| getParameterDerivatives(ParameterDriver) |   | 98% | | 88% | 1 | 5 | 0 | 12 | 0 | 1 |
| getStateDerivatives() | | 100% | | 100% | 0 | 2 | 0 | 4 | 0 | 1 |
| setStateDerivatives(double[][]) | | 100% | | 100% | 0 | 2 | 0 | 4 | 0 | 1 |
| EstimatedMeasurement(ObservedMeasurement, int, int, SpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 7 | 0 | 1 |
| getCurrentWeight() | | 100% | | 100% | 0 | 2 | 0 | 1 | 0 | 1 |
| getTimeOffset() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| setParameterDerivatives(ParameterDriver, double[]) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| setEstimatedValue(double[]) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| setCurrentWeight(double[]) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
| getEstimatedValue() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getDate() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getObservedMeasurement() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getIteration() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getCount() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getState() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |