Nozzles with rotatable sections for variable thrust
AssigneeAerojet-General Corporation
InventorsStephen Mano, Robert Black
Life of this patent
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Abstract
Thrust variability in a nozzle is achieved by constructing the nozzle in two parts, one of which is rotatable relative to the other. The nozzle includes a convergent section, a throat, and a divergent section, all of which are formed in the annular region between a centerbody and a shell. The rotation produces a variation in the cross-sectional area of the nozzle by bringing apertures in the two parts into and out of alignment and thereby partially or fully opening and closing the flow passage through the convergent section, throat, and divergent section.
Claims10
In a nozzle comprising a centerbody and a shell with an annular gap therebetween, said annular gap comprising a convergent section, a throat, and a divergent section,
- the improvement wherein said rocket nozzle comprises first and second parts, each said part comprising a plurality of apertures distributed around said centerbody, said first part being rotatable relative to said second part to cause apertures of said first part to overlap with apertures of said second part to a variable degree and thereby provide said nozzle with a variable thrust by providing said flow passage with a variable cross-sectional area.
Dependencies are inferred from the claim text.