| extractParameters(CalculusFieldElement[], FieldAbsoluteDate) |  | 100% | | 100% | 0 | 4 | 0 | 11 | 0 | 1 |
| extractParameters(double[], AbsoluteDate) | | 100% | | 100% | 0 | 4 | 0 | 11 | 0 | 1 |
| getParametersDrivers() | | 100% |  | 83% | 1 | 4 | 0 | 7 | 0 | 1 |
| acceleration(FieldSpacecraftState, CalculusFieldElement[]) | | 100% | | n/a | 0 | 1 | 0 | 4 | 0 | 1 |
| acceleration(SpacecraftState, double[]) | | 100% | | n/a | 0 | 1 | 0 | 4 | 0 | 1 |
| TimeSpanParametricAcceleration(Vector3D, boolean, AttitudeProvider, AccelerationModel) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
| addAccelerationModelValidBefore(AccelerationModel, AbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| addAccelerationModelValidAfter(AccelerationModel, AbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| TimeSpanParametricAcceleration(Vector3D, boolean, AccelerationModel) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| TimeSpanParametricAcceleration(Vector3D, AttitudeProvider, AccelerationModel) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| init(SpacecraftState, AbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getAccelerationModel(AbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| extractAccelerationModelRange(AbsoluteDate, AbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getAccelerationModelSpan(AbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| lambda$init$0(SpacecraftState, AbsoluteDate, AccelerationModel) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getFirstSpan() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |