0036] Step S6: Develop a progressive ionizing radiation shielding and protection implementation plan, clarify the protection level of individual units and shielding and protection measures, platform layout and guarantee conditions, and form an engineering implementation plan.

[0037] Compared with the prior art, the present invention has the following beneficial effects:

[0038] 1. Based on the environment of planetary exploration missions and the supporting equipment of spacecraft products, compile the total dose resistance capabilities of all individual units to achieve full coverage of weak links and ensure the effectiveness of radiation shielding methods;

[0039] 2. A single-unit radiation sensitivity assessment is adopted to analyze and confirm the radiation shielding protection level of individual units on the spacecraft. For sensitive units, a protection strategy within a centralized shielding cabin is adopted to meet the requirements of the total anti-ionization dose index.

[0040] 3. The process management is carried out using a tabular method. Through the total ionization dose depth curve table, space environment protection design requirements, and single-unit anti-ionization radiation capability statistics table, a list of single units for progressive shielding protection in strong radiation environments is formed after analysis, and a progressive shielding protection implementation plan for strong radiation environments is formed; it has great engineering reference value and is highly feasible.

[0041] 4. In view of the strict constraints on mass and energy costs of deep space exploration missions, a progressive ionizing radiation shielding and protection implementation plan is formulated to achieve the best radiation shielding effect with the least resource consumption, effectively solving the design problem of strong radiation environment protection. Attached Figure Description

[0042] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0043] Figure 1 This is a flowchart of the progressive ionizing radiation shielding protection method for planetary exploration in strong radiation environments according to the present invention. Detailed Implementation

[0044] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0045] In this embodiment, a progressive ionizing radiation shielding protection method for strong radiation environments in planetary exploration, provided by the present invention, can be used in the design phase of planetary exploration missions. By combining the analysis of the space radiation environment throughout the entire flight process, it can conduct a matching analysis of the ionizing radiation resistance capability of spacecraft components with the space environment protection design requirements, determine the protection level of individual components, and formulate a progressive radiation shielding protection implementation plan for strong radiation space environments. This invention has significant engineering implications and is highly operable.

[0046] Taking a Jupiter orbit exploration mission as an example, the method includes the following steps:

[0047] Step 1: Based on the Jupiter orbit exploration mission, the flight process includes the launch phase, the Earth-Jupiter transfer phase, and the Jupiter orbit exploration phase. Combine the orbital scheme to conduct a space radiation environment analysis, generate a total ionization dose depth curve table, and propose space environment protection design requirements, as shown below;

[0048] Total Ionization Dose Depth Curve

[0049]

[0050] Space environment protection design requirements

[0051]

[0052] Step 2: Based on the product matching of each subsystem of the spacecraft, compile the indicators of the total dose resistance of individual units and form a statistical table of the ionizing radiation resistance of individual units;

[0053] Single-unit total dose capacity statistics table

[0054]

[0055]

[0056] Step 3: Conduct individual unit radiation sensitivity assessments and confirm the protection level of each individual unit in accordance with the space environment protection design requirements; if the individual unit meets protection level I, proceed to step 4; if the individual unit meets protection level II, proceed to step 5; if the individual unit meets protection level III, proceed to step 6.

[0057] Step 4: Compile the structural dimensions and total dose resistance of sensitive units, and determine the protection strategy to be adopted in the centralized shielding chamber based on the total ionization dose depth curve table, then proceed to Step 7;

[0058] Step 5: Compile the structural dimensions and total dose resistance of the subsensitive unit, and determine the protection strategy of using a load-bearing structure shielding based on the total ionization dose depth curve table, then proceed to Step 7;

[0059] Step Six: Compile the total dose resistance capabilities of insensitive units, the total dose resistance capabilities of units with special installation requirements, and identify vulnerable components. Based on the total ionization dose depth curve table, adopt a localized radiation shielding protection strategy for units with special installation requirements, and proceed to Step Seven:

[0060] Step 7: Compile the selected individual units' radiation resistance capabilities and corresponding shielding protection measures to form a progressive shielding protection list for strong radiation environments;

[0061] List of stand-alone units for progressive shielding protection in strong radiation environments

[0062] Shielding protection level Single-player name Remark Ⅰ Ⅱ Ⅲ

[0063] Step 8: Evaluate the effectiveness of the progressive ionizing radiation shielding method using analytical methods such as 3D modeling and radiation shielding simulation calculations;

[0064] Step Nine: Develop a progressive ionizing radiation shielding and protection implementation plan, clarify the protection level of individual units and shielding and protection measures, platform layout and guarantee conditions, and form an engineering implementation plan.

[0065] In summary, this study, considering the environment of planetary exploration missions and the supporting equipment for spacecraft products, compiles the total dose resistance capabilities of individual units to achieve full coverage of weak points and ensure the effectiveness of radiation shielding methods. It employs unit radiation sensitivity evaluation to analyze and confirm the radiation shielding protection levels of individual units on the spacecraft, and adopts different protection strategies based on the protection levels described for each unit to meet the total ionizing dose resistance requirements. A tabular approach is used for process management, utilizing total ionizing dose depth curves, space environment protection design requirements, and statistical tables of unit ionizing radiation resistance capabilities. Through analysis, a progressive shielding protection list for strong radiation environments is generated, along with a progressive shielding protection implementation plan for strong radiation environments. This approach has significant engineering reference value, is highly feasible, and can be widely used in planetary exploration missions.

[0066] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A progressive ionizing radiation shielding method for planetary exploration, characterized in that, Based on the analysis of the space radiation environment, a matching analysis of the anti-ionizing radiation capability of individual spacecraft components and the space environment protection design requirements is conducted to determine the protection level of individual components and formulate a progressive radiation shielding protection implementation plan. Its characteristic is that it adopts single-unit radiation sensitivity evaluation to analyze and confirm the radiation shielding protection level of a single unit on the spacecraft, and adopts different protection strategies according to the protection level of the single unit to meet the requirements of the total anti-ionization dose index. Its characteristic is that it uses a tabular method for process management, and through analysis of the total ionization dose depth curve table, space environment protection design requirements, and single-unit anti-ionization radiation capability statistics table, a progressive shielding protection single-unit list is formed; Its features include: Step S1: Based on the flight process of the planetary orbit exploration mission and in conjunction with the orbital scheme, conduct a space radiation environment analysis, generate a total ionization dose depth curve table, and propose space environment protection design requirements; Step S2: Based on the product matching of each subsystem of the spacecraft, compile the total dose resistance index of the single unit and form a statistical table of the ionizing radiation resistance of the single unit; Step S3: Conduct individual unit radiation sensitivity assessments and confirm the protection level of each individual unit in accordance with the space environment protection design requirements; determine the corresponding protection strategies based on the protection level met by different individual units. Step S4: Compile the selected individual units' radiation resistance capabilities and corresponding shielding protection measures to form a progressive shielding protection list for strong radiation environments; The characteristic is that, in step S3: For individual units that meet protection level I, the structural dimensions and total dose resistance of sensitive units are analyzed, and the protection strategy of using a centralized shielded chamber is determined based on the total ionization dose depth curve table. For single units that meet protection level II, the structural dimensions and total dose resistance of the subsensitive units are analyzed, and the protection strategy of using load-bearing structures to shield is determined based on the total ionization dose depth curve table. For individual units that meet protection level III, the total dose resistance capabilities of insensitive units, the total dose resistance capabilities of units with special installation requirements, and weak components are analyzed. Based on the total ionization dose depth curve table, a local radiation shielding protection strategy is adopted for units with special installation requirements.

2. The progressive ionizing radiation shielding and protection method for planetary exploration according to claim 1, characterized in that, For the design phase of planetary exploration missions, a space radiation environment analysis is conducted in conjunction with the entire flight process.

3. The progressive ionizing radiation shielding and protection method for planetary exploration according to claim 1, characterized in that, The total ionization dose depth profile table is configured to record: material shielding thickness, total dose; The space environment protection design requirements are in tabular form and are configured to record: single unit, total dose radiation resistance, and shielding protection level.

4. The progressive ionizing radiation shielding and protection method for planetary exploration according to claim 1, characterized in that, The single-unit anti-ionizing radiation capability statistics table is configured to record: component name, component model, and component's total dose resistance capability; The list of individual units for progressive shielding protection in strong radiation environments is configured to record: shielding protection level and unit name.

5. The progressive ionizing radiation shielding method for planetary exploration according to claim 1, characterized in that, Also includes: Step S5: Utilize analytical methods such as 3D modeling and radiation shielding simulation calculations to evaluate the effectiveness of the progressive ionizing radiation shielding method.

6. The progressive ionizing radiation shielding method for planetary exploration according to claim 1, characterized in that, Also includes: Step S6: Develop a progressive ionizing radiation shielding and protection implementation plan, clarify the protection level of individual units and shielding and protection measures, platform layout and guarantee conditions, and form an engineering implementation plan.

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