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 |