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 | 11 | 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, PositionAngleType, 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 |