对于大长径比飞行体,需要获取弹体的固有动态特性,来进一步分析其飞行结构强度和飞行稳定性。文中利用模态识别技术进行弹体的模态试验,得到了弹体的固有特性。并利用其固有特性,求解基于模态坐标下的火箭弹气动弹性运动方程,得到了火箭弹的临界颤振速度,为其结构动态特性的修改及优化设计提供充分的依据。

For large slenderness ratio vehicles, the natural dynamic characteristics need to be obtained in flight for further analysis of structural strength and stability in flight. Using modal identification technology in modal test, the inherent characteristics of projectile were obtained, and its inherent characteristics were used for solving the aeroelastic motion equation of modal coordinates. The flutter critical speed can be obtained and the dynamic characteristics of the structure to provide sufficient basis for modification and optimization design.