| 摘要 |
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 ).
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