getMu() | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
createTLE() | | 100% | | n/a | 0 | 1 | 0 | 9 | 0 | 1 |
of(TLE, Frame) | | 100% | | n/a | 0 | 1 | 0 | 5 | 0 | 1 |
SGP4OrbitalState(AbsoluteDate, AveragedKeplerianWithMeanAngle, Frame, TimeScale) | | 100% | | n/a | 0 | 1 | 0 | 4 | 0 | 1 |
SGP4OrbitalState(AbsoluteDate, AveragedKeplerianWithMeanAngle, DataContext) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
computeMeanMotion(double) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
computeSemiMajorAxis(TLE) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
createPropagator() | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
toOsculatingOrbit() | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
SGP4OrbitalState(AbsoluteDate, AveragedKeplerianWithMeanAngle) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
getAveragedElements() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getTleMu() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getOrbitType() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getPositionAngleType() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |