考虑战斗机深失速状态的快速稳定改出问题，提出一种基于强迫振荡的有限时间深失速改出控制方法。针对深失速状态动力学特性表征需求，采用分岔理论进行分析并通过反向时间积分求解深失速吸引域。为从机理上给出准确的深失速恢复指令，基于扩展分岔分析在控制器设计中引入不稳定分岔对应的强迫振荡偏摆响应。针对深失速状态下的时变扰动和气动参数摄动影响，设计扰动观测器估计干扰项并借助神经网络处理模型不确定性，结合迎角跟踪误差反馈得到深失速改出控制器。基于李雅普诺夫稳定性分析证明了系统能够在有限时间内收敛。仿真结果表明，深失速中的战斗机能够降低迎角至安全区域并保持稳定可控，实现快速平稳的深失速状态恢复。

Considering the rapid and stable recovery from deep stall in fighter aircraft, a finite-time control strategy based on forced oscillation is proposed. To characterize the dynamics of deep stall state, bifurcation theory is employed for analysis, with the region of attraction boundaries determined through backward-time integration. For generating precise recovery commands in principle, an extended bifurcation analysis is conducted, and forced oscillation commands corresponding to unstable bifurcation points are incorporated into the controller design. To handle timevarying disturbances and aerodynamic parameter perturbations during deep stall, a disturbance observer is designed to estimate lumped uncertainties while neural networks (NNs) compensates for model uncertainties, and the deep stall recovery controller is obtained combining with angle of attack tracking error feedback. The system signals involved in the Lyapunov function are proved to be bounded and the sliding mode surface converges in finite time. Simulation results show that the proposed method can reduce the fighter aircraft’s angle of attack to a safe zone while maintaining stable controllability, achieving rapid and smooth recovery from deep stall conditions.