| DSSTKalmanModel(List, List, ParameterDriversList, PropagationType, PropagationType) |   | 85% | | 75% | 14 | 35 | 14 | 119 | 0 | 1 |
| checkDimension(int, ParameterDriversList, ParameterDriversList, ParameterDriversList) | | 24% | | 27% | 9 | 12 | 19 | 27 | 0 | 1 |
| getPhysicalMeasurementJacobian() | | 14% | | 16% | 3 | 4 | 8 | 11 | 0 | 1 |
| getPhysicalKalmanGain() | | 14% | | 16% | 3 | 4 | 8 | 11 | 0 | 1 |
| getPhysicalInnovationCovarianceMatrix() | | 15% | | 16% | 3 | 4 | 7 | 10 | 0 | 1 |
| getMeasurementMatrix() | | 84% | | 72% | 4 | 12 | 6 | 43 | 0 | 1 |
| applyDynamicOutlierFilter(EstimatedMeasurement, RealMatrix) | | 32% | | 50% | 2 | 4 | 8 | 13 | 0 | 1 |
| updateParameters() | | 79% | | 83% | 1 | 4 | 3 | 15 | 0 | 1 |
| getPhysicalEstimatedState() | | 83% | | 83% | 1 | 4 | 2 | 12 | 0 | 1 |
| getEvolution(double, RealVector, MeasurementDecorator) | | 95% | | 78% | 3 | 8 | 1 | 28 | 0 | 1 |
| getCorrectedSpacecraftStates() | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| getCorrectedMeasurement() | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| getInnovation(MeasurementDecorator, NonLinearEvolution, RealMatrix) | | 96% | | 75% | 1 | 3 | 1 | 10 | 0 | 1 |
| getErrorStateTransitionMatrix() | | 100% | | 90% | 2 | 11 | 0 | 24 | 0 | 1 |
| predictState(AbsoluteDate) | | 100% | | 83% | 1 | 4 | 0 | 10 | 0 | 1 |
| updateReferenceTrajectories(DSSTPropagator[]) | | 100% | | 100% | 0 | 2 | 0 | 9 | 0 | 1 |
| getPhysicalStateTransitionMatrix() | | 100% | | 100% | 0 | 4 | 0 | 10 | 0 | 1 |
| getPhysicalEstimatedCovarianceMatrix() | | 100% | | 100% | 0 | 3 | 0 | 7 | 0 | 1 |
| normalizeCovarianceMatrix(RealMatrix) | | 100% | | 100% | 0 | 3 | 0 | 7 | 0 | 1 |
| finalizeEstimation(ObservedMeasurement, ProcessEstimate) | | 100% | | 100% | 0 | 2 | 0 | 9 | 0 | 1 |
| getEstimatedPropagators() | | 100% | | 100% | 0 | 2 | 0 | 4 | 0 | 1 |
| filterRelevant(ObservedMeasurement, SpacecraftState[]) | | 100% | | 100% | 0 | 2 | 0 | 5 | 0 | 1 |
| getPredictedSpacecraftStates() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getCurrentMeasurementNumber() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getCurrentDate() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getPredictedMeasurement() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getEstimatedOrbitalParameters() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getEstimatedPropagationParameters() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getEstimatedMeasurementsParameters() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getEstimate() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |