In order to solve the longitudinal control problem of the boost section of certain type hypersonic aircraft, the longitudinal control strategy of the boost section of certain type hypersonic aircraft was studied based on the rocket-propelled vertical launch flight. According to the flight environment and the structure of the aircraft, the characteristics of the aircraft are analyzed and the control difficulties are analyzed. The time-varying model of motion parameters is established. The strategies of longitudinal attitude control, stabilization control and angle-of-attack protection are proposed. The analysis results show that the pitch angle controller has better stability than the angle of attack controller in terms of stability and maneuverability, and the pitch rate instruction inner loop has better robustness in boost phase than the damping inner loop.