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GB/T 40536-2021: Design requirements for residual propellant venting of spacecraft
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| GB/T 40536-2021 | English | 199 |
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Design requirements for residual propellant venting of spacecraft
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GB/T 40536-2021
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PDF similar to GB/T 40536-2021
Standard similar to GB/T 40536-2021 GB/T 43223 GB/T 32453 Basic data | Standard ID | GB/T 40536-2021 (GB/T40536-2021) | | Description (Translated English) | Design requirements for residual propellant venting of spacecraft | | Sector / Industry | National Standard (Recommended) | | Classification of Chinese Standard | V72 | | Word Count Estimation | 10,183 | | Issuing agency(ies) | State Administration for Market Regulation, China National Standardization Administration | GB/T 40536-2021: Design requirements for residual propellant venting of spacecraft---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.
Design requirements for residual propellant venting of spacecraft
ICS 49.050
CCSV72
National Standards of People's Republic of China
Design requirements for residual propellant emissions of spacecraft
Released on 2021-08-20
2022-03-01 implementation
State Administration of Market Supervision and Administration
Issued by the National Standardization Management Committee
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 of Standardization Documents"
Drafting.
Please note that some of the contents of this document may involve patents. The issuing agency of this document is not responsible for identifying patents.
This document was proposed and managed by the National Aerospace Technology and Application Standardization Technical Committee (SAC/TC425).
This document was drafted by. Beijing Institute of Control Engineering.
The main drafters of this document. Song Tao, Liang Junqiang, Ding Fenglin, Sun Shuisheng, Yin Wenjuan, Geng Yongbing, Li Ze, Gao Jun, Lin Zhen, Li Wen, Zhang Lan.
Design requirements for residual propellant emissions of spacecraft
1 Scope
This document specifies the general design requirements, details,
Detailed design requirements and other content.
This document is applicable to the active and passive emission design of propellant and high-pressure gas of spacecraft. Of other working fluids on the spacecraft
The emission design can be implemented by reference.
2 Normative references
The contents of the following documents constitute the indispensable clauses of this document through normative references in the text. Among them, the dated reference documents, only
The version corresponding to this date is applicable to this document; for undated references, the latest version (including all amendments) is applicable to this document.
GB/T 34513-2017 Space Debris Mitigation Requirements
3 Terms and definitions
The following terms and definitions defined in GB/T 34513-2017 apply to this document.
3.1
Activeventing
Propellant and high-pressure gas emissions implemented by sending instructions on the ground.
3.2
Passiveventing
The propellant discharge device on the spacecraft discharges propellant and high-pressure gas autonomously under certain preset conditions.
4 General design requirements
4.1 Design basis
The design basis generally includes.
a) The content of Chapter 6 in GB/T 34513-2017;
b) Spacecraft development mission requirements;
c) Promote the development task requirements of the subsystem;
d) Promote the reliability, safety and environmental conditions of the sub-system.
4.2 Design criteria
The design criteria are as follows.
a) The remaining propellant discharge design should meet the technical requirements specified in 6.2 of GB/T 34513-2017;
b) The design of the remaining propellant emission should start from the spacecraft program stage and run through the development process to the effect after the spacecraft in orbit is emptied.
According to different mission tracks, carry out targeted design based on the evaluation of results;
c) The design of residual propellant emissions should comprehensively consider the engineering feasibility, economic effectiveness and technological advancement of the spacecraft system;
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