GB/T 41458-2022 English PDF

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GB/T 41458-2022: Space environment - Plasma environments for generation of worst case surface electrical potential differences for spacecraft
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Basic data

Standard ID: GB/T 41458-2022 (GB/T41458-2022)
Description (Translated English): Space environment - Plasma environments for generation of worst case surface electrical potential differences for spacecraft
Sector / Industry: National Standard (Recommended)
Classification of Chinese Standard: V06
Word Count Estimation: 18,141
Issuing agency(ies): State Administration for Market Regulation, China National Standardization Administration

GB/T 41458-2022: Space environment - Plasma environments for generation of worst case surface electrical potential differences for spacecraft

---This is a DRAFT version for illustration, not a final translation. Full copy of true-PDF in English version (including equations, symbols, images, flow-chart, tables, and figures etc.) will be manually/carefully translated upon your order.
Space environment -- Plasma environments for generation of worst case surface electrical potential differences for spacecraft ICS 49.140 CCSV06 National Standards of People's Republic of China Space environment produces the harshest surface of spacecraft Plasma environment with potential difference spacecraft, MOD] Published on 2022-04-15 2022-11-01 Implementation State Administration for Market Regulation Released by the National Standardization Administration directory Preface I 1 Scope 1 2 Normative references 1 3 Terms and Definitions 1 4 Symbols and Abbreviations 2 5 Principles for the identification of the worst environment 2 6 Principles applied to spacecraft design 2 7 The worst space environment used in the simulations3 Appendix A (Informative) Spacecraft Charging Simulation Program 4 Appendix B (normative) Simulation after material aging treatment 5 Appendix C (Informative) Charging Simulation 8 Reference 14

foreword

This document is in accordance with the provisions of GB/T 1.1-2020 "Guidelines for Standardization Work Part 1.Structure and Drafting Rules of Standardization Documents" drafted. This document is modified using ISO.19923.2017 "Space Environment (Natural and Artificial) Generates Plasma with the Worst Potential Differences in Spacecraft surroundings". Compared with ISO.19923.2017, this document has the following structural adjustments. --- Adjust Annex C of ISO.19923.2017 to Annex B; --- Adjust Annex B of ISO.19923.2017 to Annex C; --- Delete Annex D of ISO.19923.2017; --- In Chapter 1 "Scope", delete the third paragraph. The technical differences between this document and ISO.19923.2017 are as follows. ---Chapter 1, "Scope", second paragraph, delete the last sentence "Severe surface charging of low-Earth orbit spacecraft may be due to caused by the high-voltage power supply of spacecraft equipment, so this document does not involve this part of the content"; delete the third paragraph "this document only involves spacecraft external surface charge"; --- Chapter 3 replaces "the following terms and definitions apply to this document" to "defined in GB/T 32452-2015 and the following terms and definitions Definitions apply to this document"; ---In 3.1 "Dual Maxwell Distribution", "v---particle velocity, in meters per second (m/s)" and other physical parameters are added. unit; --- Chapter 5, delete "This document is part of the spacecraft charging simulation"; ---In the first paragraph of 7.1, replace the "pair of Maxwell's distribution parameters for the worst plasma environment in the geosynchronous orbit" with "Table 1." When the worst case is simulated, the double Maxwell distribution given in Table 1 should be used. "Harsh Plasma Environment" instead of "Simulation of used space environment"; ---7.2 deleted "As more environmental measurement data are published, this document will update the worst plasma in polar orbit and medium Earth orbit. Child Environment Parameters". The following editorial changes have been made to this document. ---The standard name is changed to "Space Environment Produces the Plasma Environment with the Worst Potential Difference on the Surface of the Spacecraft"; --- In A.2 "NASCAP-2k", "this program is only open for use in the United States" is deleted, and "simulation using a hybrid PIC simulation method" is added Interaction process between the spacecraft surface and the plasma environment" to describe the function of the program; deleted from A.3 "COULOMB-2" Except "The program is only open for use in Russia"; --- In the title of Appendix C and each subtitle, replace "cycle simulation" with "charging simulation"; ---C.1 "NASCAP-2k charging simulation" second paragraph added "where δmax is the maximum secondary electron occurrence rate, Emax is the secondary electron The incident electron energy when the occurrence rate is maximum"; ---C.1 "NASCAP-2k charging simulation" Table C.1 header first column replace "cover glass material" with "material"; Table C.2 sixth row A column with a footnote to ATS-6 "The ATS-6 environment used by NASCAP-2k here is different from the ATS-6 environment in Table C.5 same"; ---C.1 "NASCAP-2k charging simulation" Table C.3 "NASCAP-2k simulation results" fourth row sixth column, NASA Worst Case The calculation result of the maximum potential difference of the reverse potential gradient after charging for.2000s under the sunshine environment, replace "3940" with "897"; ---C.2 "MUSCAT charging simulation" Table C.6 "MUSCAT simulation results under sunshine conditions" seventh row eighth column, LANL- For the calculation result of the maximum potential difference of the forward potential gradient of the KIT environment, replace "-23700" with "-23800"; delete the third line of C.2 A footnote to "Compton ?"; ---C.4 Add a footnote after the second sentence "Simulation results" "Because the material properties used in the simulation are not completely consistent with those used in the actual engineering Therefore, the simulation results are for reference only.” Please note that some content of this document may be patented. The issuing agency of this document assumes no responsibility for identifying patents. This document is proposed by the Chinese Academy of Sciences. This document is under the jurisdiction of the National Standardization Technical Committee for Aerospace Technology and Its Application (SAC/TC425). This document is drafted by. National Space Science Center, Chinese Academy of Sciences. The main drafters of this document. Meng Xuejie, Zhong Qiuzhen, Chen Dong, Chen Shanqiang, Miao Juan, Lin Ruilin, Zhou Zhenqi. Space environment produces the harshest surface of spacecraft Plasma environment with potential difference

1 Scope

This document describes the space plasma environment that produces the harshest potential differences at the surface of a spacecraft, and how simulation programs can be used to estimate the The worst potential difference on the surface of the celestial device. This document contains the temperature and density of plasmas in Geosynchronous Orbit (GEO), Polar Earth Orbit (PEO), and Medium Earth Orbit (MEO). degrees, excluding the temperature and density of the plasma in low Earth orbit (LEO).

2 Normative references

The contents of the following documents constitute essential provisions of this document through normative references in the text. Among them, dated citations documents, only the version corresponding to that date applies to this document; for undated references, the latest edition (including all amendments) applies to this document. GB/T 32452-2015 Space Environment Terminology for Spacecraft

3 Terms and Definitions

The terms and definitions defined in GB/T 32452-2015 and the following apply to this document. ISO and IEC maintain terminology databases for standardization at. 3.1 The distribution functions for electrons and protons in geosynchronous orbits have two temperature components, respectively. The Maxwell distribution function is as follows [1]. f(v)= 2π 3/2 n1 (kT1) exp- mv2 2kT1 n2(kT2)32exp- mv2 2kT2. 􀪁 ? ? ? 􀭥 􀪁 ?? (1) where. v --- particle velocity, in meters per second (m/s); m --- particle mass, in kilograms (kg); k ---Boltzmann constant, 1.38064852×10-23J/K; n1,n2 ---Particle number density, the unit is per cubic meter (m-3); T1, T2---particle temperature, the unit is open (K). 3.2 Differential voltage differentialvoltage The potential difference between any two points of the spacecraft when unequal charging occurs, especially the potential difference between the spacecraft body and the insulating surface. ......

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