| SpacecraftToObservedBody(Frame, Frame, AbsoluteDate, AbsoluteDate, double, double, List, int, CartesianDerivativesFilter, List, int, AngularDerivativesFilter) |   | 92% | | 77% | 4 | 10 | 4 | 50 | 0 | 1 |
| interpolate(AbsoluteDate, List) | | 70% | | 50% | 1 | 2 | 1 | 7 | 0 | 1 |
| isInRange(AbsoluteDate) | | 95% | | 50% | 2 | 3 | 0 | 2 | 0 | 1 |
| SpacecraftToObservedBody(Frame, Frame, AbsoluteDate, AbsoluteDate, double, double, List, List) | | 100% | | 100% | 0 | 2 | 0 | 14 | 0 | 1 |
| getScToInertial(AbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getInertialToBody(AbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getBodyToInertial(AbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getInertialFrame() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getBodyFrame() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getMinDate() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getMaxDate() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getTStep() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
| getOvershootTolerance() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |