Method and device for realizing space radiation environment effect evaluation for spacecraft material or device, processor and readable storage medium thereof

Abstract

The invention relates to a method for realizing space radiation environment effect evaluation aiming at a spacecraft material or device, and also relates to a device for realizing space radiation environment effect evaluation aiming at the spacecraft material or device, a processor and a computer readable storage medium thereof. According to the method, the device, the processor and the computer readable storage medium for evaluating the space radiation environment effect for the spacecraft material or device, the space radiation model, the orbit type, the service life of the spacecraft and the material characteristics are comprehensively considered; the effect of the spacecraft material or device in the space radiation environment can be simulated and evaluated more accurately, so that the reliability of the evaluation result is improved, the experiment design is optimized, and the experiment error is reduced. By constructing degradation models of materials and devices in different space environments, development and analysis of a method for reliability and life estimation of a spacecraft are facilitated, and improvement of performance and life of the spacecraft in a space radiation environment is facilitated.

Description

Technical Field

[0001] The present invention relates to the field of space environment engineering, in particular to the field of spacecraft materials, and specifically refers to a method, device, processor and computer-readable storage medium thereof for evaluating space radiation environment effects on spacecraft materials or devices. Background Art

[0002] In the field of space radiation environment effect assessment of spacecraft materials or devices, traditional research methods have some obvious limitations. These methods usually rely on simplified space radiation models and standards, lack accurate consideration of orbit type and spacecraft life, and lack comprehensive analysis of spacecraft design, applied materials and on-orbit devices. These methods often cannot provide enough data to simulate the real space radiation environment, resulting in doubts about the accuracy and reliability of the assessment results.

[0003] In addition, traditional test equipment and mathematical models are also insufficient in simulating the effects of space radiation. They may not accurately simulate the dose-depth distribution of space radiation in materials, or ignore certain key physical processes in the simulation process. These deficiencies limit the understanding of the performance of spacecraft materials or devices in the actual space environment, thus affecting the reliability and life estimation of spacecraft.

[0004] Traditional methods for assessing the space radiation environment effects of spacecraft materials or devices have obvious deficiencies in terms of model accuracy, experimental method selection, comprehensiveness of experimental results, and accuracy of degradation models. These deficiencies limit the in-depth understanding and prediction of spacecraft performance in the actual space environment, thus affecting the design and operation of spacecraft. Therefore, developing a new assessment method to overcome these limitations is of great significance for improving the reliability and life prediction of spacecraft. Summary of the invention

[0005] The purpose of the present invention is to overcome the shortcomings of the above-mentioned prior art and to provide a method, device, processor and computer-readable storage medium thereof for evaluating space radiation environment effects on spacecraft materials or devices, which are simple to operate, highly accurate and have a wide range of applications.

[0006] In order to achieve the above-mentioned purpose, the method, device, processor and computer-readable storage medium thereof for spacecraft materials or devices to implement space radiation environmental effect assessment of the present invention are as follows:

[0007] The method for evaluating the space radiation environment effect on spacecraft materials or devices is mainly characterized in that the method comprises the following steps:

[0008] (1) Obtain models and standards for space radiation, orbit types, and spacecraft lifespan, and select equivalent simulation data for ground simulation tests;

[0009] (2) Calculate the dose-depth distribution of orbital integrated radiation in the material;

[0010] (3) Select the type, energy and fluence of charged particles in ground irradiation tests;

[0011] (4) Design the irradiation test sequence.

[0012] Preferably, the step (2) is specifically as follows:

[0013] For surface functional materials, the dose-depth distribution of orbital comprehensive radiation environment in the material is analyzed and calculated, and the dose-depth distribution curve is given.

[0014] Preferably, in said step (2), for the thermal control coating, a calculation software is selected for electron or proton irradiation in an orbital irradiation environment;

[0015] In the step (2), for a given orbit, mission life and specific material being studied, the dose-depth distribution of electrons or protons irradiated in the material by the orbital environment is analyzed and calculated, and a dose-depth distribution curve is given, which is used as equivalent simulation data for ground simulation tests.

[0016] Preferably, the step (3) specifically comprises the following steps:

[0017] (3.1) Select the energy of charged particles in ground irradiation tests;

[0018] (3.2) Select charged particles and change the energy and flux of charged particles so that the integrated dose curve of the particle accelerator matches the spatial dose curve.

[0019] Preferably, the step (3.1) is specifically as follows:

[0020] Select electrons and protons as radiation simulation sources; select particle energy with a range close to the thickness of the surface functional layer.

[0021] Preferably, the step (3.2) is specifically as follows:

[0022] (3.2.1) Determine the electron and proton flux in ground irradiation tests;

[0023] (3.2.2) Use electrons to simulate the absorbed dose at a deeper level of the material and use protons to simulate the absorbed dose at the surface of the material;

[0024] (3.2.3) Calculate the dose-depth distribution of electrons and protons in the material respectively, accumulate the absorbed doses at the same depth, and calculate the total dose-depth distribution;

[0025] (3.2.4) Change the electron and proton injection until the cumulative dose curve of the two matches the spatial dose curve.

[0026] Preferably, the step (4) specifically comprises the following steps:

[0027] By using sequential irradiation of electrons or protons of different energies and selecting appropriate electron and proton irradiation injection rates, the dose-depth distribution of space irradiation in the surface layer or functional layer of the material is simulated, and the effect of actual orbital irradiation on the material is simulated.

[0028] The device for evaluating the space radiation environment effect on spacecraft materials or devices has the following main features:

[0029] a processor configured to execute computer executable instructions;

[0030] A memory stores one or more computer executable instructions, which, when executed by the processor, implement the various steps of the above-mentioned method for evaluating space radiation environment effects on spacecraft materials or devices.

[0031] The main feature of the processor for implementing space radiation environment effect assessment for spacecraft materials or devices is that the processor is configured to execute computer executable instructions, and when the computer executable instructions are executed by the processor, the various steps of the above-mentioned method for implementing space radiation environment effect assessment for spacecraft materials or devices are implemented.

[0032] The main feature of the computer-readable storage medium is that a computer program is stored thereon, and the computer program can be executed by a processor to implement the various steps of the above-mentioned method for evaluating the space radiation environment effects on spacecraft materials or devices.

[0033] The method, device, processor and computer-readable storage medium thereof for evaluating the space radiation environment effect on spacecraft materials or devices of the present invention can more accurately simulate and evaluate the effect of spacecraft materials or devices in the space radiation environment by comprehensively considering the space radiation model, orbit type, spacecraft life and material properties, thereby improving the reliability of the evaluation results, helping to optimize the experimental design and reduce experimental errors. By constructing degradation models of materials and devices in different space environments, it is helpful to develop methods for analyzing the reliability and life estimation of spacecraft, and to improve the performance and life of spacecraft in space radiation environments. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 The present invention is a flow chart of a method for evaluating space radiation environment effects on spacecraft materials or devices. DETAILED DESCRIPTION

[0035] In order to more clearly describe the technical content of the present invention, further description is given below in conjunction with specific embodiments.

[0036] The method of the present invention for evaluating space radiation environment effects on spacecraft materials or devices comprises the following steps:

[0037] (1) Obtain models and standards for space radiation, orbit types, and spacecraft lifespan, and select equivalent simulation data for ground simulation tests;

[0038] (2) Calculate the dose-depth distribution of orbital integrated radiation in the material;

[0039] (3) Select the type, energy and fluence of charged particles in ground irradiation tests;

[0040] (4) Design the irradiation test sequence.

[0041] As a preferred embodiment of the present invention, the step (2) is specifically as follows:

[0042] For surface functional materials, the dose-depth distribution of orbital comprehensive radiation environment in the material is analyzed and calculated, and the dose-depth distribution curve is given.

[0043] As a preferred embodiment of the present invention, in the step (2), for the thermal control coating, for electron or proton irradiation in the orbital irradiation environment, a calculation software is selected;

[0044] In the step (2), for a given orbit, mission life and specific material being studied, the dose-depth distribution of electrons or protons irradiated in the material by the orbital environment is analyzed and calculated, and a dose-depth distribution curve is given, which is used as equivalent simulation data for ground simulation tests.

[0045] As a preferred embodiment of the present invention, the step (3) specifically comprises the following steps:

[0046] (3.1) Select the energy of charged particles in ground irradiation tests;

[0047] (3.2) Select charged particles and change the energy and flux of charged particles so that the integrated dose curve of the particle accelerator matches the spatial dose curve.

[0048] As a preferred embodiment of the present invention, the step (3.1) is specifically as follows:

[0049] Select electrons and protons as radiation simulation sources; select particle energy with a range close to the thickness of the surface functional layer.

[0050] As a preferred embodiment of the present invention, the step (3.2) is specifically as follows:

[0051] (3.2.1) Determine the electron and proton flux in ground irradiation tests;

[0052] (3.2.2) Use electrons to simulate the absorbed dose at a deeper level of the material and use protons to simulate the absorbed dose at the surface of the material;

[0053] (3.2.3) Calculate the dose-depth distribution of electrons and protons in the material respectively, accumulate the absorbed doses at the same depth, and calculate the total dose-depth distribution;

[0054] (3.2.4) Change the electron and proton injection until the cumulative dose curve of the two matches the spatial dose curve.

[0055] As a preferred embodiment of the present invention, the step (4) specifically comprises the following steps:

[0056] By using sequential irradiation of electrons or protons of different energies and selecting appropriate electron and proton irradiation injection rates, the dose-depth distribution of space irradiation in the surface layer or functional layer of the material is simulated, and the effect of actual orbital irradiation on the material is simulated.

[0057] The device for evaluating the space radiation environment effect on spacecraft materials or devices of the present invention comprises:

[0058] a processor configured to execute computer executable instructions;

[0059] A memory stores one or more computer executable instructions, which, when executed by the processor, implement the various steps of the above-mentioned method for evaluating space radiation environment effects on spacecraft materials or devices.

[0060] The processor of the present invention implements space radiation environment effect assessment for spacecraft materials or devices, wherein the processor is configured to execute computer executable instructions, and when the computer executable instructions are executed by the processor, the various steps of the above-mentioned method for implementing space radiation environment effect assessment for spacecraft materials or devices are implemented.

[0061] The computer-readable storage medium of the present invention stores a computer program thereon, and the computer program can be executed by a processor to implement the various steps of the above-mentioned method for evaluating space radiation environment effects on spacecraft materials or devices.

[0062] In a specific embodiment of the present invention, the process of studying the space radiation environment effect of spacecraft materials or devices is as follows:

[0063] a) It is necessary to know the models and standards of space radiation (1), orbit type and spacecraft life (1), as well as spacecraft design, applied materials and on-orbit devices (3).

[0064] b) Give the requirements for test equipment, mathematical models and software tools for simulating space radiation effects (4).

[0065] c) Select the most appropriate experimental methods and equipment (5), mathematical models and software tools (7). The mathematical model of the impact of the space environment on aerospace materials can be implemented using analytical and numerical calculation methods. The recommended mathematical model for studying the interaction between spacecraft and the space environment is shown in Appendix B.

[0066] d) Integrated space experiments (6) that simultaneously study the characteristics of the space environment, the radiation conditions within the spacecraft, and the radiation effects on different materials need to be considered and analyzed together with the results of laboratory experiments and numerical simulations.

[0067] e) The data obtained by the above method will be used to construct degradation models of materials and devices under different space environments (8), and then used to develop methods for analyzing the reliability and life estimation of spacecraft (9), as well as to provide methods and suggestions for the radiation protection effect of spacecraft (10).

[0068] The specific implementation scheme of this embodiment can refer to the relevant description in the above embodiment, which will not be repeated here.

[0069] It can be understood that the same or similar parts of the above embodiments can be referenced to each other, and the contents not described in detail in some embodiments can refer to the same or similar contents in other embodiments.

[0070] It should be noted that, in the description of the present invention, the terms "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying relative importance. In addition, in the description of the present invention, unless otherwise specified, the meaning of "plurality" refers to at least two.

[0071] Any process or method description in a flowchart or otherwise described herein may be understood to represent a module, segment or portion of code that includes one or more executable instructions for implementing the steps of a specific logical function or process, and the scope of the preferred embodiments of the present invention includes alternative implementations in which functions may not be performed in the order shown or discussed, including performing functions in a substantially simultaneous manner or in the reverse order depending on the functions involved, which should be understood by those skilled in the art to which the embodiments of the present invention belong.

[0072] It should be understood that the various parts of the present invention can be implemented by hardware, software, firmware or a combination thereof. In the above-mentioned embodiments, a plurality of steps or methods can be implemented by software or firmware stored in a memory and executed by a suitable instruction execution device. For example, if implemented by hardware, as in another embodiment, it can be implemented by any one of the following technologies known in the art or their combination: a discrete logic circuit having a logic gate circuit for implementing a logic function for a data signal, a dedicated integrated circuit having a suitable combination of logic gate circuits, a programmable gate array (PGA), a field programmable gate array (FPGA), etc.

[0073] A person skilled in the art may understand that all or part of the steps in the method for implementing the above-mentioned embodiment may be completed by instructing related hardware through a program, and the corresponding program may be stored in a computer-readable storage medium, which, when executed, includes one of the steps of the method embodiment or a combination thereof.

[0074] In addition, each functional unit in each embodiment of the present invention may be integrated into a processing module, or each unit may exist physically separately, or two or more units may be integrated into one module. The above-mentioned integrated module may be implemented in the form of hardware or in the form of a software functional module. If the integrated module is implemented in the form of a software functional module and sold or used as an independent product, it may also be stored in a computer-readable storage medium.

[0075] The storage medium mentioned above can be a read-only memory, a magnetic disk or an optical disk, etc.

[0076] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "examples", "specific examples", or "some examples" means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner.

[0077] The method, device, processor and computer-readable storage medium thereof for evaluating the space radiation environment effect on spacecraft materials or devices of the present invention can more accurately simulate and evaluate the effect of spacecraft materials or devices in the space radiation environment by comprehensively considering the space radiation model, orbit type, spacecraft life and material properties, thereby improving the reliability of the evaluation results, helping to optimize the experimental design and reduce experimental errors. By constructing degradation models of materials and devices in different space environments, it is helpful to develop methods for analyzing the reliability and life estimation of spacecraft, and to improve the performance and life of spacecraft in space radiation environments.

[0078] In this specification, the present invention has been described with reference to specific embodiments thereof. However, it is apparent that various modifications and variations may be made without departing from the spirit and scope of the present invention. Therefore, the specification and drawings should be regarded as illustrative rather than restrictive.

Claims

1. A method for evaluating space radiation environment effects on spacecraft materials or devices, characterized in that: The method comprises the following steps: (1) Obtain models and standards for space radiation, orbit types, and spacecraft lifespan, and select equivalent simulation data for ground simulation tests; (2) Calculate the dose-depth distribution of orbital integrated radiation in the material; (3) Select the type, energy and fluence of charged particles in ground irradiation tests; (4) Design the irradiation test sequence.

2. The method for evaluating space radiation environmental effects on spacecraft materials or devices according to claim 1, characterized in that: The step (2) is specifically as follows: For surface functional materials, the dose-depth distribution of orbital comprehensive radiation environment in the material is analyzed and calculated, and the dose-depth distribution curve is given.

3. The method for evaluating space radiation environmental effects on spacecraft materials or devices according to claim 2, characterized in that: In step (2), for the thermal control coating, a calculation software is selected for electron or proton irradiation in an orbital irradiation environment; In the step (2), for a given orbit, mission life and specific material being studied, the dose-depth distribution of electron or proton irradiation in the material in the orbital environment is analyzed and calculated, and a dose-depth distribution curve is given, which is used as equivalent simulation data for ground simulation tests.

4. The method for evaluating space radiation environmental effects on spacecraft materials or devices according to claim 1, characterized in that: The step (3) specifically comprises the following steps: (3.1) Select the energy of charged particles in ground irradiation tests; (3.2) Select charged particles and change the energy and flux of charged particles so that the integrated dose curve of the particle accelerator matches the spatial dose curve.

5. The method for evaluating space radiation environmental effects on spacecraft materials or devices according to claim 4, characterized in that: The step (3.1) is specifically: Select electrons and protons as radiation simulation sources; select particle energy with a range close to the thickness of the surface functional layer.

6. The method for evaluating space radiation environmental effects on spacecraft materials or devices according to claim 4, characterized in that: The step (3.2) is specifically: (3.2.1) Determine the electron and proton flux in ground irradiation tests; (3.2.2) Use electrons to simulate the absorbed dose at a deeper level of the material and use protons to simulate the absorbed dose at the surface of the material; (3.2.3) Calculate the dose-depth distribution of electrons and protons in the material respectively, accumulate the absorbed doses at the same depth, and calculate the total dose-depth distribution; (3.2.4) Change the electron and proton injection until the cumulative dose curve of the two matches the spatial dose curve.

7. The method for evaluating space radiation environmental effects on spacecraft materials or devices according to claim 1, characterized in that: The step (4) specifically comprises the following steps: By using sequential irradiation of electrons or protons of different energies and selecting appropriate electron and proton irradiation injection rates, the dose-depth distribution of space irradiation in the surface layer or functional layer of the material is simulated, and the effect of actual orbital irradiation on the material is simulated.

8. A device for evaluating space radiation environmental effects on spacecraft materials or devices, characterized in that: The device comprises: a processor configured to execute computer executable instructions; A memory storing one or more computer executable instructions, wherein when the computer executable instructions are executed by the processor, the steps of the method for evaluating space radiation environment effects on spacecraft materials or devices as described in any one of claims 1 to 7 are implemented.

9. A processor for evaluating space radiation environment effects on spacecraft materials or devices, characterized in that: The processor is configured to execute computer executable instructions. When the computer executable instructions are executed by the processor, the various steps of the method for evaluating space radiation environment effects on spacecraft materials or devices described in any one of claims 1 to 7 are implemented.

10. A computer-readable storage medium, characterized in that: A computer program is stored thereon, and the computer program can be executed by a processor to implement the various steps of the method for evaluating space radiation environment effects on spacecraft materials or devices as described in any one of claims 1 to 7.

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