addForceModel(ForceModel) |   | 81% |   | 83% | 1 | 4 | 3 | 12 | 0 | 1 |
resetInitialState(FieldSpacecraftState) |   | 73% |   | 50% | 1 | 2 | 1 | 5 | 0 | 1 |
removeForceModels() |  | 0% | | n/a | 1 | 1 | 2 | 2 | 1 | 1 |
initializeAttitudeProviderForDerivatives() |   | 81% |   | 50% | 1 | 2 | 0 | 3 | 0 | 1 |
tolerances(CalculusFieldElement, CalculusFieldElement, FieldOrbit, OrbitType) |  | 100% |  | 100% | 0 | 4 | 0 | 26 | 0 | 1 |
FieldNumericalPropagator(Field, FieldODEIntegrator, AttitudeProvider) |  | 100% | | n/a | 0 | 1 | 0 | 12 | 0 | 1 |
tolerances(CalculusFieldElement, FieldOrbit, OrbitType) |  | 100% | | n/a | 0 | 1 | 0 | 5 | 0 | 1 |
hasNewtonianAttraction() |  | 100% |   | 75% | 1 | 3 | 0 | 2 | 0 | 1 |
setMu(CalculusFieldElement) |  | 100% |  | 100% | 0 | 2 | 0 | 4 | 0 | 1 |
createMapper(FieldAbsoluteDate, CalculusFieldElement, OrbitType, PositionAngleType, AttitudeProvider, Frame) |  | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
FieldNumericalPropagator(Field, FieldODEIntegrator) |  | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
getMainStateEquations(FieldODEIntegrator) |  | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
setIgnoreCentralAttraction(boolean) |  | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
superSetMu(CalculusFieldElement) |  | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
getAllForceModels() |  | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
setOrbitType(OrbitType) |  | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
setPositionAngleType(PositionAngleType) |  | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
setInitialState(FieldSpacecraftState) |  | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
getOrbitType() |  | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
superGetOrbitType() |  | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getPositionAngleType() |  | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |