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Experimental and numerical investigation of a jet vane of thrust vector control system

Söğütcü, Burak.
Thrust vectoring is generally used in tactical missile systems when attitude control with conventional control systems is inadequate. One of the most widely used thrust vectoring method is to employ jet vanes in the divergent section of the rocket motor nozzle to have the desired thrust vectoring. In the present study, the flow over the jet vane of a thrust vector control system is investigated using both numerical and experimental techniques. Three dimensional, unsteady and viscous flow over the jet vane is solved numerically, in which the interaction of high temperature and high speed combustion gas flow with the jet vane located in the exit plane of the solid rocket motor nozzle is examined in detail. In addition, static firing tests of a rocket motor, which contains jet vanes at the nozzle exit plane, are conducted in the static rocket motor stand of TÜB˙ITAK-SAGE. The thrust and the side forces due to the jet vane are measured for different angles of attack values of jet vanes. The nozzle shock pattern in the presence of the jet vane is also visualized by using the Schlieren technique.