考虑导弹自动驾驶仪动态特性的H_∞导引律
H_∞ Guidance Law Accounting for Dynamics of Missile Autopilot
查看参考文献20篇
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文摘
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为拦截机动目标并克服导弹自动驾驶仪动态特性对制导性能的不利影响,提出一种考虑自动驾驶仪动态特性的H_∞鲁棒导引律。将综合制导与自动驾驶仪2阶动态特性的3阶线性时变状态方程表示为多面体线性参变系统,应用线性矩阵不等式(LMI)方法设计了具有参数依赖增益的线性状态反馈形式的新型H_∞鲁棒导引律,参数依赖增益中的系数是通过求解以LMI为约束的凸优化问题得到的。仿真结果表明:尽管不需要目标加速度的任何信息,新型H_∞导引律依然具有较强的鲁棒性,且具有较高的制导精度。 |
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其他语种文摘
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In order to intercept the maneuvering targets and overcome the adverse effect of the missile autopilot's dynamics on the guidance performance, this paper aims to propose a H_∞ robust guidance law with the dynamics of the autopilot considered. The third-order linear time-varying state equation for the integrated guidance and second-order dynamics of autopilot is expressed as a polytopic LPV system. A novel H_∞ robust guidance law, in the form of linear state-feedback with parameter-dependent gain, is designed using LMI method. The coefficients in the parameter-dependent gain are obtained by solving a convex optimization problem with LMI constraints. Simulation results indicate that, even if the target's acceleration is not known, the H_∞ guidance law can still achieve strong robustness and obtain high guidance precision. |
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来源
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兵工学报
,2016,37(7):1194-1202 【核心库】
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DOI
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10.3969/j.issn.1000-1093.2016.07.006
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关键词
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控制科学与技术
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导引律
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线性矩阵不等式
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自动驾驶仪动态特性
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H_∞控制
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鲁棒性
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地址
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哈尔滨工业大学航天学院, 黑龙江, 哈尔滨, 150001
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语种
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中文 |
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文献类型
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研究性论文 |
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ISSN
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1000-1093 |
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学科
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航天(宇宙航行) |
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基金
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国家自然科学基金项目
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文献收藏号
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CSCD:5778478
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