Satellite EMC Testing Trends and Validation Strategies

1.1 Why EMC Is Directly Linked to Mission Reliability in Satellite Systems

A satellite is a system in which communications equipment, power conversion devices, attitude control devices, sensors, and scientific payloads operate together within a confined space. Each device operates at different frequencies and signal levels, but they share power supplies, wiring, and structures or are installed in close proximity. Therefore, even when individual devices function normally, electromagnetic interference (EMI) between devices in the integrated configuration can affect mission execution.

Interference does not occur solely through electromagnetic waves radiated through space. Harnesses consisting of power and signal lines, common grounding paths, and electrical connections between structures and equipment can also serve as paths through which interference energy is transmitted. In particular, even small amounts of interference can affect signal detection or measurement in sensitive receivers and scientific payloads. Therefore, the magnitude of the interference source must be examined together with the coupling path and the susceptibility characteristics of the affected equipment.

The NASA SWOT case demonstrates the need for this system-level approach. In an environment where high-power transmitters and sensitive receivers were installed on the same satellite, researchers evaluated compatibility between equipment through RF coupling analysis and testing. SMAP likewise established mission-specific radiated emissions requirements to protect L-band scientific observations and conducted design and test activities that included harness shielding and equipment packaging. These cases demonstrate that satellite EMC requirements must originate from the mission performance to be protected, as well as general equipment compliance.

Therefore, a satellite’s electromagnetic compatibility (EMC) is difficult to determine simply by compiling equipment-level test results. It is necessary to identify which interference sources are active in actual operating modes, through which paths they affect other equipment, and whether those effects remain within the allowable limits for mission performance.

1.2 EMC Verification from Design Through System Testing

Satellite EMC verification begins before a completed satellite is measured in a test chamber. First, the performance to be protected must be defined based on communications performance, payload measurement sensitivity, transmit and receive frequencies, and operational scenarios. These must then be translated into verifiable requirements, such as radiated and conducted emissions limits, susceptibility test conditions, and allowable levels of interference between equipment.

These requirements are incorporated into the design and development process through an EMC Control Plan. The scope of control includes grounding and bonding, harness classification and routing, shielding and shield termination, equipment interfaces, and frequency operating conditions. Solar Orbiter literature also presents strategies for translating scientific observation requirements into EMC requirements and linking equipment-level design control with system-level verification.

Verification proceeds through the unit, subsystem, and integrated spacecraft levels. At the unit and subsystem stages, major emissions sources and susceptibility characteristics are identified, and the effectiveness of design improvements is confirmed. At the integration stage, self-compatibility—whether the equipment inside the satellite can operate without interfering with one another’s functions—is evaluated by reflecting the actual harnesses, equipment arrangement, and major operating modes. In the Flying Laptop case, transmitter intermodulation products and the system’s electromagnetic susceptibility were examined using the integrated satellite.

When physical testing cannot adequately reproduce the actual flight configuration, analysis and measurement must be linked. As in the SWOT case, modeling major coupling paths and comparing them with measurement results can help evaluate differences between the test and flight configurations. The model’s scope of application, assumptions, and level of agreement with measurements must also be managed.

EMC verification is thus a process of maintaining the connection between requirements and test results. When equipment, software, harnesses, or grounding configurations change during development, their effects on existing verification results must be reviewed, and the necessary scope of analysis and testing must be reassessed.

1.3 Test Infrastructure Determines the Reliability of Verification Results

Satellite EMC test infrastructure needs to provide not only space that accommodates the size of the test object but also an environment in which the required signal levels can be measured and satellite functions verified during testing. To achieve this, teams first define the test object, frequency range, emissions limits, electromagnetic field levels to be applied, and operating conditions. The shielding environment, absorbers, antennas, RF instruments, and associated interfaces are then configured accordingly.

Particularly when measuring low-level emissions, signals entering from outside the satellite have to be distinguished from noise generated by the test system itself. Ground Support Equipment (GSE), power supplies, control equipment, and connecting cables can affect measurements. Solar Orbiter literature also discusses the effects of the ground-test noise floor and electrical ground support equipment on verification. Therefore, background noise and GSE effects should be checked before testing, and it must be determined whether sufficient measurement margin is available to evaluate the required limits.

The reproducibility of the test configuration is also important. Changes in antenna position and polarization, harness routing, shield termination, grounding and bonding conditions, and satellite operating modes can alter interference coupling conditions. These physical and electrical configurations must be recorded together with instrument settings and calibration information so that measurement results can be interpreted and compared with subsequent tests. Automation may be used to improve the consistency of repeated measurements and records, with its scope determined by the test objectives and operational constraints.

Susceptibility testing also requires the satellite’s condition to be observed while electromagnetic fields are applied. Telemetry, communications status, payload outputs, and function-specific acceptance criteria must be linked to test procedures to identify temporary performance degradation or abnormal operation. Monitoring equipment should likewise be positioned and connected after reviewing its effects on the test environment.

Reliable satellite EMC test infrastructure is a verification system that connects the measurement environment, satellite operation, functional monitoring, and configuration records. Test results must retain not only measurement values but also the conditions under which those results were obtained, the acceptance criteria, and the scope of application.

The purpose of satellite EMC verification is to confirm the compliance of individual devices and to demonstrate that they maintain the performance required for the mission once integrated.

Satellite EMC verification must examine interactions within the integrated system in addition to the emissions and susceptibility characteristics of individual devices. Limited installation space, sensitive scientific payloads, high-power transmitters, and complex deployable structures create conditions that are difficult to evaluate through equipment-level testing alone. Accordingly, a verification strategy is needed that defines mission-specific requirements and connects analysis and testing while considering the actual operational configuration.

2.1 Increasing Potential for Interference Between Electronic Systems in Confined Spaces

Satellite harnesses connect multiple subsystems by carrying power, commands, and measurement data. At the same time, they can serve as coupling paths through which electromagnetic interference generated by one device is transmitted to another. When power and signal lines are routed close together or multiple devices share a common electrical path, changes in one device’s operation can affect another device’s input or reference potential.

Coupling through harnesses occurs in several forms. Between adjacent wires, wire-to-wire coupling can occur through parasitic capacitance and mutual inductance. Surrounding electromagnetic fields can cause field-to-wire coupling, inducing voltages or currents in cables. Common impedance coupling can also occur when multiple circuits share the impedance of a power return or grounding path.

ISRO literature on spacecraft harness design explains that the electrical distribution system serves both as a functional interface between subsystems and as a major path for interference transmission. Accordingly, harness design must manage routing and separation, grounding and bonding, and shielding continuity together.

Shielding is likewise not completed simply by applying a metallic shield layer to a cable. The characteristics of the shielding path extending through connectors and backshells to the equipment enclosure affect overall performance. ESA-related harness research demonstrates that shielding design involves trade-offs that consider mass and implementation constraints alongside EMI suppression.

Therefore, equipment arrangement and wiring are difficult to address separately in EMC design for highly integrated satellites. The relationships between interference sources, coupling paths, and sensitive circuits must first be identified and then reflected in the harness configuration and interface design.

2.2 Mission-Specific EMC Required by Sensitive Payloads

Scientific and observation satellites have different EMC requirements depending on the signals their payloads must detect and the allowable measurement errors. Even when communications or control functions remain normal, noise generated inside the satellite can affect scientific data quality if it enters the observation band. Therefore, passing general equipment-level tests and meeting mission performance requirements should be evaluated separately.

NASA SMAP illustrates the importance of these mission-specific EMC requirements. Because SMAP’s L-band radiometer observes weak natural emissions, radiated noise generated by the spacecraft itself had to be strictly controlled. The related literature addresses mission-specific radiated emissions requirements that are more stringent than the general MIL-STD-461 RE102 limits to protect the observation band, and describes harness shielding, equipment packaging, and staged testing to meet them.

The important point is not to apply the limits from one mission directly to another satellite. The requirements for a given mission must be derived from the receive band and sensitivity of the protected equipment, the characteristics of interference signals, coupling between antennas and equipment, and allowable performance degradation. Test conditions, including measurement bandwidth and detector type, also need to be defined so that emissions limits can be interpreted consistently.

For Solar Orbiter, magnetic cleanliness and electrostatic environment control were important considerations alongside electromagnetic emissions control. Because its payloads observe particles and electromagnetic fields, a strategy was presented for managing the effects of the platform and other payloads on the observation environment from the early stages of development.

Satellite EMC requirements thus vary according to the mission and payload characteristics. Test infrastructure should also be configured to evaluate the observation bands to be protected and the required detection levels, beyond simply covering a general frequency range.

2.3 Coexistence of High-Power Transmitters and Sensitive Receivers

When radar, data transmission transmitters, and sensitive receivers are installed on the same satellite, the paths through which transmitted energy reaches other equipment must be evaluated. Even when transmitters and receivers have different center frequencies, interference can remain possible through out-of-band emissions, harmonics, receiver out-of-band susceptibility, or nonlinear responses.

NASA SWOT is a case in which a high-power Ka-band radar operates alongside multiple RF devices. The related research performed high-fidelity RF coupling analysis that considered antennas and spacecraft structures and linked the results to testing and equipment-specific susceptibility requirements. Self-compatibility was also evaluated by examining transmitter out-of-band emissions and coupling to receiving equipment.

In such an environment, interference risk is difficult to assess from transmitter power alone. Antenna radiation patterns, distances and orientations between devices, shielding and scattering by structures, reflector arrangement, and receiver characteristics all contribute. In particular, the applicability of simple distance-based calculations must be examined under near-field conditions or in the presence of complex structures.

Verification needs to connect equipment-level test results to actual operational combinations. Conditions in which transmitters operate individually should be distinguished from those in which multiple devices operate together, while functional acceptance indicators such as reception status and payload outputs should also be observed.

Therefore, the criteria for verifying the coexistence of high-power transmitters and sensitive receivers must include, in addition to the compliance of individual devices, whether reception performance and mission functions remain within allowable limits in actual operational combinations.

2.4 Complex Satellite Structures That Are Difficult to Verify Through Testing Alone

It may be difficult to fully reproduce a satellite’s flight configuration in ground testing. Large deployable antennas and reflectors may be constrained by test facility space, while gravity loads and support fixtures may make it difficult to reproduce the on-orbit arrangement. Power, control, and measurement connections needed on the ground can also create electrical paths that differ from those in flight.

These differences affect the scope of application of EMC test results. Changes in antenna or reflector positions can alter electromagnetic field distributions and coupling between devices. Differences in harness routing and grounding configurations can also change interference transmission paths. Therefore, when results obtained in a test configuration are applied to the flight configuration, those differences must be explainable.

The SWOT study identified test conditions that could not reproduce the actual flight configuration and evaluated the associated effects by linking RF modeling and measurements. This approach supplements the limitations of physical testing with analysis while examining the relationship between the model and actual measurements.

Analysis and testing provide different forms of evidence. Analysis can be used to determine the scope of testing and identify high-risk combinations, while measurements confirm the response of actual hardware and provide a basis for reviewing the model. When the results differ, the causes must be narrowed down by examining input conditions, test configurations, and model assumptions.

Ultimately, EMC verification of complex satellites must assess the sufficiency of verification coverage as well as whether tests were performed. By separately recording conditions directly verified, conditions supplemented by analysis, and remaining uncertainties, verification results can be used to assess mission reliability.

Changes in satellite EMC testing involve both an increase in measurement items and the need to connect design, analysis, and testing around mission requirements and actual operational configurations.

Not all electromagnetic energy generated inside a satellite leads to functional abnormalities. For interference to become a problem, an energy-generating source, a coupling path that transmits the energy, and affected equipment or circuitry have to be connected. The actual performance impact is then determined by the frequency, magnitude, and duration of the interference, together with the susceptibility characteristics and operating state of the receiving equipment.

Therefore, satellite EMC verification needs to compare emissions levels with test limits while also identifying how interference is transmitted and which functions it affects. Understanding this relationship allows effective measures to be selected from source suppression, transmission path improvement, and receiver protection, and enables test results to be connected to mission risk.

3.1 Source – Coupling Path – Victim

Electromagnetic interference can be analyzed through the relationship between the source, coupling path, and victim equipment or circuit. Sources include power conversion devices, digital circuits, RF transmitters, and switching loads. The energy they generate can be transmitted to other equipment through power and signal wiring, common return paths, structures, or space.

Even the same interference source can have different effects depending on the coupling path and the characteristics of the receiving equipment. For example, noise of the same magnitude can cause problems if it reaches a sensitive analog input or receiver front end, while remaining at an acceptable level at an interface with sufficient filtering and interference margin. Therefore, system risk is difficult to assess from source emissions magnitude alone.

Spacecraft harness design literature explains that the electrical distribution system is both a functional interface connecting multiple subsystems and a major path for transmitting interference. This is why EMC analysis must examine wiring and connection structures together with the characteristics of the equipment itself.

The purpose of this analysis extends beyond listing possible sources of interference. It is to identify which relationships affect mission performance and to define test conditions and acceptance criteria that can verify those relationships.

3.2 Radiated Emission and Radiated Susceptibility

Radiated Emission (RE) evaluates electromagnetic energy radiated into space from equipment and wiring. For satellites, the possibility that these emissions may enter another device’s receive band or couple into sensitive circuitry should be examined. Emissions measurements needs to control equipment operating modes, measurement positions, antenna polarization, and measurement bandwidth, together with frequency-specific levels.

Radiated Susceptibility (RS) evaluates whether equipment or system performance remains within allowable limits when a specified electromagnetic field is applied. During testing, the functions to be protected—including communications errors, sensor output changes, control states, and payload data should be observed in addition to whether satellite power is maintained. Criteria for normal operation must be defined before testing.

The two items are related but provide different information. Radiated emissions testing is used to characterize the environment created by interference sources, while radiated susceptibility testing determines the level a device can withstand in a specified environment. Assessing actual self-compatibility requires consideration of both coupling from the source to the victim equipment and the susceptibility characteristics of the receiving equipment.

The SWOT study evaluated the electromagnetic environment at different locations inside the satellite based on RF coupling analysis and linked it to equipment radiated susceptibility test requirements. This methodology examines actual arrangements and coupling conditions rather than assuming that the same electromagnetic field exists at every location.

Therefore, radiated test results need to be interpreted together with the locations, operating states, and scope of functional assessment represented by the results, in addition to measurement values or applied levels.

3.3 Conducted Emission and Cable Coupling

Conducted Emission (CE) evaluates unwanted voltages or currents transmitted through electrical connections such as power lines. Inside a satellite, noise from power conversion devices and switching loads can enter the power distribution network or affect the reference potential of other equipment through common return paths.

Cable Coupling includes a broader range of transmission phenomena. Capacitive and inductive coupling between wires and induction by external electromagnetic fields can also generate interference voltages or currents in cables. A conducted emissions result therefore does not verify every harness coupling issue.

Transmission characteristics vary with cable type and length, wire spacing, parallel routing lengths, shielding, and termination conditions. The arrangement of signal and return lines is also important. Designers route the circuit so that current returns through the intended path, and testing confirms that the path holds. Harness design literature addresses these wiring, grounding, and shielding conditions as major control items in system EMC design.

The Flying Laptop conducted emissions tests compared results with and without the satellite battery connected. The literature reports lower power-line emissions when the battery was connected. This case demonstrates that power configuration and connection conditions can affect measurement results; it does not mean that the same effect is guaranteed for other satellites.

Verifying conducted interference means recording the power configuration, load state, harness arrangement, and termination conditions, along with measurement locations and instrument conditions. Teams manage differences between the test and flight configurations together with the scope of application of the results.

3.4 Grounding and Bonding

Grounding defines the reference potential and current return paths of circuits. In a satellite, grounding is a matter of establishing electrical relationships between circuit references, power returns, and structures rather than connection to the Earth. Bonding establishes intended electrical connections between structures, equipment enclosures, and connection points.

When a grounding path has finite impedance, changes in current produce voltage differences. If sensitive signal circuits and noise currents share the same path, these voltage differences can be transmitted as interference. When multiple connection paths are formed, the possibility of unintended circulating currents or coupling must also be examined.

Bonding requires consideration of impedance at the frequencies of interest, as well as connection resistance. Even when low DC resistance is achieved, high-frequency performance can vary because of inductance associated with connection length and geometry. Therefore, connection surface condition, fastening structure, strap geometry, and actual assembly condition must be managed together. Literature on spacecraft assembly and electrical protection also explains the need to examine grounding design in connection with its implementation during assembly.

The grounding method follows signal characteristics, frequency, structures, and interface configurations. Rather than uniformly applying single-point or multipoint grounding to all circuits, the roles of power returns, signal references, enclosures, and shields must be distinguished in the design. Research on multicable shield grounding also presents an approach that analyzes coupling characteristics under different grounding conditions and confirms them experimentally.

Verification confirms whether the connections specified in the design match those in the actual hardware. It also examines the effects of additional grounding paths introduced by test GSE or instrument connections.

3.5 Harness Shielding and Shield Termination

Harness shielding reduces the coupling of external electromagnetic fields into internal conductors or the radiation of internal signals to the outside. Shielding performance depends not only on the material and structure of the shielding layer but also on the characteristics of the entire assembly extending through connectors and backshells to the equipment enclosure. Even when the cable itself performs well, overall performance can be limited if shielding continuity is interrupted at terminations or interfaces.

Shield Termination is the method used to connect the shielding layer to a connector or enclosure. Because high-frequency impedance can vary with connection length, geometry, and contact condition, the termination method must be selected considering the frequencies of interest and assembly conditions. Shield connections must also be checked after cable replacement or connector reassembly.

ESA-related harness research distinguishes between Transfer Impedance and Shielding Effectiveness when evaluating shielding performance. Transfer impedance describes the relationship between current flowing in the shield and the voltage induced in the internal circuit, while shielding effectiveness describes the reduction in an electromagnetic field or induced signal produced by shielding under specified conditions. Evaluation methods need to be selected considering their applicable frequency ranges and the effects of the test configuration.

Shielding design needs to consider mass, flexibility, ease of assembly, and maintenance conditions alongside performance improvement. Defining the required performance and identifying the contribution of each component makes it possible to meet requirements while reducing excessive additions of shielding.

3.6 Payload Self-Compatibility

Self-Compatibility means that equipment inside a satellite does not interfere with one another’s required performance when operating together. Verification covers interactions between payloads, as well as interference between payloads and the satellite bus, between transmitters and receivers, and between power and control devices.

Self-compatibility testing must define combinations of simultaneous operations that are possible during the actual mission. Transmitter operation, payload observation, power load changes, and control device operation need to be considered, and potentially affected functions must be observed under each condition. Examining reception status, errors, sensor outputs, and scientific data changes together with emissions spectra helps establish the relationship between interference and functional effects.

In the Flying Laptop case, analysis of transmitter intermodulation products and examination of GPS–S-band interference were performed separately. The intermodulation test examined unwanted components both near the transmitted signals and in frequency regions farther away. In a separate antenna pretest, researchers evaluated whether signals from the closely positioned S-band downlink antenna could drive the amplifier behind the GPS antenna into compression. The literature reports that sufficient margin was available under the tested conditions to prevent saturation of the GPS amplifier.

These two tests must be interpreted separately. A test evaluating unwanted transmitter components and a test evaluating the effects of strong signals entering a receiver front end address different interference mechanisms. Therefore, this case must not be described as one in which an intermodulation problem between GPS and S-band was discovered.

The final assessment of self-compatibility must retain both the operational combinations tested and the conditions not verified. Even if test results are satisfactory, the validity of existing results needs to be reviewed when equipment arrangements, transmission conditions, harnesses, or software operating methods change.

Satellite EMC verification connects source emissions, transmission paths, and receiver responses and confirms whether the results remain within allowable limits for mission performance.

The reliability of satellite EMC testing depends not only on whether test items have been performed, but also on how appropriately mission requirements have been implemented as test conditions and how effectively variables affecting the results have been controlled. Particularly for satellites with sensitive payloads and complex harnesses, test facilities, ground support equipment, and measurement connections can themselves alter the electromagnetic environment of the verification target.

Therefore, the measurability of requirements, representativeness of the flight configuration, measurement sensitivity and dynamic range, GSE effects, and test configuration traceability must be examined together from the test planning stage.

4.1 Translating Mission Requirements into Testable EMC Requirements

Mission requirements are expressed as functional objectives such as observation accuracy, communications quality, positioning performance, or control stability. To apply them to EMC testing, it is necessary to analyze which interference affects that performance and to define allowable interference levels and verification methods.

For example, protecting a sensitive receiver requires examination of its receive frequency and bandwidth, allowable performance degradation, susceptibility characteristics, and coupling to interference sources. Equipment-specific emissions limits and susceptibility test conditions must then be established, together with functional acceptance criteria to be checked in the integrated configuration. Limits need to specify not only frequency ranges and units but also measurement bandwidth, detector type, measurement position, and operating conditions.

Solar Orbiter’s EMC strategy describes the translation of scientific observation requirements into engineering EMC requirements as a major task in early development. SMAP likewise incorporated mission-specific radiated emissions requirements into design and testing to protect L-band observations. Both cases demonstrate the need to define the performance to be protected first and then translate it into equipment and system verification conditions.

In practice, verification methods such as testing, analysis, and inspection must be assigned to each requirement, with acceptance criteria linked to the necessary evidence. For requirements that are difficult to measure directly, the combination of analysis and partial testing needs to be determined in advance to reduce verification gaps.

4.2 Reproducing the Flight Configuration in the Test Environment

Flight Configuration includes not only the equipment list but also equipment arrangement, harness routing, shield termination, grounding and bonding conditions, and software operating conditions. Because changes to any of these can alter source characteristics or coupling paths, the representativeness of the test configuration must be confirmed.

Ground testing introduces external power and control cables, support fixtures, and measurement connections needed to operate the satellite. Space for deployable structures and gravity conditions may also make it difficult to reproduce the same geometry as in flight. Therefore, when differences are unavoidable, the changes need to be identified and their effects on verification results evaluated.

The SWOT study addressed limitations in reproducing the flight configuration, including deployable antennas, and evaluated the associated effects by linking high-fidelity RF analysis and measurements. In other words, this approach goes beyond recording differences in test configuration by establishing verification evidence to compensate for them.

Before testing, it is useful to prepare a list comparing the flight and test configurations. Linking each difference to potentially affected requirements, supplementary analyses or tests, and the scope of application of the results enables a clear basis for judgment to be presented during final verification.

4.3 Measuring Sensitive Signals and Achieving High Dynamic Range

The lower the emissions limits required to protect sensitive payloads, the smaller the signals the measurement system must be able to distinguish. In actual measurements, however, external signals, receiver noise, cable leakage, and GSE emissions can be observed together. Therefore, it must be determined whether measured signals originate from the satellite, and sufficient sensitivity needs to be secured to assess the required limits.

A low Noise Floor and a wide Dynamic Range need to be examined separately. Even with a low noise floor, strong transmitted signals can drive a receiver or preamplifier into compression and distort the measurement of weak signals. The possibility that overload or nonlinear responses inside an instrument may produce components that do not actually exist in the satellite must also be managed.

Solar Orbiter literature discusses achievable ground-test noise levels and the effects of electrical ground support equipment on measurements. The SWOT study also describes situations in which the measurement noise floor limited the range of results that could be confirmed. These cases demonstrate the need to confirm the measurement capability achieved in the actual test configuration, in addition to the instruments’ nominal specifications.

Filters, attenuators, and preamplifiers may be combined as needed, but the effects of each component on sensitivity and overload margin must be evaluated together. When measurement bandwidth is changed, the resulting change in noise level and consistency with the test requirements also need to be checked.

If a measurement is obscured by the noise floor, it must not be interpreted as the absence of emissions. The relationship between the detection limit under the relevant settings and the required limit must be presented. If a determination is difficult, the measurement configuration needs to be improved or supplementary verification performed.

4.4 GSE Becoming a New EMI Source

Ground Support Equipment (GSE) supplies power to the satellite and manages commands, telemetry, and test status. At the same time, switching power supplies, digital communications, and connecting cables can generate unwanted electromagnetic energy or create new coupling paths.

GSE effects extend beyond its own emissions. External power and communications connections can change the satellite’s return current paths and common-mode conditions. Therefore, even when equipment is moved outside the chamber, effects through cables and penetrations may remain. Shielding, filters, and isolation interfaces must be examined together with power and signal requirements and the satellite’s grounding design.

SWOT test procedures include activities to examine the effects of GSE connected to the payload. This demonstrates the need to understand how the test support configuration affects measurement results before evaluating satellite emissions.

Where possible, it is useful to measure the facility background, GSE operating state, and satellite operating state separately. However, disconnecting the satellite can change the GSE load and operating state, so the extent to which GSE-only measurements represent actual test conditions also needs to be assessed.

When the source of an observed signal is unclear, the cause needs to be narrowed down by controlling equipment activation sequences, operating modes, and connection conditions. These background measurements are used as evidence for identifying interference sources and must not be used as a basis for arbitrary subtraction from measured values.

4.5 Verifying Complex Harness Grounding Conditions

In a multicable environment, the shield grounding condition of one cable can affect coupling with other cables or equipment. This is because equipment enclosures, common structures, and signal return paths act together with the locations and methods of shield connection.

Therefore, neither single-point nor both-end grounding can be assumed to be superior in every situation. The phenomena of interest—such as potential differences and circulating currents at low frequencies, and termination impedance and shielding continuity at high frequencies—must be distinguished and evaluated according to the frequency and interface conditions of the relevant circuit.

Research on multicable shield grounding optimization analyzed coupling characteristics under different grounding conditions and verified them experimentally by applying the approach to a spaceborne scanning mirror drive and control system. Rather than applying the results of a specific configuration to every satellite, this study can be used as an example of a method for evaluating grounding conditions according to actual cable connections.

The performance of a cable alone must also be distinguished from that of a harness assembly including connectors and backshells. ESA-related research addresses methods for evaluating shields and terminations together and identifying the contributions of individual components. This supports the need to include actual assembly conditions within the scope of shield grounding verification.

In practice, it is necessary first to confirm whether the designed grounding conditions have been implemented in the actual hardware and then to verify high-risk cable combinations through analysis and measurement. After improvements, other affected interfaces and operating conditions also need to be examined to confirm the validity of the changes.

4.6 Ensuring Test Repeatability and Configuration Traceability

Test repeatability is the degree to which similar results can be obtained under the same conditions. Configuration Traceability is the ability to identify the hardware, software, wiring, and measurement conditions under which each result was obtained. Both must be secured to determine whether differences between tests are caused by design changes or changes in measurement conditions.

In satellite EMC testing, antenna position and polarization, harness routing, grounding connections, DUT operating modes, and GSE states can affect results. Therefore, storing frequency-specific measurement values alone makes it difficult to reproduce the same conditions in subsequent testing. Photographs, layout drawings, connection diagrams, and equipment settings need to be managed in connection with measurement data.

The following items provide a practical management approach for designing test configuration records.

Automation can be used to reduce omissions in records and variations in repetitive tasks by linking equipment settings, operating modes, and measurement data. However, physical changes such as cable movement or connection reassembly must be checked and recorded separately.

After retesting or design changes, differences from the previous configuration need to be examined first. Even if results improve, the improvement cannot immediately be attributed to the design change if operating modes or measurement conditions have also changed. The final report must retain the test configuration, differences from the flight configuration, and the scope of application of the results, together with pass or fail status.

Reliable satellite EMC test results must retain not only measurement values but also the conditions under which they were obtained and the basis for assessing compliance with mission requirements.

Satellite EMC test infrastructure needs to be designed as an interconnected combination of shielded space, RF instruments, satellite operating equipment, and a data management system. Each component has to secure measurement sensitivity and test levels while supporting observation of DUT functions and reproduction of the conditions under which results were obtained.

This chapter presents a reference configuration for designing a satellite EMC test environment. The actual scope of implementation depends on whether the test object is equipment, a payload, or an integrated satellite, as well as the applicable requirements and operational constraints. The same chamber type or positioning equipment is not required for every test, and the need for each component needs to be linked to the verification objectives.

A Shielded Chamber suppresses the entry of external RF signals and the leakage of electromagnetic energy generated during testing. To measure low-level emissions or apply specified electromagnetic fields, the necessary shielding performance and background noise levels have to be achieved at the frequencies of interest.

Shielding performance is affected not only by walls but also by doors, ventilation openings, cable penetrations, and joints. Because power, control, and communications connections cross the chamber boundary, appropriate filters and feedthroughs need to be examined for the signal characteristics and power conditions of each connection. When optical communications interfaces are used, the emissions and power connections of internal converters also have to be checked.

Chamber dimensions need to be determined based on the entire test arrangement in addition to the satellite body’s external dimensions. The distance between the antenna and the test object, absorbers, support fixtures, harness and GSE arrangements, and working space all have to be included. Flying Laptop EMC testing was also performed in an anechoic shielded environment that suppressed external interference.

The suitability of the shielding environment needs to be checked against both installation specifications and actual test conditions. It has to be verified that the required background environment is maintained after the penetrations and support equipment used for testing are connected.

Inside a shielded chamber, electromagnetic fields reflected from walls and structures can affect measurement results. Absorbers are used to reduce these reflections at the frequencies of interest. The configuration of an anechoic or semi-anechoic environment needs to be determined according to the applicable test method, ground plane requirements, frequencies, and DUT geometry.

Absorber types and arrangements have to be selected considering operating frequencies, reflection characteristics, incidence angles, and power handling capability. Tests that operate high-power transmitters also need to examine the local power incident on absorbers and their thermal conditions. The SWOT study addresses test operations that considered absorber temperature increases and the possibility of damage during high-power RF testing.

The Working Volume needs to be distinguished from the space in which the satellite can physically fit. This is because the required measurement or applied electromagnetic field conditions have to be achievable within that volume. Antenna positions, test distances and polarization, support structures, and cable arrangements need to be examined together.

Installing absorbers alone does not guarantee sufficient reflection suppression or low measurement uncertainty at all frequencies. The usable range has to be defined through environmental checks and measurement system verification appropriate to the applicable test procedures.

The RF measurement system is configured by distinguishing between emissions measurement and susceptibility testing. For emissions measurement, antennas, cables, filters and preamplifiers where needed, and a receiver or spectrum analyzer form a measurement path. For susceptibility testing, signal generators, amplifiers, power monitoring devices, and antennas are connected to establish the required electromagnetic field.

Even when individual devices cover sufficient frequency ranges, it needs to be confirmed that the performance of the entire path meets the test requirements. Cable and switch losses, filter transfer characteristics, amplifier linearity, and antenna characteristics affect the final measurement values and applied levels.

Before testing, correction values and valid ranges have to be confirmed for each path actually used. When cables or switching paths are changed, the continued applicability of existing correction values should be reviewed.

This RF system alone cannot perform every EMC test item. Additional tests, including conducted emissions and susceptibility tests, require current probes, coupling devices, and power interfaces appropriate to the applicable methods to be configured separately.

The position and orientation of the Device Under Test (DUT) are part of the measurement conditions. The positioning system establishes distance, orientation, and polarization relationships between the antenna and DUT and repeatedly provides the required measurement positions.

For satellite testing, the use of a turntable needs to be determined considering mass, center of gravity, support conditions, and harness connections. If rotation applies tension to cables or changes grounding and return paths, it can affect measurement conditions and hardware condition. In some cases, fixing the satellite in place and moving the antenna or probe may be more appropriate.

Positioning equipment and support structures can also affect the electromagnetic environment, so their materials, geometry, drive emissions, and wiring must be examined. After movement, reference points and measurement distances need to be checked, and layout photographs and coordinates stored as needed.

The purpose of this system lies in consistently establishing and reproducing the required measurement geometry, rather than in rotation or movement itself.

Ground Support Equipment (GSE) supports satellite power, commands, telemetry, and operating modes. It needs to be configured to maintain the functions required during testing while preventing its own emissions or connection paths from interfering with measurements.

The arrangement has to distinguish between equipment needed inside the chamber and equipment that can be operated outside it. Even externally installed equipment can introduce noise or additional return paths through connecting cables, so the path through chamber penetrations to satellite interfaces needs to be examined.

SWOT test procedures include activities to examine the effects of GSE connected to the payload. Solar Orbiter literature also addresses the effects of electrical GSE and the ground-test noise environment on verification.

Therefore, the GSE configuration needs to include equipment lists and connection diagrams, power and grounding methods, operating software, and background measurement results. When GSE is changed or connections are added, the effects on the measurement environment and satellite operation have to be reviewed.

The monitoring system observes satellite status during testing and acquires the data needed for functional assessment. Particularly during susceptibility testing, it must be possible to identify temporary errors, performance degradation, and recovery while electromagnetic fields are applied.

Monitoring items are derived from mission and test requirements. They may include power voltage and current, communications status, error counters, reset history, and sensor and payload outputs. Cameras provide supplementary observation of physical conditions and need to be used together with telemetry or functional data.

Linking the frequency, level, and application timing of the test signal to the timestamps of satellite status data makes it easier to trace the conditions under which anomalies occurred. Data collection intervals and event recording methods have to be set considering the duration of the phenomena to be detected.

The monitoring equipment’s own emissions and susceptibility also should be checked. The system has to be configured to distinguish whether an observed error originated in the DUT or resulted from disruption of monitoring equipment or communications connections.

Grounding and harness interfaces define the electrical relationships between the satellite, GSE, and test facility. Circuit references, power returns, structural bonding, cable shields, and facility protective earth need to be distinguished, and the purpose of each connection clarified.

Test ground planes and grounding straps are configured according to the applicable procedures and verification objectives. Connecting all equipment to facility ground must not be assumed to represent the satellite’s actual electrical conditions. The return paths and coupling effects introduced by additional connections must be examined.

For harnesses, routing and separation, shield termination, connectors and backshells, and connections through to equipment enclosures need to be managed. ESA-related research explains that shielding continuity has to extend beyond cables to connectors and equipment interfaces.

Connections need to be checked before testing, and paths introduced by additional measurement or monitoring cables also have to be recorded. If a change occurs during testing, its timing needs to be linked to the data and reflected in the interpretation of results.

Test automation can be used to control frequency sweeps, instrument settings, antenna positions, and DUT operating modes according to defined procedures. The data acquisition system links and stores RF measurements, satellite status, and test events.

The scope of automation is determined by equipment control interfaces and test complexity. Even when starting with simple repeated measurements, settings and actual equipment status must be checked, and the handling of data during errors or communications interruptions has to be defined. Susceptibility test procedures also need to include stepwise level application and stop conditions when anomalies occur.

When automated comparison is applied, consistency between measurement units, correction values, bandwidth, and applicable limits should be checked. Items requiring manual review of monitoring data need to be recorded separately from automated judgments.

Automation programs and test scripts are also subject to configuration management. Versions and configuration files need to be linked to results, and raw data have to be stored separately from corrected and processed data to enable subsequent review and reanalysis.

The test report should present requirement-specific results and the basis for acceptance. Each result has to be linked to the DUT configuration, operating mode, and instrument settings under which it was obtained, and changes and anomalies during testing need to be traceable.

The following records can be used when designing a reporting and configuration management system.

The final assessment has to distinguish between requirements that have been met and items requiring further review. If measurement sensitivity or test configuration imposes limitations, the scope of application of the results and supplementary evidence need to be presented together.

These records remain useful after design changes. They provide a basis for comparing existing tests with changed configurations, determining the need for retesting, and confirming the range over which verification results remain valid.

Satellite EMC test infrastructure must to be designed to demonstrate compliance with requirements by connecting the measurement environment, satellite operation and functional monitoring, and configuration records.

Satellite EMC verification is a process of defining mission requirements, managing interference risks through design and analysis, and confirming compliance through staged testing. The results of each stage must serve as inputs to the next. When testing or design changes provide new information, earlier analyses and verification plans also need to be updated.

This chapter organizes these activities into six stages. Each Validation Gate provides criteria to be checked before proceeding to the next activity and is further specified and applied according to the project’s development schedule and verification responsibilities.

First, define the mission performance to be protected and the expected electromagnetic environment. Major inputs include payload measurement sensitivity, transmit and receive frequencies and bandwidths, transmit power, receiver characteristics, operating modes, and simultaneous operational combinations. Environments during mission phases such as launch preparation, launch, and orbital operation should also be examined according to the scope of application.

Based on these inputs, establish allowable interference levels and functional degradation criteria, then translate them into radiated and conducted emissions limits and susceptibility test conditions. Requirements must also specify the conditions needed for assessment, including frequency ranges, measurement units, bandwidth, detector type, and test configurations.

Solar Orbiter’s EMC strategy addresses the translation of scientific observation requirements into engineering EMC requirements. SMAP likewise incorporated mission-specific emissions requirements into design and testing to protect sensitive L-band observations.

Validation Gate: Confirm that each requirement is linked to the protected target, applicable conditions, acceptance criteria, and verification method.

Main Deliverables: EMC requirements specification, operating mode matrix, and requirement-specific verification matrix.

The EMC Control Plan is a document that connects requirements to design, manufacturing, integration, and test activities. It defines grounding and bonding, harness classification and routing, shielding and shield termination, power and signal interfaces, and frequency operating conditions as control items.

The plan should include responsible organizations, review milestones, change approval, and nonconformance handling procedures alongside technical rules. Interface requirements and verification responsibilities must be clearly allocated so that equipment suppliers and the system integration organization do not design to different criteria.

The Satellite EMI/ESD Control Plan literature describes a management framework that connects design rules, EMC analysis, and testing throughout development. This approach can be used to manage the actual implementation of design rules together with verification evidence.

Validation Gate: Confirm that design rules and responsibilities for major interfaces are defined and that changes and exceptions can be traced.

Main Deliverables: EMC Control Plan, grounding and bonding concept diagram, harness classification and routing rules, frequency plan, and interface requirements.

During analysis, establish the relationships between interference sources, coupling paths, and victim equipment. Identify high-risk combinations involving high-power transmitters and sensitive receivers, antennas and structures, and power and signal harnesses.

Select analysis methods according to the phenomena being investigated. Interference budgets and circuit or transmission-line models can be used for initial reviews, while detailed electromagnetic models may be considered when complex antenna arrangements or structural scattering are important. Input data accuracy, model assumptions, and applicable frequency and configuration ranges should be recorded together.

The SWOT study used high-fidelity RF coupling analysis to evaluate compatibility between equipment and link the results to test requirements. This case demonstrates an approach for defining major risks and necessary verification conditions during development through analysis.

Analysis results are reflected in design improvements and test priorities. Combinations with small predicted margins or high input uncertainty must be designated for additional characterization measurements or partial testing.

Validation Gate: Confirm that major interference paths have been identified and that design measures and test plans are established for high-risk combinations.

Main Deliverables: Coupling analysis results, interference budgets, risk lists, model assumption and input records, and priority verification items.

At the unit and subsystem stages, emissions and susceptibility characteristics, power and signal interfaces, and shielding performance are examined. Measurements are used to assess equipment compliance, supplement system analysis inputs, and determine observation items for integrated testing.

Tests must reflect representative operating modes and load states, power and return configurations, and cable termination conditions. If actual flight harnesses or loads cannot be used, the characteristics and limitations of the simulated configuration must be recorded. After design improvements, the problem items and affected related conditions need to be rechecked.

In the SMAP case, emissions suppression measures involving harnesses and equipment packaging were verified through subsystem- and spacecraft-level testing. This connects pre-integration characterization and improvement activities to system verification.

Validation Gate: Confirm that nonconformances and uncertainties that may affect integration have been identified and that completion of corrective actions or follow-up verification plans has been approved.

Main Deliverables: Unit and subsystem test results, interface characteristic data, improvement records, updated analysis models, and residual risk lists.

Integrated testing configures flight hardware, harnesses, and payloads and reproduces major operating modes to evaluate system-level requirements and self-compatibility. Before testing, a configuration baseline must be established, and differences from the flight configuration and their effects need to be identified.

Test items and their sequence are defined in the mission-specific verification plan. Emissions measurements, susceptibility tests, interference between transmitters and receivers, and simultaneous operation verification are arranged according to requirements, with the functions to be checked and data collection methods defined for each condition.

The Flying Laptop case combined emissions measurements and susceptibility assessments of the integrated satellite with examination of potential interference between GPS and S-band antennas in a separate configuration. This demonstrates an approach that combines system testing with testing of specific coupling paths.

If an anomaly occurs during testing, the frequency, level, operating mode, and functional data at that time must be preserved. The effects of the DUT, GSE, and measurement system must then be distinguished, and retest conditions defined.

Validation Gate: Confirm that execution of the planned tests and their results are linked to requirements, and that assessments of anomalies and test configuration differences are retained.

Main Deliverables: Integrated EMC test report, raw and functional data, configuration records, and anomaly and retest records.

Final verification compares analysis and measurements under matched conditions and evaluates whether the model sufficiently explains major coupling characteristics. Comparison targets may include frequency-dependent trends, resonance characteristics, coupling levels, and functional effects. Acceptable agreement criteria must be defined according to the analysis objectives and the margin needed for judgment.

When results differ, geometry, materials, boundary conditions, cable and termination configurations, input signals, and measurement uncertainty should be examined. If the model is revised, the basis for the changes and comparison results must be recorded, and its applicable range redefined.

The SWOT study supplemented verification of a complex configuration by linking RF analysis and measurements. When applying this approach, separate uncertainties and limitations must also be stated for predictions extending beyond the range confirmed by measurement.

Finally, requirement-specific evidence is reviewed to determine compliance. Items that are unmet or lack sufficient evidence must be classified for additional testing or analysis, design changes, or formal exception handling, and the judgment of the person responsible for verification must be retained.

Validation Gate: Confirm that all applicable requirements are linked to a basis for judgment and that outstanding items and the scope of application of the results have been reviewed and approved.

Main Deliverables: Analysis–measurement comparison report, final verification matrix, and residual risk and exception records.

Validation Roadmap

Building test infrastructure is a process of translating verification targets and requirements into facility, measurement, and operational designs. Initially, representative DUT configurations and required performance are defined. Spatial arrangements, electrical connections, measurement paths, and data management systems are then developed in detail.

These items are difficult to determine independently. Test distance affects chamber dimensions and amplifier output, while GSE connections can change shielding penetrations and grounding configurations. Therefore, related items should be reviewed together when designs change.

First, define whether the test object is individual equipment, a payload or subsystem, or an integrated satellite. Then identify its assembly and deployment conditions during testing, operating modes, required harnesses and GSE, and support fixtures.

Space calculations must include antenna arrangements, measurement distances, cable paths, and working and maintenance space in addition to DUT dimensions. Mass, center of gravity, floor loads, access routes, and handling methods should also be examined. If deployable structures are simulated or only partially installed, the representativeness of that configuration and supplementary verification methods must be established.

Design Verification Criteria: Layouts and handling conditions must be defined for representative test configurations, and the required working volume must be explainable.

Main Deliverables: DUT definition document, representative test configuration drawings, dimensional and load conditions table, and access and handling plan.

The test frequency range is determined from mission transmit and receive bands, protected targets, expected interference sources, and applicable test requirements. Emissions testing must specify limits and required measurement sensitivity, while susceptibility testing needs to specify applied levels and relevant conditions such as modulation and duration.

The measurement system must be configured to meet the required performance at each frequency. Susceptibility testing requires calculation of the necessary output considering antenna characteristics, test distance, and cable losses, while emissions measurement requires joint examination of the noise floor and overload margin.

Design Verification Criteria: Measurement and application paths must be defined for each requirement, with evidence that target performance can be achieved.

Main Deliverables: Frequency and level requirements table, RF path diagram, output and sensitivity calculations, and equipment selection criteria.

The chamber layout includes the DUT, antennas, absorbers, and support structures. Measurement distances, positions, and polarization required by the applicable test procedures must be secured, and the space occupied by cables and GSE should be checked for each arrangement.

For large satellites, a decision needs to be made on whether to rotate the DUT or move the antenna. This requires examination of harness tension, changes in grounding connections, and positioning reproducibility in addition to the mechanical movement range. If high-power testing is included, absorber power handling conditions must also be incorporated. The SWOT case likewise considered thermal effects on absorbers during high-power testing.

Design Verification Criteria: Required geometry and working space must be secured in representative test arrangements, and constraints associated with movement, deployment, and power conditions must be manageable.

Main Deliverables: Chamber layout drawings, antenna position table, working volume definition, and positioning and support structure requirements.

Define the relationships between power returns, signal references, structural bonding, cable shields, and facility protective earth in drawings. Examine the ground planes and straps required by the applicable tests, and identify paths introduced by GSE and instrument connections.

Connections must be evaluated for their characteristics at the frequencies of interest in addition to DC continuity. Check whether test connections bypass the satellite’s actual return paths or create unintended loops. Methods for inspecting connections and the scope of rechecking after changes should also be established.

Design Verification Criteria: The purpose and verification method of each grounding and bonding connection must be defined, and differences between test and flight configurations identified.

Main Deliverables: Grounding and bonding drawings, connection lists, connection inspection procedures, and configuration difference assessments.

Classify power, RF, control, and monitoring cables and specify each cable’s route, termination, and penetration location. Distinguish sensitive signals from wiring with high interference potential and reflect separation and shielding conditions in the layout.

Penetrations must satisfy both shielding performance and signal transmission requirements. When filters are applied, rated voltage and current, insertion loss, and signal integrity need to be examined. Shielded cables must also be checked to ensure that shield connections are properly maintained at penetrations and connectors. Harness shielding research explains the importance of the complete connection, including cables, connectors, and backshells.

Design Verification Criteria: The functions and electrical conditions of all penetrating connections must be identified, and leakage, coupling, and signal transmission effects examined.

Main Deliverables: Cable lists and routing drawings, penetration schedule, and the basis for filter and feedthrough selection.

Divide GSE and monitoring equipment into equipment that must be installed inside and equipment that can be operated outside. Determine their arrangement by considering cable lengths, signal quality, equipment accessibility, and electromagnetic effects together.

For internal equipment, examine its own emissions and susceptibility, shielding, and power configuration. External equipment can also have effects through penetrating cables, so the entire connection path needs to be checked. Monitoring items must be linked to requirement-specific acceptance criteria, and the system configured to distinguish DUT anomalies from measurement or communications anomalies.

Design Verification Criteria: GSE effects and the background environment must be verified under representative operating conditions, and the required functional data must be obtainable.

Main Deliverables: GSE and monitoring equipment layout, connection diagrams, monitoring item and acceptance criteria table, and background verification procedures.

Check instrument calibration status and prepare correction information that includes the actual cables, switching paths, and amplifiers used. Confirm that antenna factors and path losses are applied appropriately for the relevant settings and frequencies.

Calibration characterizes instruments and does not replace system checks immediately before testing. Measurement paths must be verified using known signals or appropriate check procedures to identify connection errors, component damage, overload, and setting errors. Background noise for emissions measurements and applied conditions for susceptibility testing must also be checked according to the applicable methods.

Design Verification Criteria: Valid calibration and correction information and system check results must be available, and the target limits must be evaluable.

Main Deliverables: Calibration and correction lists, path-specific correction data, pretest check records, and measurement capability and uncertainty assessments.

Automation design defines the equipment to be controlled, settings and measurement data to be recorded, DUT status, and events. Link test conditions and functional data by time, and establish procedures for handling communications interruptions and anomalies.

Automated comparison against limits requires procedures to check consistency in units, bandwidth, corrections, and detector conditions. Distinguish items that can be judged automatically from those requiring functional data review, and define responsibility and approval procedures for final acceptance.

Store raw values, corrected and processed values, and reported results separately. Manage versions of test scripts, configuration files, and applicable limits together, and ensure that the configuration and processing used for each result can be traced.

Design Verification Criteria: Representative testing must confirm the connection between setting, acquisition, storage, assessment, and reporting, and enable error recovery and data reprocessing.

Main Deliverables: Automation functional specification, data structure and naming rules, version and backup policies, and integrated operation verification records.

The criteria for building satellite EMC test infrastructure include the range of equipment available and the ability to verify defined requirements in representative configurations and trace the supporting evidence.

Satellite EMC verification is a development activity that protects mission performance. Mission requirements must be translated into measurable EMC requirements, reflected in grounding, bonding, harness, and shielding designs, and verified through analysis and staged testing. By verifying self-compatibility in actual operational combinations alongside the compliance of individual devices, test results can be connected to assessments of mission reliability.

The cases examined in this white paper demonstrate the need for this approach. SMAP illustrates the importance of mission-specific emissions control to protect sensitive observation bands, while SWOT presents a method for evaluating complex RF coupling through analysis and testing. Solar Orbiter’s EMC strategy demonstrates the connection between scientific requirements and design and verification activities, while Flying Laptop demonstrates the use of integrated spacecraft testing and examination of specific interference paths. The requirement levels and test conditions in each case must be interpreted within the context of that mission.

Test infrastructure must likewise be configured to support this verification process. Shielding and absorber environments and RF measurement systems provide the necessary measurement capability, while GSE and monitoring systems support satellite operation and the identification of functional changes. Positioning, automation, and configuration management are means of improving the reproducibility of test conditions and the traceability of results. Their actual scope of application must be determined according to the test object and requirements.

Final verification must present the test configuration, differences from the flight configuration, the scope of analysis applicability, and remaining uncertainties, together with measurement values and pass or fail status. This evidence must be linked to each requirement so that the validity of existing results and the need for additional verification can be assessed after design changes.

The value of satellite EMC test infrastructure lies in its ability to verify mission requirements in representative configurations and to reproduce and trace the basis for those judgments.

This appendix provides reference materials for verification planning and test infrastructure design. Test items, facility configurations, and acceptance criteria must be specified according to the project’s applicable requirements and approved verification plan.

Appendix A. Satellite EMC Verification Flow

This flow is iterative. When a new interference path is identified during testing or the design changes, the relevant analysis and test scope must be updated. Analysis–measurement comparisons can also be performed during partial testing and equipment characterization, as well as at the final stage.

Appendix B. Major EMC Test and Verification Items

These items include testing at different levels as well as analysis and inspection. They do not mean that every item must be performed in the same configuration or at the integrated spacecraft level. For ESD, ground handling and space charging environments must also be distinguished when determining applicable requirements and verification methods.

Appendix C. EMC Test Infrastructure Checklist

Appendix D. Major Standards and References

MIL-STD-464 presents requirements and verification criteria for system-level Electromagnetic Environmental Effects (E3). MIL-STD-461 addresses requirements and verification methods for the electromagnetic interference emissions and susceptibility characteristics of equipment and subsystems.

The requirements, test items, and limits applied to actual satellite EMC testing must be determined according to the standard revisions specified in the contract, mission-specific EMC requirements, and approved test procedures.

Appendix E. Terminology

Appendix F. Research References

1. Chahat, N. E., Gonzales, E., Decrossas, E., Stevens, A., Keyawa, M., & Narvaez, P. S. (2025). EMI-EMC qualification of the NASA SWOT mission using high fidelity modeling. IEEE Journal of Microwaves, 5(1), 116–129.
   https://doi.org/10.1109/JMW.2024.3522819
2. Dayashankara, K. S., Hariharan, V. K., Rao, M. N., Rajan, G. V. C., & Bokil, A. A. (1997). EMC considerations in spacecraft harness design. In Proceedings of International Symposium on Electromagnetic Compatibility (pp. 239–242). IEEE.
   https://ieeexplore.ieee.org/document/617132
3. Gong, Z., Du, H., Wu, W., Chen, K., Tian, J., Ji, C., Sun, D., & Liu, Y. (2023). Shielding grounding optimization method for spaceborne multi-cable. Applied Sciences, 13(6), Article 3389.
   https://doi.org/10.3390/app13063389
4. Hariharan, V. K., Murthy, P. V. N., Damodaran, A., Ghatpande, N. D., Danabalan, T. L., & Katti, V. R. (2008). Satellite EMI/ESD control plan. In 2008 10th International Conference on Electromagnetic Interference & Compatibility (INCEMIC) (pp. 501–507). IEEE.
   https://ieeexplore.ieee.org/document/5154340
5. Huang, C.-C. N., Ghaneh, A., & Comandur, S. (2016). Electromagnetic compatibility design, implementation and test of the SMAP spacecraft to meet stringent L-band radiated emissions requirements. In 2016 IEEE International Symposium on Electromagnetic Compatibility (EMC) (pp. 13–18). IEEE.
   https://doi.org/10.1109/ISEMC.2016.7571568
6. Junge, A., Wolf, J., Mora, N., Rachidi, F., & Pelissou, P. (2014). Electromagnetic interference control techniques for spacecraft harness. In Proceedings of the 2014 International Symposium on Electromagnetic Compatibility (EMC'14/Tokyo) (pp. 840–843). IEICE.
   https://doi.org/10.34385/proc.18.16P2-S1
7. Lengowski, M., Steinmetz, F., Bucher, N., Klemich, K., Lützner, M., Klinkner, S., Mikulz, E., Babben, S., Eickhoff, J., Stiehle, H., & Jean, C. (2015). Environmental flight acceptance tests of the small Earth observation satellite Flying Laptop. In Proceedings of the 29th Annual AIAA/USU Conference on Small Satellites (Paper SSC15-P-43).
   https://digitalcommons.usu.edu/smallsat/2015/all2015/93/
8. Pudney, M., King, S., Horbury, T., Maksimovic, M., Owen, C. J., & Laget, P. (2019). Solar Orbiter strategies for EMC control and verification. In 2019 ESA Workshop on Aerospace EMC (Aerospace EMC) (pp. 1–6). IEEE.
   https://doi.org/10.23919/AeroEMC.2019.8788930
9. U.S. Department of Defense. (1997). Electromagnetic environmental effects requirements for systems (MIL-STD-464).
10. Xu, B., Fang, Z., Zhang, B., Lv, J., & Liu, Y. (2018). Electromagnetic isolation and electrical protection in spacecraft general assembly. MATEC Web of Conferences, 173, Article 01037.
    https://doi.org/10.1051/matecconf/201817301037