| 摘要 |
A rocket nozzle having a plurality of internal vanes located downstream of the nozzle throat for imparting rotational spin to the rocket about its longitudinal axis. Each vane may have a nonablative body having a cross section symmetric with the nozzle axis and a consummable ablative body attached thereto to provide a composite cross section asymmetric to the nozzle axis. The ablative material, imparts spin stabilization to the rocket leaving only the symmetric nonablative vane portions, thus preventing excessive spin rates.
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