| computeMeanOrbit(SpacecraftState, AttitudeProvider, Collection) |   | 94% | | 72% | 5 | 10 | 1 | 42 | 0 | 1 |
| getSelectedCoefficients() | | 0% | | 0% | 2 | 2 | 2 | 2 | 1 | 1 |
| setAttitudeProvider(AttitudeProvider) | | 57% | | 50% | 1 | 2 | 2 | 5 | 0 | 1 |
| setSatelliteRevolution(int) | | 0% | | n/a | 1 | 1 | 2 | 2 | 1 | 1 |
| removeForceModels() | | 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 |
| beforeIntegration(SpacecraftState, AbsoluteDate) | | 100% | | 100% | 0 | 4 | 0 | 19 | 0 | 1 |
| computeOsculatingOrbit(SpacecraftState, List) | | 100% | | 100% | 0 | 3 | 0 | 12 | 0 | 1 |
| computeOsculatingState(SpacecraftState, AttitudeProvider, Collection) | | 100% | | 100% | 0 | 2 | 0 | 10 | 0 | 1 |
| afterIntegration() | | 100% | | 100% | 0 | 5 | 0 | 12 | 0 | 1 |
| createMapper(AbsoluteDate, double, OrbitType, PositionAngle, AttitudeProvider, Frame) | | 100% | | 100% | 0 | 2 | 0 | 7 | 0 | 1 |
| DSSTPropagator(ODEIntegrator, boolean) | | 100% | | n/a | 0 | 1 | 0 | 8 | 0 | 1 |
| DSSTPropagator(ODEIntegrator) | | 100% | | n/a | 0 | 1 | 0 | 8 | 0 | 1 |
| computeMeanState(SpacecraftState, AttitudeProvider, Collection) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getInitialIntegrationState() | | 100% | | 100% | 0 | 2 | 0 | 3 | 0 | 1 |
| setSelectedCoefficients(Set) | | 100% | | 100% | 0 | 2 | 0 | 3 | 0 | 1 |
| addForceModel(DSSTForceModel) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| resetInitialState(SpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| setInitialState(SpacecraftState, boolean) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| setInterpolationGridToFixedNumberOfPoints(int) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| setInterpolationGridToMaxTimeGap(double) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getMainStateEquations(ODEIntegrator) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| setInitialState(SpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| tolerances(double, Orbit) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |