| setInitialStateTransitionMatrix(SpacecraftState, RealMatrix, OrbitType, PositionAngleType) |  | 100% | | 100% | 0 | 5 | 0 | 19 | 0 | 1 |
| computePartials(SpacecraftState) | | 100% | | 100% | 0 | 4 | 0 | 15 | 0 | 1 |
| updateFactorForParameters(ForceModel, NumericalGradientConverter, Gradient[], DoubleArrayDictionary, SpacecraftState, double[]) | | 100% | | 100% | 0 | 6 | 0 | 12 | 0 | 1 |
| updateDictionaryEntry(DoubleArrayDictionary, TimeSpanMap.Span, Gradient[], int) | | 100% | | 100% | 0 | 3 | 0 | 9 | 0 | 1 |
| flatten(RealMatrix) | | 100% | | 100% | 0 | 3 | 0 | 6 | 0 | 1 |
| combinedDerivatives(SpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 5 | 0 | 1 |
| AbstractStateTransitionMatrixGenerator(String, List, AttitudeProvider, int) | | 100% | | n/a | 0 | 1 | 0 | 8 | 0 | 1 |
| wrapAttitudeProviderIfPossible() | | 100% | | 100% | 0 | 2 | 0 | 3 | 0 | 1 |
| yields(SpacecraftState) | | 100% | | 100% | 0 | 2 | 0 | 1 | 0 | 1 |
| addObserver(String, AbstractStateTransitionMatrixGenerator.PartialsObserver) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getDecompositionSolver(RealMatrix) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| lambda$computePartials$0(ForceModel) | | 100% | | 100% | 0 | 2 | 0 | 1 | 0 | 1 |
| getName() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getDimension() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getStateDimension() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getForceModels() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getPartialsObservers() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| static {...} | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |