| removeForceModels() |  | 0% | | 0% | 2 | 2 | 8 | 8 | 1 | 1 |
| addForceModel(DSSTForceModel) |  | 73% | | 83% | 1 | 4 | 3 | 13 | 0 | 1 |
| computeMeanOrbit(FieldSpacecraftState, AttitudeProvider, Collection, double, int) | | 95% | | 72% | 5 | 10 | 1 | 44 | 0 | 1 |
| getSelectedCoefficients() | | 0% | | 0% | 2 | 2 | 2 | 2 | 1 | 1 |
| afterIntegration() | | 71% | | 75% | 1 | 3 | 2 | 8 | 0 | 1 |
| setSatelliteRevolution(int) | | 0% | | n/a | 1 | 1 | 2 | 2 | 1 | 1 |
| getSatelliteRevolution() | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| initialIsOsculating() | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| getOrbitType() | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| getPositionAngleType() | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| beforeIntegration(FieldSpacecraftState, FieldAbsoluteDate) | | 100% | | 100% | 0 | 5 | 0 | 22 | 0 | 1 |
| computeOsculatingOrbit(FieldSpacecraftState, List) | | 100% | | 100% | 0 | 3 | 0 | 12 | 0 | 1 |
| computeOsculatingState(FieldSpacecraftState, AttitudeProvider, Collection) | | 100% | | 100% | 0 | 2 | 0 | 10 | 0 | 1 |
| createMapper(FieldAbsoluteDate, CalculusFieldElement, OrbitType, PositionAngleType, AttitudeProvider, Frame) | | 100% | | 100% | 0 | 2 | 0 | 7 | 0 | 1 |
| FieldDSSTPropagator(Field, FieldODEIntegrator, PropagationType, AttitudeProvider) | | 100% | | n/a | 0 | 1 | 0 | 9 | 0 | 1 |
| FieldDSSTPropagator(Field, FieldODEIntegrator, AttitudeProvider) | | 100% | | n/a | 0 | 1 | 0 | 9 | 0 | 1 |
| tolerances(CalculusFieldElement, FieldOrbit) | | 100% | | n/a | 0 | 1 | 0 | 5 | 0 | 1 |
| setAttitudeProvider(AttitudeProvider) | | 100% | | 100% | 0 | 2 | 0 | 5 | 0 | 1 |
| hasNewtonianAttraction() | | 100% | | 100% | 0 | 3 | 0 | 2 | 0 | 1 |
| computeMeanState(FieldSpacecraftState, AttitudeProvider, Collection, double, int) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| resetInitialState(FieldSpacecraftState) | | 100% | | 100% | 0 | 2 | 0 | 5 | 0 | 1 |
| getInitialIntegrationState() | | 100% | | 100% | 0 | 2 | 0 | 3 | 0 | 1 |
| resetInitialState(FieldSpacecraftState, PropagationType) | | 100% | | 100% | 0 | 2 | 0 | 3 | 0 | 1 |
| setSelectedCoefficients(Set) | | 100% | | 100% | 0 | 2 | 0 | 3 | 0 | 1 |
| tolerances(CalculusFieldElement, CalculusFieldElement, FieldOrbit) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| FieldDSSTPropagator(Field, FieldODEIntegrator, PropagationType) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| setInterpolationGridToFixedNumberOfPoints(int) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| setInterpolationGridToMaxTimeGap(CalculusFieldElement) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| FieldDSSTPropagator(Field, FieldODEIntegrator) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| setMu(CalculusFieldElement) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| computeMeanState(FieldSpacecraftState, AttitudeProvider, Collection) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getMainStateEquations(FieldODEIntegrator) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| setInitialState(FieldSpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| setInitialState(FieldSpacecraftState, PropagationType) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| superSetMu(CalculusFieldElement) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getAllForceModels() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |