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A free scan shows the junk files, broken settings and background clutter dragging Windows down - then fixes them in one click.Free scan · Windows 10 & 11Design the FPGA around the mission’s radiation environment, duration, criticality, and recovery requirements—not around a generic claim that a device is “space-grade.” For a long-duration mission, the design must account separately for configuration-memory faults, functional logic and state faults, and what the spacecraft does after detecting an error. Device evidence, fault-injection and radiation testing, and the project’s assurance baseline all belong in the design decision.
What must be decided before choosing an FPGA?
Start with mission and system requirements. A device choice or mitigation scheme cannot be justified independently of the environment and behavior the mission requires. Record the relevant orbit or trajectory, radiation environment, mission duration, design criticality, and permitted outage or recovery time. Also capture performance, power, resource limits, reconfiguration needs, and development and assurance constraints.
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Translate those inputs into observable system requirements: which faults must be detected, how long the system may operate in a degraded or safe mode, what outputs must be inhibited after a fault, and what recovery action is acceptable. These requirements give the team a basis for comparing parts and architectures rather than treating a radiation-tolerance label as a verdict.
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How does FPGA technology change the fault picture?
In an SRAM-based reprogrammable FPGA, configuration memory holds the programmed logic and routing. A single-event upset in that memory can therefore alter behavior, not merely corrupt user data. Configuration-memory upsets are a distinct concern from faults in functional data paths or state. ESA describes this distinction for reprogrammable FPGAs in its overview of FPGAs in space; NASA’s presentation on mitigation strategies for critical space applications also distinguishes antifuse, SRAM, flash, and hardened-SRAM configuration types.
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Use that technology distinction to frame a part trade, not to assume a universal ranking. Ask what the evidence for the exact device and revision covers in the mission’s environment, and whether the design can detect, contain, and recover from the fault modes that matter.
| Design choice or fault area | What to evaluate | What it does not establish by itself |
|---|---|---|
| SRAM-based reprogrammable configuration | Configuration-memory upset susceptibility, detection and correction coverage, and the system’s response to altered logic or routing. | That a scrubber restores corrupted functional state or provides complete fault tolerance. |
| Antifuse, flash, or hardened-SRAM configuration | Device-specific radiation evidence, applicable failure modes, and the design’s remaining functional-logic and state risks. | That a configuration-technology label alone proves suitability for the mission. |
| Functional logic and state | Which data-path or state faults can affect externally visible behavior, how they are detected, and how state is restored or the system is reset. | That correcting configuration memory has corrected the functional state. |
How should faults be contained and recovered from?
Analyze configuration memory and functional logic/state as separate fault domains, then trace how each could propagate to a mission-visible failure. NASA presenter Melanie Berg states the key recovery issue in the 2018 presentation: “Correcting a configuration bit does not mean that you have fixed the state in the functional logic path.” A design may need state restoration, a reset, or full device reconfiguration after configuration correction; recovery behavior must therefore be specified as part of the architecture.
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Choose mitigation techniques according to the device, architecture, upset type, and mission requirements. The options below are tools to evaluate, not automatic guarantees:
| Technique | What it can contribute | Design question to resolve |
|---|---|---|
| Logic replication and voting | Redundant logic paths and a way to compare or vote on their outputs. | Which faults are actually independent, and what happens when paths disagree? |
| Configuration scrubbing | For SRAM-configuration devices, correction of configuration-memory errors while logic is operating. | What cadence is justified by the mission radiation environment, device characteristics, and fault-tolerance analysis? |
| Upset detection or correction | Identification or correction of faults within the implemented detection and correction coverage. | Which configuration bits, logic, and state are covered, and what faults remain outside that coverage? |
| State restoration, reset, or full reconfiguration | A defined recovery route when configuration correction alone is insufficient. | Which trigger initiates recovery, how is state made valid again, and what interruption or safe-mode behavior follows? |
Scrub cadence has no generally valid numerical value in the available evidence. Derive it for the selected device and mission rather than copying a period from another design. Similarly, a mitigation is only useful at system level if detection, fault containment, and recovery lead to an acceptable operational outcome.
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How can the implemented design be evaluated?
Analyze how injected faults affect the implemented design, including whether they are detected, contained, and followed by the intended recovery sequence. ESA describes FLIPPER as a fault-injection capability that introduces SEU-like faults into user flip-flops, configuration memory, and reconfiguration control registers. It can help evaluate unprotected designs and mitigation behavior; it is not a replacement for radiation testing or mission qualification. ESA also records lessons from audits of FPGA designs on Rosetta, underscoring that review should include system and operational failure handling as well as device-level mechanisms. See ESA’s FPGA-in-space material.
Make the verification campaign traceable to requirements: identify the injected fault or test condition, expected detection, containment and recovery behavior, observed result, and any residual limitation. Include cases where configuration repair succeeds but state remains invalid, where a reset or reconfiguration is required, and where a fault is not corrected. The specific test set should follow the design’s fault analysis and assurance plan.
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What can radiation-test evidence tell you?
Use radiation evidence only within the bounds of the tested part and design context. ESA reports that damage to a critical FPGA part leads to functional failures. The same activity describes a complex space design implemented on a commercial off-the-shelf RTG4 that performed as expected under heavy-ion irradiation, with many corrected errors and very few design resets. The activity closed in 2021. These results are evidence about that part and test/design context; they do not establish another device’s lifetime reliability or qualify a different mission configuration. See ESA’s radiation-testing summary.
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What engineering and assurance evidence should the project maintain?
Assurance is part of the engineering work, not a final paperwork step. ESA identifies ECSS-E-ST-20-40C for ASIC, FPGA, and IP-core engineering and ECSS-Q-ST-60-03C for product assurance; ESA gives 11 October 2023 as the publication date for both on its microelectronics development methodology page. Confirm applicable revisions, project tailoring, and required lifecycle outputs against the current project baseline. Naming a standard does not itself demonstrate compliance.
Maintain a traceable record connecting mission requirements to design decisions and evidence. Depending on the project baseline, this may include the fault analysis, device and radiation evidence, mitigation coverage, fault-injection results, recovery requirements and tests, design reviews, and assurance approvals. Review the FPGA’s behavior in the wider spacecraft context, including how operators or other onboard systems respond to detected faults.
NASA’s SpaceCube description offers an architecture example: a NASA Goddard FPGA-based onboard hybrid science-data processing system uses commercial radiation-tolerant Xilinx Virtex FPGA technology with integrated upset detection and correction. It illustrates one system strategy; it is not a template or endorsement for every mission.
Quick Recap
How to turn the analysis into a design decision
- Define mission constraints. Record the radiation environment, trajectory or orbit, duration, criticality, permitted interruption, performance and power limits, and assurance baseline.
- Compare candidate devices against evidence. For each exact device and revision, assess configuration technology, applicable radiation data, resource and power fit, reconfiguration needs, and development constraints.
- Map fault paths. Separate configuration-memory upsets from functional logic and state faults; determine which can reach externally visible outputs or disrupt mission functions.
- Specify detection and recovery. Decide how the system detects faults and when it restores state, resets, reconfigures, enters a safe mode, or changes redundancy configuration.
- Verify the implemented response. Use analysis and fault injection to evaluate coverage and recovery behavior, and use radiation evidence appropriate to the selected part and mission.
- Close the assurance case. Trace requirements, design evidence, verification, reviews, and tailoring to the current project baseline before treating the architecture as acceptable.
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