getProcessNoiseMatrix(SpacecraftState, SpacecraftState) | | 100% | | 66% | 2 | 4 | 0 | 14 | 0 | 1 |
getInertialOrbitalProcessNoiseMatrix(SpacecraftState, SpacecraftState) | | 100% | | 100% | 0 | 2 | 0 | 15 | 0 | 1 |
getPropagationProcessNoiseMatrix(SpacecraftState, SpacecraftState) | | 100% | | 100% | 0 | 2 | 0 | 7 | 0 | 1 |
getMeasurementsProcessNoiseMatrix(SpacecraftState, SpacecraftState) | | 100% | | 100% | 0 | 2 | 0 | 7 | 0 | 1 |
UnivariateProcessNoise(RealMatrix, LOFType, PositionAngleType, UnivariateFunction[], UnivariateFunction[], UnivariateFunction[]) | | 100% | | n/a | 0 | 1 | 0 | 7 | 0 | 1 |
UnivariateProcessNoise(RealMatrix, LOFType, PositionAngleType, UnivariateFunction[], UnivariateFunction[]) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
getLofCartesianOrbitalParametersEvolution() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getPropagationParametersEvolution() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getMeasurementsParametersEvolution() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getLofType() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getPositionAngleType() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |