| computeMeanParameters(CircularOrbit, double) |   | 94% | | 62% | 6 | 9 | 1 | 21 | 0 | 1 |
| writeReplace() | | 96% | | 92% | 1 | 7 | 2 | 26 | 0 | 1 |
| toCartesian(AbsoluteDate, DerivativeStructure[]) | | 100% | | n/a | 0 | 1 | 0 | 24 | 0 | 1 |
| meanToEccentric(DerivativeStructure, DerivativeStructure, DerivativeStructure) | | 100% | | 75% | 1 | 3 | 0 | 17 | 0 | 1 |
| EcksteinHechlerPropagator(Orbit, AttitudeProvider, double, double, double, double, double, double, double, double) | | 100% | | n/a | 0 | 1 | 0 | 9 | 0 | 1 |
| EcksteinHechlerPropagator(Orbit, AttitudeProvider, double, UnnormalizedSphericalHarmonicsProvider, UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| resetIntermediateState(SpacecraftState, boolean) | | 100% | | 100% | 0 | 2 | 0 | 6 | 0 | 1 |
| resetInitialState(SpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 4 | 0 | 1 |
| propagateOrbit(AbsoluteDate) | | 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) | | 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 |