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 | 19 | 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 |
resetInitialState(SpacecraftState, PropagationType) |  | 100% | | n/a | 0 | 1 | 0 | 2 | 0 | 1 |
lambda$propagate$0(SpacecraftState, EventDetector) |  | 100% | | n/a | 0 | 1 | 0 | 1 | 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 |