Aiming at the design problem of the guidance and control system of glide-booster vehicles, the aircraft control system is modeled first, the three-channel transfer function is established and the control loop is designed to facilitate the control implementation of the subsequent simulation, the three-channel coupling problem of Bank to turn (BTT) control is discussed and the solution is given. Then, aiming at the problem of the range extension of airborne missile aircraft and the effective attack on specific targets in the final guidance stage, the trajectory design of glide-boost stage based on the maximum lift-drag ratio and the trajectory design of final guidance stage based on the specified fall angle constraint are proposed. The aerodynamic data of given trajectory characteristic points measured experimentally are processed to obtain the maximum lift-drag ratio corresponding to the angle of attack under different Mach numbers. Aiming at the Mach number-angle of attack point pair obtained, the polynomial function is used to fit, and the control law of the angle of attack in the glide-boost phase is obtained. Biased proportional guidance is adopted in the final guidance segment. Based on the proportional guidance, the biased term with the final falling angle constraint as the parameter is introduced as the control law of the final guidance segment. Finally, the trajectory simulation results show that the maximum lift-drag ratio glide trajectory has a significant range-increasing effect under the condition of meeting the final velocity constraint, and the bias proportional guidance law can achieve accurate target attack while converging to the specified angle of fall.