resetInitialState(SpacecraftState) | | 71% | | 50% | 1 | 2 | 1 | 5 | 0 | 1 |
tolerances(double, Orbit, OrbitType) | | 100% | | 100% | 0 | 4 | 0 | 24 | 0 | 1 |
NumericalPropagator(AbstractIntegrator) | | 100% | | n/a | 0 | 1 | 0 | 9 | 0 | 1 |
setMu(double) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
createMapper(AbsoluteDate, double, OrbitType, PositionAngle, AttitudeProvider, Frame) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
addForceModel(ForceModel) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
getPVCoordinates(AbsoluteDate, Frame) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getMainStateEquations(AbstractIntegrator) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
removeForceModels() | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
setOrbitType(OrbitType) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
setPositionAngleType(PositionAngle) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
setInitialState(SpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
getForceModels() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getNewtonianAttractionForceModel() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getOrbitType() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getPositionAngleType() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |