CAJ | 학술논문

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。
이용MSC．Nastran중기탄분석연건건립료도탄타면급탄신적전진동역학유한원모형화기동모형，대불동지탱강도、불동타면중심상태적타면진행료전진특성분석，발현지탱강도화타면중심변화회사타면적모태발생교명현적변화，종이대도탄타면전진림계속도산생교대영향，병가통과제고타면뉴전지탱강도화조정타면질량분포량항조시우화，만족도탄타면공정연제시적전진요구。
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.