integrateDynamics(AbsoluteDate, boolean) | | 89% | | 90% | 1 | 6 | 2 | 30 | 0 | 1 |
propagate(AbsoluteDate) | | 79% | | 75% | 1 | 3 | 1 | 5 | 0 | 1 |
secondary(SpacecraftState) | | 96% | | 75% | 1 | 3 | 1 | 10 | 0 | 1 |
secondaryDerivative(SpacecraftState) | | 96% | | 75% | 1 | 3 | 1 | 10 | 0 | 1 |
propagate(AbsoluteDate, AbsoluteDate) | | 100% | | 100% | 0 | 5 | 0 | 18 | 0 | 1 |
updateAdditionalStatesAndDerivatives(SpacecraftState, ODEStateAndDerivative) | | 100% | | 100% | 0 | 3 | 0 | 12 | 0 | 1 |
createInitialState(SpacecraftState) | | 100% | | 100% | 0 | 3 | 0 | 10 | 0 | 1 |
getManagedAdditionalStates() | | 100% | | 100% | 0 | 2 | 0 | 6 | 0 | 1 |
convert(SpacecraftState) | | 100% | | n/a | 0 | 1 | 0 | 6 | 0 | 1 |
AbstractIntegratedPropagator(ODEIntegrator, PropagationType) | | 100% | | n/a | 0 | 1 | 0 | 9 | 0 | 1 |
isAdditionalStateManaged(String) | | 100% | | 100% | 0 | 4 | 0 | 7 | 0 | 1 |
addAdditionalDerivativesProvider(AdditionalDerivativesProvider) | | 100% | | 100% | 0 | 2 | 0 | 6 | 0 | 1 |
setAttitudeProvider(AttitudeProvider) | | 100% | | n/a | 0 | 1 | 0 | 5 | 0 | 1 |
createODE(ODEIntegrator) | | 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(double) | | 100% | | n/a | 0 | 1 | 0 | 4 | 0 | 1 |
setUpUserEventDetectors() | | 100% | | 100% | 0 | 2 | 0 | 4 | 0 | 1 |
convert(ODEStateAndDerivative) | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
getEphemerisGenerator() | | 100% | | n/a | 0 | 1 | 0 | 3 | 0 | 1 |
initMapper() | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
setUpEventDetector(ODEIntegrator, EventDetector) | | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
addEventDetector(EventDetector) | | 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 |
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 |
setUpStmAndJacobianGenerators() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
beforeIntegration(SpacecraftState, AbsoluteDate) | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |
afterIntegration() | | 100% | | n/a | 0 | 1 | 0 | 1 | 0 | 1 |