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For a solid propellant rocket ramjet engine missile, the economical efficiency of engine and reliability of inlet should be fully considered in trajectory planning. According to the real time flight state, trajectory planning should fulfill the requirements as regulating gas flow for optimize control, and limit the pressure of afterburning chamber to satisfy the needs of supersonic inlet safety margin. In this paper, one method is proposed with velocity control strategy for integrated missile and engine system. Based on mathematical linearization control model of missile and engine, the control rate is well designed and following the model is simulated. As a result, the simulation results show that the longitudinal channel control system from this paper can realize energy control for missile, and the inlet can be protected to meet ramjet engine’s requirements.