| NumericalPropagator.Main(NumericalPropagator, ODEIntegrator, OrbitType, PositionAngleType, List) |   | 95% | | 80% | 2 | 6 | 0 | 10 | 0 | 1 |
| setUpInternalEventDetector(ODEIntegrator, EventDetector, NumericalTimeDerivativesEquations) | | 100% | | 100% | 0 | 3 | 0 | 13 | 0 | 1 |
| setUpInternalDetectors(ODEIntegrator) | | 100% | | 100% | 0 | 2 | 0 | 7 | 0 | 1 |
| computeDerivatives(SpacecraftState) | | 100% | | 100% | 0 | 2 | 0 | 6 | 0 | 1 |
| init(SpacecraftState, AbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 4 | 0 | 1 |
| lambda$setUpInternalDetectors$1(ODEIntegrator, NumericalTimeDerivativesEquations, EventDetector) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| lambda$setUpInternalDetectors$0(ODEIntegrator, NumericalTimeDerivativesEquations, EventDetector) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| lambda$init$2(SpacecraftState, AbsoluteDate, ForceModel) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |