BS EN 16603-20-07-2014 Space engineering Electromagnetic compatibility《航天工程 电磁兼容性》.pdf

1、BSI Standards PublicationBS EN 16603-20-07:2014Space engineering Electromagnetic compatibilityBS EN 16603-20-07:2014 BRITISH STANDARDNational forewordThis British Standard is the UK implementation of EN 16603-20-07:2014.The UK participation in its preparation was entrusted to Technical Committee ACE

2、/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. The British Standards Instit

3、ution 2014.Published by BSI Standards Limited 2014ISBN 978 0 580 83975 7ICS 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 31 July 2014.Amendments/corrige

4、nda issued since publicationDate T e x t a f f e c t e dBS EN 16603-20-07:2014EUROPEAN STANDARD NORME EUROPENNE EUROPISCHE NORM EN 16603-20-07 July 2014 ICS 49.140 English version Space engineering - Electromagnetic compatibility Ingnirie spatiale - Compatibilit lectromagntique Raumfahrttechnik - El

5、ektromagnetische Kompabilitt This European Standard was approved by CEN on 10 February 2014. 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

6、. Up-to-date lists and bibliographical references concerning such national standards may be obtained on application to the CEN-CENELEC Management Centre or to any CEN and CENELEC member. This European Standard exists in three official versions (English, French, German). A version in any other langua

7、ge made by translation under the responsibility of a 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 Aust

8、ria, Belgium, Bulgaria, Croatia, Cyprus, Czech 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, Swede

9、n, Switzerland, Turkey and United Kingdom. CEN-CENELEC 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 16603-20-07:2014 EBS EN 16603-20-07:20

10、14EN 16603-20-07:2014 (E) 2 Table of contents Foreword 6 Introduction 7 1 Scope . 8 2 Normative references . 9 3 Terms, definitions and abbreviated terms 10 3.1 Terms from other standards 10 3.2 Terms specific to the present standard . 11 3.3 Abbreviated terms. 13 4 Requirements 15 4.1 General syste

11、m requirements . 15 4.2 Detailed system requirements 15 4.2.1 Overview . 15 4.2.2 EMC with the launch system . 15 4.2.3 Lightning environment . 16 4.2.4 Spacecraft charging and effects 16 4.2.5 Spacecraft DC magnetic emission 17 4.2.6 Radiofrequency compatibility 18 4.2.7 Hazards of electromagnetic

12、radiation 18 4.2.8 Intrasystem EMC 18 4.2.9 EMC with ground equipment . 19 4.2.10 Grounding . 19 4.2.11 Electrical bonding requirements 20 4.2.12 Shielding (excepted wires and cables) 21 4.2.13 Wiring (including wires and cables shielding) 21 5 Verification 23 5.1 Overview 23 5.1.1 Introduction . 23

13、 5.1.2 Electromagnetic effects verification plan . 23 5.1.3 Electromagnetic effects verification report . 23 BS EN 16603-20-07:2014EN 16603-20-07:2014 (E) 3 5.2 Test conditions . 23 5.2.1 Measurement tolerances . 23 5.2.2 Test site 24 5.2.3 Ground plane 26 5.2.4 Power source impedance 26 5.2.5 Gener

14、al test precautions . 28 5.2.6 EUT test configurations . 28 5.2.7 Operation of EUT 31 5.2.8 Use of measurement equipment . 32 5.2.9 Emission testing 33 5.2.10 Susceptibility testing 35 5.2.11 Calibration of measuring equipment 36 5.3 System level . 37 5.3.1 General . 37 5.3.2 Safety margin demonstra

15、tion for critical or EED circuits 37 5.3.3 EMC with the launch system . 37 5.3.4 Lightning . 38 5.3.5 Spacecraft and static charging 38 5.3.6 Spacecraft DC magnetic field emission . 38 5.3.7 Intrasystem electromagnetic compatibility . 38 5.3.8 Radiofrequency compatibility 38 5.3.9 Grounding . 39 5.3

16、.10 Electrical bonding 39 5.3.11 Wiring and shielding 39 5.4 Equipment and subsystem level test procedures 39 5.4.1 Overview . 39 5.4.2 CE, power leads, differential mode, 30 Hz to 100 kHz . 40 5.4.3 CE, power and signal leads, 100 kHz to 100 MHz . 42 5.4.4 CE, power leads, inrush current 45 5.4.5 D

17、C Magnetic field emission, magnetic moment . 47 5.4.6 RE, electric field, 30 MHz to 18 GHz . 50 5.4.7 CS, power leads, 30 Hz to 100 kHz . 54 5.4.8 CS, bulk cable injection, 50 kHz to 100 MHz . 56 5.4.9 CS, power leads, transients 59 5.4.10 RS, magnetic field, 30 Hz to 100 kHz 62 5.4.11 RS, electric

18、field, 30 MHz to 18 GHz . 66 5.4.12 Susceptibility to electrostatic discharges . 71 BS EN 16603-20-07:2014EN 16603-20-07:2014 (E) 4 Annex A (informative) Subsystem and equipment limits 77 A.1 Overview 77 A.2 CE on power leads, differential mode, 30 Hz to 100 MHz . 77 A.3 CE on power leads, in-rush c

19、urrents . 79 A.4 CE on power and signal leads, common mode, 100 kHz to 100 MHz . 79 A.5 CE on antenna ports . 80 A.6 DC magnetic field emission 80 A.6.1 General . 80 A.6.2 Characterization 81 A.6.3 Limit 82 A.7 RE, low-frequency magnetic field 82 A.8 RE, low-frequency electric field . 82 A.9 RE, ele

20、ctric field, 30 MHz to 18 GHz . 83 A.10 CS, power leads, differential mode, 30 Hz to 100 kHz 84 A.11 CS, power and signal leads, common mode, 50 kHz to 100 MHz . 85 A.12 CS, power leads, short spike transients 85 A.13 RS, magnetic field, 30 Hz to 100 kHz 86 A.14 RS, electric field, 30 MHz to 18 GHz

21、. 87 A.15 Susceptibility to electrostatic discharge . 88 Figures Figure 4-1: Bonding requirements 20 Figure 5-1: RF absorber loading diagram . 25 Figure 5-2: Line impedance stabilization network schematic 27 Figure 5-3: General test setup 29 Figure 5-4: Typical calibration fixture 33 Figure 5-5: Con

22、ducted emission, 30 Hz to 100 kHz, measurement system check 42 Figure 5-6: Conducted emission, 30 Hz to 100 kHz, measurement setup . 42 Figure 5-7: Conducted emission, measurement system check . 43 Figure 5-8: Conducted emission, measurement setup in differential mode . 43 Figure 5-9: Conducted emis

23、sion, measurement setup in common mode 44 Figure 5-10: Inrush current: measurement system check setup 46 Figure 5-11: Inrush current: measurement setup 46 Figure 5-12: Smooth deperm procedure . 50 Figure 5-13: Electric field radiated emission. Basic test setup 52 Figure 5-14: Electric field radiated

24、 emission. Antenna positioning 52 Figure 5-15: Electric field radiated emission. Multiple antenna positions 53 BS EN 16603-20-07:2014EN 16603-20-07:2014 (E) 5 Figure 5-16: CS, power leads, measurement system check set-up 55 Figure 5-17: CS, power leads, signal injection 55 Figure 5-18: Bulk cable in

25、jection, measurement system check set-up 58 Figure 5-19: Signal test waveform 59 Figure 5-20: CS of power and signal leads, bulk cable injection . 59 Figure 5-21: CS of power leads, transients, calibration set-up 61 Figure 5-22: CS of power leads, spike series injection test setup . 61 Figure 5-23:

26、CS of power leads, spike parallel injection test setup . 61 Figure 5-24: Measurement system check configuration of the radiating system . 64 Figure 5-25: Basic test set-up . 64 Figure 5-26: Test equipment configuration . 68 Figure 5-27: RS Electric field. Multiple test antenna positions. 68 Figure 5

27、-28: Receive antenna procedure . 69 Figure 5-29: Spacecraft charging ESD susceptibility test 74 Figure 5-30: Susceptibility to ESD: calibration configuration . 74 Figure 5-31: Susceptibility to ESD: test equipment configuration 75 Figure A-1 : Power leads, differential mode conducted emission limit

28、. 78 Figure A-2 : Common mode conducted emission limit 80 Figure A-3 : Radiated electric field limit 83 Figure A-4 : Conducted susceptibility limit, frequency domain 84 Figure A-5 : CS, voltage spike in percentage of test bus voltage 86 Figure A-6 : Radiated susceptibility limit . 87 Tables Table 5-

29、1: Absorption at normal incidence 25 Table 5-2: Bandwidth and measurement time 34 Table 5-3: Correspondence between test procedures and limits 40 Table A-1 : Equipment: susceptibility to conducted interference, test signal . 85 BS EN 16603-20-07:2014EN 16603-20-07:2014 (E) 6 Foreword This document (

30、EN 16603-20-07:2014) has been prepared by Technical Committee CEN/CLC/TC 5 “Space”, the secretariat of which is held by DIN. This standard (EN 16603-20-07:2014) originates from ECSS-E-ST-20-07C Rev. 1. This European Standard shall be given the status of a national standard, either by publication of

31、an identical text or by endorsement, at the latest by January 2015, and conflicting national standards shall be withdrawn at the latest by January 2015. Attention is drawn to the possibility that some of the elements of this document may be the subject of patent rights. CEN and/or CENELEC shall not

32、be held responsible for identifying any or all such patent rights. This document has been developed to cover specifically space systems and has therefore precedence over any EN covering the same scope but with a wider domain of applicability (e.g. : aerospace). According to the CEN-CENELEC Internal

33、Regulations, the national standards organizations of the following countries are bound to implement this European Standard: Austria, Belgium, Bulgaria, Croatia, Cyprus, Czech Republic, Denmark, Estonia, Finland, Former Yugoslav Republic of Macedonia, France, Germany, Greece, Hungary, Iceland, Irelan

34、d, Italy, Latvia, Lithuania, Luxembourg, Malta, Netherlands, Norway, Poland, Portugal, Romania, Slovakia, Slovenia, Spain, Sweden, Switzerland, Turkey and the United Kingdom.” BS EN 16603-20-07:2014EN 16603-20-07:2014 (E) 7 Introduction Electromagnetic compatibility (EMC) of a space system or equipm

35、ent is the ability to function satisfactorily in its electromagnetic environment without introducing intolerable electromagnetic disturbances to anything in that environment. The space system is designed to be compatible with its external natural, induced, or man-made electromagnetic environment. Na

36、tural components are lightning for launchers, the terrestrial magnetic field for space vehicles. Spacecraft charging is defined as voltage building-up of a space vehicle or spacecraft units when immerged in plasma. Electrostatic discharges result from spacecraft charging with possible detrimental ef

37、fects. External man-made interference, intentional or not, are caused by radar or telecommunication beams during ground operations and the launching sequence. Intersystem EMC also applies between the launcher and its payload or between space vehicles. Intrasystem EMC is defined between all electrica

38、l, electronic, electromagnetic, and electromechanical equipment within the space vehicle and by the presence of its self-induced electromagnetic environment. It comprises the intentional radiated electromagnetic fields and parasitic emission from on-board equipment. Both conducted and radiated emiss

39、ions are concerned. An electromagnetic interference safety margin is defined at system critical points by comparison of noise level and susceptibility at these points. BS EN 16603-20-07:2014EN 16603-20-07:2014 (E) 8 1 Scope EMC policy and general system requirements are specified in ECSS-E-ST-20. Th

40、is ECSS-E-ST-20-07 Standard addresses detailed system requirements (Clause 4), general test conditions, verification requirements at system level, and test methods at subsystem and equipment level (Clause 5) as well as informative limits (Annex A). Associated to this standard is ECSS-E-ST-20-06 “Spa

41、cecraft charging”, which addresses charging control and risks arising from environmental and vehicle-induced spacecraft charging when ECSS-E-ST-20-07 addresses electromagnetic effects of electrostatic discharges. Annexes A to C of ECSS-E-ST-20 document EMC activities related to ECSS-E-ST-20-07: the

42、EMC Control Plan (Annex A) defines the approach, methods, procedures, resources, and organization, the Electromagnetic Effects Verification Plan (Annex B) defines and specifies the verification processes, analyses and tests, and the Electromagnetic Effects Verification Report (Annex C) document veri

43、fication results. The EMEVP and the EMEVR are the vehicles for tailoring this standard. This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00. BS EN 16603-20-07:2014EN 16603-20-07:2014 (E) 9 2 Normative references The followi

44、ng normative documents 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 encourag

45、ed to investigate the 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

46、 16603-20 ECSS-E-ST-20 Space engineering - Electrical and electronic EN 16603-20-06 ECSS-E-ST-20-06 Space engineering - Spacecraft charging EN 16603-33-11 ECSS-E-ST-33-11 Space engineering - Explosive systems and devices EN 16603-50-14 ECSS-E-ST-50-14 Space engineering - Spacecraft discrete interfac

47、es IEC 61000-4-2 (Edition 1.2) Electromagnetic compatibility (EMC) - Part 4-2: Testing and measurement techniques - Electrostatic discharge immunity test BS EN 16603-20-07:2014EN 16603-20-07:2014 (E) 10 3 Terms, definitions and abbreviated terms 3.1 Terms from other standards For the purpose of this

48、 Standard, the terms and definitions from ECSS-S-ST-00-01 apply, in particular for the following terms: critical item customer equipment item launcher, launch vehicle mission requirement safety critical function supplier spacecraft, space vehicle subsystem system test verification For the purposes o

49、f this Standard, the following terms have a specific definition contained in ECSS-E-ST-20: conducted emission electromagnetic compatibility electromagnetic compatibility control electromagnetic interference electromagnetic interference safety margin emission high-voltage lightning indirect effects BS EN 16603-20-07:2014EN 16603-20-07:2014 (E) 11 radiated emission radiofrequency susceptibility susceptibility threshold For the purposes of this document, the following terms have a specific definition contained in ECSS-E-ST-20-06: electrostatic discharge (ESD) secondary arc For the