| getShortPeriodicVariations(AbsoluteDate, double[]) |  | 100% | | 100% | 0 | 5 | 0 | 16 | 0 | 1 |
| initializeStep(AuxiliaryElements) | | 100% | | n/a | 0 | 1 | 0 | 23 | 0 | 1 |
| getMeanElementRate(SpacecraftState) | | 100% | | 100% | 0 | 6 | 0 | 13 | 0 | 1 |
| getRatesDiff(double[], double[]) | | 100% | | 100% | 0 | 3 | 0 | 5 | 0 | 1 |
| static {...} | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getMeanElementRate(SpacecraftState, AbstractGaussianContribution.GaussQuadrature, double, double) | | 100% | | 100% | 0 | 2 | 0 | 5 | 0 | 1 |
| AbstractGaussianContribution(double, ForceModel) | | 100% | | n/a | 0 | 1 | 0 | 6 | 0 | 1 |
| initialize(AuxiliaryElements, boolean) | | 100% | | 100% | 0 | 2 | 0 | 4 | 0 | 1 |
| getAcceleration(SpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| resetShortPeriodicsCoefficients() | | 100% |  | 50% | 1 | 2 | 0 | 3 | 0 | 1 |
| computeShortPeriodicsCoefficients(SpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| registerAttitudeProvider(AttitudeProvider) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |