Planetary exploration progressive ionizing radiation shielding protection method

Abstract

The invention provides a planetary exploration intense 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 ionization total dose depth curve table, and formulating space environment protection design requirements; arranging total dose resistance capability indexes of all single machines to form a single machine ionization radiation resistance capability statistical table; carrying out protection grade confirmation on the matching of each single machine and the space environment protection design requirement; forming an intense radiation environment progressive shielding protection single machine list; performing effect evaluation on the shielding protection strategy of the progressive ionizing radiation screen; and formulating a progressive ionizing radiation shielding protection implementation scheme, defining a single-machine protection level, a shielding protection strategy, platform layout and guarantee conditions, and forming an engineering implementation scheme. The invention provides an intense radiation environment protection method aiming at the ionizing radiation protection requirement of a planetary exploration task, and the method can be applied and implemented in engineering.

Description

Technical Field

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

[0002] Planetary exploration refers to the exploration of planets in the solar system and interstellar space using artificial spacecraft. With the development of human space activities, the targets of planetary exploration have expanded from the Earth to Venus, Mars, Mercury, Jupiter and Saturn, and even planets farther away. Compared with the Van Allen radiation belts of the Earth, similar radiation belt phenomena have been found on other planets and satellites, among which the Jupiter radiation belt is the most energetic and the largest in the solar system.

[0003] It is generally believed that the maximum energy of electrons in Earth orbit is less than 10MeV, while the maximum energy of electrons in Jupiter orbit can reach 1GeV, and the maximum energy of protons is several GeV. Comparing the energy spectra of high-energy particles in the geosynchronous orbit (GEO) and at 4Rj (Rj = 71492km, the radius of Jupiter) on the equatorial plane of Jupiter, the flux of high-energy protons and electrons in Jupiter orbit is more than 2 orders of magnitude greater than that of the Earth, and the maximum energy is 2 orders of magnitude higher than that of the Earth. The outer edge of the Earth's radiation belt is 7Re (Re = 6371km, the radius of the Earth), while the boundary of Jupiter's main radiation belt can reach 17Rj.

[0004] Therefore, when conducting orbiting exploration of Jupiter and its inner solar system, the total ionization dose level encountered by the spacecraft far exceeds the total dose level encountered by Earth's high-orbit satellites. How to provide good radiation shielding protection in a strong radiation environment is an important prerequisite for ensuring the success of planetary exploration missions.

[0005] In the design of spacecraft radiation shielding, the main measures to locally shield weak components are to increase the thickness of shielding materials (such as aluminum) or use high atomic number materials (such as tantalum, tungsten, lead, etc.), which consumes a large amount of redundant mass. However, deep space exploration missions such as Jupiter are far away from the earth and have limited launch capabilities. In order to maximize the scientific exploration payload, the constraints on mass and energy costs are extremely strict. Therefore, how to achieve the best radiation shielding effect with the minimum resource cost while meeting the electromechanical and thermal performance of the entire mission segment is a difficult problem faced by the strong radiation environment protection design of planetary exploration missions.

[0006] Search of prior art:

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

[0008] (2) Patent document CN115146385A discloses a guidance method for radiation shielding reinforcement of spacecraft. The method proposed in this invention patent includes constructing a three-dimensional structural model of the spacecraft, performing ray tracing operations on multiple detection points in the structural model to obtain data; inputting the range on the coordinate axis, determining the rectangular box area, and dividing it into uniform grid areas; inputting the expected total dose upper limit and the dose data of each detection point, and taking the dose data of each detection point from large to small as the maximum reference dose in order, until the dose of each detection point with the maximum reference dose as the upper limit is less than the total dose upper limit data, and obtaining the reinforcement area; emitting a ray from the grid area to the detection point that needs to be reinforced, calculating the direction vector, and judging whether the angle is within the reinforcement area. This invention solves the problem of calculating the dose of multiple detection points of a spacecraft at the same time and weighing the radiation shielding reinforcement area.

[0009] (3) In the article “Spacecraft Radiation Protection Materials and Protection Structures” published in the 2020 issue of Aerospace Materials and Technology by Shen Zicai et al. from the Beijing Institute of Satellite Environment Engineering, in response to the needs of aerospace radiation protection, the article introduces mass shielding protection materials, electrostatic protection materials, anti-radiation functional materials, and space radiation protection structures from three different dimensions: materials, subsystems (or components), and spacecraft. In order to achieve uniform distribution of mass shielding protection inside the spacecraft, the layout of instruments, equipment, fuel and other materials in the cabin is optimized to obtain a relatively uniform mass shielding thickness for sensitive devices or astronaut cabins in the cabin. However, local shielding protection is adopted for sensitive devices, components or astronauts and their sensitive parts, and shielding layers, shielding cabins or emergency shielding rooms (for astronauts) are added to the sensitive parts separately to achieve radiation shielding in transient high-intensity environments or for more sensitive devices.

[0010] (4) In the article “Radiation Environment Effects and Key Protection Technologies of Jupiter System Particles” published in Volume 35, Issue 5 of Spacecraft Environment Engineering in 2018, Wang Jianzhao et al. from the Beijing Spacecraft General Design Department analyzed radiation effects including total ionization dose, internal charge, single particle, displacement damage, etc. based on the special high radiation, low light, and ultra-low temperature environment of Jupiter, and focused on discussing the difficulties faced in the study of radiation environment effects. In the Jupiter system exploration mission, existing methods should be integrated and optimized to adapt to Jupiter’s unique radiation environment and develop new 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. In addition, since the orbit transfer stage is very long, the total dose contribution of this stage should also be considered. For the internal charge effect, the specific shielding material should be combined with the orbit design, and the influence of low temperature on dielectric resistivity should also be considered. For the single particle effect, the influence of low temperature environment and total dose effect should be considered, and the single particle effect caused by high-energy electrons should be studied. For the displacement damage effect, the influence of low temperature and low light environment should be considered.

[0011] (5) In the article “Juno Radiat ion Design and Implementation” published in IEEE TRANSACTIONS ON NUCLEAR SCIENCE, Vol. 66, No. 10, 2019, Sammy Kayali et al. from the Jet Propulsion Laboratory (JPL) of the United States analyzed the proton and electron flux distribution and the total ionization dose of the mission phase based on the Juno ring-Jupiter exploration 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 instrument electronics in a rectangular titanium structure (Vault), and introduced in detail the material selection, structural optimization design, radiation testing and analysis, etc.

[0012] The two patents cited in the previous article both use numerical simulation methods to evaluate the total ionization dose effect of spacecraft. The last three papers, based on the application background, propose the radiation effects and difficulties that need to be solved in a strong radiation environment, and provide some explanations on local shielding protection measures.

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

[0014] However, in deep space exploration missions, mass and energy constraints are limited by the launch capability and the ability to communicate with the Earth. Therefore, conventional local shielding protection methods are no longer applicable. There is an urgent need for a systematic radiation shielding protection method with the best radiation shielding effect at the lowest resource cost. Summary of the invention

[0015] In view of the defects in the prior art, an object of the present invention is to provide a progressive ionizing radiation shielding protection method for planetary exploration.

[0016] According to a progressive ionizing radiation shielding protection method for planetary exploration provided by the present invention, based on the space radiation environment analysis, an analysis of the matching between the anti-ionizing radiation capability of a single unit of a spacecraft and the design requirements for space environment protection is conducted, the protection level of the single unit is determined, and a progressive radiation shielding protection implementation plan is formulated.

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

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

[0019] Preferably, a tabular method is used for process management, and a progressive shielding protection single-machine list is formed through analysis of the total ionizing dose depth curve table, space environment protection design requirements, and single-machine anti-ionizing radiation capability statistics table.

[0020] Preferably, it includes:

[0021] Step S1: According to the flight process of the planetary orbiting exploration mission, combined with the orbit plan, the space radiation environment analysis is carried out to form a total ionization dose depth curve table and propose space environment protection design requirements;

[0022] Step S2: According to the product matching of each subsystem of the spacecraft, the total dose resistance capability index of the single machine is sorted out to form a statistical table of the ionizing radiation resistance capability of the single machine;

[0023] Step S3: Conduct single-machine radiation sensitivity evaluation, confirm the protection level of each single machine and the space environment protection design requirements; determine the corresponding protection strategy according to the protection level of different single machines;

[0024] Step S4: sort out the selected single-machine radiation resistance capabilities and corresponding shielding protection measures to form a list of single-machines with progressive shielding protection for strong radiation environments.

[0025] Preferably, in step S3:

[0026] For single machines that meet protection level I, the structural dimensions and total dose resistance of sensitive single machines are sorted out, and the protection strategy in the centralized shielding cabin is determined based on the total ionization dose depth curve table;

[0027] For single machines that meet protection level II, the structural dimensions and total dose resistance of the sub-sensitive single machines are sorted out, and the protection strategy of using load-bearing structure shielding is determined based on the total ionization dose depth curve table;

[0028] For single machines that meet protection level III, the total dose resistance capabilities of insensitive single machines, the total dose resistance capabilities of single machines with special installation requirements, and weak components are sorted out. According to the total ionization dose depth curve table, a local radiation shielding protection strategy is adopted for single machines with special installation requirements.

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

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

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

[0032] The strong radiation environment progressive shielding protection single machine list is configured to record: shielding protection level, single machine name.

[0033] Preferably, it also includes:

[0034] Step S5: using three-dimensional modeling, radiation shielding simulation calculation and other analysis methods to evaluate the effect of the progressive ionizing radiation screen shielding method.

[0035] Preferably, it also includes:

[0036] Step S6: Formulate a progressive ionizing radiation shielding protection implementation plan, clarify the single-machine protection level and shielding 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. According to the planetary exploration mission environment and spacecraft product matching, sort out the total dose resistance capabilities of all single machines, achieve full coverage of weak links, and ensure the effectiveness of radiation shielding methods;

[0039] 2. Use single-machine radiation sensitivity evaluation to analyze and confirm the radiation shielding protection level of single machines on the spacecraft. For sensitive single machines, adopt a centralized shielding cabin protection strategy to meet the total anti-ionization dose index requirements;

[0040] 3. Use a tabular method to manage the process. Through the total ionization dose depth curve table, space environment protection design requirements, and single-machine anti-ionizing radiation capability statistics table, a list of single machines 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 is of great engineering reference value and highly feasible.

[0041] 4. In view of the mission characteristics of deep space exploration that have strict constraints on quality and energy costs, a progressive ionizing radiation shielding protection implementation plan is formulated to achieve the best radiation shielding effect with the minimum resource cost, effectively solving the design problem of strong radiation environment protection. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0043] Figure 1 This is a flow chart of the progressive ionizing radiation shielding protection method for planetary exploration in a strong radiation environment according to the present invention. DETAILED DESCRIPTION

[0044] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0045] In this embodiment, a progressive ionizing radiation shielding protection method for a strong radiation environment of planetary exploration is provided according to the present invention. The present invention can be used in the design stage of planetary exploration missions. Combined with the space radiation environment analysis of the entire flight process, an analysis of the matching between the anti-ionizing radiation capability of a single unit of the spacecraft and the design requirements of the space environment protection is carried out, the protection level of the single unit is determined, and a progressive radiation shielding protection implementation plan is formulated in a strong radiation space environment. This has important engineering significance and strong operability.

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

[0047] Step 1: According to the Jupiter orbiting exploration mission, the flight process includes the launch phase, the Earth-Jupiter transfer phase, and the Jupiter orbiting exploration phase. Combined with the orbit plan, the space radiation environment analysis is carried out to form a total ionization dose depth curve table and propose space environment protection design requirements, as shown below;

[0048] Total ionization dose depth curve table

[0049]

[0050] Space environment protection design requirements

[0051]

[0052] Step 2: According to the matching products of each subsystem of the spacecraft, sort out the total dose resistance capability indicators of each unit and form a statistical table of the ionizing radiation resistance capability of each unit;

[0053] Statistics table of total dose resistance of single machine

[0054]

[0055]

[0056] Step 3: Conduct single-machine radiation sensitivity evaluation and confirm the protection level of each single machine based on its compatibility with the space environment protection design requirements; if the single machine meets protection level I, proceed to step 4; if the single machine meets protection level II, proceed to step 5; if the single machine meets protection level III, proceed to step 6;

[0057] Step 4: Sort out the structural dimensions and total dose resistance of the sensitive single machine, determine the protection strategy in the centralized shielding cabin according to the total ionization dose depth curve table, and proceed to step 7;

[0058] Step 5: Sort out the structural dimensions and total dose resistance of the sub-sensitive unit, determine the protection strategy of using load-bearing structure shielding according to the total ionization dose depth curve table, and proceed to step 7;

[0059] Step 6: Sort out the total dose resistance of insensitive units, the total dose resistance of units with special installation requirements, and weak components. According to the total ionization dose depth curve table, adopt a local radiation shielding protection strategy for units with special installation requirements, and proceed to step 7:

[0060] Step 7: Sort out and select the radiation resistance of individual machines and the corresponding shielding protection measures to form a list of progressive shielding protection individual machines in a strong radiation environment;

[0061] List of progressive shielding protection units for strong radiation environments

[0062] Shielding protection level Machine name Remark Ⅰ Ⅱ Ⅲ

[0063] Step 8: Use 3D modeling, radiation shielding simulation calculation and other analysis methods to evaluate the effectiveness of the progressive ionizing radiation shielding method;

[0064] Step 9: Develop a progressive ionizing radiation shielding protection implementation plan, clarify the single-machine protection level and shielding protection measures, platform layout and guarantee conditions, and form an engineering implementation plan.

[0065] To summarize, in view of the planetary exploration mission environment and spacecraft product matching, the total dose resistance capability of each unit is sorted out to achieve full coverage of weak links and ensure the effectiveness of radiation shielding methods; the radiation sensitivity evaluation of each unit is used to analyze and confirm the radiation shielding protection level of each unit on the spacecraft, and different protection strategies are adopted according to the protection level of the single unit to meet the total dose resistance index requirements; a tabular method is used for process management, and a list of units with progressive shielding protection for strong radiation environments is formed through analysis of the total ionization dose depth curve table, space environment protection design requirements, and statistical tables of single-unit anti-ionizing radiation capabilities, and a progressive shielding protection implementation plan for strong radiation environments is formed; it is of great engineering reference significance and highly feasible, and can be widely used in planetary exploration missions.

[0066] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A planetary exploration progressive ionizing radiation shielding protection method, characterized in that: Based on the space radiation environment analysis, an analysis is conducted on the matching between the anti-ionizing radiation capability of a single unit of the spacecraft and the design requirements for space environment protection, the protection level of the single unit is determined, and a progressive radiation shielding protection implementation plan is formulated.

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

3. The planetary exploration progressive ionizing radiation shielding protection method according to claim 1, characterized in that: The radiation shielding protection level of each unit on the spacecraft is analyzed and confirmed by single-unit radiation sensitivity evaluation. Different protection strategies are adopted according to the protection level of each unit to meet the total anti-ionization dose index requirements.

4. The planetary exploration progressive ionizing radiation shielding protection method according to claim 1, characterized in that: A tabular method is used for process management. Through analysis of the total ionization dose depth curve table, space environment protection design requirements, and single-machine anti-ionizing radiation capability statistics table, a progressive shielding protection single-machine list is formed.

5. The planetary exploration progressive ionizing radiation shielding protection method according to claim 1, characterized in that: include: Step S1: According to the flight process of the planetary orbiting exploration mission, combined with the orbit plan, the space radiation environment analysis is carried out to form a total ionization dose depth curve table and propose space environment protection design requirements; Step S2: According to the product matching of each subsystem of the spacecraft, the total dose resistance capability index of the single machine is sorted out to form a statistical table of the ionizing radiation resistance capability of the single machine; Step S3: Conduct single-machine radiation sensitivity evaluation, confirm the protection level of each single machine and the space environment protection design requirements; determine the corresponding protection strategy according to the protection level of different single machines; Step S4: sort out the selected single-machine radiation resistance capabilities and corresponding shielding protection measures to form a list of single-machines with progressive shielding protection for strong radiation environments.

6. The planetary exploration progressive ionizing radiation shielding protection method according to claim 5, characterized in that: In step S3: For single machines that meet protection level I, the structural dimensions and total dose resistance of sensitive single machines are sorted out, and the protection strategy in the centralized shielding cabin is determined based on the total ionization dose depth curve table; For single machines that meet protection level II, the structural dimensions and total dose resistance of the sub-sensitive single machines are sorted out, and the protection strategy of using load-bearing structure shielding is determined based on the total ionization dose depth curve table; For single machines that meet protection level III, the total dose resistance capabilities of insensitive single machines, the total dose resistance capabilities of single machines with special installation requirements, and weak components are sorted out. According to the total ionization dose depth curve table, a local radiation shielding protection strategy is adopted for single machines with special installation requirements.

7. The planetary exploration progressive ionizing radiation shielding protection method according to claim 5, characterized in that: The total ionizing dose depth curve 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 machine, total radiation dose resistance, and shielding protection level.

8. The planetary exploration progressive ionizing radiation shielding protection method according to claim 5, characterized in that: The single-machine ionizing radiation resistance statistical table is configured to record: component name, component model, and component total dose resistance capability; The list of single machines with progressive shielding protection in strong radiation environment is configured to record: shielding protection level and single machine name.

9. The planetary exploration progressive ionizing radiation shielding protection method according to claim 5, characterized in that: Also includes: Step S5: using three-dimensional modeling, radiation shielding simulation calculation and other analysis methods to evaluate the effect of the progressive ionizing radiation screen shielding method.

10. The planetary exploration progressive ionizing radiation shielding protection method according to claim 5, characterized in that: Also includes: Step S6: Formulate a progressive ionizing radiation shielding protection implementation plan, clarify the single-machine protection level and shielding protection measures, platform layout and guarantee conditions, and form an engineering implementation plan.

Images