| getCorrectedSpacecraftStates() |  | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| getPredictedSpacecraftStates() | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| processMeasurements(List, ExtendedKalmanFilter) |  | 89% | | n/a | 0 | 1 | 2 | 10 | 0 | 1 |
| getEvolution(double, RealVector, MeasurementDecorator) | | 97% | | 83% | 1 | 4 | 1 | 33 | 0 | 1 |
| SemiAnalyticalKalmanModel(DSSTPropagatorBuilder, CovarianceMatrixProvider, ParameterDriversList, CovarianceMatrixProvider) | | 98% | | 92% | 3 | 20 | 1 | 80 | 0 | 1 |
| getScale() | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| getMeasurementMatrix() | | 100% | | 95% | 1 | 11 | 0 | 45 | 0 | 1 |
| getErrorStateTransitionMatrix() | | 100% | | 88% | 2 | 10 | 0 | 24 | 0 | 1 |
| updateParameters() | | 100% | | 100% | 0 | 7 | 0 | 15 | 0 | 1 |
| getPhysicalEstimatedState() | | 100% | | 100% | 0 | 7 | 0 | 15 | 0 | 1 |
| computeOsculatingElements(RealVector) | | 100% | | 100% | 0 | 3 | 0 | 15 | 0 | 1 |
| finalizeEstimation(ObservedMeasurement, ProcessEstimate) | | 100% | | 50% | 1 | 2 | 0 | 15 | 0 | 1 |
| updateReferenceTrajectory(DSSTPropagator) | | 100% | | 100% | 0 | 2 | 0 | 8 | 0 | 1 |
| initializeShortPeriodicTerms(SpacecraftState) | | 100% | | 100% | 0 | 2 | 0 | 8 | 0 | 1 |
| updateShortPeriods(SpacecraftState) | | 100% | | 100% | 0 | 2 | 0 | 5 | 0 | 1 |
| getNumberSelectedOrbitalDriversValuesToEstimate() | | 100% | | 100% | 0 | 2 | 0 | 5 | 0 | 1 |
| getNumberSelectedPropagationDriversValuesToEstimate() | | 100% | | 100% | 0 | 2 | 0 | 5 | 0 | 1 |
| getNumberSelectedMeasurementDriversValuesToEstimate() | | 100% | | 100% | 0 | 2 | 0 | 5 | 0 | 1 |
| getPhysicalMeasurementJacobian() | | 100% | | 100% | 0 | 2 | 0 | 3 | 0 | 1 |
| getPhysicalKalmanGain() | | 100% | | 100% | 0 | 2 | 0 | 3 | 0 | 1 |
| getPhysicalInnovationCovarianceMatrix() | | 100% | | 100% | 0 | 2 | 0 | 3 | 0 | 1 |
| updateNominalSpacecraftState(SpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 4 | 0 | 1 |
| getPhysicalStateTransitionMatrix() | | 100% | | 100% | 0 | 2 | 0 | 2 | 0 | 1 |
| getInnovation(MeasurementDecorator, NonLinearEvolution, RealMatrix) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getPhysicalEstimatedCovarianceMatrix() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getEstimatedPropagator() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| predictFilterCorrection(RealMatrix) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| analyticalDerivativeComputations(SpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| setObserver(KalmanObserver) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getNumberSelectedOrbitalDrivers() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getNumberSelectedPropagationDrivers() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getObserver() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getEstimate() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| finalizeOperationsObservationGrid() | | 100% | | n/a | 0 | 1 | 0 | 2 | 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 |
| 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 |
| getCorrectedMeasurement() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |