3 Terms, definitions and abbreviated terms
3.1 Terms defined in other standards
3.2 Terms specific to the present standard
4.1 Plasma interaction effects
4.1.2 Most common engineering concerns
4.1.3 Overview of physical mechanisms
4.2 Relationship with other standards
6 Surface material requirements
6.1.1 Description and applicability
6.1.2 Purpose common to all spacecraft
6.1.3 A special case: scientific spacecraft with plasma measurement instruments
6.2.1 Maximum permitted voltage
6.3 Electrical continuity, including surfaces and structural and mechanical parts.
6.3.1 Grounding of surface metallic parts
6.3.3 Electrical continuity for surface materials
6.6 Testing of materials and assemblies
6.6.2 Material characterization tests
6.6.3 Material and assembly qualification
6.7 Scientific spacecraft with plasma measurement instruments
7.1 Description and applicability
7.3 Other exposed parts of the power system including solar array drive mechanisms
8 High voltage system requirements
9 Internal parts and materials requirements
9.2.1 Internal charging and discharge effects
9.2.2 Grounding and connectivity
9.2.3 Dielectric electric fields and voltages
10.2.1 Hazards arising on tethered spacecraft due to voltages generated by conductive tethers
10.2.2 Current collection and resulting problems
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
11 Electric propulsion requirements
11.1.2 Coverage of the requirements
11.2.1 Spacecraft neutralization
11.3.2 Computer modelling characteristics
Annex A (normative) Electrical hazard mitigation plan - DRD
Annex B (informative) Tailoring guidelines
B.2.2 LEO orbits with high inclination
B.4 Spacecraft with onboard plasma detectors
B.8 Other planetary magnetospheres
Annex C (informative) Physical background to the requirements
C.3.2 The electrostatic potential
C.3.5 Models of current through the sheath
C.3.6 Thin sheath – space-charge-limited model
C.3.7 Thick sheath – orbit motion limited (OML) model
C.3.9 Magnetic field modification of charging currents
C.4 Current collection and grounding to the plasma
C.5.4 Surface emission processes
C.5.6 Conductivity and resistivity
C.6.2 Motion across the magnetic field
C.7.2 Electric propulsion thrusters
C.7.3 Induced plasma characteristics
C.7.5 Neutral particle effects
C.7.6 Effect on floating potential
C.8 Internal and deep-dielectric charging
C.8.2 Relationship to surface charging
C.8.6 Geometric considerations
C.8.7 Isolated internal conductors
C.8.8 Electric field sensitive systems
C.9.3 Dielectric material discharge.
C.9.5 Internal dielectric discharge
C.9.6 Secondary powered discharge
Annex D (informative) Charging simulation
D.3 Environment model for internal charging
Annex E (informative) Testing and measurement.
E.2.2 Pre-testing of the solar array simulator (SAS)
E.2.3 Solar array test procedure
E.2.5 The solar panel simulation device
E.3 Measurement of conductivity and resistivity
E.3.1 Determination of intrinsic bulk conductivity by direct measurement
E.3.2 Determination of radiation-induced conductivity coefficients by direct measurement
E.3.3 Determination of conductivity and radiation-induced conductivity by electron irradiation
Figures
Figure 6‑1: Applicability of electrical continuity requirements
Figure 7‑1: Solar array test set-up
Figure C-1 : Schematic diagram of potential variation through sheath and pre-sheath.
Figure C-2 : Example secondary yield curve
Figure C-4 : Schematic diagram of void region
Figure C-5 : Schematic diagram of internal charging in a planar dielectric
Figure C-6 : Dielectric discharge mechanism.
Figure C-7 :Shape of the current in relation to discharge starting point.
Figure E-2 : Schematic diagram of power supply test circuit
Figure E-3 : Example of a measured power source switch response.
Figure E-4 : Example solar array simulator
Figure E-5 : Absolute capacitance of the satellite
Figure E-6 : Junction capacitance of a cell versus to voltage.
Figure E-7 : The shortened solar array sample and the missing capacitances
Figure E-8 : Discharging circuit oscillations
Figure E-9 : Effect of an added resistance in the discharging circuit (SAS + resistance)
Figure E-10 : Setup simulating the satellite including flashover current
Figure E-11 : Basic arrangement of apparatus for measuring dielectric conductivity in planar samples
Figure E-13 : Arrangement for carrying out conductivity tests on planar samples under irradiation
Figure E-14 : Basic experimental set up for surface conductivity
Tables
Table 4‑1: List of electrostatic and other plasma interaction effects on space systems
Table 7‑1: Tested voltage-current combinations
Table 7‑2: Typical inductance values for cables
Table C-1 : Parameters in different regions in space
Table C-2 : Typical plasma parameters for LEO and GEO
Table C-3 : Plasma conditions on exit plane of several electric propulsion thrusters
Table C-4 : Emission versus backflow current magnitudes for several electric propulsion thrusters
Table C-5 : Value of Ea for several materials