舵机动态响应下导弹阻尼回路稳定性

V249; 针对导弹控制参数稳定区域的研究大多忽略了舵机的动态响应过程对参数稳定区域的影响,首先建立了阻尼驾驶仪控制的导弹动力学方程以及舵机的动力学方程,然后考虑舵机的稳态响应和动态响应,应用劳斯判据给出了非旋转弹阻尼反馈增益与舵机控制参数的动态关系.为推导旋转弹阻尼反馈增益的稳定区域,分析了舵机在准弹体坐标系下的表达式,然后采用复姿态角方法和Lyapunov稳定性判据,给出了旋转弹动态稳定性条件.最后以某一导弹飞行参数为例进行了仿真,验证了本文所得出的稳定性条件的有效性....

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Published in系统工程与电子技术 Vol. 44; no. 10; pp. 3200 - 3206
Main Authors 周志明, 刘振, 易建强, 姚晓先
Format Journal Article
LanguageChinese
Published 中国科学院自动化研究所,北京100081%北京理工大学宇航学院,北京100081 01.10.2022
Subjects
舵机动态响应
Lyapunov稳定性判据
阻尼回路
导弹
复姿态角方法
Online AccessGet full text
ISSN1001-506X
DOI10.12305/j.issn.1001-506X.2022.10.24

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Abstract V249; 针对导弹控制参数稳定区域的研究大多忽略了舵机的动态响应过程对参数稳定区域的影响,首先建立了阻尼驾驶仪控制的导弹动力学方程以及舵机的动力学方程,然后考虑舵机的稳态响应和动态响应,应用劳斯判据给出了非旋转弹阻尼反馈增益与舵机控制参数的动态关系.为推导旋转弹阻尼反馈增益的稳定区域,分析了舵机在准弹体坐标系下的表达式,然后采用复姿态角方法和Lyapunov稳定性判据,给出了旋转弹动态稳定性条件.最后以某一导弹飞行参数为例进行了仿真,验证了本文所得出的稳定性条件的有效性.
AbstractList V249; 针对导弹控制参数稳定区域的研究大多忽略了舵机的动态响应过程对参数稳定区域的影响,首先建立了阻尼驾驶仪控制的导弹动力学方程以及舵机的动力学方程,然后考虑舵机的稳态响应和动态响应,应用劳斯判据给出了非旋转弹阻尼反馈增益与舵机控制参数的动态关系.为推导旋转弹阻尼反馈增益的稳定区域,分析了舵机在准弹体坐标系下的表达式,然后采用复姿态角方法和Lyapunov稳定性判据,给出了旋转弹动态稳定性条件.最后以某一导弹飞行参数为例进行了仿真,验证了本文所得出的稳定性条件的有效性.
Author 易建强
姚晓先
刘振
周志明
AuthorAffiliation 中国科学院自动化研究所,北京100081%北京理工大学宇航学院,北京100081
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YAO Xiaoxian
ZHOU Zhiming
LIU Zhen
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Lyapunov稳定性判据
阻尼回路
导弹
复姿态角方法
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