Penetration design for the boost phase of near space aircraft

Near space aircraft enters a glide phase after the boost phase. A low glide altitude can reduce the hostile warning time to enhance penetration possibility. Therefore a lower boost phase altitude is favorable. The trajectory optimization of the boost phase for a three-stage solid rocket is an optimal control problem subject to various constraints. This problem is reformulated as a nonlinear programming by using Gauss pseudospectral method (GPM). The angle of attack sequence satisfying the constraint conditions can be obtained by using sequential quadratic programming(SQP). Finally, simulation results verify the effectiveness of the algorithm.