Standards Development

Scope

This standard specifies the purpose, principle, timing, indicators and process of design and verification for diagnosability and reconfigurability of spacecraft.

This standard is applicable to evaluate and design the diagnosability and reconfigurability of spacecraft throughout their entire life cycle.

This standard focuses on the spacecraft system that can be reconfigured after a fault occurs, such as the attitude and orbit control system, power system, TT&C system, etc.

Purpose

To achieve safe, reliable autonomous operation of a spacecraft, the function of failure detection isolation and system reconfiguration (FDIR) must be concerned during the design stage of the spacecraft. However, in the existing standards, the FDIR requirements are proposed qualitatively without detailed explanations of how to design and verify them. No relevant standards have been proposed to regulate how to quantify the FDIR requirements to guide the system design and how to evaluate the system FDIR capability to verify the design result. This document is proposed for the following reasons:

(1) To quantitative analyze the diagnosability and reconfigurability of spacecraft systems with different equipment, configurations, design schemes, and given fault sets.

(2) To Identify weak links in the system to ensure that the spacecraft system can meet diagnostic and reconfigurable requirements at different stages such as ground design and in-orbit operation phases.

(3) To provide a reference for international communication, so that various problems encountered in international cooperation can be regulated to improve communication efficiency in international business cooperation and avoid misunderstandings and contradictions caused by inconsistent understanding; It is conducive to achieving the universality of related products between different countries, increasing the possibility of deep international commercial cooperation, expanding the procurement channels of system integrators, thereby reducing costs and improving economic benefits.

(4) There are no obstacles in the establishment and application of this standard.

(5) The definition and requirements of the control engineering involved in this project are easy to reach agreement and can be applied for a long time.

(6) Currently, there are no relevant ISO standards, and there is an urgent need to establish relevant standards.

(7) Without relevant standards established, it is not conducive to improving the standardization and generalization of the spacecraft design, which will increase communication costs.

(8) This standard does not duplicate or conflict with existing ISO standards.