采用慢变参数法研究了低速旋转昆翼式弹丸在大攻角飞行时,受非线性Magnus力矩作用的共振不稳定性,求出了共振期间的角运动的近似解析解.经数值计算表明精度是可以保证的.还着重讨论了弹轴自由运动趋于稳态后和一般情况下发生共振期间的攻角变化规律及其特性,并得出了共振期间强迫响应稳定的条件。 The slow-changing parameter method was used to study the resonant instability caused by the nonlinear Magnus moment when the low-velocity rotating warhead wing projectile was flying at high angle of attack, and the approximate analytical solution of the angular motion during the resonance was obtained. The numerical results show that the accuracy It is guaranteed that the change of the angle of attack during the period of resonance after the free movement of the elastic shaft tends to be steady and under normal circumstances and the characteristics of the angle of attack during the resonance are also discussed emphatically.