| updateParameters() |   | 61% | | 66% | 2 | 4 | 4 | 12 | 0 | 1 |
| SemiAnalyticalUnscentedKalmanModel(DSSTPropagatorBuilder, CovarianceMatrixProvider, ParameterDriversList, CovarianceMatrixProvider) | | 93% | | 81% | 4 | 12 | 3 | 60 | 0 | 1 |
| getProcessNoiseMatrix(double, RealVector, MeasurementDecorator) | | 77% | | 50% | 1 | 2 | 2 | 12 | 0 | 1 |
| getEvolution(double, RealVector[], MeasurementDecorator) | | 92% | | 83% | 1 | 4 | 1 | 13 | 0 | 1 |
| getPhysicalEstimatedState() | | 100% | | 100% | 0 | 4 | 0 | 12 | 0 | 1 |
| getPredictedMeasurements(RealVector[], MeasurementDecorator) | | 100% | | 100% | 0 | 2 | 0 | 9 | 0 | 1 |
| finalizeEstimation(ObservedMeasurement, ProcessEstimate) | | 100% | | 50% | 1 | 2 | 0 | 12 | 0 | 1 |
| getInnovation(MeasurementDecorator, RealVector, RealVector, RealMatrix) | | 100% | | n/a | 0 | 1 | 0 | 10 | 0 | 1 |
| processMeasurements(List, UnscentedKalmanFilter) | | 100% | | n/a | 0 | 1 | 0 | 8 | 0 | 1 |
| getStm() | | 100% | | n/a | 0 | 1 | 0 | 9 | 0 | 1 |
| initializeShortPeriodicTerms(SpacecraftState) | | 100% | | 100% | 0 | 2 | 0 | 6 | 0 | 1 |
| estimateMeasurement(ObservedMeasurement, int, SpacecraftState[]) | | 100% | | n/a | 0 | 1 | 0 | 8 | 0 | 1 |
| updateShortPeriods(SpacecraftState) | | 100% | | 100% | 0 | 2 | 0 | 4 | 0 | 1 |
| updateNominalSpacecraftState(SpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 4 | 0 | 1 |
| toRealVector(SpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| computeOsculatingElements(RealVector, SpacecraftState, RealVector) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getPredictedSpacecraftStates() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getCorrectedSpacecraftStates() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getEstimatedPropagator() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| setObserver(KalmanObserver) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getPhysicalEstimatedCovarianceMatrix() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getPhysicalInnovationCovarianceMatrix() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getPhysicalKalmanGain() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getNumberSelectedOrbitalDrivers() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getNumberSelectedPropagationDrivers() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getNumberSelectedMeasurementDrivers() | | 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 |
| getPhysicalStateTransitionMatrix() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getPhysicalMeasurementJacobian() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |