中文摘要：

建立了具有气动力／直接侧向力混合控制的导弹动力学模型，采用反馈加前馈控制结构，设计了导弹复合控制系统，实现了气动力／直接侧向力的解耦控制。建立了导弹复合控制系统性能代价函数，并采用进化策略实现了复合控制系统参数的多目标优化。仿真结果表明：进化策略收敛速度快，优化以后的导弹复合控制系统具有很好的快速大机动跟踪能力，且直接力控制有效补偿了气动面控制效益低下和非最小相位系统造成的响应延迟。

英文摘要：

The blended dynamic model of missile with aerodynamic fin and side thruster is developed. The mixed missile control system combined with feedback controller and feedforward controller is designed, which results in the uncoupled control between the aerodynamic fin and side thruster. The multi-objective performance cost function of the missile blended control system is established, and the parameters of the blended control system are optimized based on evolutionary strategies （ES）. The simulation results show the fast convergence of the ES algorithms. The optimized blended control system of missile can track the great maneuver acceleration command accurately and rapidly. The reduced aerodynamic control effectiveness in high altitude or at high angle of attack and the response delay of missile caused by nonminimal phase system can be compensated by the control of direct side thruster.