| setInitialStateTransitionMatrix(SpacecraftState, RealMatrix, OrbitType, PositionAngleType) |  | 98% |  | 91% | 1 | 7 | 1 | 20 | 0 | 1 |
| computePartials(SpacecraftState) | | 100% | | 100% | 0 | 11 | 0 | 51 | 0 | 1 |
| multiplyMatrix(double[], double[], double[], int) | | 100% | | 100% | 0 | 2 | 0 | 7 | 0 | 1 |
| combinedDerivatives(SpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 5 | 0 | 1 |
| StateTransitionMatrixGenerator(String, List, AttitudeProvider) | | 100% | | n/a | 0 | 1 | 0 | 6 | 0 | 1 |
| wrapAttitudeProviderIfPossible(List, AttitudeProvider) | | 100% | | 100% | 0 | 2 | 0 | 3 | 0 | 1 |
| yields(SpacecraftState) | | 100% | | 100% | 0 | 2 | 0 | 1 | 0 | 1 |
| addObserver(String, StateTransitionMatrixGenerator.PartialsObserver) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| lambda$computePartials$0(ForceModel) | | 100% | | 100% | 0 | 2 | 0 | 1 | 0 | 1 |
| getName() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| static {...} | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getDimension() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |