固定翼双旋弹动力学特性分析

固定翼双旋弹作为一种特殊的弹道修正弹，在飞行过程中其前体弹道修正引信（CCF）和后体以不同转速绕弹轴旋转。根据固定翼双旋弹气动不对称的特性，推导出固定翼双旋弹的动力学模型，经过模型简化，得到其非齐次角运动方程，根据这个角运动方程对角运动特性和飞行稳定性进行了分析。结果显示：当CCF转速固定时，转速的大小和滚转的方向都会影响弹体的角运动特性，由于弹体的共振，不合理的转速可能引起角运动的不稳定；当CCF转角固定时，弹体可以获得与CCF的鸭翼安装角近似呈正比的弹道修正能力。对固定翼双旋弹的飞行稳定性判据进行了研究，飞行稳定性判据为固定翼双旋弹前后体转速和初始射角的设计提供了参考。

Analysis of Dynamic Characteristics of Fixed-wing Dual-spin Projectiles

Fixed-wing dual-spin projectile is a class of trajectory correction projectile, of which the forward course correction fuze (CCF) and aft body can rotate at different spin rates during flight. According to its aerodynamic asymmetry characteristics, the dynamic model of fixed-wing dual-spin projectiles is derived. Nonhomogeneous angular motion equations are calculated by simplifying the model. The angular motion characteristics and stability of fixed-wing dual-spin projectiles are studied based on the angular motion equations. The results show that, when the roll rate of the CCF is constant, the angular motion characteristics of projectile are greatly affected by both the roll rate and rolling direction, and an unreasonable roll rate may cause the instability of angular motion because of the resonance; when the spin angle of the CCF stays at any angular position, the projectile has the course correction ability which is proportional to the installation angle of the canard wings. Ultimately the stability criterion of fixed-wing dual-spin projectiles is studied.