Element | Missed Instructions | Cov. | Missed Branches | Cov. | Missed | Cxty | Missed | Lines | Missed | Methods |
Total | 0 of 230 | 100% | 0 of 0 | n/a | 0 | 12 | 0 | 37 | 0 | 12 |
propagateInEcef(AbsoluteDate) | 100% | n/a | 0 | 1 | 0 | 14 | 0 | 1 | ||
SBASPropagator(SBASOrbitalElements, Frame, Frame, AttitudeProvider, double, double) | 100% | n/a | 0 | 1 | 0 | 11 | 0 | 1 | ||
propagateOrbit(AbsoluteDate) | 100% | n/a | 0 | 1 | 0 | 3 | 0 | 1 | ||
resetInitialState(SpacecraftState) | 100% | n/a | 0 | 1 | 0 | 1 | 0 | 1 | ||
resetIntermediateState(SpacecraftState, boolean) | 100% | n/a | 0 | 1 | 0 | 1 | 0 | 1 | ||
getDT(AbsoluteDate) | 100% | n/a | 0 | 1 | 0 | 1 | 0 | 1 | ||
getMU() | 100% | n/a | 0 | 1 | 0 | 1 | 0 | 1 | ||
getECI() | 100% | n/a | 0 | 1 | 0 | 1 | 0 | 1 | ||
getECEF() | 100% | n/a | 0 | 1 | 0 | 1 | 0 | 1 | ||
getSBASOrbitalElements() | 100% | n/a | 0 | 1 | 0 | 1 | 0 | 1 | ||
getFrame() | 100% | n/a | 0 | 1 | 0 | 1 | 0 | 1 | ||
getMass(AbsoluteDate) | 100% | n/a | 0 | 1 | 0 | 1 | 0 | 1 |