1、BSI Standards PublicationBS EN 16603-10-03:2014Space engineering TestingBS EN 16603-10-03:2014 BRITISH STANDARDNational forewordThis British Standard is the UK implementation of EN16603-10-03:2014. It supersedes BS EN 14824:2003 which iswithdrawn.The UK participation in its preparation was entrusted
2、 to TechnicalCommittee ACE/68, Space systems and operations.A list of organizations represented on this committee can beobtained on request to its secretary.This publication does not purport to include all the necessaryprovisions of a contract. Users are responsible for its correctapplication. The B
3、ritish Standards Institution 2014. Published by BSI StandardsLimited 2014ISBN 978 0 580 83403 5ICS 49.140Compliance with a British Standard cannot confer immunity fromlegal obligations.This British Standard was published under the authority of theStandards Policy and Strategy Committee on 31 August
4、2014.Amendments issued since publicationDate Text affectedBS EN 16603-10-03:2014EUROPEAN STANDARDNORME EUROPENNEEUROPISCHE NORMEN 16603-10-03August 2014ICS 49.140 Supersedes EN 14824:2003English versionSpace engineering - TestingIngnerie spatiale - Tests Raumfahrttechnik - TestsThis European Standar
5、d was approved by CEN on 28 December 2013.CEN and CENELEC members are bound to comply with the CEN/CENELEC Internal Regulations which stipulate the conditions for giving this European Standard the status of a national standard without any alteration. Up-to-date lists and bibliographical references c
6、oncerning such national standards may be obtained on application to the CEN-CENELEC Management Centre or to any CEN and CENELECmember.This European Standard exists in three official versions (English, French, German). A version in any other language made by translation under the responsibility of a
7、CEN and CENELEC member into its own language and notified to the CEN-CENELEC Management Centre has the same status as the official versions.CEN and CENELEC members are the national standards bodies and national electrotechnical committees of Austria, Belgium, Bulgaria, Croatia, Cyprus, Czech Republi
8、c, Denmark, Estonia, Finland, Former Yugoslav Republic of Macedonia, France, Germany, Greece, Hungary, Iceland, Ireland, Italy, Latvia, Lithuania, Luxembourg, Malta, Netherlands, Norway, Poland, Portugal, Romania, Slovakia, Slovenia, Spain, Sweden, Switzerland, Turkey and United Kingdom.CEN-CENELEC
9、Management Centre:Avenue Marnix 17, B-1000 Brussels 2014 CEN/CENELEC All rights of exploitation in any form and by any means reserved worldwide for CEN national Members and for CENELEC Members.Ref. No. EN 16603-10-03:2014 EBS EN 16603-10-03:2014EN 16603-10-03:2014 (E) 2 Table of contentsForeword 5 I
10、ntroduction 6 1 Scope. 8 2 Normative references.10 3 Terms, definitions and abbreviated terms12 3.1 Terms from other standards12 3.2 Terms specific to the present standard .18 3.3 Abbreviated terms.24 4 General requirements.27 4.1 Test programme .27 4.2 Development test prior qualification 27 4.3 Te
11、st management.28 4.3.1 General.28 4.3.2 Test reviews28 4.3.3 Test documentation.32 4.3.4 Anomaly or failure during testing.33 4.3.5 Test data.33 4.4 Test conditions, tolerances, and accuracies33 4.4.1 Test conditions33 4.4.2 Test tolerances .34 4.4.3 Test accuracies.36 4.5 Test objectives38 4.5.1 Ge
12、neral requirements .38 4.5.2 Qualification testing.38 4.5.3 Acceptance testing39 4.5.4 Protoflight testing 39 4.6 Retesting 40 4.6.1 Overview.40 BS EN 16603-10-03:2014EN 16603-10-03:2014 (E) 3 4.6.2 Implementation of a design modification after completion of qualification.40 4.6.3 Storage after prot
13、oflight or acceptance testing 40 4.6.4 Space segment element or equipment to be re-flown41 4.6.5 Flight use of qualification Space segment element or equipment 42 5 Space segment equipment test requirements .43 5.1 General requirements.43 5.2 Qualification tests requirements45 5.3 Acceptance test re
14、quirements 53 5.4 Protoflight test requirements .59 5.5 Space segment equipment test programme implementation requirements .66 5.5.1 General tests.66 5.5.2 Mechanical tests .69 5.5.3 Structural integrity tests.72 5.5.4 Thermal tests 73 5.5.5 Electrical/RF tests .75 5.5.6 Mission specific test 76 6 S
15、pace segment element test requirements78 6.1 General requirements.78 6.2 Qualification test requirements .79 6.3 Acceptance test requirements 86 6.4 Protoflight test requirements .91 6.5 Space segment elements test programme implementation requirements .98 6.5.1 General tests.98 6.5.2 Mechanical tes
16、ts .102 6.5.3 Structural integrity tests.107 6.5.4 Thermal tests 108 6.5.5 Electromagnetic tests110 6.5.6 Mission specific tests 111 6.5.7 Crewed mission specific tests . 111 7 Pre-launch testing 113 Annex A (normative) Assembly, integration and test plan (AITP) - DRD115 Annex B (normative) Test spe
17、cification (TSPE) - DRD.118 Annex C (normative) Test procedure (TPRO) - DRD 121 BS EN 16603-10-03:2014EN 16603-10-03:2014 (E) 4 Annex D (informative) Guidelines for tailoring and verification of this standard .124 Bibliography.128 FiguresFigure 3-1: Space system breakdown 13 Figure 3-2: Space segmen
18、t examples 17 Figure 5-1: Space segment equipment test sequence45Figure D-1 : Logic for customer tailoring and supplier answer through compliance and verification matrix .126 Figure D-2 : Clauses selection in First step of the tailoring .126 TablesTable 4-1: Allowable tolerances35 Table 4-2: Test ac
19、curacies .37 Table 5-1: Space segment equipment - Qualification test baseline.46 Table 5-2: Space segment equipment - Qualification test levels and duration 48 Table 5-3: Space segment equipment - Acceptance test baseline54 Table 5-4: Space segment equipment - Acceptance test levels and duration .56
20、 Table 5-5: Space segment equipment - Protoflight test baseline 60 Table 5-6: Space segment equipment - Protoflight test levels and duration62 Table 6-1: Space segment element - Qualification test baseline.80 Table 6-2: Space segment element - Qualification test levels and duration 82 Table 6-3: Spa
21、ce segment element - Acceptance test baseline86 Table 6-4: Space segment element - Acceptance test levels and duration .88 Table 6-5: Space segment element - Protoflight test baseline 92 Table 6-6: Space segment element - Protoflight test levels and duration94Table D-1 : Guideline for verification c
22、lose-out .127 BS EN 16603-10-03:2014EN 16603-10-03:2014 (E) 5 Foreword This document (EN 16603-10-03:2014) has been prepared by Technical Committee CEN/CLC/TC 5 “Space”, the secretariat of which is held by DIN. This standard (EN 16603-10-03:2014) originates from ECSS-E-ST-10-03C. This European Stand
23、ard shall be given the status of a national standard, either by publication of an identical text or by endorsement, at the latest by February 2015, and conflicting national standards shall be withdrawn at the latest by February 2015. Attention is drawn to the possibility that some of the elements of
24、 this document may be the subject of patent rights. CEN and/or CENELEC shall not be held responsible for identifying any or all such patent rights. This document will supersede EN 14824:2003. This document has been developed to cover specifically space systems and has therefore precedence over any E
25、N covering the same scope but with a wider domain of applicability (e.g. : aerospace). According to the CEN-CENELEC Internal Regulations, the national standards organizations of the following countries are bound to implement this European Standard: Austria, Belgium, Bulgaria, Croatia, Cyprus, Czech
26、Republic, Denmark, Estonia, Finland, Former Yugoslav Republic of Macedonia, France, Germany, Greece, Hungary, Iceland, Ireland, Italy, Latvia, Lithuania, Luxembourg, Malta, Netherlands, Norway, Poland, Portugal, Romania, Slovakia, Slovenia, Spain, Sweden, Switzerland, Turkey and the United Kingdom.
27、BS EN 16603-10-03:2014EN 16603-10-03:2014 (E) 6 Introduction The requirements on the systems engineering process are gathered in ECSS-E-ST-10; while specific aspects are further elaborated in dedicated standards, in particular: ECSS-E-ST-10-06, ECSS-E-ST-10-02 and the present standard (ECSS-E-ST-10-
28、03) In the System Engineering branch (ECSS-E-10) this standard aims at a consistent application of on ground testing requirements to allow proper qualification and acceptance of space products Experience has demonstrated that incomplete or improper on ground testing approach significantly increase p
29、roject risks leading to late discovery of design or workmanship problem(s) or in-orbit failure(s). Testing is part of the system engineering process as defined in ECSS-E-ST-10. This starts at the early phase of the mission when defining verification process in terms of the model philosophy and test
30、sequence and ends at the last testing phase prior launch. In the level of decomposition of a space system, this standard addresses the requirements for space segment element and space segment equipment. The document is organised such that: clause 4 provides requirements for overall test programme, t
31、est management and test conditions, tolerances and accuracy; clause 5 provides requirements for Space segment equipment; clause 6 provides requirements for Space segment element; clause 7 provides requirements for Pre-launch testing. Clauses 5 and 6 are organised as follows: general requirements for
32、 the products under test applicable to all models (clause 5.1 or 6.1); requirements applicable to qualification model (clause 5.2 or 6.2); requirements applicable to acceptance model (clause 5.3 or 6.3); requirements applicable to protoflight model (clause 5.4 or 6.4); detailed implementation requir
33、ements (clause 5.5 or 6.5); BS EN 16603-10-03:2014EN 16603-10-03:2014 (E) 7 In the clause providing requirements for each model (i.e. clauses 5.2, 5.3, 5.4, 6.2, 6.3 and 6.4), the first table of the clause: lists all types of test and defines their applicability and conditions; links to the second t
34、able of the clause that defines tests level and duration; provides reference to the clause defining the detailed implementation requirements for the given test (clause 5.5 or 6.5). For space segment equipment, the required sequence of test, for each model, is defined after the two tables in clause 5
35、.2, 5.3 or 5.4. Since testing activities are part of the overall verification activities, test documentation to be produced (DRDs) are either specified in the ECSS-E-ST-10-02 (case of the test report) or in this document. Annex D gives guidelines for performing the tailoring of this standard as well
36、 as the generation of the compliance and verification matrices.BS EN 16603-10-03:2014EN 16603-10-03:2014 (E) 8 1 ScopeThis standard addresses the requirements for performing verification by testing of space segment elements and space segment equipment on ground prior to launch. The document is appli
37、cable for tests performed on qualification models, flight models (tested at acceptance level) and protoflight models. The standard provides: Requirements for test programme and test management, Requirements for retesting, Requirements for redundancy testing, Requirements for environmental tests, Gen
38、eral requirements for functional and performance tests, NOTE Specific requirements for functional and performance tests are not part of this standard since they are defined in the specific project documentation. Requirements for qualification, acceptance, and protoflight testing including qualificat
39、ion, acceptance, and proto-fight models test margins and duration, Requirements for test factors, test condition, test tolerances, and test accuracies, General requirements for development tests pertinent to the start of the qualification test programme, NOTE Development tests are specific and are a
40、ddressed in various engineering discipline standards. Content of the necessary documentation for testing activities (e.g. DRD). Due to the specific aspects of the following types of test, this Standard does not address: Space system testing (i.e. testing above space segment element), in particular t
41、he system validation test, In-orbit testing, Testing of space segment subsystems, BS EN 16603-10-03:2014EN 16603-10-03:2014 (E) 9 NOTE Tests of space segment subsystems are often limited to functional tests that, in some case, are run on dedicated models. If relevant, qualification tests for space s
42、egment subsystems are assumed to be covered in the relevant discipline standards. Testing of hardware below space segment equipment levels (including assembly, parts, and components), Testing of stand-alone software, NOTE For verification of flight or ground software, ECSS-E-ST-40 and ECSS-Q-ST-80 a
43、pply. Qualification testing of two-phase heat transport equipment, NOTE For qualification testing of two-phase heat transport equipment, ECSS-E-ST-31-02 applies. Tests of launcher segment, subsystem and equipment, and launch facilities, Tests of facilities and ground support equipment, Tests of grou
44、nd segment. This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00. Annex D gives guidelines for performing this tailoring. BS EN 16603-10-03:2014EN 16603-10-03:2014 (E) 10 2 Normative referencesThe following normative documen
45、ts contain provisions which, through reference in this text, constitute provisions of this ECSS Standard. For dated references, subsequent amendments to, or revision of any of these publications do not apply. However, parties to agreements based on this ECSS Standard are encouraged to investigate th
46、e possibility of applying the more recent editions of the normative documents indicated below. For undated references, the latest edition of the publication referred to applies. EN reference Reference in text Title EN 16601-00-01 ECSS-S-ST-00-01 ECSS system - Glossary of terms EN 16603-10-02 ECSS-E-
47、ST-10-02 Space engineering - Verification EN 16603-20 ECSS-E-ST-20 Space engineering - Electrical and electronic EN 16003-20-01 ECSS-E-20-01 Space engineering - Multipaction design and test EN 16603-20-06 ECSS-E-ST-20-06 Space engineering - Spacecraft charging EN 16603-20-07 ECSS-E-ST-20-07 Space en
48、gineering - Electromagnetic compatibility EN 16603-20-08 ECSS-E-ST-20-08 Space engineering - Photovoltaic assemblies and components EN 16603-31 ECSS-E-ST-31 Space engineering - Thermal control general requirements EN 16603-32 ECSS-E-ST-32 Space engineering - Structural general requirements EN 16603-
49、32-02 ECSS-E-ST-32-02 Space engineering - Structural design and verification of pressurized hardware EN 16603-32-10 ECSS-E-ST-32-10 Space engineering - Structural factors of safety for spaceflight hardware EN 16603-32-11 ECSS-E-ST-32-11 Space engineering - Modal survey assessment EN 16603-33-01 ECSS-E-ST-33-01 Space engineering - Mechanisms EN 16601-40 ECSS-M-ST-40 Space project management - Configuration and information management EN 16602-10-09 ECSS-Q-ST-10-09 Space product assurance - Nonconformance control system EN 166
