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 |