GB/T 32295-2015 English PDF
Basic dataStandard 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 ForewordThis 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 requirements1 ScopeThis 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 documentsThe 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 definitionsThe 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. ......Tips & Frequently Asked Questions:Question 1: How long will the true-PDF of GB/T 32295-2015_English be delivered?Answer: Upon your order, we will start to translate GB/T 32295-2015_English as soon as possible, and keep you informed of the progress. 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