| buildPvCovarianceMatrix(double[][], double[][]) |   | 76% | | 75% | 3 | 7 | 3 | 14 | 0 | 1 |
| buildPvCovarianceMatrix(double[], double[]) | | 79% | | 83% | 1 | 4 | 1 | 9 | 0 | 1 |
| static {...} | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| theoreticalEvaluationWithoutDerivatives(int, int, SpacecraftState[]) | | 100% | | n/a | 0 | 1 | 0 | 5 | 0 | 1 |
| PV(AbsoluteDate, Vector3D, Vector3D, MeasurementQuality, ObservableSatellite) | | 100% | | n/a | 0 | 1 | 0 | 4 | 0 | 1 |
| PV(AbsoluteDate, Vector3D, Vector3D, double[], double, ObservableSatellite) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| PV(AbsoluteDate, Vector3D, Vector3D, double[][], double, ObservableSatellite) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| PV(AbsoluteDate, Vector3D, Vector3D, double, double, double, ObservableSatellite) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getPosition() | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getVelocity() | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| theoreticalEvaluation(int, int, SpacecraftState[]) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| PV(AbsoluteDate, Vector3D, Vector3D, double[], double[], double, ObservableSatellite) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| PV(AbsoluteDate, Vector3D, Vector3D, double[][], double[][], double, ObservableSatellite) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |