| setInitialStateTransitionMatrix(SpacecraftState, RealMatrix) |   | 59% | | 70% | 3 | 6 | 3 | 12 | 0 | 1 |
| yields(SpacecraftState) | | 77% | | 50% | 1 | 2 | 0 | 1 | 0 | 1 |
| computePartials(SpacecraftState) | | 100% | | 100% | 0 | 8 | 0 | 37 | 0 | 1 |
| init(SpacecraftState, AbsoluteDate) | | 100% | | 100% | 0 | 4 | 0 | 15 | 0 | 1 |
| combinedDerivatives(SpacecraftState) | | 100% | | 100% | 0 | 4 | 0 | 11 | 0 | 1 |
| DSSTStateTransitionMatrixGenerator(String, List, AttitudeProvider, PropagationType) | | 100% | | n/a | 0 | 1 | 0 | 7 | 0 | 1 |
| addToRow(double[], int, RealMatrix) | | 100% | | 100% | 0 | 2 | 0 | 3 | 0 | 1 |
| addObserver(String, DSSTStateTransitionMatrixGenerator.DSSTPartialsObserver) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getName() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getDimension() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |