SIST EN 16603-20-07:2014
(Main)Space engineering - Electromagnetic compatibility
Space engineering - Electromagnetic compatibility
EMC policy and general system requirements are specified in ECSS-E-ST-20. This 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 “Spacecraft 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 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 verification 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.
Raumfahrttechnik - Elektromagnetische Kompabilität
Ingéniérie spatiale - Compatibilité électromagnétique
Les principes de CEM et les exigences générales applicables au système sont spécifiés dans l'ECSS-E-ST-20.
Cette norme ECSS-E-ST-20-07 spécifie les exigences détaillées applicables au système (article 4), les conditions générales d'essai, les exigences de vérifications au niveau système et les méthodes d'essai aux niveaux sous-systèmes et équipements (article 5) ainsi que les limites données à titre d'information (Annexe A).
L'ECSS-E-ST-20-06 « Charge de l'engin spatial » est associée à la présente norme. Elle traite du contrôle de la charge et des risques provenant de la charge de l'engin spatial induite par l'environnement et le véhicule, tandis que l'ECSS-E-ST-20-07 traite des effets électromagnétiques des décharges électrostatiques.
Les annexes A à C de l'ECSS-E-ST-20 documentent les activités CEM liées à l'ECSS E ST 20 07 : le plan de contrôle CEM (annexe A) définit l'approche, les méthodes, les procédures, les ressources et l'organisation ; le plan de vérification des effets électromagnétiques (annexe B) définit et spécifie les processus de vérification, les analyses et les essais, enfin le rapport de vérification des effets électromagnétiques (annexe C) documente les résultats de vérification. EMEVP et EMEVR constituent le moyen de mise en place de la présente norme.
La présente norme peut être adaptée aux caractéristiques et contraintes spécifiques d'un projet spatial conformément à l'ECSS-S-ST-00.
Vesoljska tehnika - Elektromagnetna združljivost
Politika glede elektromagnetne združljivosti in splošne sistemske zahteve so opredeljene v standardu ECSS-E-ST-20. Ta standard ECSS-E-ST-20-07 obravnava podrobne sistemske zahteve (točka 4), splošne preskusne pogoje, pogoje glede preverjanja na sistemski ravni in preskusne metode na ravni podsistemov in opreme (točka 5) ter tudi informativne omejitve (dodatek A). S tem standardom je povezan standard ECSS-E-ST-20-06 o napajanju vesoljskih plovil, ki obravnava nadzor nad polnjenjem in tveganja, ki izhajajo iz okoljskega napajanja vesoljskih plovil ter napajanja, ki ga sproži vozilo, medtem ko standard ECSS-E-ST-20-07 obravnava elektromagnetne učinke elektrostatičnih praznitev. Dodatki A do C standarda ECSS-E-ST-20 beležijo dejavnosti v zvezi z elektromagnetno združljivostjo, povezane s standardom ECSS-E-ST-20-07: načrt obvladovanja elektromagnetne združljivosti (dodatek A) določa pristop, metode, postopke, vire in organizacijo, načrt za preverjanje elektromagnetnih učinkov (dodatek B) določa in opredeljuje procese, analize in preskuse v zvezi s preverjanjem, poročilo o preverjanju elektromagnetnih učinkov (dodatek C) pa beleži rezultate preverjanja. Načrt za preverjanje elektromagnetnih učinkov in poročilo o preverjanju elektromagnetnih učinkov služita za prilagajanje tega standarda. Ta standard se lahko prilagodi posameznim lastnostim in omejitvam vesoljskega projekta v skladu s standardom ECSS-S-ST-00.
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Standards Content (Sample)
2003-01.Slovenski inštitut za standardizacijo. Razmnoževanje celote ali delov tega standarda ni dovoljeno.Vesoljska tehnika - Elektromagnetna združljivostRaumfahrttechnik - Elektromagnetische KompabilitätIngéniérie spatiale - Compatibilité électromagnétiqueSpace engineering - Electromagnetic compatibility49.140Vesoljski sistemi in operacijeSpace systems and operations33.100.01Elektromagnetna združljivost na splošnoElectromagnetic compatibility in generalICS:Ta slovenski standard je istoveten z:EN 16603-20-07:2014SIST EN 16603-20-07:2014en01-oktober-2014SIST EN 16603-20-07:2014SLOVENSKI
STANDARD
SIST EN 16603-20-07:2014
EUROPEAN STANDARD NORME EUROPÉENNE EUROPÄISCHE NORM
EN 16603-20-07
July 2014 ICS 49.140
English version
Space engineering - Electromagnetic compatibility
Ingéniérie spatiale - Compatibilité électromagnétique
Raumfahrttechnik - Elektromagnetische Kompabilität 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. 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 language 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 Austria, 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, Sweden, 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 E SIST EN 16603-20-07:2014
EN 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 system 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 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 5.1.2 Electromagnetic effects verification plan . 23 5.1.3 Electromagnetic effects verification report . 23 SIST EN 16603-20-07:2014
EN 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 General 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 demonstration 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 Intra–system electromagnetic compatibility . 38 5.3.8 Radiofrequency compatibility . 38 5.3.9 Grounding . 39 5.3.10 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 DC 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 field, 30 MHz to 18 GHz . 66 5.4.12 Susceptibility to electrostatic discharges . 71 SIST EN 16603-20-07:2014
EN 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 currents . 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, electric 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 . 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: Conducted 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 emission, 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 emission. Antenna positioning . 52 Figure 5-15: Electric field radiated emission. Multiple antenna positions . 53 SIST EN 16603-20-07:2014
EN 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 injection, 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: 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 5-28: 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 . 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 5-1: 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
SIST EN 16603-20-07:2014
EN 16603-20-07:2014 (E) 6 Foreword This document (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 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 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 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, Ireland, Italy, Latvia, Lithuania, Luxembourg, Malta, Netherlands, Norway, Poland, Portugal, Romania, Slovakia, Slovenia, Spain, Sweden, Switzerland, Turkey and the United Kingdom.” SIST EN 16603-20-07:2014
EN 16603-20-07:2014 (E) 7 Introduction Electromagnetic compatibility (EMC) of a space system or equipment 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. Natural 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 effects. 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 electrical, 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 emissions are concerned. An electromagnetic interference safety margin is defined at system critical points by comparison of noise level and susceptibility at these points. SIST EN 16603-20-07:2014
EN 16603-20-07:2014 (E) 8 1 Scope EMC policy and general system requirements are specified in ECSS-E-ST-20. This 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 “Spacecraft 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 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 verification 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.
SIST EN 16603-20-07:2014
EN 16603-20-07:2014 (E) 9 2 Normative references The following 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 encouraged 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 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 interfaces
IEC 61000-4-2 (Edition 1.2) Electromagnetic compatibility (EMC) - Part 4-2: Testing and measurement techniques - Electrostatic discharge immunity test
SIST EN 16603-20-07:2014
EN 16603-20-07:2014 (E) 10 3 Terms, definitions and abbreviated terms 3.1 Terms from other standards For the purpose of this 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 of 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 SIST EN 16603-20-07:2014
EN 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 purposes of this document, the following term has a specific definition contained in ECSS-E-ST-33-11: electro-explosive device (EED) 3.2 Terms specific to the present standard 3.2.1 ambient level level of radiated and conducted signal, and noise that exist at the specified test location and time when the equipment under test is not operating NOTE
E.g. atmospherics, interference from other sources, and circuit noise or other interference generated within the measuring set compose the “ambient level”. 3.2.2 antenna factor factor that, when properly applied to the voltage at the input terminals of the measuring instrument, yields the electric or magnetic field strength NOTE 1 This factor includes the effects of antenna effective length, mismatch, and transmission losses. NOTE 2 The electric field strength is normally expressed in V/m and the magnetic field strength in A/m or T. 3.2.3 common mode voltage voltage difference between source and receiver ground references 3.2.4 contact discharge method method of testing in which the electrode of the high-voltage test generator is held in contact with the discharge circuit, and the discharge actuated by a discharge switch SIST EN 16603-20-07:2014
EN 16603-20-07:2014 (E) 12 3.2.5 electromagnetic environmental effects impact of the electromagnetic environment upon equipment, systems, and platforms NOTE
It encompasses all electromagnetic disciplines, including electromagnetic compatibility; electromagnetic interference, electromagnetic vulnerability, hazards of electromagnetic radiation to personnel, electro-explosive devices, volatile materials, and natural phenomena effects. 3.2.6 field strength resultant of the radiation, induction and quasi-static components of the electric or magnetic field NOTE
The term “electric field strength” or “magnetic field strength” is used, according to whether the resultant, electric or magnetic field, respectively, is measured. 3.2.7 ground plane metal sheet or plate used as a common reference point for circuit returns and electrical or signal potentials 3.2.8 improper response subsystem or equipment response which can be either inadvertent or unacceptable 3.2.9 inadvertent response proper subsystem functional response (within normal range of limits) actuated by electromagnetic interference, but occurring at other than the normal operational cycle, which in turn causes improper response to the total space system 3.2.10 line impedance stabilization network (LISN) network inserted in the supply leads of an apparatus to be tested which provides, in a given frequency range, a specified source impedance for the measurement of disturbance currents and voltages and which can isolate the apparatus from the supply mains in that frequency range 3.2.11 not operating condition wherein no power is applied to the equipment 3.2.12 overshield shield surrounding a bundle or a shielded cable 3.2.13 passive intermodulation product generation of a signal at frequency f = n*f1 + m*f2 from two signals at frequencies f1 and f2, where n and m are positive or negative integers, by a passive device, usually an electrical contact SIST EN 16603-20-07:2014
EN 16603-20-07:2014 (E) 13 3.2.14 port place of access to a device or network where energy can be supplied or withdrawn, or where the device or network variables can be observed or measured 3.2.15 power quality requirements requirements which define the conducted voltage noise or impedance the power user can expect NOTE
Noise e.g. from load regulation, spikes, and sags. 3.2.16 soft magnetic material ferromagnetic material with a coercivity smaller than 100 A/m 3.2.17 spurious emission electromagnetic emission from the intended output terminal of an electronic device, but outside of the designed emission bandwidth 3.2.18 test antenna antenna of specified characteristics designated for use under specified conditions in conducting tests 3.2.19 unit equipment that is viewed as an entity for purposes of analysis, manufacturing, maintenance, or record keeping NOTE
E.g. hydraulic actuators, valves, batteries, and individual electronic boxes such as on-board computer, inertial measurement unit, reaction wheel, star tracker, power conditioning unit, transmitters, receivers, or multiplexers. 3.3 Abbreviated terms For the purpose of this standard, the abbreviated terms of ECSS-S-ST-00-01 and the following apply: Abbreviation Meaning AC alternating current ACS attitude control system AM amplitude modulation AWG American wire gauge BCI bulk cable injection CE conducted emission CS conducted susceptibility CW continuous wave DC direct current SIST EN 16603-20-07:2014
EN 16603-20-07:2014 (E) 14 EED electro-explosive device EGSE electrical ground support equipment EHF extremely high frequency (30 GHz-300 GHz) EMC electromagnetic compatibility EMCAB electromagnetic compatibility advisory board EMCCP electromagnetic compatibility control plan EMEVP electromagnetic effects verification plan EMEVR electromagnetic effects verification report EMI electromagnetic interference EMISM electromagnetic interference safety margin ESD electrostatic discharge EUT equipment under test HV high voltage ICD interface control document LEO low Earth orbit LF low frequency LISN line impedance stabilization network MGSE mechanical ground support equipment PAM pulse amplitude modulation PCM pulse coded modulation RE radiated emission RF radio frequency r.m.s. root-mean-square RS radiated susceptibility SHF super-high frequency (3 GHz-30 GHz) SIST EN 16603-20-07:2014
EN 16603-20-07:2014 (E) 15 4 Requirements 4.1 General system requirements EMC policy and general system requirements, and the spacecraft charging protection program are specified in ECSS-E-ST-20 Electromagnetic Compatibility clause and EMC Plan DRD. 4.2 Detailed system requirements 4.2.1 Overview This clause 4.2 defines the requirements for design and realization at system level. They are the basis for definition of activities of the EMC programme to ensure space-system-level compatibility with minimum impact to programme, cost, schedule, and operational capabilities. 4.2.2 EMC with the launch system 4.2.2.1 Overview General system requirements for “EMC with the launch system” are defined in ECSS-E-ST-20. 4.2.2.2 Detailed system requirements a. Overload capability of the spacecraft RF receivers during the pre-launch and launch phases with or without fairing, shall be demonstrated by the spacecraft supplier. NOTE 1 It is expected the electromagnetic environment generated by companion payloads is assessed by the launching company and addressed in the User’s Manual. NOTE 2 A conductive fairing is likely to cause resonances and cavity effects. b. Spacecraft equipment shall not exhibit any malfunction, degradation of p
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