Abstract：To resolve the problem of low terminal velocity of high and long-range ballistic missiles, combiningthe
application of a double-pulse solid rocket motor in air defense missiles, this study analyzed the influence of thrust of the
solid rocket motor and ignition interval of the two-stage engine on the terminal velocity of a high and long-range ballistic
missile. Focusing on maximizing the terminal velocity of air defense missiles on highand long-rangetrajectories, the
thrust and ignition interval of the double-pulse solid rocket motor were optimized using the improved Classified
Chemical Reaction Optimization (CCRO) algorithms established in this study. Finally, the optimal energy distribution
scheme for the motorenhancing the missile’s terminal velocity was achieved.
