Abstract
Theme A PROCEDURE is presented for preliminary design of a liquid-injection thrust-vector-control (LITVC) system for solid-propellant rockets. In LITVC, a rocket jet is deflected for steering purposes by injecting liquid into the side of the nozzle exit flow (see Fig. 1). The liquid is preferably both dense and exothermally reactive. The injection produces side thrust and added axial thrust mainly by pressures on the nozzle wall caused by shock waves and addition of mass and energy to the flow.
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