Synthesis of a high-performance two-pulse-motor-propelled missile by simultaneous optimization of trajectory and propulsion systems in two operational scenarios is described. This work employed a quasiNewton parameter optimization scheme with penalty functions to meet terminal and path constraints. The trajectory control variables were parameterized using piecewise linear open-loop commands and piecewise constant linear feedback gains. The pulse motor parameters optimized were pulse split, average thrust levels, neutrality factors, pulse burn times, and the interpiilse delay. Optimization of the rocket motor thrust time curve in addition to the trajectory increased the range by up to 11% when compared with the trajectories optimized with originally specified rocket motor propulsion data.