带有燃气舵的导弹舵面颤振分析方法  

Rudder flutter analysis method of missile with jet vane

作　　者：荆志伟[1] 吴志刚[1] 杨超[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院

出　　处：《北京航空航天大学学报》2010年第8期991-995,共5页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家自然科学基金资助项目(90716006,10902006)

摘　　要：传统的颤振分析方法以及商业软件不能分析带有燃气舵的导弹舵面颤振.为此,提出了一个解决带有燃气舵的导弹舵面颤振分析方法.采用动态子结构方法建立带有燃气舵的导弹舵面颤振状态空间运动方程和分析方法,结构质量矩阵和刚度矩阵分成对应于广义坐标的块矩阵;可以考虑不同来流气动效应和翼-体组合对气流的影响,用非定常气动力有理函数拟合法建立时域非定常气动力求解模型.算例数值结果表明：燃气舵舵轴与空气舵舵轴刚度之间的不利耦合会让空气舵颤振速度降低.上述分析方法和计算结果为导弹设计提供参考.Traditional flutter analysis and commercial software can not analyze rudder flutter of missile with jet vane.An approach for solving rudder flutter of missile with jet vane was presented.Dynamic sub-structure method was applied to establish dynamic formulation of rudder flutter in state space and analysis method of missile with jet vane.Structural mass matrix and stiffness matrix were partitioned according to the vectors of generalized coordinates.The aeroelastic influence of different stream and the influence of wing-body on the airstream were considered.The calculation model of unsteady aerodynamics in time-domain was based on the rational aerodynamic approximation method.Numerical results indicate that adverse stiffness coupling between jet vane shaft and rudder shaft can deteriorate the rudder flutter velocity.The analysis method and results above can supply reference for the missile design.

关 键 词：气动弹性 颤振 燃气舵 空气舵 动态子结构方法 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]