This standard 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\u2019s 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.<\/p>\n
| PDF Pages<\/th>\n | PDF Title<\/th>\n<\/tr>\n | ||||||
|---|---|---|---|---|---|---|---|
| 14<\/td>\n | 1 Scope <\/td>\n<\/tr>\n | ||||||
| 15<\/td>\n | 2 Normative references <\/td>\n<\/tr>\n | ||||||
| 16<\/td>\n | 3 Terms, definitions and abbreviated terms 3.1 Terms defined in other standards 3.2 Terms specific to the present standard <\/td>\n<\/tr>\n | ||||||
| 19<\/td>\n | 3.3 Abbreviated terms <\/td>\n<\/tr>\n | ||||||
| 21<\/td>\n | 4 Overview 4.1 Plasma interaction effects 4.1.1 Presentation 4.1.2 Most common engineering concerns <\/td>\n<\/tr>\n | ||||||
| 22<\/td>\n | 4.1.3 Overview of physical mechanisms <\/td>\n<\/tr>\n | ||||||
| 24<\/td>\n | 4.2 Relationship with other standards <\/td>\n<\/tr>\n | ||||||
| 26<\/td>\n | 5 Protection programme <\/td>\n<\/tr>\n | ||||||
| 27<\/td>\n | 6 Surface material requirements 6.1 Overview 6.1.1 Description and applicability <\/td>\n<\/tr>\n | ||||||
| 28<\/td>\n | 6.1.2 Purpose common to all spacecraft 6.1.3 A special case: scientific spacecraft with plasma measurement instruments 6.2 General requirements 6.2.1 Maximum permitted voltage <\/td>\n<\/tr>\n | ||||||
| 29<\/td>\n | 6.2.2 Maximum resistivity 6.3 Electrical continuity, including surfaces and structural and mechanical parts 6.3.1 Grounding of surface metallic parts <\/td>\n<\/tr>\n | ||||||
| 30<\/td>\n | 6.3.2 Exceptions <\/td>\n<\/tr>\n | ||||||
| 31<\/td>\n | 6.3.3 Electrical continuity for surface materials 6.3.3.1 Applicability <\/td>\n<\/tr>\n | ||||||
| 32<\/td>\n | 6.3.3.2 General 6.3.3.3 Blankets 6.3.3.4 Material assemblies 6.3.3.5 Conductive coatings 6.3.3.6 Dielectric materials <\/td>\n<\/tr>\n | ||||||
| 34<\/td>\n | 6.4 Surface charging analysis 6.5 Deliberate potentials 6.6 Testing of materials and assemblies 6.6.1 General <\/td>\n<\/tr>\n | ||||||
| 35<\/td>\n | 6.6.2 Material characterization tests <\/td>\n<\/tr>\n | ||||||
| 36<\/td>\n | 6.6.3 Material and assembly qualification 6.7 Scientific spacecraft with plasma measurement instruments <\/td>\n<\/tr>\n | ||||||
| 37<\/td>\n | 6.8 Verification 6.8.1 Grounding 6.8.2 Material selection 6.8.3 Environmental effects <\/td>\n<\/tr>\n | ||||||
| 38<\/td>\n | 6.8.4 Computer modelling 6.9 Triggering of ESD <\/td>\n<\/tr>\n | ||||||
| 39<\/td>\n | 7 Secondary arc requirements 7.1 Description and applicability <\/td>\n<\/tr>\n | ||||||
| 40<\/td>\n | 7.2 Solar arrays 7.2.1 Overview 7.2.2 General requirement 7.2.3 Testing of solar arrays 7.2.3.1 General <\/td>\n<\/tr>\n | ||||||
| 41<\/td>\n | 7.2.3.2 Test characteristics: <\/td>\n<\/tr>\n | ||||||
| 44<\/td>\n | 7.2.3.3 Test criteria 7.3 Other exposed parts of the power system including solar array drive mechanisms <\/td>\n<\/tr>\n | ||||||
| 46<\/td>\n | 8 High voltage system requirements 8.1 Description 8.2 Requirements 8.3 Validation <\/td>\n<\/tr>\n | ||||||
| 47<\/td>\n | 9 Internal parts and materials requirements 9.1 Description 9.2 General 9.2.1 Internal charging and discharge effects 9.2.2 Grounding and connectivity <\/td>\n<\/tr>\n | ||||||
| 48<\/td>\n | 9.2.3 Dielectric electric fields and voltages <\/td>\n<\/tr>\n | ||||||
| 49<\/td>\n | 9.3 Validation <\/td>\n<\/tr>\n | ||||||
| 52<\/td>\n | 10 Tether requirements 10.1 Description 10.2 General 10.2.1 Hazards arising on tethered spacecraft due to voltages generated by conductive tethers 10.2.2 Current collection and resulting problems <\/td>\n<\/tr>\n | ||||||
| 53<\/td>\n | 10.2.3 Hazards arising from high currents flowing through the tether and spacecraft structures 10.2.4 Continuity of insulation. 10.2.5 Hazards from undesired conductive paths 10.2.6 Hazards from electro-dynamic tether oscillations 10.2.7 Other effects <\/td>\n<\/tr>\n | ||||||
| 54<\/td>\n | 10.3 Validation <\/td>\n<\/tr>\n | ||||||
| 55<\/td>\n | 11 Electric propulsion requirements 11.1 Overview 11.1.1 Description 11.1.2 Coverage of the requirements <\/td>\n<\/tr>\n | ||||||
| 57<\/td>\n | 11.2 General 11.2.1 Spacecraft neutralization <\/td>\n<\/tr>\n | ||||||
| 58<\/td>\n | 11.2.2 Beam neutralization 11.2.3 Contamination <\/td>\n<\/tr>\n | ||||||
| 59<\/td>\n | 11.2.4 Sputtering 11.2.5 Neutral gas effects 11.3 Validation 11.3.1 Ground testing <\/td>\n<\/tr>\n | ||||||
| 60<\/td>\n | 11.3.2 Computer modelling characteristics 11.3.3 In-flight monitoring 11.3.4 Sputtering 11.3.5 Neutral gas effects <\/td>\n<\/tr>\n<\/table>\n","protected":false},"excerpt":{"rendered":" Space engineering. Spacecraft charging<\/b><\/p>\n |