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。
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.
出处
《导弹与航天运载技术》
北大核心
2010年第4期1-5,9,共6页
Missiles and Space Vehicles
关键词
气动弹性
稳定性
颤振
气动伺服弹性
Aeroelasticity
Stability
Flutter
Servo aeroelasticity