computeMeanParameters(CircularOrbit) |   | 97% |   | 73% | 6 | 12 | 1 | 43 | 0 | 1 |
propagateOrbit(AbsoluteDate) |  | 100% | | n/a | 0 | 1 | 0 | 74 | 0 | 1 |
EcksteinHechlerPropagator(Orbit, AttitudeProvider, double, double, double, double, double, double, double, double) |  | 100% | | n/a | 0 | 1 | 0 | 14 | 0 | 1 |
EcksteinHechlerPropagator(Orbit, AttitudeProvider, double, UnnormalizedSphericalHarmonicsProvider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics) |  | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
resetInitialState(SpacecraftState) |  | 100% | | n/a | 0 | 1 | 0 | 4 | 0 | 1 |
EcksteinHechlerPropagator(Orbit, double, double, double, double, double, double, double) |  | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
EcksteinHechlerPropagator(Orbit, double, double, double, double, double, double, double, double) |  | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
EcksteinHechlerPropagator(Orbit, AttitudeProvider, double, double, double, double, double, double, double) |  | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
EcksteinHechlerPropagator(Orbit, UnnormalizedSphericalHarmonicsProvider) |  | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
EcksteinHechlerPropagator(Orbit, double, UnnormalizedSphericalHarmonicsProvider) |  | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
EcksteinHechlerPropagator(Orbit, AttitudeProvider, UnnormalizedSphericalHarmonicsProvider) |  | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
EcksteinHechlerPropagator(Orbit, AttitudeProvider, double, UnnormalizedSphericalHarmonicsProvider) |  | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
getMass(AbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |