AttitudeSequence transition not computed with analytical propagators

In the case of an attitude transition is triggered by an event detector during an analytical propagation, the attitude of the satellite is not correctly computed if the beginning of the propagation is before the transition and the end of the propagation is after the transition.

The origin of the bug is : the final SpacecraftState is computed before the event triggering, but the attitude transition is computed only after the events triggering. So the returned SpacecraftState is computed with the initial attitude law, not the updated one after the transition.