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GB/T 45741-2025 English PDF

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GB/T 45741-2025: Lifetime estimation method of space debris in low earth orbit
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Basic data

Standard ID GB/T 45741-2025 (GB/T45741-2025)
Description (Translated English) Lifetime estimation method of space debris in low earth orbit
Sector / Industry National Standard (Recommended)
Classification of Chinese Standard V70
Classification of International Standard 49.140
Word Count Estimation 18,121
Date of Issue 2025-05-30
Date of Implementation 2025-09-01
Issuing agency(ies) State Administration for Market Regulation, China National Standardization Administration

GB/T 45741-2025: Lifetime estimation method of space debris in low earth orbit

---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.
ICS 49.140 CCSV70 National Standard of the People's Republic of China Calculation method of lifetime of space debris in low earth orbit Released on 2025-05-30 2025-09-01 Implementation State Administration for Market Regulation The National Standardization Administration issued

Table of contents

Preface III 1 Scope 1 2 Normative references 1 3 Terms and Definitions 1 4 Track life calculation process 2 5 Area-to-mass ratio estimation 4 6 Low Earth Orbit Lifetime Calculation Model 5 Appendix A (Informative) Conversion method between instantaneous orbital elements and average orbital elements 7 Appendix B (Informative) Matters Needing Attention in Life Calculation 8 Appendix C (Informative) Principles of the method for calculating the lifetime of low-orbit space debris 9 Reference 10

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 for standardization documents" Drafting. Please note that some of the contents of this document may involve patents. The issuing organization of this document does not assume the responsibility for identifying patents. This document was proposed and coordinated by the National Technical Committee for Standardization of Aerospace Technology and Its Applications (SAC/TC425). This document was drafted by. National Astronomical Observatory of the Chinese Academy of Sciences, Major Special Project Center of the State Administration of Science, Technology and Industry for National Defense, Beijing Aerospace University, China Institute of Aerospace Standardization, and Beijing Space Vehicle General Design Department. The main drafters of this document are. Liu Jing, Zhang Yao, Li David, Tang Menghui, Wang Yue, Zheng Fengchun, Li Yang, Quan Haofang, Feng Hao, Zhao Nanying. Calculation method of lifetime of space debris in low earth orbit

1 Scope

This document specifies the methods for calculating the on-orbit lifetime of low-Earth orbit space debris, including the area-to-mass ratio calculation method and the lifetime time calculation method. method. This document is applicable to the design of space debris mitigation programmes, the design of spacecraft and launch vehicle deorbit trajectories, and the overall space debris environment assessment. Estimation, etc.

2 Normative references

This document has no normative references.

3 Terms and definitions

The following terms and definitions apply to this document. 3.1 Low Earth Orbit lowearthorbit;LEO An Earth orbit with an apogee altitude of less than.2000 km. 3.2 The orbital elements of the instantaneous position and velocity vectors of a space object. 3.3 Mean orbital elements meanorbitelements The orbital elements of the average orbital motion of space objects obtained by ignoring some changes in periodic terms introduced by disturbances. 3.4 orbitallifetime From the completion of the space object's operation phase (if any) and post-mission disposal phase-related operations or the formation of space debris to its re-entry into the Earth Time interval at 120km altitude on the surface. 3.5 estimation of lifetime The orbital lifetime of space debris is predicted using information such as orbital parameters, shape parameters and space environment parameters of space debris. 3.6 The ratio of the equivalent frontal area of space debris relative to the direction of atmospheric motion to the mass of space debris when the space debris is in orbit. 3.7 When space debris is in orbit, the ratio of the equivalent cross-sectional area of the space debris subjected to the solar radiation pressure to the mass of the space debris. 3.8 The disturbance caused by the deviation effect of the earth's gravity relative to the gravity of the earth's mass.

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