EN 16603-20-06:2020
(Main)Space engineering - Spacecraft charging
Space engineering - Spacecraft charging
This activity will be the update of EN16603-20-06 (published 2014).
This activity was started in ECSS to implement as urgent classified Change Requests.
Raumfahrttechnik - Aufladung von Raumfahrzeugen
Ingéniérie spatiale - Charges électrostatiques des engins spatiaux
La présente norme s'inscrit dans la hiérarchie des normes ECSS. Elle est rattachée 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
General Information
Relations
Standards Content (Sample)
SLOVENSKI STANDARD
01-november-2020
Nadomešča:
SIST EN 16603-20-06:2014
Vesoljska tehnika - Napajanje vesoljskih plovil
Space engineering - Spacecraft charging
Raumfahrttechnik - Aufladung von Raumfahrzeugen
Ingéniérie spatiale - Charges électrostatique des vehicules spatiales
Ta slovenski standard je istoveten z: EN 16603-20-06:2020
ICS:
49.140 Vesoljski sistemi in operacije Space systems and
operations
2003-01.Slovenski inštitut za standardizacijo. Razmnoževanje celote ali delov tega standarda ni dovoljeno.
EUROPEAN STANDARD
EN 16603-20-06
NORME EUROPÉENNE
EUROPÄISCHE NORM
September 2020
ICS 49.140
Supersedes EN 16603-20-06:2014
English version
Space engineering - Spacecraft charging
Ingéniérie spatiale - Charges électrostatiques des Raumfahrttechnik - Teil 20-06: Aufladung von
engins spatiaux Raumfahrzeugen
This European Standard was approved by CEN on 3 May 2020.
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, France, Germany, Greece, Hungary, Iceland, Ireland, Italy,
Latvia, Lithuania, Luxembourg, Malta, Netherlands, Norway, Poland, Portugal, Republic of North Macedonia, Romania, Serbia,
Slovakia, Slovenia, Spain, Sweden, Switzerland, Turkey and United Kingdom.
CEN-CENELEC Management Centre:
Rue de la Science 23, B-1040 Brussels
© 2020 CEN/CENELEC All rights of exploitation in any form and by any means Ref. No. EN 16603-20-06:2020 E
reserved worldwide for CEN national Members and for
CENELEC Members.
Table of contents
European Forword . 9
Introduction . 11
1 Scope . 13
2 Normative references . 14
3 Terms, definitions and abbreviated terms . 15
3.1 Terms defined in other standards . 15
3.2 Terms specific to the present standard . 15
3.3 Abbreviated terms. 18
3.4 Nomenclature . 19
4 Overview . 21
4.1 Plasma interaction effects . 21
4.1.1 Presentation . 21
4.1.2 Most common engineering concerns . 21
4.1.3 Overview of physical mechanisms . 22
4.2 Relationship with other standards . 24
5 Protection programme . 26
6 Surface material requirements . 27
6.1 Overview . 27
6.1.1 Description and applicability . 27
6.1.2 Purpose common to all spacecraft . 28
6.1.3 A special case: scientific spacecraft with plasma measurement
instruments . 28
6.2 General requirements . 28
6.2.1 Maximum permitted voltage . 28
6.2.2 Maximum resistivity . 29
6.3 Electrical continuity, including surfaces and structural and mechanical parts . 29
6.3.1 Grounding of surface metallic parts . 29
6.3.2 Exceptions . 30
6.3.3 Electrical continuity for surface materials . 31
6.4 Surface charging analysis . 35
6.5 Deliberate potentials . 35
6.6 Testing of materials and assemblies . 35
6.6.1 General . 35
6.6.2 Material characterization tests . 37
6.6.3 Material and assembly qualification . 37
6.7 Scientific spacecraft with plasma measurement instruments . 38
6.8 Verification . 38
6.8.1 Grounding . 38
6.8.2 Material selection . 39
6.8.3 Environmental effects . 39
6.8.4 Computer modelling . 39
6.9 Triggering of ESD . 40
7 Secondary arc requirements . 41
7.1 Description and applicability . 41
7.2 Solar arrays . 42
7.2.1 Overview . 42
7.2.2 General requirement . 42
7.2.3 Testing of solar arrays . 43
7.3 Other exposed parts of the power system including solar array drive
mechanisms . 47
8 High voltage system requirements . 48
8.1 Description . 48
8.2 Requirements . 48
8.3 Validation . 48
9 Internal parts and materials requirements . 49
9.1 Description . 49
9.2 General . 49
9.2.1 Internal charging and discharge effects . 49
9.2.2 Grounding and connectivity . 49
9.2.3 Dielectric electric fields and voltages . 50
9.3 Validation . 51
10 Tether requirements . 55
10.1 Description . 55
10.2 General . 55
10.2.1 Hazards arising on tethered spacecraft due to voltages generated by
conductive tethers . 55
10.2.2 Current collection and resulting problems . 55
10.2.3 Hazards arising from high currents flowing through the tether and
spacecraft structures . 56
10.2.4 Continuity of insulation. . 56
10.2.5 Hazards from undesired conductive paths . 56
10.2.6 Hazards from electro-dynamic tether oscillations . 56
10.2.7 Other effects . 56
10.3 Validation . 57
11 Electric propulsion requirements . 58
11.1 Overview . 58
11.1.1 Description . 58
11.1.2 Coverage of the requirements . 58
11.2 General . 60
11.2.1 Spacecraft neutralization . 60
11.2.2 Beam neutralization . 61
11.2.3 Contamination . 62
11.2.4 Sputtering . 62
11.2.5 Neutral gas effects . 62
11.3 Validation . 63
11.3.1 Ground testing . 63
11.3.2 Computer modelling characteristics . 63
11.3.3 In-flight monitoring. 63
11.3.4 Sputtering . 63
11.3.5 Neutral gas effects . 64
Annex A (normative) Electrical hazard mitigation plan - DRD . 65
A.1 DRD identification . 65
A.1.1 Requirement identification and source document . 65
A.1.2 Purpose and objective . 65
A.2 Expected response . 65
A.2.1 Scope and content . 65
A.2.2 Special remarks . 66
Annex B (informative) Tailoring guidelines . 67
B.1 Overview . 67
B.2 LEO . 67
B.2.1 General . 67
B.2.2 LEO orbits with high inclination . 68
B.3 MEO and GEO orbits . 68
B.4 Spacecraft with onboard plasma detectors .
...
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