| 导弹自适应结构滤波器的设计与仿真 |
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| 引用本文： | 楚龙飞,吴志刚,杨超,唐长红.导弹自适应结构滤波器的设计与仿真[J].航空学报,2011,32(2):195-201. |
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| 作者姓名： | 楚龙飞 吴志刚 杨超 唐长红 |
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| 作者单位： | 1. 北京航空航天大学航空科学与工程学院,北京,100191
2. 中国航空工业集团公司第一飞机设计研究院,陕西西安,710089 |
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| 基金项目： | 国家自然科学基金，航天科技创新基金 |
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| 摘 要： | 由于飞行过程中飞行环境与自身特性的大幅度变化,导弹的飞行动力学特性和结构模态参数变化范围很大,难以精确建模,对导弹的气动伺服弹性稳定性带来潜在危险,传统结构滤波器的适用性也难以保证.提出一种自适应结构滤波器的设计方法,利用导弹输入指令和传感器输出的采样信号,建立导弹的自回归滑动平均(ARMA)模型;采用递归最小二乘算法...
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| 关 键 词： | 气动伺服弹性 结构滤波器 自适应控制 系统在线辨识 导弹 |
Design and Simulation of Adaptive Structure Filter for Missiles |
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| CHU Longfei,WU Zhigang,YANG Chao,TANG Changhong.Design and Simulation of Adaptive Structure Filter for Missiles[J].Acta Aeronautica et Astronautica Sinica,2011,32(2):195-201. |
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| Authors: | CHU Longfei WU Zhigang YANG Chao TANG Changhong |
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| Institution: | CHU Longfei1,WU Zhigang1,YANG Chao1,TANG Changhong2 1.School of Aeronautic Science and Engineering,Beijing University of Aeronautics and Astronautics,Beijing 100191,China 2.The First Aircraft Institute,Aviation Industry Corporation of China,Xi'an 710089,China |
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| Abstract: | Because of the existence of significant variation of the environment and vehicle characteristics during the flight of missiles,the flight dynamic characteristics and the structure modal parameters of missiles also vary in a wide range,thus making it hard to model the system accurately.This brings potential danger to the aeroservoelastic stability of missiles.Conventional structure filters are often unsuitable for use.This article presents a new design method of adaptive structure filters for missiles.Sample... |
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| Keywords: | aeroservoelasticity structure filter adaptive control system online-identification missile |
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