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In the design of solid propellant ducted rocket missile longitudinal channel control system, the controllability,economical efficiency and safety of ducted rocket should be considered. The ducted rocket itself should be fully verified by experiments, and the problems should be found and solved through experiments, to create conditions for the control of the missile. In this paper, one method is proposed with afterburning chamber control strategy. Based on mathematical linearization control model of solid propellant ducted rocket, the control rate is designed and following the model is simulated. As a result, the simulation results show that the afterburning chamber control system from this paper can realize energy control, and the inlet can be protected to meet ducted rocket’s requirements.