针对存在推力线偏斜、显著非对称气动及高空切变风干扰的面对称飞行器助推段姿态跟踪控制问题，提出一种自适应预设时间/性能控制方法，使姿态控制的收敛时间与稳态精度可由过程函数中的两个独立参数便捷地预先设定。首先建立面对称飞行器动力学模型，并转化为双积分串联形式的控制模型；其次设计分段连续的过程函数用以约束收敛时间与稳态精度，结合障碍函数对其变换进而获得无约束系统；随后基于反步法，设计保证无约束变量有界的自适应控制律，引入分段连续函数避免控制抖振，并采用神经网络自适应逼近补偿扰动；针对风切变带来突发大偏差下预设性能方法存在奇异性的问题，设计过程函数重置策略放宽约束边界，消除控制奇异；最后基于Lyapunov理论证明闭环系统的稳定性，并通过数值仿真验证控制方法的有效性。

In this paper, an adaptive prescribed-time/performance control method is proposed for the plane-symmetric aircraft in the boost phase subject to thrust misalignment, significant asymmetric aerodynamics, and high-altitude wind shear. This method allows the convergence time and steady-state accuracy of attitude control to be conveniently pre-set using two independent parameters of the process function. Firstly, a dynamic model of the symmetrical air-craft is established and transformed into a double integrator cascaded control-oriented model. Secondly, a piece-wise continuous process function is designed to constrain the convergence time and steady-state accuracy, and an unconstrained system is obtained by combining it with a barrier function transformation. Thirdly, based on the back-stepping method, an adaptive control law is designed to ensure the boundedness of the unconstrained variables. A segmented continuous function is introduced to avoid control chattering, and a neural network is employed for adaptive disturbance compensation. To address the singularity issue of the prescribed-performance control method under large deviations caused by wind shear, a reset strategy of process function is devised to relax the constraint boundaries and eliminate control singularities. Finally, the stability of the closed-loop system is proven based on Lyapunov method, and the effectiveness of the control method is validated through numerical simulations.