导弹的LPV建模与混合H2/Hinf自动驾驶仪设计

导弹在飞行过程中,高度、速度、攻角、动压等变量变化剧烈,如何在其大范围变化情况下设计满足要求的自动驾驶仪是研究的重点所在.论文利用线性参数时变方法对导弹动态系统完成建模过程,并采用线性分式变换将控制器设计问题转换为设计名义主控制器与根据飞行状态实时调整的参数控制器的过程,同时以混合H2/Hinf为性能指标,利用线性矩阵不等式对上述问题完成求解.最后以导弹自动驾驶仪设计为例对文中算法进行仿真验证,经验证表明此算法可以满足跟踪指令输入并具有较好的鲁棒稳定性.

LPV Modeling and Mixed H2/Hinf Design for Missile Autopilot

When missile is in flight, height, velocity, attack angle and dynamic pressure change dramatically, How to design autopilot to adapt the large-scale changed parameters is always the emphases. In this article a linear parameter-varying method is used in modeling process of missile, linear fractional transformation is used to change the controller synthesis prob- lem to design a nominal controller and a parameter-varying controller with flight state. Mixed H2/H-infinity performance in- dex is used and Linear matrix inequality method is used to solve this problem. A missile autopilot design problem is used to verify this algorithm. Result shows that this algorithm can satisfy the command and has excellent robust stability.