| addContribution(SpacecraftState, TimeDerivativesEquations) |   | 99% | | 92% | 1 | 7 | 1 | 171 | 0 | 1 |
| CunninghamAttractionModel(Frame, double, double, double[][], double[][]) | | 0% | | n/a | 1 | 1 | 2 | 2 | 1 | 1 |
| CunninghamAttractionModel(Frame, UnnormalizedSphericalHarmonicsProvider) | | 100% | | n/a | 0 | 1 | 0 | 6 | 0 | 1 |
| accelerationDerivatives(AbsoluteDate, Frame, FieldVector3D, FieldVector3D, FieldRotation, DerivativeStructure) | | 100% | | 100% | 0 | 2 | 0 | 3 | 0 | 1 |
| setSteps(double, double) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| accelerationDerivatives(SpacecraftState, String) | | 100% | | 100% | 0 | 2 | 0 | 3 | 0 | 1 |
| setParameter(String, double) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| getParameter(String) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getTideSystem() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getEventsDetectors() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |