computeMeanParameters(CircularOrbit, double, double, int) |   | 94% |   | 87% | 2 | 9 | 1 | 34 | 0 | 1 |
resetIntermediateState(SpacecraftState, boolean, double, int) |   | 77% |   | 50% | 1 | 2 | 1 | 7 | 0 | 1 |
toCartesian(AbsoluteDate, UnivariateDerivative2[]) |  | 100% | | n/a | 0 | 1 | 0 | 33 | 0 | 1 |
meanToEccentric(UnivariateDerivative2, UnivariateDerivative2, UnivariateDerivative2) |  | 100% |   | 75% | 1 | 3 | 0 | 17 | 0 | 1 |
EcksteinHechlerPropagator(Orbit, AttitudeProvider, double, double, double, double, double, double, double, double, PropagationType, double, int) |  | 100% | | n/a | 0 | 1 | 0 | 9 | 0 | 1 |
resetInitialState(SpacecraftState, PropagationType, double, int) |  | 100% |  | 100% | 0 | 2 | 0 | 7 | 0 | 1 |
EcksteinHechlerPropagator(Orbit, AttitudeProvider, double, UnnormalizedSphericalHarmonicsProvider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics, PropagationType) |  | 100% | | n/a | 0 | 1 | 0 | 7 | 0 | 1 |
EcksteinHechlerPropagator(Orbit, AttitudeProvider, double, UnnormalizedSphericalHarmonicsProvider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics) |  | 100% | | n/a | 0 | 1 | 0 | 7 | 0 | 1 |
computeMeanOrbit(Orbit, UnnormalizedSphericalHarmonicsProvider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics, double, int) |  | 100% | | n/a | 0 | 1 | 0 | 7 | 0 | 1 |
computeMeanOrbit(Orbit, double, double, double, double, double, double, double, double, int) |  | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
propagateOrbit(AbsoluteDate) |  | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
EcksteinHechlerPropagator(Orbit, AttitudeProvider, double, double, double, double, double, double, double, double, PropagationType) |  | 100% | | n/a | 0 | 1 | 0 | 2 | 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, double) |  | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
EcksteinHechlerPropagator(Orbit, UnnormalizedSphericalHarmonicsProvider, PropagationType) |  | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
EcksteinHechlerPropagator(Orbit, UnnormalizedSphericalHarmonicsProvider) |  | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
EcksteinHechlerPropagator(Orbit, double, UnnormalizedSphericalHarmonicsProvider) |  | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
EcksteinHechlerPropagator(Orbit, AttitudeProvider, double, double, double, double, double, double, double) |  | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
createHarvester(String, RealMatrix, DoubleArrayDictionary) |  | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
EcksteinHechlerPropagator(Orbit, AttitudeProvider, double, UnnormalizedSphericalHarmonicsProvider, PropagationType) |  | 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 |
computeMeanOrbit(Orbit, UnnormalizedSphericalHarmonicsProvider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics) |  | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
resetInitialState(SpacecraftState, PropagationType) |  | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
resetIntermediateState(SpacecraftState, boolean) |  | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
getMass(AbsoluteDate) |  | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
resetInitialState(SpacecraftState) |  | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
getCk0() |  | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getMu() |  | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getReferenceRadius() |  | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |