accelerationDerivatives(SpacecraftState, String) | | 59% | | 50% | 2 | 4 | 4 | 11 | 0 | 1 |
setParameter(String, double) | | 0% | | 0% | 2 | 2 | 5 | 5 | 1 | 1 |
getParameter(String) | | 0% | | 0% | 2 | 2 | 4 | 4 | 1 | 1 |
ConstantThrustManeuver(AbsoluteDate, double, double, double, Vector3D) | | 100% | | 100% | 0 | 2 | 0 | 11 | 0 | 1 |
accelerationDerivatives(AbsoluteDate, Frame, FieldVector3D, FieldVector3D, FieldRotation, DerivativeStructure) | | 100% | | 100% | 0 | 2 | 0 | 5 | 0 | 1 |
getEventsDetectors() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
addContribution(SpacecraftState, TimeDerivativesEquations) | | 100% | | 100% | 0 | 2 | 0 | 4 | 0 | 1 |
getISP() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getThrust() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getFlowRate() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |