The invention relates to a rocket engine nozzle comprising a system for controlling
jet separation of the flow in the nozzle, wherein said control system exhibits
a plurality of separation triggering elements (5, 10) arranged in such a
way as to generate, from mutually spaced initiation points (9), distinct
zones (6) of jet separation, so as to form a three-dimensional separation
of the flow.
The flow control system can exhibit at least two triggering elements (5, 10).