integrateDynamics(FieldAbsoluteDate) | | 90% | | 87% | 1 | 5 | 2 | 31 | 0 | 1 |
propagate(FieldAbsoluteDate) | | 79% | | 75% | 1 | 3 | 1 | 5 | 0 | 1 |
secondary(FieldSpacecraftState) | | 96% | | 75% | 1 | 3 | 1 | 10 | 0 | 1 |
secondaryDerivative(FieldSpacecraftState) | | 96% | | 75% | 1 | 3 | 1 | 10 | 0 | 1 |
propagate(FieldAbsoluteDate, FieldAbsoluteDate) | | 100% | | 100% | 0 | 5 | 0 | 16 | 0 | 1 |
convert(FieldODEStateAndDerivative) | | 100% | | 100% | 0 | 3 | 0 | 16 | 0 | 1 |
createInitialState(FieldSpacecraftState) | | 100% | | 100% | 0 | 3 | 0 | 10 | 0 | 1 |
updateAdditionalStatesAndDerivatives(FieldSpacecraftState, FieldODEStateAndDerivative) | | 100% | | 100% | 0 | 3 | 0 | 12 | 0 | 1 |
getManagedAdditionalStates() | | 100% | | 100% | 0 | 2 | 0 | 6 | 0 | 1 |
convert(FieldSpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 6 | 0 | 1 |
FieldAbstractIntegratedPropagator(Field, FieldODEIntegrator, PropagationType) | | 100% | | n/a | 0 | 1 | 0 | 9 | 0 | 1 |
isAdditionalStateManaged(String) | | 100% | | 100% | 0 | 4 | 0 | 7 | 0 | 1 |
addAdditionalDerivativesProvider(FieldAdditionalDerivativesProvider) | | 100% | | 100% | 0 | 2 | 0 | 6 | 0 | 1 |
setAttitudeProvider(AttitudeProvider) | | 100% | | n/a | 0 | 1 | 0 | 5 | 0 | 1 |
createODE(FieldODEIntegrator) | | 100% | | 100% | 0 | 2 | 0 | 5 | 0 | 1 |
setOrbitType(OrbitType) | | 100% | | n/a | 0 | 1 | 0 | 4 | 0 | 1 |
setPositionAngleType(PositionAngleType) | | 100% | | n/a | 0 | 1 | 0 | 4 | 0 | 1 |
setMu(CalculusFieldElement) | | 100% | | n/a | 0 | 1 | 0 | 4 | 0 | 1 |
initMapper(Field) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
setUpUserEventDetectors() | | 100% | | 100% | 0 | 2 | 0 | 4 | 0 | 1 |
getEphemerisGenerator() | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
setUpEventDetector(FieldODEIntegrator, FieldEventDetector) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
addEventDetector(FieldEventDetector) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
setResetAtEnd(boolean) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
getIntegratorName() | | 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 |
getMu() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getAdditionalDerivativesProviders() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getEventsDetectors() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
clearEventsDetectors() | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
getResetAtEnd() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
initializeAttitudeProviderForDerivatives() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
isMeanOrbit() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getPropagationType() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getCalls() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getInitialIntegrationState() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getIntegrator() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
getBasicDimension() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
beforeIntegration(FieldSpacecraftState, FieldAbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
afterIntegration() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |