GB/T 45736-2025Stable operation requirements for spacecraft attitude and orbit control system (English PDF)

航天器姿态和轨道控制系统稳定运行要求

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Issued by

SAMR; SAC

Level / Type

National · Recommended

Issue date

May 30, 2025

Implementation date

December 1, 2025

Scope

GB/T 45736-2025 is the English-translated version of 航天器姿态和轨道控制系统稳定运行要求.

GB/T 45736-2025 is the Chinese national standard covering keeping a satellite pointed when its own control loop starts lying — the validity checks on data before it is used, the anomaly detection at component and at system level, the split between soft faults that can be cleared and hard faults that cannot, the safety boundaries on structure, on power and on propellant, and the emergency safe modes, sun-pointing or control stopped, that hold the spacecraft while the ground decides. First edition, in force from 1 December 2025. Issued on 30 May 2025, it has been in force since 1 December 2025.

Document preview — GB/T 45736-2025

National Standard of the People's Republic of China

ICS: 49.140
Classification: V 73

Issued by: State Administration for Market Regulation; Standardization Administration of the PRC

PrefaceIII
1 Scope1
2 Normative references1
3 Terms and Definitions1
4 General Requirements1
4.1 Overall Design1
4.2 Operation status classification2
4.3 Factors affecting stable operation2
4.4 Stable operation capability building2
5 Data validity judgment3
5.1 Basic principles for judging data validity3
5.2 Data Validity Judgment Method3
6 Anomaly Detection5
6.1 Anomaly Detection Level Division5
6.2 Component-level anomaly detection5
6.3 System-level anomaly detection5
7 Soft/Hard Fault Handling5
7.1 Fault Classification5
7.2 Soft Fault Handling5
7.3 Hard Fault Handling6
8 Safety Boundary Detection6
8.1 Safety Boundary Detection Principles6
8.2 Safety Boundary Detection for Spacecraft Structures/Mechanisms6
8.3 Safety Boundary Detection for Spacecraft Energy6
8.4 Safety Boundary Detection for Spacecraft Propellants6
9 Emergency safety mode7
9.1 Classification of emergency safety modes7
9.2 Directed safety mode treatment for Japan7
9.3 Stop control safety mode disposal7

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 Device subsystem

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.

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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This preview omits tables, figures, formulas and parts of the technical clauses. The complete document — 15 pages — is available in the English PDF.

Editions of GB/T 45736

Edition	Title	Revision	Status
GB/T 45736-2025	Stable operation requirements for spacecraft attitude and orbit control system	current edition	Current

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