| 引用本文: | 于剑桥,罗冠辰,文仲辉.基于准线性化模型设计导弹H∞增益调度自动驾驶仪[J].控制理论与应用,2009,26(4):.[点击复制] |
| YU Jian-qiao,LUO Guan-chen,WEN Zhong-hui.Missile H∞ gain-scheduled autopilot design based on quasi-linear model[J].Control Theory and Technology,2009,26(4):.[点击复制] |
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| 基于准线性化模型设计导弹H∞增益调度自动驾驶仪 |
| Missile H∞ gain-scheduled autopilot design based on quasi-linear model |
| 摘要点击 1152 全文点击 624 投稿时间：2008-04-09 修订日期：2008-09-08 |
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| DOI编号 10.7641/ |
| 2009,26(4):- |
| 中文关键词 H∞增益调度控制 准线性化模型 LPV/μ控制方法 自动驾驶仪 |
| 英文关键词 H∞ gain-scheduled control quasi-linear model LPV/μ control method autopilot |
| 基金项目 兵器基金 |
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| 中文摘要 |
| 实现针对系统快变量攻角的自适应参数调节是导弹鲁棒增益调度自动驾驶仪设计的一个难点.为解决此问题,提出采用由状态替换方法建立的导弹准线性化模型作为设计模型,基于线性参数时变(LPV)/μ控制技术构造自动驾驶仪设计结构,并通过D-K-D迭代算法设计导弹H∞增益调度自动驾驶仪.所设计的自动驾驶仪不仅能够实现对马赫数和高度两个系统慢变量的自适应参数调节,还能实现对系统快变量攻角的自适应参数调节.非线性仿真结果验证了所提出方法的有效性. |
| 英文摘要 |
| It is a difficult problem for missile gain-scheduled autopilot design to realize adaptive parameter adjustment with respect to angle of attack,which is a fast variable of missile system. A new approach is developed to resolve this problem by adopting missile quasi-linear model established using state transformation method as design model, constructing autopilot design structure based on linear parameter varying (LPV)/μ control technique, and designing missile H∞ gain-scheduled autopilot through D-K-D iteration. The designed autopilot can not only adjust parameters with respect to flight Mach number and altitude, which are system slow variables, but also angle of attack,which is system fast variable. Nonlinear simulation validates the effectiveness of the proposed approach. |
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