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 |