| beforeIntegration(SpacecraftState, AbsoluteDate) |   | 40% | | 50% | 2 | 4 | 11 | 18 | 0 | 1 |
| afterIntegration() | | 9% | | 12% | 4 | 5 | 10 | 12 | 0 | 1 |
| setAttitudeProvider(AttitudeProvider) | | 60% | | 50% | 1 | 2 | 2 | 5 | 0 | 1 |
| setInitialState(SpacecraftState) | | 0% | | n/a | 1 | 1 | 2 | 2 | 1 | 1 |
| setSatelliteRevolution(int) | | 0% | | n/a | 1 | 1 | 2 | 2 | 1 | 1 |
| initialIsOsculating() | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| removeForceModels() | | 0% | | n/a | 1 | 1 | 2 | 2 | 1 | 1 |
| getSatelliteRevolution() | | 0% | | n/a | 1 | 1 | 1 | 1 | 1 | 1 |
| computeMeanState(SpacecraftState, Collection) | | 100% | | 100% | 0 | 2 | 0 | 10 | 0 | 1 |
| computeOsculatingState(SpacecraftState, Collection) | | 100% | | 100% | 0 | 2 | 0 | 9 | 0 | 1 |
| createMapper(AbsoluteDate, double, OrbitType, PositionAngle, AttitudeProvider, Frame) | | 100% | | 100% | 0 | 3 | 0 | 9 | 0 | 1 |
| DSSTPropagator(AbstractIntegrator, boolean) | | 100% | | n/a | 0 | 1 | 0 | 6 | 0 | 1 |
| DSSTPropagator(AbstractIntegrator) | | 100% | | n/a | 0 | 1 | 0 | 6 | 0 | 1 |
| addForceModel(DSSTForceModel) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| setInitialState(SpacecraftState, boolean) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| resetInitialState(SpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| getMainStateEquations(AbstractIntegrator) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| tolerances(double, Orbit) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |