The injector is part of a jet propulsion apparatus. It is used for controlling the direction of thrust produced by a nozzle to thereby control the direction of movement of a rocket propelled missile. The nozzle is a converging-diverging De Laval type. The nozzle is provided with four angularly spaced discharge orifices. These orifices are of variable area, suitable valving apparatus being disposed directly adjacent the point of fluid discharge rather than remotely as in the prior art.
Variable Area Orifice Injector
1965
1 pages
Report
Keine Angabe
Englisch
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