Startup and cutoff of secondary hot gas injection thrust vector control system of solid rocket motor are simulated numerically with three-dimensional unsteady flow model. The influence of hot gas ejection and secondary injection in transient process on internal flow filed and interior ballistic performance of solid rocket motor are investigated. During startup process, visible difference on dynamic performance is displayed, compared with the situation of steady operation. Especially, lateral control force, chamber pressure and motor thrust are changed remarkably. The effect of unsteady characteristic should be paid attention to in aerocraft design. During cutoff process, strong pressure oscillation occurs in the flow field around the hot gas ejection hole and secondary hot gas injection hole. Dynamic load resulted from unsteady process would bring structure oscillation for aerocraft. Residual influence of jet flow disturbing force is obvious and reduces slowly with time. The effect of unsteady delayed characteristic should be paid attention to in control design. Conclusions obtained above provide technical guidance for future research on secondary hot gas injection thrust vector control system.
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