基于MSC.Nastran的导弹舵面颤振分析与优化  

Missile Rudder Surface Flutter Analysis and Optimization Based on MSC. Nastran

作　　者：沈颖[1] 张鹏[2] 寇艳丽[2] 杨硕[1] 

机构地区：[1]驻中国空空导弹研究院军事代表室,河南洛阳471009 [2]中国空空导弹研究院,河南洛阳471009

出　　处：《航空兵器》2014年第5期19-22,共4页Aero Weaponry

摘　　要：利用MSC.Nastran中气弹分析软件建立了导弹舵面及弹身的颤振动力学有限元模型和气动模型,对不同支撑刚度、不同舵面重心状态的舵面进行了颤振特性分析,发现支撑刚度和舵面重心变化会使舵面的模态发生较明显的变化,从而对导弹舵面颤振临界速度产生较大影响,并可通过提高舵面扭转支撑刚度和调整舵面质量分布两项措施优化,满足导弹舵面工程研制时的颤振要求。Using MSC.Nastran aero elastic analysis software, the flutter dynamic finite element mod-el and aerodynamic model of the missile body and rudder surface are established.By analyzing the rudder surface flutter characteristics for the different support stiffness and different gravity center state, it is found that the support stiffness and the rudder surface gravity change will make the rudder mode change obvious-ly, and will produce a greater impact on the critical velocity to missile rudder flutter.This can be opti-mized by the two measures, which are increasing the rudder torsion support stiffness and adjusting the rudder surface mass distribution to meet the flutter requirements of engineering development of missile rud-der.

关 键 词：导弹舵面 颤振分析 有限元模型 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程] TJ011.3