SpacecraftToObservedBody(Frame, Frame, AbsoluteDate, AbsoluteDate, double, double, List, int, CartesianDerivativesFilter, List, int, AngularDerivativesFilter) | | 92% | | 77% | 4 | 10 | 4 | 50 | 0 | 1 |
interpolate(AbsoluteDate, List) | | 100% | | 100% | 0 | 2 | 0 | 7 | 0 | 1 |
SpacecraftToObservedBody(Frame, Frame, AbsoluteDate, AbsoluteDate, double, double, List, List) | | 100% | | 100% | 0 | 2 | 0 | 14 | 0 | 1 |
isInRange(AbsoluteDate) | | 100% | | 100% | 0 | 3 | 0 | 2 | 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 |