本文介绍了一种关于大攻角飞行条件下，飞行器非线性动稳定性分析的数学方法。基于飞行器整体运动的低频特点（ｋ１），将动稳定性导数的概念推广到大攻角有限摆幅振荡飞行的稳定性分析，给出了逐次求取各阶动导数的摄动方法，导出了小参数形式的非线性动力学方程。结合常微分方程的定性理论，可以揭示大攻角飞行中的某些非线性特征，方法原则上可推广到多自由度问题。 This paper presents a mathematical approach to the analysis of aircraft nonlinear dynamic stability under high-angle-of-flight flight conditions. Based on the low frequency characteristic (k1) of the whole vehicle movement, this paper extends the concept of dynamic stability derivative to the stability analysis of finite amplitude oscillating flight at high angles of attack, and gives the perturbation method of sequentially obtaining the moving derivatives of each order. The nonlinear dynamical equations in the form of small parameters are derived. Combined with the qualitative theory of ordinary differential equations, some non-linear features in flight at high angles of attack can be revealed. In principle, the method can be generalized to multi-degree of freedom problems.