The transition window of aerospace vehicles (ASVs) is defined as the connection point of different flight phases or the engine mode transition point. For ASVs, one of the critical problems is the precise tracking of transition window that would enable the engine to implement the mode transition successfully. Since the engine of ASVs is independently controlled, it is required that ASV eliminates both velocity and position tracking errors within a specified time to reach the transition window accurately. In addition, the tracking control of ASVs is affected by uncertain aerodynamic parameter, initial deviation, and control constraint. Therefore, an innovative tracking control of transition window (TWTC) scheme is developed, which is composed of transient reference trajectory generation and control modules. A dynamic transient trajectory is generated to modify the tracking command to expand the initial feasible region. A piecewise robust preview control algorithm is presented for the control module design, which fuses the preview information of the reference signal, control constraint, equality constraint of ASV dynamics, and performance index function. Simulation results of a nonlinear ASV model show the effectiveness of TWTC scheme under uncertain aerodynamic parameters and initial deviations.

航空航天器（ASV）的过渡窗口定义为不同飞行阶段的连接点或引擎模式过渡点。对于ASV，关键问题之一是对转换窗口的精确跟踪，这将使引擎能够成功实现模式转换。由于ASV的引擎是独立控制的，因此要求ASV在指定的时间内消除速度和位置跟踪误差，以准确到达过渡窗口。此外，对ASV的跟踪控制还受到不确定的空气动力学参数，初始偏差和控制约束的影响。因此，开发了一种由过渡参考轨迹生成和控制模块组成的新颖的过渡窗口跟踪控制（TWTC）方案。产生动态瞬态轨迹以修改跟踪命令以扩展初始可行区域。提出了一种用于控制模块设计的分段鲁棒预览控制算法，该算法融合了参考信号的预览信息，控制约束，ASV动力学的等式约束和性能指标函数。非线性ASV模型的仿真结果表明TWTC方案在不确定的空气动力学参数和初始偏差下的有效性。