CAJ | 학술논문

应用数值方法,考虑弹体结构与气流的耦合作用,对空中跨音速飞行条件下导弹壳体的动态特性进行研究.得到作用于弹性壳体的气动脉动压力,同时得到弹体仪器舱段上节点的位移、速度、加速度脉动情况,这些将为分析导弹仪器舱内仪器设备的抗振性能提供支持数据.对比弹性弹体模型和刚性弹体模型的受载情况,以此说明对于流固耦合作用的考虑是否充分(结构弹性变形是否被考虑)直接影响弹体受力特性的研究,从而影响结构振动特性的研究.
응용수치방법,고필탄체결구여기류적우합작용,대공중과음속비행조건하도탄각체적동태특성진행연구.득도작용우탄성각체적기동맥동압력,동시득도탄체의기창단상절점적위이、속도、가속도맥동정황,저사장위분석도탄의기창내의기설비적항진성능제공지지수거.대비탄성탄체모형화강성탄체모형적수재정황,이차설명대우류고우합작용적고필시부충분(결구탄성변형시부피고필)직접영향탄체수력특성적연구,종이영향결구진동특성적연구.
Considering the interaction between airflow and missile structure, dynamic characteristic of transonic flying missile was studied through numerical method. Values of fluctuating aerodynamic force acting on the elastic missile structure were obtained with fluctuating-values of displacement, velocity, and acceleration for nodes on missile instrument-bay shell. These values can provide important support for analyzing the anti-vibration performance of instruments. Properties of fluctuating aerodynamic loads born respectively by elastic missile-structure model and rigid missile-structure model were compared, in order to show whether the elastic deformation is considered will lead to different results about structural bearing-load performance, and then different results about structural dynamic characteristic.