| getMu(AbsoluteDate) |  | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| getMeanElementRate(FieldSpacecraftState, FieldAuxiliaryElements, CalculusFieldElement[]) |  | 100% | | n/a | 0 | 1 | 0 | 6 | 0 | 1 |
| getMeanElementRate(SpacecraftState, AuxiliaryElements, double[]) | | 100% | | n/a | 0 | 1 | 0 | 5 | 0 | 1 |
| DSSTNewtonianAttraction(double) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| initializeStep(AuxiliaryElements, double[]) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| initializeStep(FieldAuxiliaryElements, CalculusFieldElement[]) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| static {...} | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getParametersDrivers() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| initializeShortPeriodTerms(AuxiliaryElements, PropagationType, double[]) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| initializeShortPeriodTerms(FieldAuxiliaryElements, PropagationType, CalculusFieldElement[]) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| registerAttitudeProvider(AttitudeProvider) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| updateShortPeriodTerms(double[], SpacecraftState[]) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| updateShortPeriodTerms(CalculusFieldElement[], FieldSpacecraftState[]) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |