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 |