针对导弹驾驶仪结构复杂,设计点越来越多的特点,提出了基于粒子群算法的导弹驾驶仪参数设计方法。利用设定的适应度函数,将改进和优化后的粒子群算法应用到控制器参数设计中,寻优确定结果。从依赖于设计者经验的人工设计,效率低下,上升到统一的专家准则,提升效率和可靠性。还可以综合各类准则,达到设计和验证同步进行,兼顾各项指标。仿真校验表明,在导弹驾驶仪模型上,取得了较好的设计结果,并且具有广阔的工程应用价值。 In view of the complex structure of missile pilot and the increasing number of design points, a parametric design method of missile pilot based on particle swarm optimization is proposed. By using the fitness function, the improved and optimized particle swarm optimization algorithm is applied to the controller parameter design to find the optimal result. From artificial designs that rely on designer experience, inefficiencies rise to uniform expert guidelines that increase efficiency and reliability. You can also integrate various guidelines to achieve the design and verification simultaneously, taking into account the indicators. Simulation results show that the missile pilot model has achieved good design results and has a wide range of engineering applications.