getCoordinates(SpacecraftState, int, int) | | 100% | | n/a | 0 | 1 | 0 | 16 | 0 | 1 |
signalTimeOfFlight(TimeStampedFieldPVCoordinates, FieldVector3D, FieldAbsoluteDate) | | 100% | | 75% | 1 | 3 | 0 | 10 | 0 | 1 |
AbstractMeasurement(AbsoluteDate, double, double, double, List) | | 100% | | n/a | 0 | 1 | 0 | 10 | 0 | 1 |
signalTimeOfFlight(TimeStampedPVCoordinates, Vector3D, AbsoluteDate) | | 100% | | 75% | 1 | 3 | 0 | 10 | 0 | 1 |
AbstractMeasurement(AbsoluteDate, double[], double[], double[], List) | | 100% | | n/a | 0 | 1 | 0 | 10 | 0 | 1 |
estimate(int, int, SpacecraftState[]) | | 100% | | 100% | 0 | 2 | 0 | 5 | 0 | 1 |
addModifier(EstimationModifier) | | 100% | | n/a | 0 | 1 | 0 | 3 | 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 |
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 |