EN 16603-20-07:2014

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
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

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

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
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
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

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

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

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

Most of spacecraft equipment is not operating during launch. During the launching sequence spacecraft transmitters and receivers (platform and payload) can be either in OFF- or ON-state depending on the launch vehicle. c. The electromagnetic interference safety margin (EMISM) of safety critical equipment shall be applied to equipment in ON-state during prelaunch and launch phase and to EEDs. 4.2.3 Lightning environment 4.2.3.1 Overview Protection of the space system against both direct and indirect effects of lightning can be a combination of operational avoidance of the lightning environment and electrical overstress design techniques. 4.2.3.2 Requirements to the space system a. Assessment of risk, on the launch pad inside the protected area, for the space system and its equipment against direct and indirect effects of lightning before lift-off, shall be performed. b. The spacecraft supplier shall obtain from the launching company the electromagnetic environment imposed on the launcher payloads in case of lightning. 4.2.4 Spacecraft charging and effects
4.2.4.1 Overview Mitigation of risks related to spacecraft charging results of a combination of rules and methods preventing voltage build-up and so minimizing the occurrence of ESD, and techniques for controlling EMI from residual ESD. ECSS-E-ST-20 addresses management of spacecraft charging protection and system-level performance under effects of spacecraft charging and related ESD or secondary arcs. ECSS-E-ST-20-06 addresses charging control and risks arising from spacecraft charging and other environmental effects on the spacecraft’s electrical behaviour. SIST EN 16603-20-07:2014

Analysis or tests can be defined in the time or frequency domain. They are expected to evaluate the coupling level from the ESD source to critical points. b. EMI control from residual ESD shall be performed by a combination of shielding and passive or active filtering techniques, implemented on the main structure, at subsystem level or inside equipment. c. EMI control efficiency shall be verified by test at subsystem or equipment level. 4.2.5 Spacecraft DC magnetic emission 4.2.5.1 Spacecraft with susceptible payload a. As part of the EMCCP, a magnetic cleanliness control plan shall document: 1. magnetic control guidelines 2. emission limits to magnetic sources 3. a magnetic budget 4. specific test methods applied to equipments for emission measurement and characterization NOTE
The test method described in 5.4.5 providing a dipole model can be inadequate and replaced by a multiple dipole model or a spherical harmonics model. 4.2.5.2 Attitude control system (ACS) a. As part of the EMCCP, a magnetic budget shall be maintained providing: 1. Three-axes components of the space vehicle magnetic dipole (component decreasing with the inverse cube law with distance). NOTE
Typical values lie in the range 1 Am2 or less for small spacecraft to much more than 10 Am2 for large spacecraft. 2. If the solar array is rotating in the space vehicle axes, separate evaluation for the main body and the solar array. 3. When the space vehicle is using a magnetic sensor as part of the ACS, evaluation of the magnetic induction at its location. NOTE
The angular deviation is the basic requirement; however, the requirement is generally expressed in terms of modification of the natural field strength SIST EN 16603-20-07:2014

Recommended data is defined in Annex A for equipment and subsystems. b. control of conducted and radiated propagation paths methods defined by clauses 4.2.10 to 4.2.13. SIST EN 16603-20-07:2014

b. The EGSE shall be immune to signals used for spacecraft susceptibility tests. 4.2.10 Grounding 4.2.10.1 Overview As specified in ECSS-E-ST-20, a controlled ground reference concept is defined for the space system. Structural elements, antenna and RF reference grounds, power and signal returns, shields and cable shields, safety grounds, EGSE grounds are considered. 4.2.10.2 Requirements a. A system-level grounding diagram shall be established including the EGSE. b. A ground reference shall be identified for each power, signal, or RF source or receiver. c. An upper value of common mode voltage shall be specified considering: 1. power quality requirements defined in ECSS-E-ST-20 for “Spacecraft bus”, 2. type of detectors and sensitivity, 3. characteristics of analogue signal monitor receiver circuit, in accordance with ECSS-E-ST-50-14, Table 5-2 d, 4. characteristics of bi-level signal monitor receiver circuit, in accordance with
ECSS-E-ST-50-14, clause Table 6-2 e, 5. hazards due to fault currents internal to the space vehicle or between the space vehicle and its EGSE. d. When power and signal share common paths (wire or structure), the magnitude of ground impedance shall be limited over the affected signal spectrum. NOTE
Non-exclusive techniques for reducing the impedance are decrease of common path length, decrease of wire and ground impedance, filters on common paths. SIST EN 16603-20-07:2014

Bonding requirements for charging control are specified in ECSS-E-ST-20-06 “Electrical continuity”, including surfaces and structural and mechanical parts.
Main frame Vehicle structure Nearby structure grounding Bonding strap < 20 mΩ Vehicle-bonding attachment point Ground reference point at system level < 2,5 mΩ Equipment housing Connector =Equipment bonding stud < 10 mΩ
Figure 4-1: Bonding requirements 4.2.11.2 Normative provisions a. A vehicle bonding attachment point connected to the vehicle structure shall be provided as a ground reference point at system level. b. An equipment bonding stud connected to the unit housing shall be provided as a ground reference at equipment level. c. Each unit housing shall be bonded to the nearby spacecraft structure from the equipment bonding stud. d. The DC resistance between the equipment bonding stud and the nearby spacecraft structure shall be less than 2,5 mΩ. e. The inductance between the equipment bonding stud and the nearby spacecraft structure shall be less than 30 nH.
f. The DC resistance between the unit housing and the vehicle bonding attachment point shall be less than 20 mΩ.= g. The DC resistance between the equipment bonding stud and each connector housing shall be less than 10 . h. Bonds shall be capable to carry the fault currents determined by analysis at system level, without fusing, burning, or arcing. SIST EN 16603-20-07:2014

Charge equalization is needed prior to implementing other procedures or the application of power across the interface. 4.2.12 Shielding (excepted wires and cables) 4.2.12.1 Overview When shielding is used to control EMC with the environment, it can be provided by the basic space vehicle structure designed as a “Faraday cage”, by enclosures of electronics boxes, or by cable or bundle overshields. 4.2.12.2 Requirement a. Electronics units and cables external to the basic space vehicle structure shall have individual shields providing attenuation to EMI. NOTE
It is important to consider apertures used for pressure drop during ascent and for outgassing. 4.2.13 Wiring (including wires and cables shielding) 4.2.13.1 Classification of cables a. Categorisation of harness and separate routings for wires of different categories shall be defined as follows: 1. applicable to critical lines as defined in ECSS-E-ST-20, Clause “Electromagnetic interference safety margin”. 2. made on the basis of the characteristics of the signals on the wire (and hence the interference generated), and on the susceptibility of the circuit to EMI. b. Wires falling into one category shall be assembled into a same bundle.
c. Bundles of different categories shall be separated either by a separation distance of 5 cm from the outer circumference or by a metallic screen when they are routed on parallel paths. NOTE
Overshields or spacecraft walls can be used to fulfil the requirement. SIST EN 16603-20-07:2014

No grounding inside the equipment through a connector ground pin in order to prevent any perturbation inside the equipment. 2. Connection to electrical reference is performed through dedicated pins. NOTE
This case typically appears in the design of detection chains. e. Overshields shall be bonded to chassis ground: 1. at both ends, 2. using a 360° direct contact or a bond strap of less than 30 nH NOTE
See NOTE of clause 4.2.11.2e. f. Overshields should be bonded to chassis ground at intermediary points with a separation distance less than 1m between two grounding points. SIST EN 16603-20-07:2014

Example of RF absorber material are carbon impregnated foam pyramids, and ferrite tiles. c. The RF absorber shall be placed above, behind, and on both sides of the EUT, and behind the radiating or receiving antenna as shown in Figure 5-1. d. Minimum performance of the material shall be as specified in Table 5-1. NOTE
The manufacturer’s specification of their RF absorber material
...