中文摘要：

提出了具有异构多控制机构的飞行器复合控制决策与管理系统结构,建立了具有气动力/推力矢量/直接侧向力的异构多操纵机构的飞行器动力学模型,提出了模糊自适应控制分配与复合控制器优化集成设计方案。设计了基于参考模型的模糊自适应控制分配策略,使气动力/推力矢量/直接力任意形式组合及动态分配过程中复合执行机构等效动态特性与参考模型一致。采用进化策略对导弹复合控制系统参数进行了多目标优化设计。分别针对不同的组合形式进行了仿真研究,证明了具有异构多操纵机构的飞行器复合控制系统具有很好的快速大机动跟踪能力,实现了飞行器气动力/推力矢量/直接侧向力之间不同形式组合控制系统的自适应控制分配。

英文摘要：

The Scheme of decision and management system for combinational flight control with differential kinds of control effectors were proposed. The blended dynamic model of missile with aerodynamic fin, thruster vector control and side thruster was developed. The design scheme integrating control allocation with blended controller optimizing was proposed. Control allocation strategy based on fuzzy logic and model reference adaptive control was developed, which made the equivalent dynamics of the blended actuators between the aerodynamic fin, thruster vector control and side thruster equal to the one of the reference model. The parameters of the blended control system were selected by optimizing a multi-objective cost function using evolutionary strategies （ES）. The simulations on different kinds of control combinations demonstrated the blended control system had strong abilities of tracking high maneuver acceleration command rapidly and implementing the adaptive control allocation among the aerodynamic fin, thruster vector control and side thruster with different combinations.