| 导弹气动弹性稳定性分析 |
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| 引用本文： | 惠俊鹏,杨勇,杨建民.导弹气动弹性稳定性分析[J].导弹与航天运载技术,2010(4). |
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| 作者姓名： | 惠俊鹏 杨勇 杨建民 |
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| 作者单位： | 中国运载火箭技术研究院研发中心,北京,100076;中国运载火箭技术研究院研发中心,北京,100076;中国运载火箭技术研究院研发中心,北京,100076 |
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| 摘 要： | 以某导弹为例,从颤振和气动伺服弹性两方面对导弹气动弹性稳定性进行了分析研究.在颤振分析中,开展了全弹结构动特性计算,采用超声速偶极子格网法计算了高超声速非定常气动力,对导弹部件和全弹进行颤振计算分析,对空气舵舵系统刚度设计提出了要求.在气动伺服弹性稳定性分析中,建立了导弹俯仰通道气动伺服弹性运动方程,采用Nyquist方法分析了闭环系统的稳定性和稳定裕度.
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| 关 键 词： | 气动弹性 稳定性 颤振 气动伺服弹性 |
Analysis of Missile Aeroelastic Stability |
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| Hui Junpeng,Yang Yong,Yang Jianmin.Analysis of Missile Aeroelastic Stability[J].Missiles and Space Vehicles,2010(4). |
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| Authors: | Hui Junpeng Yang Yong Yang Jianmin |
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| Affiliation: | Hui Junpeng,Yang Yong,Yang Jianmin(Research , Development Center,China Academy of Launch Vehicle Technology,Beijing,100076) |
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| Abstract: | Aeroelastic stability of a missile(including flutter and servo aeroelasticity) is analyzed.Based on calculation of structure dynamic characteristics and supersonic unsteady aerodynamics of missile,flutter analysis is performed and thus design requirements for rudder system stiffness of the missile are proposed.In servo aeroelastic stability analysis,servo aeroelastic equation of pitch direction is established,and Nyquist method is used to calculate stability margins of close-loop system. |
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| Keywords: | Aeroelasticity Stability Flutter Servo aeroelasticity |
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