| getCoordinates(SpacecraftState, int, int) |  | 100% | | n/a | 0 | 1 | 0 | 16 | 0 | 1 |
| AbstractMeasurement(AbsoluteDate, double, double, double, List) | | 100% | | n/a | 0 | 1 | 0 | 11 | 0 | 1 |
| AbstractMeasurement(AbsoluteDate, double[], double[], double[], List) | | 100% | | n/a | 0 | 1 | 0 | 10 | 0 | 1 |
| theoreticalEvaluationWithoutDerivatives(int, int, SpacecraftState[]) | | 100% | | n/a | 0 | 1 | 0 | 6 | 0 | 1 |
| estimateWithoutDerivatives(int, int, SpacecraftState[]) | | 100% | | 100% | 0 | 2 | 0 | 5 | 0 | 1 |
| estimate(int, int, SpacecraftState[]) | | 100% | | 100% | 0 | 2 | 0 | 5 | 0 | 1 |
| addParametersDrivers(List) | | 100% | | 100% | 0 | 2 | 0 | 4 | 0 | 1 |
| addModifier(EstimationModifier) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| setObservedValue(double[]) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| addParameterDriver(ParameterDriver) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getTheoreticalStandardDeviation() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getBaseWeight() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getObservedValue() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| lambda$new$0(ObservableSatellite) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getParametersDrivers() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| setEnabled(boolean) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getDimension() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getModifiers() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| isEnabled() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getSatellites() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getDate() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |