BS ISO 16694-2015 Space systems The measured parameters at firing bench and flight tests of liquid rocket engines《航天系统 液体火箭发动机点火工作台和飞行试验的测量参数》.pdf

《BS ISO 16694-2015 Space systems The measured parameters at firing bench and flight tests of liquid rocket engines《航天系统 液体火箭发动机点火工作台和飞行试验的测量参数》.pdf》由会员分享，可在线阅读，更多相关《BS ISO 16694-2015 Space systems The measured parameters at firing bench and flight tests of liquid rocket engines《航天系统 液体火箭发动机点火工作台和飞行试验的测量参数》.pdf（24页珍藏版）》请在麦多课文档分享上搜索。

1、BSI Standards PublicationBS ISO 16694:2015Space systems The measuredparameters at firing benchand flight tests of liquid rocketenginesBS ISO 16694:2015 BRITISH STANDARDNational forewordThis British Standard is the UK implementation of ISO 16694:2015. The UK participation in its preparation was entru

2、sted 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 responsible for its correct application

3、. The British Standards Institution 2015.Published by BSI Standards Limited 2015ISBN 978 0 580 73120 4ICS 49.140Compliance with a British Standard cannot confer immunity from legal obligations.This British Standard was published under the authority of the Standards Policy and Strategy Committee on 3

4、1 March 2015.Amendments/corrigenda issued since publicationDate T e x t a f f e c t e dBS ISO 16694:2015 ISO 2015Space systems The measured parameters at firing bench and flight tests of liquid rocket enginesSystmes spatiaux Paramtres mesurs au banc dallumage et essais de vol des moteurs propergol l

5、iquideINTERNATIONAL STANDARDISO16694First edition2015-03-01Reference numberISO 16694:2015(E)BS ISO 16694:2015ISO 16694:2015(E)ii ISO 2015 All rights reservedCOPYRIGHT PROTECTED DOCUMENT ISO 2015All rights reserved. Unless otherwise specified, no part of this publication may be reproduced or utilized

6、 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 requester.ISO copyright of

7、ficeCase postale 56 CH-1211 Geneva 20Tel. + 41 22 749 01 11Fax + 41 22 749 09 47E-mail copyrightiso.orgWeb www.iso.orgPublished in SwitzerlandBS ISO 16694:2015ISO 16694:2015(E)Foreword ivIntroduction v1 Scope . 12 Normative references 13 Symbols and abbreviations . 14 General 24.1 Classification of

8、measured parameters . 24.2 Firing stand and flight tests operation conditions . 35 The measured parameters at tests of LRE . 35.1 The measured parameters at firing stand test of LRE 45.2 The measured parameters at flight tests of LRE 4 ISO 2015 All rights reserved iiiContents PageBS ISO 16694:2015IS

9、O 16694:2015(E)ForewordISO (the International Organization for Standardization) is a worldwide federation of national standards 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

10、 for which a technical committee has been established has the right to be represented on that committee. International organizations, governmental and non-governmental, in liaison with ISO, also take part in the work. ISO collaborates closely with the International Electrotechnical Commission (IEC)

11、on all matters of electrotechnical standardization.The procedures used to develop this document and those intended for its 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 note

12、d. This document was drafted in accordance with the editorial rules of the ISO/IEC Directives, Part 2 (see www.iso.org/directives).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 a

13、ny or all such patent rights. Details of any patent rights identified during the development of the document will be in the 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 u

14、sers and does not constitute an endorsement.For an explanation on the meaning of ISO specific terms and expressions related to conformity assessment, as well as information about ISOs adherence to the WTO principles in the Technical Barriers to Trade (TBT), see the following URL: Foreword Supplement

15、ary information .The committee responsible for this document is ISO/TC 20, Aircraft and space vehicles, Subcommittee SC 14, Space systems and operations.iv ISO 2015 All rights reservedBS ISO 16694:2015ISO 16694:2015(E)IntroductionThis International Standard provides customers, designers, and manufac

16、turers of liquid rocket engines with general provisions to the parameters measured under firing stand tests, under break-in, and flight tests. Parameters subjected to be measured are determined in the design documentation and are used under the analysis of reliability and quality control of liquid r

17、ocket engines.The determination of common requirements to the parameters of liquid rocket engines measured at firing stand and flight tests on a global scale was developed: to provide the required quality and reliability of rocket engines being created and used; to compare tests results and engines

18、impartially; to provide safety of final items and environmental protection.This International Standard will allow the development of a common criteria of evaluating and comparing of liquid rocket engines created by different countries according to the results of firing stand and flight tests. ISO 20

19、15 All rights reserved vBS ISO 16694:2015BS ISO 16694:2015Space systems The measured parameters at firing bench and flight tests of liquid rocket engines1 ScopeThis International Standard applies to all types of liquid rocket engines for expendable launch systems and satellites:a) Combustible fuel (

20、including cryogenic);b) Large-thrust, multiple component engines, with and without afterburning;c) Low-thrust engines, one component (mono-propellant) and two-component (bi-propellant).This International Standard establishes a list of parameters to be measured and registered with the firing stand an

21、d flight tests of serial LRE.The order of preparation and carrying out of stand and flight tests, methods of processing, and analysis of tests results of liquid rocket engines, also measurement accuracy requirements are not regulated by this International Standard. Measurement accuracy requirements

22、are established by engine designer.Parameters listed in this International Standard characterize performance attributes of liquid rocket engines and are used for evaluating of technical state of engines (operative, inoperative), if they correspond to the requirements specified and possibilities of p

23、utting them into operation.There are parameters specified in this International Standard, obligatory for registration and optional ones.The manufacturer of liquid rocket engines can determine additional list of parameters for specific items taking into account their design and diagrammatical feature

24、s.The meaning “optional parameter” denotes (in cases when a proper unit or a component can be the part of an engine) that according to the manufacturers decision, measurements are allowed not to be made.Measurement of parameters at firing stand and flight tests of liquid rocket engines is be made by

25、 means of the same sensors if possible.2 Normative referencesThe following documents, in whole or in part, are normatively referenced in this document and are indispensable for its application. For dated references, only the edition cited applies. For undated references, the latest edition of the re

26、ferenced document (including any amendments) applies.ISO 15864:2004, Space systems General test methods for space craft, subsystems and unitsISO 15865:2005, Space systems Qualification assessmentISO 24917:2010, Space systems General test requirements for launch vehicles3 Symbols and abbreviationsAVR

27、 apparent velocity regulatorBTPU booster turbo pumpCFC components-flow controllerINTERNATIONAL STANDARD ISO 16694:2015(E) ISO 2015 All rights reserved 1BS ISO 16694:2015ISO 16694:2015(E)CST confirmatory sampling testDD design documentationEV electric valveFCR regulator of fuel components ratio in co

28、mbustion chamberIDT interdepartmental testsLV launch vehicleLRE liquid rocket engineLTE low thrust enginePA pressure alarmPS propulsion systemPST pressure stabilizerSAT sampling acceptance testSST special sampling testSV space vehicleTDS tank depletion systemTPU turbopumpTT technological test4 Gener

29、al4.1 Classification of measured parameters4.1.1 The main purpose of measurement at proof tests of serial LRE (firing stand and flight tests) is to provide information for reliability analysis and quality control of engines.4.1.2 Parameters measured at firing stand and flight tests of LRE are subdiv

30、ided into the following groups:a) parameters characterizing test operation conditions;b) main parameters;c) parameters characterizing the engine ability to operate without any degradation.4.1.3 Parameters that characterize the actual test operation conditions are compared to required test operation

31、conditions. These parameters include:a) environmental parameters before and during the tests,b) fuel components state before and during the tests, andc) LRE characteristics (thrust and specific impulse).2 ISO 2015 All rights reservedBS ISO 16694:2015ISO 16694:2015(E)4.1.4 The main parameters charact

32、erize the ability of an engine to fulfill requirements determined by the technical documentation of the manufacturer.4.1.5 Parameters characterizing the ability of an engine to operate without any degradation are used to control the loads imposed over the engine elements.This group consists of param

33、eters whose values cannot be determined directly with measurements made during the assembly production process. Among these parameters are ones characterizing strength and heat-resistance of the combustion chamber and gas generator and the stability of working process in these assemblies. In case of

34、 an emergency situation these parameters (together with the main parameters and parameters characterizing the conditions of test operation) are used for the reasons of emergency process analysis.4.2 Firing stand and flight tests operation conditions4.2.1 Qualification tests of LRE are carried out in

35、 order to verify a safety margin beyond the expected life in accordance with the manufacturer of LV (SV) in consideration of the environmental factors and engine operation modes.4.2.2 Technological tests are carried out under values of the environmental factors and engine operation mode with operati

36、ng time necessary for measurement of parameters.4.2.3 Sampling acceptance tests are performed for checking lifetime which is agreed upon with the manufacturer of LV (SV) under values of the environmental factors and engine operation modes.4.2.4 Confirmatory Sampling Test (CST) is carried out within

37、the guarantee limits of the lifelength and operation conditions of LRE. It is allowed to carry out CST above guarantee limits one at a time or under any system of operation conditions of LRE.4.2.5 Special tests of LRE are carried out in accordance with special programs defined by a designer or a man

38、ufacturer of LRE and ratified by both enterprises.4.2.6 Flight tests of LRE are carried out in a LV (SV) at the real conditions of operation with the purpose of verifying conformance of LRE with specifications and determination of readiness of use.4.2.7 Purposes and objectives of flight tests are pr

39、esented in details in ISO 24917.4.2.8 General methods of tests of spacecrafts, subsystems, and units are presented in ISO 15864.4.2.9 Flight test analysis is performed according to the requirements of ISO 15865.5 The measured parameters at tests of LREThe measured parameters at firing stand and flig

40、ht tests of LRE are presented in the respective tables.LRE with afterburning (staged combustion cycle) and without afterburning (gas generator cycle/expander cycle/pressure fed cycle) used in launch vehicles and space vehicles are represented.Parameters measured under tests of LRE are subdivided int

41、o the following groups:a) obligatory;b) supplemental, depending on situation;c) interchangeable, obligatory to be measured. ISO 2015 All rights reserved 3BS ISO 16694:2015ISO 16694:2015(E)In the “Note” column in Tables 1 to 3, some necessary clarifications and additions to the specific parameters ar

42、e given.5.1 The measured parameters at firing stand test of LRE5.1.1 The measured parameters at commissioning and sampling tests (CTT, CST, and SST) of LRE are presented in Table 1.5.1.2 Table 2 is additional to Table 1 and contains parameters measured at qualification tests of LRE.5.2 The measured

43、parameters at flight tests of LRE5.2.1 The measured parameters at flight tests of LRE are presented in Table 3.The following symbols are used in the tables: required parameter subjected to be obligatory measured; measuring of a parameter does not regulated by this International Standard; supplementa

44、l, depending on situation;minterchangeable parameter to be measured where m is a serial number of a parameter in the respective table which can be used instead of the specified one in the clause.Table 1 The measured parameters at TT, SAT, CST, and SSTDescription of a parameterLRE typeNotewithout aft

45、erburn-ingwith afterburningfor LV for SV for LV for SV1. Parameters characterizing test operation conditions1.1 Ambient pressure 1.2 Ambient temperature 1.3 Ambient humidity 1.4 Direction and speed of air 1.5 Fuel components temperature in the place of flow rate meters installa-tion and at the engin

46、e inlet 1.6 Chemical composition of the fuel components 1.7 Specific weight of the fuel compo-nents (except cryogenic) 1.8 Content of solute gases in fuel components with a process of forced gassing 2. Main parameters2.1 LRE thrust 2.2 Mass outflow of fuel components through the engine (engine nozzl

47、e) per second 2.3 Combustion chamber pressure X3.8X3.8X3.8X3.84 ISO 2015 All rights reservedBS ISO 16694:2015ISO 16694:2015(E)Description of a parameterLRE typeNotewithout afterburn-ingwith afterburningfor LV for SV for LV for SV1. Parameters characterizing test operation conditions2.4 Fuel componen

48、ts pressure at the engine inlet 3. Parameters characterizing the ability of an engine to operate without any degradation3.1 Oxidizer pressure after the pump Parameters 3.1 and 3.2 are subjected to be measured after final stage (for multi-stage pumps and after booster stage).3.2 Fuel pressure after t

49、he pump 3.3 Oxidizer pressure after the booster pump of oxidizer Parameter 3.5 is meas-ured by means of sen-sors allowing to measure pressure change under the transient process. Under sampling accept-ance tests of engines without afterburning, parameter 3.5 is sub-jected to be measured if the engine construction provides the ability of the respective sensors installation.3.4 Fuel pressure after the booster pump of fuel 3.5 Gas pre