NASA Spacecraft Reliability Engine
This system analyzes spacecraft reliability and telemetry anomalies.
Reliability Simulation
Expected Failures
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Observed Failures
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Failure Rate
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Simulation Accuracy
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Anomaly Assessment
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Failure Attribution
V2 uses Bayesian inference to estimate the possible cause of a failure.
P(C|E) = P(E|C)P(C) / P(E)
Confusion Matrix
No simulation data yet.
Attribution Performance
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Simulation Details
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Analysis Summary
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Limitations
- V1 uses simulated system failures.
- V2 depends on the probability assumptions used for the simulated causes.
- The result is probabilistic and does not directly diagnose physical hardware.
NASA Telemetry Analysis
Precision
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Recall
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F1 Score
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Anomalies
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Threshold
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Persistence
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Telemetry Result
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Detection Details
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Performance
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Analysis Summary
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Limitations
- Telemetry can contain different types of anomalies.
- Model performance can change between telemetry channels.
- Threshold and persistence are calibrated from validation experiments.
- Anomaly detection does not confirm a physical hardware failure.