SIST EN 16603-20-06:2014
(Main)Space engineering - Spacecraft charging
Space engineering - Spacecraft charging
EN 16603-20-06 is a standard within the ECSS hierarchy. It forms part of the electrical and electronic engineering discipline (ECSS-E-ST-20) of the engineering branch of the ECSS system (ECSS-E). It provides clear and consistent provisions to the application of measures to assess, in order to avoid and minimize hazardous effects arising from spacecraft charging and other environmental effects on a spacecraft’s electrical behaviour. This standard is applicable to any type of spacecraft including launchers, when above the atmosphere. Although spacecraft systems are clearly subject to electrical interactions while still on Earth (e.g. lightning and static electricity from handling), these aspects are not covered, since they are common to terrestrial systems and covered elsewhere. Instead this standard covers electrical effects occurring in space (i.e. from the ionosphere upwards). This standard may be tailored for the specific characteristic and constrains of a space project in conformance with ECSS-S-ST-00.
Raumfahrttechnik - Aufladung von Raumfahrzeugen
Ingéniérie spatiale - Charges électrostatique des vehicules spatiales
La présente norme s'inscrit dans la hiérarchie ECSS. Elle est rattaché à la discipline « génie électrique et électronique » (ECSS-E-ST-20) de la branche ingénierie du système ECSS (ECSS-E). Elle contient des dispositions claires et cohérentes relatives à l'application de mesures visant à prévenir et minimiser les effets dangereux associés à la charge électrostatique des engins spatiaux, ainsi que les autres effets environnementaux sur le comportement électrique d'un engin spatial.
Cette norme s'applique à tout type d'engin spatial, y compris les lanceurs, au-dessus de l'atmosphère terrestre.
Bien que les systèmes d'engins spatiaux soient clairement soumis à des interactions électriques lorsqu'ils sont au sol (par exemple, éclair et électricité statique pendant la manutention), ces aspects ne sont pas couverts par la présente norme puisqu'ils sont communs aux systèmes terrestres et font l'objet d'autres publications. La présente norme s'attache plus particulièrement aux effets électriques survenant dans l'espace (c'est-à-dire au-delà de l'ionosphère).
La présente norme peut être adaptée aux caractéristiques et contraintes spécifiques d'un projet spatial conformément à l'ECSS-S-ST-00.
Vesoljska tehnika - Napajanje vesoljskih plovil
Standard EN 16603-20-06 je standard v okviru hierarhije ECSS. Je del discipline električnega in elektronskega načrtovanja (ECSS-E-ST-20) veje načrtovanja sistema ECSS (ECSS-E). Zagotavlja jasne in skladne določbe za uporabo ukrepov za oceno, da bi se preprečili in čim bolj zmanjšali nevarni vplivi, ki izhajajo iz napajanja vesoljskih plovil, in drugi okoljski vplivi na električno obnašanje vesoljskega plovila. Ta standard se uporablja za vse vrste vesoljskih plovil, vključno z napravami za izstrelitev, ko so nad atmosfero. Čeprav na sisteme vesoljskih plovil, ko so še na Zemlji, seveda vplivajo električne motnje (npr. strela in statična elektrika zaradi ravnanja), ti vidiki niso obravnavani, saj so skupni zemeljskim sistemom in so obravnavani v drugih standardih. Namesto tega ta standard obravnava električne učinke, do katerih prihaja v vesolju (tj. od ionosfere navzgor). 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 - Napajanje vesoljskih plovilRaumfahrttechnik - Aufladung von RaumfahrzeugenIngéniérie spatiale - Charges électrostatique des vehicules spatialesSpace engineering - Spacecraft charging49.140Vesoljski sistemi in operacijeSpace systems and operationsICS:Ta slovenski standard je istoveten z:EN 16603-20-06:2014SIST EN 16603-20-06:2014en01-september-2014SIST EN 16603-20-06:2014SLOVENSKI
STANDARD
SIST EN 16603-20-06:2014
EUROPEAN STANDARD NORME EUROPÉENNE EUROPÄISCHE NORM
EN 16603-20-06
July 2014 ICS 49.140
English version
Space engineering - Spacecraft charging
Ingéniérie spatiale - Charges électrostatique des vehicules spatiales
Raumfahrttechnik - Aufladung von Raumfahrzeugen 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 16603-20-06:2014 E SIST EN 16603-20-06:2014
EN 16603-20-06:2014 (E) 2 Table of contents Foreword . 9 Introduction . 10 1 Scope . 12 2 Normative references . 13 3 Terms, definitions and abbreviated terms . 14 3.1 Terms defined in other standards . 14 3.2 Terms specific to the present standard . 14 3.3 Abbreviated terms. 17 4 Overview . 19 4.1 Plasma interaction effects . 19 4.1.1 Presentation . 19 4.1.2 Most common engineering concerns . 19 4.1.3 Overview of physical mechanisms . 20 4.2 Relationship with other standards . 22 5 Protection programme . 24 6 Surface material requirements . 25 6.1 Overview . 25 6.1.1 Description and applicability . 25 6.1.2 Purpose common to all spacecraft . 26 6.1.3 A special case: scientific spacecraft with plasma measurement instruments . 26 6.2 General requirements . 26 6.2.1 Maximum permitted voltage . 26 6.2.2 Maximum resistivity . 27 6.3 Electrical continuity, including surfaces and structural and mechanical parts . 27 6.3.1 Grounding of surface metallic parts . 27 6.3.2 Exceptions . 28 6.3.3 Electrical continuity for surface materials . 29 SIST EN 16603-20-06:2014
EN 16603-20-06:2014 (E) 3 6.4 Surface charging analysis . 32 6.5 Deliberate potentials . 32 6.6 Testing of materials and assemblies . 32 6.6.1 General . 32 6.6.2 Material characterization tests . 33 6.6.3 Material and assembly qualification . 34 6.7 Scientific spacecraft with plasma measurement instruments . 34 6.8 Verification . 35 6.8.1 Grounding . 35 6.8.2 Material selection . 35 6.8.3 Environmental effects . 35 6.8.4 Computer modelling . 36 6.9 Triggering of ESD . 36 7 Secondary arc requirements . 37 7.1 Description and applicability . 37 7.2 Solar arrays . 38 7.2.1 Overview . 38 7.2.2 General requirement . 38 7.2.3 Testing of solar arrays . 38 7.3 Other exposed parts of the power system including solar array drive mechanisms . 42 8 High voltage system requirements . 44 8.1 Description . 44 8.2 Requirements . 44 8.3 Validation . 44 9 Internal parts and materials requirements . 45 9.1 Description . 45 9.2 General . 45 9.2.1 Internal charging and discharge effects . 45 9.2.2 Grounding and connectivity . 45 9.2.3 Dielectric electric fields and voltages . 46 9.3 Validation . 47 10 Tether requirements . 50 10.1 Description . 50 10.2 General . 50 SIST EN 16603-20-06:2014
EN 16603-20-06:2014 (E) 4 10.2.1 Hazards arising on tethered spacecraft due to voltages generated by conductive tethers . 50 10.2.2 Current collection and resulting problems . 50 10.2.3 Hazards arising from high currents flowing through the tether and spacecraft structures . 51 10.2.4 Continuity of insulation. . 51 10.2.5 Hazards from undesired conductive paths . 51 10.2.6 Hazards from electro-dynamic tether oscillations . 51 10.2.7 Other effects . 51 10.3 Validation . 52 11 Electric propulsion requirements . 53 11.1 Overview . 53 11.1.1 Description . 53 11.1.2 Coverage of the requirements . 53 11.2 General . 55 11.2.1 Spacecraft neutralization . 55 11.2.2 Beam neutralization . 56 11.2.3 Contamination . 56 11.2.4 Sputtering . 57 11.2.5 Neutral gas effects . 57 11.3 Validation . 57 11.3.1 Ground testing . 57 11.3.2 Computer modelling characteristics . 58 11.3.3 In-flight monitoring. 58 11.3.4 Sputtering . 58 11.3.5 Neutral gas effects . 58 Annex A (normative) Electrical hazard mitigation plan - DRD . 60 A.1 DRD identification . 60 A.1.1 Requirement identification and source document . 60 A.1.2 Purpose and objective . 60 A.2 Expected response . 60 A.2.1 Scope and content . 60 A.2.2 Special remarks . 61 Annex B (informative) Tailoring guidelines . 62 B.1 Overview . 62 B.2 LEO . 62 B.2.1 General . 62 SIST EN 16603-20-06:2014
EN 16603-20-06:2014 (E) 5 B.2.2 LEO orbits with high inclination . 63 B.3 MEO and GEO orbits . 63 B.4 Spacecraft with onboard plasma detectors . 63 B.5 Tethered spacecraft . 64 B.6 Active spacecraft . 64 B.7 Solar Wind . 64 B.8 Other planetary magnetospheres . 64 Annex C (informative)
Physical background to the requirements . 65 C.1 Introduction . 65 C.2 Definition of symbols . 65 C.3 Electrostatic sheaths . 65 C.3.1 Introduction . 65 C.3.2 The electrostatic potential . 66 C.3.3 The Debye length . 66 C.3.4 Presheath . 67 C.3.5 Models of current through the sheath . 68 C.3.6 Thin sheath – space-charge-limited model . 68 C.3.7 Thick sheath – orbit motion limited (OML) model . 69 C.3.8 General case . 70 C.3.9 Magnetic field modification of charging currents . 70 C.4 Current collection and grounding to the plasma . 70 C.5 External surface charging . 71 C.5.1 Definition . 71 C.5.2 Processes . 71 C.5.3 Effects . 72 C.5.4 Surface emission processes . 72 C.5.5 Floating potential . 73 C.5.6 Conductivity and resistivity . 74 C.5.7 Time scales . 76 C.6 Spacecraft motion effects . 76 C.6.1 Wakes . 76 C.6.2 Motion across the magnetic field . 79 C.7 Induced plasmas . 80 C.7.1 Definition . 80 C.7.2 Electric propulsion thrusters . 81 C.7.3 Induced plasma characteristics . 81 C.7.4 Charge-exchange effects . 82 SIST EN 16603-20-06:2014
EN 16603-20-06:2014 (E) 6 C.7.5 Neutral particle effects . 83 C.7.6 Effect on floating potential . 83 C.8 Internal and deep-dielectric charging . 83 C.8.1 Definition . 83 C.8.2 Relationship to surface charging . 84 C.8.3 Charge deposition . 85 C.8.4 Material conductivity . 85 C.8.5 Time dependence . 88 C.8.6 Geometric considerations. 88 C.8.7 Isolated internal conductors . 89 C.8.8 Electric field sensitive systems . 89 C.9 Discharges and transients . 90 C.9.1 General definition . 90 C.9.2 Review of the process . 90 C.9.3 Dielectric material discharge. . 91 C.9.4 Metallic discharge . 93 C.9.5 Internal dielectric discharge . 94 C.9.6 Secondary powered discharge . 95 C.9.7 Discharge thresholds . 95 Annex D (informative)
Charging simulation . 97 D.1 Surface charging codes . 97 D.1.1 Introduction . 97 D.2 Internal charging codes . 99 D.2.1 DICTAT . 99 D.2.2 ESADDC . 99 D.2.3 GEANT-4 . 100 D.2.4 NOVICE . 100 D.3 Environment model for internal charging . 100 D.3.1 FLUMIC . 100 D.3.2 Worst case GEO spectrum . 100 Annex E (informative) Testing and measurement. . 101 E.1 Definition of symbols . 101 E.2 Solar array testing. 101 E.2.1 Solar cell sample . 101 E.2.2 Pre-testing of the solar array simulator (SAS) . 102 E.2.3 Solar array test procedure . 104 E.2.4 Other elements . 108 SIST EN 16603-20-06:2014
EN 16603-20-06:2014 (E) 7 E.2.5 The solar panel simulation device . 109 E.3 Measurement of conductivity and resistivity . 110 E.3.1 Determination of intrinsic bulk conductivity by direct measurement . 110 E.3.2 Determination of radiation-induced conductivity coefficients by direct measurement . 112 E.3.3 Determination of conductivity and radiation-induced conductivity by electron irradiation. 113 E.3.4 The ASTM method for measurement of surface resistivity and its adaptation for space used materials . 113 References . 115 Bibliography . 119
Figures Figure 6-1: Applicability of electrical continuity requirements . 29 Figure 7-1: Solar array test set-up . 41 Figure C-1 : Schematic diagram of potential variation through sheath and pre-sheath. . 67 Figure C-2 : Example secondary yield curve . 73 Figure C-3 : Schematic diagram of wake structure around an object at relative motion with respect to a plasma . 77 Figure C-4 : Schematic diagram of void region . 78 Figure C-5 : Schematic diagram of internal charging in a planar dielectric . 84 Figure C-6 : Dielectric discharge mechanism. . 92 Figure C-7 :Shape of the current in relation to discharge starting point. . 92 Figure C-8 : Example of discharge on pierced aluminized Teflon® irradiated by electrons with energies ranging from 0 to 220 keV. . 93 Figure C-9 : Schematic diagram of discharge at a triple point in the inverted voltage gradient configuration with potential contours indicated by colour scale. . 94 Figure E-1 : Photograph of solar cells sample – Front face & Rear face (Stentor Sample. Picture from Denis Payan - CNES®). 102 Figure E-2 : Schematic diagram of power supply test circuit . 103 Figure E-3 : Example of a measured power source switch response . 103 Figure E-4 : Example solar array simulator . 104 Figure E-5 : Absolute capacitance of the satellite . 105 Figure E-6 : Junction capacitance of a cell versus to voltage . 107 Figure E-7 : The shortened solar array sample and the missing capacitances . 108 Figure E-8 : Discharging circuit oscillations . 109 Figure E-9 : Effect of an added resistance in the discharging circuit (SAS + resistance) . 109 Figure E-10 : Setup simulating the satellite including flashover current . 110 SIST EN 16603-20-06:2014
EN 16603-20-06:2014 (E) 8 Figure E-11 : Basic arrangement of apparatus for measuring dielectric conductivity in planar samples . 111 Figure E-12 : Arrangement for measuring cable dielectric conductivity and cross-section through co-axial cable . 111 Figure E-13 : Arrangement for carrying out conductivity tests on planar samples under irradiation . 112 Figure E-14 : Basic experimental set up for surface conductivity . 114
Tables Table 4-1: List of electrostatic and other plasma interaction effects on space systems . 21 Table 7-1: Tested voltage-current combinations . 38 Table 7-2: Typical inductance values for cables . 42 Table C-1 : Parameters in different regions in space . 67 Table C-2 : Typical plasma parameters for LEO and GEO . 78 Table C-3 : Plasma conditions on exit plane of several electric propulsion thrusters . 82 Table C-4 : Emission versus backflow current magnitudes for several electric propulsion thrusters . 82 Table C-5 : Value of Ea for several materials . 86
SIST EN 16603-20-06:2014
EN 16603-20-06:2014 (E) 9 Foreword This document (EN 16603-20-06:2014) has been prepared by Technical Committee CEN/CLC/TC 5 “Space”, the secretariat of which is held by DIN. This standard (EN 16603-20-06:2014) originates from ECSS-E-ST-20-06C. 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 16603-20-06:2014
EN 16603-20-06:2014 (E) 10 Introduction The subject of spacecraft plasma interactions has been part of the spacecraft design process since spacecraft surface charging was first encountered as a problem in the earliest geostationary spacecraft. However, spacecraft surface charging is only one of the ways in which the space environment can adversely affect the electrical state of spacecraft and satellite technology has evolved over the years.
A need was identified for a standard that is up to date and comprehensive in its treatment of all the main environment-induced plasma and charging processes that can affect the performance of
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