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GB/T 47036-2026: Analytical calculation method of orbit perturbation for space objects
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Analytical calculation method of orbit perturbation for space objects
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Standard similar to GB/T 47036-2026
GB/T 43223 | GB/T 32453 | GB/T 47037 | GB/T 47035 | Basic data
| Standard ID | GB/T 47036-2026 (GB/T47036-2026) |
| Description (Translated English) | Analytical calculation method of orbit perturbation for space objects |
| Sector / Industry | National Standard (Recommended) |
| Classification of Chinese Standard | V70 |
| Classification of International Standard | 49.140 |
| Date of Issue | 2026-01-28 |
| Date of Implementation | 2026-05-01 |
GB/T 47036-2026: Analytical calculation method of orbit perturbation for space objects
---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 Standards of the People's Republic of China
Analytical Calculation Method for Orbital Perturbation of Space Objects
Published on 2026-01-28
Implemented on May 1, 2026
State Administration for Market Regulation
The State Administration for Standardization issued a statement.
Table of contents
Preface III
1.Scope 1
2 Normative References 1
3.Terms and Definitions 1
4 Symbols 2
4.1 Basic Symbols 2
4.2 Auxiliary Symbols 3
5 General Requirements 4
5.1 Time System 4
5.2 Coordinate System 4
5.3 Orbital State Quantities 4
5.4 Normalization 4
5.5 Orbit Type Classification 5
6.Basic Model for Analytical Calculation of Orbital Perturbation of Space Objects 5
6.1 Relationship between instantaneous roots and average roots 5
6.2 Change of average number of roots over time 5
7.Calculation flow of the analytical calculation method based on the orbital perturbation of space objects 6.
7.1 Calculation process for converting instantaneous roots to average roots 6
7.2 Calculation process for converting average root number to instantaneous root number 6
7.3 Calculation process of extrapolated average roots 6
7.4 Calculation process for extrapolated instantaneous roots 7
Appendix A (Informative). Conversion between Kepler elements and rectangular coordinates with elements without singularities 8
A.1 Converting Kepler roots to singularity-free roots 8
A.2 Converting non-singular radicals to Keplerian radicals 8
A.3 Rectangular coordinates to roots without singularities 8
A.4 Radicals without singularities converted to rectangular coordinates 9
Appendix B (Informative) Physical Model Parameters Applicable to the APS Method 10
B.1 General Physical Model Parameters 10
B.2 Lunar orbital parameters 11
B.3 Atmospheric density parameter 12
Appendix C (Normative) Analytical Calculation Formula for Orbit Perturbation using the APS Method 13
C.1 Instructions for Use and Preparations 13
C.2 Analytical Formula for Short-Period Term of Orbital Perturbation 13
C.3 Analytical Formula for the Variation Term of the Mean Root of Orbital Perturbation 23
Appendix D (Informative) Analytical Calculation Formulas for Extended Perturbations Using the APS Method 30
D.1 Instructions for Use and Preparations 30
D.2 Analytical Calculation Formula for Solar Radiation Pressure Perturbation 30
D.3 Analytical Calculation Formula for Continuous Constant Small Thrust Perturbation 34
Appendix E (Informative) Reference and Suggestions for Using the APS Method 37
E.1 Verification of APS method calculation results 37
E.2 APS method calculation accuracy reference 37
E.3 Customization and Tailoring of the APS Methodology 39
References 40
Foreword
This document complies with the provisions of GB/T 1.1-2020 "Standardization Work Guidelines Part 1.Structure and Drafting Rules of Standardization Documents".
Drafting.
Please note that some content in this document may involve patents. The issuing organization of this document assumes no responsibility for identifying patents.
This document was proposed and is under the jurisdiction of the National Technical Committee on Standardization of Aerospace Technology and Its Applications (SAC/TC425).
This document was drafted by. Nanjing University, National Astronomical Observatories of the Chinese Academy of Sciences, Xi'an Satellite Control Center, and Beijing Aerospace Flight Control Center.
China Aerospace Standardization Institute.
The main drafters of this document are. Tang Jingshi, Liu Jing, Cheng Haowen, Liu Lin, Wang Yanrong, Cao Jianfeng, Zheng Fengchun, Li Dawei, Hu Songhua, and Zhang Yao.
Gan Qingbo, Quan Haofang, Zhao Nanying.
Analytical Calculation Method for Orbital Perturbation of Space Objects
1 Scope
This document describes an analytical calculation method for the orbital perturbation of a space object.
This document applies to calculations such as instantaneous radical transformation and orbital extrapolation for space objects orbiting the Earth. It is used for space target cataloging and navigation.
Specific tasks include spacecraft tracking and control and operation management, collision risk calculation, long-term orbit evolution, orbit life estimation, safety avoidance and deorbit strategy formulation, etc.
Calculate the scenario.
2 Normative references
The contents of the following documents, through normative references within the text, constitute essential provisions of this document. Dated citations are not included.
For references to documents, only the version corresponding to that date applies to this document; for undated references, the latest version (including all amendments) applies.
This document.
GB/T 30114.3 Terminology for Space Science and its Applications Part 3.Space Astronomy
GB/T 43223 Specification for Orbital Data of Space Objects
GB/T 45621 Space Terminology - Space Debris
3 Terms and Definitions
The terms and definitions defined in GB/T 30114.3, GB/T 43223 and GB/T 45621, as well as the following terms and definitions, apply to this document.
3.1
non-singular element
The orbital parameters defined based on Kepler elements eliminate one or more singularities that could cause the definition of Kepler elements to fail.
Note. One type of orbital element.
3.2
Orbit perturbation
For a space object orbiting the Earth, in addition to the Earth's two-body gravitational pull, other disturbances affect its orbit.
3.3
short-period term
The terms with short periods and rapid changes in the orbital elements of a space object.
Note. In mathematics, this type of term is represented by an average value of zero over the orbital period.
3.4
Instantaneous roots osculating element
Keplerian elements or singularity-free elements that describe the actual orbital state of a space object at a given moment.
Note. Also known as "instantaneous roots", "kissing root count", or "closest root count".
3.5
mean element
The value obtained by subtracting the short-period term from the instantaneous roots at a given moment can describe the average motion of a spatial object at that moment.
Keplerian roots of a state or roots without singularities.
Note. Also known as "flat root". Sometimes the average number of roots defined in this way is also called the pseudo-average root or pseudo-flat root.
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