1、BS ISO 17540:2016Space systems Liquid rocketengines and test stands Terms and definitionsBSI Standards PublicationWB11885_BSI_StandardCovs_2013_AW.indd 1 15/05/2013 15:06BS ISO 17540:2016 BRITISH STANDARDNational forewordThis British Standard is the UK implementation of ISO 17540:2016. The UK partic
2、ipation in its preparation was entrusted to TechnicalCommittee ACE/68, Space systems and operations.A list of organizations represented on this committee can be obtained on request to its secretary.This publication does not purport to include all the necessary provisions of a contract. Users are res
3、ponsible for its correct application. The British Standards Institution 2016. Published by BSI Standards Limited 2016ISBN 978 0 580 82528 6 ICS 49.140 Compliance with a British Standard cannot confer immunity from legal obligations.This British Standard was published under the authority of the Stand
4、ards Policy and Strategy Committee on 30 November 2016.Amendments/corrigenda issued since publicationDate T e x t a f f e c t e dBS ISO 17540:2016 ISO 2016Space systems Liquid rocket engines and test stands Terms and definitionsSystmes spatiaux Moteurs de fuse liquides et stands dessai Termes et dfi
5、nitionsINTERNATIONAL STANDARDISO17540First edition2016-12-15Reference numberISO 17540:2016(E)BS ISO 17540:2016ISO 17540:2016(E)ii ISO 2016 All rights reservedCOPYRIGHT PROTECTED DOCUMENT ISO 2016, Published in SwitzerlandAll rights reserved. Unless otherwise specified, no part of this publication ma
6、y be reproduced or utilized otherwise in any form or by any means, electronic or mechanical, including photocopying, or posting on the internet or an intranet, without prior written permission. Permission can be requested from either ISO at the address below or ISOs member body in the country of the
7、 requester.ISO copyright officeCh. de Blandonnet 8 CP 401CH-1214 Vernier, Geneva, SwitzerlandTel. +41 22 749 01 11Fax +41 22 749 09 47copyrightiso.orgwww.iso.orgBS ISO 17540:2016ISO 17540:2016(E)Foreword vIntroduction vi1 Scope . 12 Terms and definitions . 12.1 General . 12.2 Engine units . 12.3 Eng
8、ine types by way of work process . 22.4 Engine types by multiplicity of use and integration . 22.5 Engine types by purpose 22.6 Low-thrust engine types by way of work process 32.7 General parameters and performance of engine . 32.8 Engine time characteristics, types of operating and resources 62.9 L
9、ow-thrust engine performance 72.10 Engine operation modes . 92.11 Low-thrust engine operation modes 102.12 Chamber (gas generator) components . 102.13 Gas generator types . 122.14 Operating process in chamber (gas generator) . 122.15 Nozzle types . 142.16 Nozzle items . 152.17 Nozzle characteristics
10、 162.18 Nozzle operation modes 162.19 Flow in nozzle . 162.20 Turbine pump components . 172.21 Pump characteristics 182.22 Turbine pump general characteristics 182.23 Automation units . 192.24 Devices and methods of control efforts creation in engines 192.25 Engine cooling 192.26 Engine thermal prot
11、ection . 202.27 Engine tests: General 202.28 Types of engine tests: Thermal loads . 212.29 Types of engine tests: Associate with rocket . 212.30 Types of engine tests: Test site . 212.31 Types of engine tests: Organizational factor and test site 212.32 Types of engine tests: Test conditions . 212.33
12、 Types of engine tests: Accelerated data accessing 222.34 Types of engine tests: Test purposes 222.35 Types of tests specific for low-thrust engines .232.36 Test technology 232.37 Test conditions . 232.38 Test results. 242.39 Engine reliability 242.40 Engine defects . 252.41 Engine failure modes 252
13、.42 Engine operation 252.43 Analysis of engine technical status . 262.44 Engine reliability index . 262.45 Engine quality control . 262.46 Structural and functional analysis of reliability 272.47 Test stands: General . 272.48 Stand types 282.49 Stand systems . 282.50 Post-test processing. 29 ISO 201
14、6 All rights reserved iiiContents PageBS ISO 17540:2016ISO 17540:2016(E)2.51 Stand system elements 302.52 Stand compartments . 31iv ISO 2016 All rights reservedBS ISO 17540:2016ISO 17540:2016(E)ForewordISO (the International Organization for Standardization) is a worldwide federation of national sta
15、ndards bodies (ISO member bodies). The work of preparing International Standards is normally carried out through ISO technical committees. Each member body interested in a subject for which a technical committee has been established has the right to be represented on that committee. International or
16、ganizations, governmental and non-governmental, in liaison with ISO, also take part in the work. ISO collaborates closely with the International Electrotechnical Commission (IEC) on all matters of electrotechnical standardization.The procedures used to develop this document and those intended for it
17、s further maintenance are described in the ISO/IEC Directives, Part 1. In particular the different approval criteria needed for the different types of ISO documents should be noted. This document was drafted in accordance with the editorial rules of the ISO/IEC Directives, Part 2 (see www.iso.org/di
18、rectives).Attention is drawn to the possibility that some of the elements of this document may be the subject of patent rights. ISO shall not be held responsible for identifying any or all such patent rights. Details of any patent rights identified during the development of the document will be in t
19、he Introduction and/or on the ISO list of patent declarations received (see www.iso.org/patents).Any trade name used in this document is information given for the convenience of users and does not constitute an endorsement.For an explanation on the meaning of ISO specific terms and expressions relat
20、ed to conformity assessment, as well as information about ISOs adherence to the World Trade Organization (WTO) principles in the Technical Barriers to Trade (TBT) see the following URL: www.iso.org/iso/foreword.html.The committee responsible for this document is ISO/TC 20, Aircraft and space vehicle
21、s, Subcommittee SC 14, Space systems and operations. ISO 2016 All rights reserved vBS ISO 17540:2016ISO 17540:2016(E)IntroductionThis International Standard is intended to be applied for all types of rocket engines which use a liquid propellant.The terms in this International Standard are specified
22、in scope of design, testing, reliability analysis and quality control of liquid rocket engines.The terms are intended to be required for use in all types of documentation and literature including in scope of standardization or using results of this activity.vi ISO 2016 All rights reservedBS ISO 1754
23、0:2016Space systems Liquid rocket engines and test stands Terms and definitions1 ScopeThe International Standard provides terms and definitions in scope of design, testing, reliability analysis and quality control of liquid rocket engines. The terms are required for use in all types of documentation
24、 and literature including in the scope of standardization or using the results of this activity.2 Terms and definitions2.1 General2.1.1rocket engineREreaction engine producing thrust for vehicle movement with the help of substances and energy sources contained within the vehicle being moved2.1.2liqu
25、id rocket engineLRErocket engine (2.1.1) using propellants in liquid form2.1.3low-thrust engineLTErocket engine (2.1.1) of a thrust not more than 5 000 N2.1.4liquid rocket propulsion systempropulsion system including engine, propellant tanks, avionics for control sub-systems, pressure vessels and co
26、ntrol devices for pneumatic and hydraulic control sub-systems, propellant feed system, actuators for steering sub-systems, and auxiliary equipment2.1.5clustered engineliquid rocket propulsion system (2.1.4) consisting of multiple rocket engines (2.1.1), common propellant tanks, and autonomous (indep
27、endent) propellant feed systems2.2 Engine units2.2.1chamberengine assembly where propellant and/or gas generation products, as a result of chemical reactions, are converted into products of combustion, created at the expiration of the reactive force2.2.2turbo-pumpTPengine component designed to pump
28、propellant into the chamber (2.2.1), gas generator sets and automatic engineINTERNATIONAL STANDARD ISO 17540:2016(E) ISO 2016 All rights reserved 1BS ISO 17540:2016ISO 17540:2016(E)2.2.3booster turbo-pumpBTPturbo-pump (2.2.2) engine support designed to increase propellant pressure in the pipelines t
29、o pump (2.20.1)2.2.4gas generatorunit of engine wherein propellant, as a result of chemical reaction, is converted in gaseous products of reaction at relatively low temperature2.2.5automatic engine controllerengine assembly designed for automatic control, regulation or maintenance of engine2.3 Engin
30、e types by way of work process2.3.1engine with afterburningengine where gas generation products after their use are used to drive the turbo-pump (2.2.2) assembly2.3.2engine without afterburningengine where gas generation products after their use to drive the turbo-pump (2.2.2) assembly are released
31、into the environmentNote 1 to entry: Engine without afterburning have a pump (2.20.1) or a pressurized fuel supply.2.3.3single-mode engineengine with one major mode2.3.4multimode engineengine with several basic modes2.4 Engine types by multiplicity of use and integration2.4.1expendable engineengine
32、intended for a specific purpose and used only one time2.4.2nonexpendable engineengine intended for a specific purpose and used multiple times2.4.3single-start engineengine started only once for a specific purpose2.4.4multi-start enginerestartable engineengine started multiple times for one specific
33、purpose2.5 Engine types by purpose2.5.1main engineengine intended to accelerate the space vehicle2 ISO 2016 All rights reservedBS ISO 17540:2016ISO 17540:2016(E)2.5.2correction engineengine intended to correct the speed during the correction of trajectory of the space vehicle2.5.3control engineengin
34、e intended to control the correction of the vector of the space vehicle in the active phase of the trajectory of motion2.5.4retrorocket engineengine intended to reduce the speed of the space vehicle2.6 Low-thrust engine types by way of work process2.6.1catalytic engineLTE (2.1.3) where the transform
35、ation of propellant into gaseous chemical reaction products is performed with the help of a catalyst2.6.2thermo-catalytic enginecatalytic LTE where the catalyst is heated by the external heat source2.6.3electro-thermo-catalytic enginethermo-catalytic LTE using an electrical source of energy2.6.4radi
36、o-thermo-catalytic enginethermo-catalytic LTE using a radioactive source of energy2.6.5thermal engineLTE (2.1.3) where the conversion of propellant in the gaseous products of chemical reactions is affected by heating the fuel from an external source of energy which increases their rate of expiration
37、Note 1 to entry: Energy is fed to the propellant or products of chemical reactions.2.6.6electro-thermal enginethermal LTE using an electrical energy source2.6.7radio-thermal enginethermal LTE using a radioactive energy source2.6.8electrolytic engineone-component of the LTE (2.1.3) where the electrol
38、ysis of the propellant is part of operating process2.6.9adjustable enginelow-thrust engine (2.1.3) that has a device to change the thrust2.7 General parameters and performance of engine2.7.1rated performanceset of nominal values of the engine designated in the specifications ISO 2016 All rights rese
39、rved 3BS ISO 17540:2016ISO 17540:2016(E)2.7.2mass flow ratemass of fluid passing a specified line or gate in unit time2.7.3volume flow ratevolume of fluid passing a specified line or gate in unit time2.7.4pre-start consumptionpropellant mass consumption during the time interval from the first start
40、command until the thrust build-up to a specified value equal to 5 % of the nominal2.7.5mixture ratioratio of oxidizer mass flow rate (2.7.2) to the fuel mass flow rate2.7.6volume ratioratio of oxidizer volume flow rate (2.7.3) to the fuel volume rate2.7.7pressureaverage static pressure of combustion
41、 products at the beginning of the combustion chamber (2.12.1) at the mixing system chamber2.7.8pressureaverage static pressure of gas generation at the beginning of the combustion chamber (2.12.2) at the mixing system gas generator2.7.9combustion temperaturestagnation temperature of combustion produ
42、cts at the exit from the combustion chamber (2.12.1)2.7.10combustion temperaturestagnation temperature of gas generation at the exit from the gas generator (2.2.4)2.7.11exhaust velocityvelocity of exhaust stream through the nozzle (2.12.16) or a reaction engine, relative to the nozzle2.7.12engine re
43、active forcegas and fluid flow resultant force acting on the thrust chamber internal surfaces resulting from the combustion gases2.7.13engine thrustresultant of the engine reactive force (2.7.12) and the environment pressure forces acting on the engine external surfaces (excluding external aerodynam
44、ic drag forces)2.7.14engine impulsetime integral of engine thrust2.7.15cut-off impulseimpulse (2.9.5) of engine thrust for the time interval defining the engine tail-off4 ISO 2016 All rights reservedBS ISO 17540:2016ISO 17540:2016(E)2.7.16specific impulseratio of engine thrust to the mass flow of pr
45、opellant IRms=Note 1 to entry: Thrust engine (chamber) specific impulse is converted in a vacuum and at sea level.Note 2 to entry: Thrust engine (chamber) specific impulse is also an equalled derivative from the thrust engine (chamber) impulse by weight or volume of propellant consumed.Note 3 to ent
46、ry: For LTE (2.1.3), the term “specific impulse” is used for steady-state continuous mode, single inclusions mode and the steady-state impulse mode.2.7.17volume specific impulseratio of engine thrust to the propellant volume flow rate IRvsv,=2.7.18thrust coefficientratio of chamber thrust to the pro
47、duct of the nozzle stagnation pressure (or chamber total pressure at nozzle inlet) and the area of nozzle throat2.7.19coefficient of specific impulseratio of actual specific impulse to the theoretical value that is defined by the same values of mixture ratio (2.7.5), the nozzle stagnation pressure o
48、r chamber total pressure at nozzle inlet2.7.20total coefficient of specific impulsecoefficient of specific impulse (2.7.16) defined at the mixture ratio (2.7.5) to be the maximum ideal value2.7.21consumable complex of chamberconsumable complexproduct of the combustion pressure in a given section of
49、the chamber (2.2.1) to a nozzle throat area, referred to the mass flow of the propellant in chamberNote 1 to entry: Given section of the chamber (2.2.1) is in analysis of camera characteristics stability during serial production initial section of combustion chamber (2.12.1) at (near) mixing system (2.12.3) and in analysis of multiphase flows (2.19.4) initial section of nozzle (2.12.16).2.7.22thrust complexratio of engine thrust chamber pressure and the product of combustion products in a given section of the chambe
