针对舰载垂直起降(VTOL)飞机过渡过程中推进系统与气动力之间的强耦合非线性，以及过渡结束时升力风扇进气口盖关闭引起的气动系数瞬态突变，提出一种高精度舰载VTOL飞机过渡轨迹优化与控制方法。首先，考虑到复杂的作动结构和升力风扇进气口盖影响，基于风洞实验数据建立了舰载VTOL飞机过渡模型；其次，通过可达平衡集方法绘制过渡走廊，并以走廊边界、动态约束，过渡高度和过渡时间为安全和性能指标定义过渡目标，提出轨迹优化问题，基于自适应伪谱法设计过渡轨迹优化方法；最后，设计基于预设时间扰动观测器的增量式动态逆(PTOD-INDI)方法进行飞机控制，该方法能够在预设时间观测到扰动，并克服不确定干扰，提高鲁棒性。仿真和半实物实验表明：所提方法实现了舰载VTOL飞机过渡轨迹优化以及对最优轨迹的准确跟踪，同时有效抑制扰动影响，达到了兼顾安全与性能的高精度过渡目标。

A high-precision transition trajectory optimization and control method for shipborne vertical takeoff and landing (VTOL) aircraft is proposed to address the strong coupling nonlinearity between the propulsion system and aerodynamic forces during the transition process, and the sudden change in aerodynamic coefficients caused by the closure of the lift fan inlet hatch at the end of the transition. Firstly, considering the complex actuation structure and the influence of the lift fan inlet hatch, a transition model of the shipborne VTOL aircraft is established based on wind tunnel experimental data, and the attainable equilibrium set method is used to draw the transition corridor; Secondly, transition objectives are defined based on corridor boundaries, aircraft dynamic constraints, transition height, and transition time as safety and performance indicators, and an optimization problem is established to solve the optimal transition trajectory using adaptive pseudo-spectral method; Finally, a preset time-disturbance observer of incremental dynamic inversion (PTOD-INDI) method is designed for aircraft control. This method can observe disturbances at pre-set times, overcome uncertain disturbances, and improve robustness. Simulation and semi physical verification show that the proposed method achieves the optimization of the transition trajectory of shipborne VTOL aircraft and accurate tracking of the optimal trajectory, while effectively suppressing disturbance effects, achieving high-precision transition goals that balance safety and performance.