尾翼式柔性弹箭飞行稳定性研究

建立了低速旋转的尾翼式弹箭飞行运动和柔性弯曲变形耦合的动力学模型和一般运动方程组，以梁的弯曲理论为基础，推导了柔性弹箭的弯曲变形方程，在准静态变形条件下推导出了柔性弹箭的攻角运动方程，并由此获得了尾翼式柔性弹箭的静态稳定性条件和动态稳定性条件，从中可以看出柔性变形对弹箭飞行稳定性的影响，为大长细经弹箭的设计提供了重要的理论依据。

THEORY OF FLIGHT STABILITY FOR FLEXIBLE FINNED MISSILES

In the paper, a dynamic coupled model of the flight motion and the flexible bending motion for a finned missiles with low spin rate is created and the general equations of motion is developed. Based on the bending theory of beam, the equation of bending deformation of a flexible missile is formulated. For the case of quasi static deformation, the equation of attack of a flexible missile are obtained, and hence the conditions of static and dynamic stabilization are presented in the paper. The bending effects are shown to decrease the flight stabilization of finned projectiles.