Ascent Phase Trajectory Optimization for Missile with Booster Based on the Gauss Pseudospectral Method

In this paper, the ascent phase trajectory optimization problem for missile with two-stage booster is studied. Firstly, in consideration of the coupling relationship between the aerodynamic and the state of the missile, such as speed, altitude, and center of mass, the effect of rudder is introduced to establish a modified model of aerodynamic parameters. Secondly, in view of the discontinuous thrust when dispensing, a strategy is designed to select the switch-flight-state. In this regard, considering the constraints such as overload, dynamic pressure, and terminal trajectory, the trajectory optimization design of the missile ascending phase is carried out based on the adaptive pseudo-spectrum method. Finally, the simulation analysis verifies the effectiveness of the method.