| getBody() | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| updateShortPeriodTerms(CalculusFieldElement[], FieldSpacecraftState[]) |  | 100% | | 100% | 0 | 5 | 0 | 53 | 0 | 1 |
| updateShortPeriodTerms(double[], SpacecraftState[]) | | 100% | | 100% | 0 | 5 | 0 | 50 | 0 | 1 |
| getMeanElementRate(FieldSpacecraftState, FieldAuxiliaryElements, CalculusFieldElement[]) | | 100% | | n/a | 0 | 1 | 0 | 24 | 0 | 1 |
| getMeanElementRate(SpacecraftState, AuxiliaryElements, double[]) | | 100% | | n/a | 0 | 1 | 0 | 14 | 0 | 1 |
| initializeShortPeriodTerms(FieldAuxiliaryElements, PropagationType, CalculusFieldElement[]) | | 100% | | n/a | 0 | 1 | 0 | 9 | 0 | 1 |
| DSSTThirdBody(CelestialBody, double) | | 100% | | n/a | 0 | 1 | 0 | 11 | 0 | 1 |
| initializeShortPeriodTerms(AuxiliaryElements, PropagationType, double[]) | | 100% | | n/a | 0 | 1 | 0 | 9 | 0 | 1 |
| computeAoR3Pow(FieldDSSTThirdBodyDynamicContext) | | 100% | | 100% | 0 | 2 | 0 | 7 | 0 | 1 |
| computeAoR3Pow(DSSTThirdBodyDynamicContext) | | 100% | | 100% | 0 | 2 | 0 | 6 | 0 | 1 |
| initializeStaticContextIfNeeded(AuxiliaryElements, double, double, double[]) | | 100% | | 100% | 0 | 2 | 0 | 4 | 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 |
| registerAttitudeProvider(AttitudeProvider) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |