| getJacobian(Orbit, PositionAngleType, double[][]) |   | 96% | | 86% | 2 | 12 | 3 | 31 | 0 | 1 |
| updateOrbit(Orbit) | | 100% | | 100% | 0 | 3 | 0 | 14 | 0 | 1 |
| evaluateJ0Dot() | | 100% | | 100% | 0 | 4 | 0 | 15 | 0 | 1 |
| SmallManeuverAnalyticalModel(SpacecraftState, OrbitType, Frame, Vector3D, double) | | 100% | | 100% | 0 | 2 | 0 | 17 | 0 | 1 |
| apply(SpacecraftState) | | 100% | | 100% | 0 | 2 | 0 | 4 | 0 | 1 |
| apply(Orbit) | | 100% | | 100% | 0 | 2 | 0 | 3 | 0 | 1 |
| SmallManeuverAnalyticalModel(SpacecraftState, Frame, Vector3D, double) | | 100% | | 100% | 0 | 2 | 0 | 2 | 0 | 1 |
| SmallManeuverAnalyticalModel(SpacecraftState, OrbitType, Vector3D, double) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| SmallManeuverAnalyticalModel(SpacecraftState, Vector3D, double) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| updateMass(double) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getDate() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getInertialFrame() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getInertialDV() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |