GB/T 45736-2025 English PDF

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GB/T 45736-2025: Stable operation requirements for spacecraft attitude and orbit control system
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Basic data

Standard ID: GB/T 45736-2025 (GB/T45736-2025)
Description (Translated English): Stable operation requirements for spacecraft attitude and orbit control system
Sector / Industry: National Standard (Recommended)
Classification of Chinese Standard: V73
Classification of International Standard: 49.140
Word Count Estimation: 14,121
Date of Issue: 2025-05-30
Date of Implementation: 2025-12-01
Issuing agency(ies): State Administration for Market Regulation, China National Standardization Administration

GB/T 45736-2025: Stable operation requirements for spacecraft attitude and orbit control system

---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 CCSV73 National Standard of the People's Republic of China Requirements for stable operation of spacecraft attitude and orbit control systems Released on 2025-05-30 2025-12-01 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 General Requirements 1 4.1 Overall Design 1 4.2 Operation status classification 2 4.3 Factors affecting stable operation 2 4.4 Stable operation capability building 2 5 Data validity judgment 3 5.1 Basic principles for judging data validity 3 5.2 Data Validity Judgment Method 3 6 Anomaly Detection 5 6.1 Anomaly Detection Level Division 5 6.2 Component-level anomaly detection 5 6.3 System-level anomaly detection 5 7 Soft/Hard Fault Handling 5 7.1 Fault Classification 5 7.2 Soft Fault Handling 5 7.3 Hard Fault Handling 6 8 Safety Boundary Detection 6 8.1 Safety Boundary Detection Principles 6 8.2 Safety Boundary Detection for Spacecraft Structures/Mechanisms 6 8.3 Safety Boundary Detection for Spacecraft Energy 6 8.4 Safety Boundary Detection for Spacecraft Propellants 6 9 Emergency safety mode 7 9.1 Classification of emergency safety modes 7 9.2 Directed safety mode treatment for Japan 7 9.3 Stop control safety mode disposal 7

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. Beijing Institute of Control Engineering, China Academy of Space Technology, Beijing Institute of Space Science and Technology Information, Shanghai Aerospace Institute of Control Technology, China Aerospace Standardization Institute. The main drafters of this document are. Yuan Li, Liu Xiaoxiang, Zhu Qi, Wang Shuyi, Wang Shuo, Zhong Xiaoqing, Guo Jianxin, Fan Weina, Gong Jinggang, Zhang Lan, Zhang Yi, Zhan, Bowen, and Wu, Jingyu. Requirements for stable operation of spacecraft attitude and orbit control systems

1 Scope

This document specifies the overall requirements for attitude and orbit control systems for stable operation of spacecraft, data validity judgment, anomaly detection, software/ Hard fault handling, safety boundary detection and emergency safety mode. This document is applicable to the design, application, and ground operation and maintenance of attitude and orbit control for all types of spacecraft.

2 Normative references

This document has no normative references.

3 Terms and definitions

The following terms and definitions apply to this document. 3.1 According to the predetermined rules or ground control instructions, the spacecraft software and hardware are organically combined to complete the spacecraft attitude and orbit control. Device subsystem. 3.2 anomaly The phenomenon that the actual state does not match the expected state. 3.3 Fault An event or condition in which a system or part of a system is unable to perform its specified function. 3.4 emergencysafemode When a spacecraft control system fails and cannot complete its scheduled mission, in order to ensure the energy safety, structural and mechanism safety and propulsion of the spacecraft, Agent safety, controls the operating mode of the system while waiting for processing.

4 General requirements

4.1 Overall Design This document proposes the following aspects. AOCS data validity judgment, anomaly detection, fault handling, safety boundary detection, emergency safety mode handling, etc. The overall design requirements are as follows. a) With the overall mission of the spacecraft as the goal, AOCS should ensure that the spacecraft operates autonomously according to the expected attitude and orbit, and ensure that the control system functions Normal function and stable performance; b) When there is external interference or certain faults or abnormal conditions occur in the spacecraft control system, the AOCS should have certain system Robustness, capable of rapid anomaly detection and fault handling, keeping the spacecraft's attitude and orbit in an expected state or within a bounded domain of state sequences; ......

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