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 |