| Standard ID | Contents [version] | USD | STEP2 | [PDF] delivered in | Standard Title (Description) | Status | PDF |
| GB/T 32295-2015 | English | 150 |
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Design requirements for residual propellant venting of launch vehicle
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GB/T 32295-2015
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Basic data | Standard ID | GB/T 32295-2015 (GB/T32295-2015) | | Description (Translated English) | Design requirements for residual propellant venting of launch vehicle | | Sector / Industry | National Standard (Recommended) | | Classification of Chinese Standard | V71 | | Classification of International Standard | 49.020 | | Word Count Estimation | 11,140 | | Date of Issue | 2015-12-31 | | Date of Implementation | 2016-07-01 | | Quoted Standard | ISO 24113-2011 | | Regulation (derived from) | State Standard Announcement 2015 No.43 | | Issuing agency(ies) | General Administration of Quality Supervision, Inspection and Quarantine of the People's Republic of China, Standardization Administration of the People's Republic of China | | Summary | This standard specifies the general design requirements, detailed design requirements and effect evaluation of the design criteria, emission options, etc. of the remaining propellant emissions of the final stage of a launch vehicle in flight. This standard applies to the use of room temperature liquid propellant and cryogenic liquid propellant carrier rocket residual propellant emission design, the upper stage of the rocket and other residual propellant treatment related design can refer to the implementation. | GB/T 32295-2015: Design requirements for residual propellant venting of launch vehicle---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 launch vehicle
ICS 49.020
V71
National Standards of People's Republic of China
Launch vehicle rocket - propellant emission design requirements
2015-12-31 released
2016-07-01 implementation
General Administration of Quality Supervision, Inspection and Quarantine of the People's Republic of China
China National Standardization Management Committee released
Foreword
This standard is drafted in accordance with the rules given in GB/T 1.1-2009.
This standard is proposed by China Aerospace Science and Technology Corporation.
This standard is nationalized by the National Aeronautical Technology and Its Application Standardization Technical Committee (SAC/TC425).
The drafting of this standard. China Aerospace Science and Technology Corporation Shanghai Aerospace Systems Engineering Research Institute.
The main drafters of this standard. Gu Yanfeng, Lin Jianfeng, Tang Mingliang, Zhu Yin.
Launch vehicle rocket - propellant emission design requirements
1 Scope
This standard specifies the general design requirements for the design criteria and emission options for the remaining propellant emissions of the last launch vehicle in flight.
Fine design requirements and performance evaluation and so on.
This standard applies to the use of room temperature liquid propellant and cryogenic liquid propellant carrier rocket final propellant discharge design,
The rocket above the level of the remaining propellant processing related design can refer to the implementation.
2 normative reference documents
The following documents are indispensable for the application of this document. For dated references, only the dated edition applies to this article
Pieces. For undated references, the latest edition (including all modifications) applies to this document.
ISO 24113..2011 Space debris mitigation requirements (Spacesystems-Spacedebrismitigationrequirements)
3 terms and definitions
The following terms and definitions apply to this document.
3.1
Residual propellant discharge residual brelantventing
Carrying the final stage of the carrier after the completion of the task, the safe release of its own tanks and pipelines within the remaining propellant process.
3.2
Residual propellant discharge system residualpropelantventingsystem
The final stage of the launch vehicle is used to implement the system of its own tank and the remaining propellant discharge in the pipeline. The system is
Arrow on both the system extension.
3.3
Arrow distance from spacecraft/launch-illuminated
Spacecraft and the carrier after the final separation, the minimum relative distance between the two.
3.4
Plume angle angleofplume
The angle between the envelope tangent and the nozzle centerline formed by the lower end of the carrier rocket or its combustion products.
3.5
The amount of amountofencounter
During the discharge of the final propellant of the launch vehicle, the quality of the pollutants discharged from the surface area of the spacecraft.
3.6
Space debris mitigation spacedebrismitigation
Through the reduction and control of space debris generated by the way and measures to ease the growth trend of space debris.
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