| getEccentricAnomaly(double, double) |   | 82% | | 70% | 3 | 6 | 4 | 27 | 0 | 1 |
| eMeSinE(double, double) | | 55% | | 50% | 1 | 2 | 4 | 10 | 0 | 1 |
| computeMoonElements(GLONASSDate) | | 100% | | n/a | 0 | 1 | 0 | 46 | 0 | 1 |
| computeSunElements(GLONASSDate) | | 100% | | n/a | 0 | 1 | 0 | 29 | 0 | 1 |
| getPVInPZ90(SpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 26 | 0 | 1 |
| getPVInInertial(GLONASSDate) | | 100% | | n/a | 0 | 1 | 0 | 14 | 0 | 1 |
| GLONASSNumericalPropagator(ClassicalRungeKuttaIntegrator, GLONASSOrbitalElements, Frame, AttitudeProvider, double, DataContext, boolean) | | 100% | | 100% | 0 | 2 | 0 | 19 | 0 | 1 |
| propagate(AbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 12 | 0 | 1 |
| setInitialState() | | 100% | | n/a | 0 | 1 | 0 | 5 | 0 | 1 |
| getTrueAnomaly(double, double) | | 100% | | n/a | 0 | 1 | 0 | 4 | 0 | 1 |
| static {...} | | 100% | | n/a | 0 | 1 | 0 | 6 | 0 | 1 |
| createMapper(AbsoluteDate, double, OrbitType, PositionAngle, AttitudeProvider, Frame) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getMainStateEquations(ODEIntegrator) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getGLONASSOrbitalElements() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |