Trajectory of Hypersonic Gliding Vehicles (HGV) designed and optimized generally is an especial path with actual task requirements, which mostly provide feasible flight information for the design of guidance and control system. This paper mainly presents a framework of trajectory design and optimization for HGV, and differences between design and optimization results are discussed. In the first part of the framework, the trajectory is designed mainly by the programming angle commands. Specifically, the pitch angle as the control variable in the boost phase, and the angle of attack (AOA) as the control variable in the glide phase are considered. Then, establishing a trajectory optimization model, which has coincident initial and terminal conditions with the trajectory design part if it's reasonable, and additional constraints. Applying a Legendre-Gauss-Radau (LGR) orthogonal collocation method for solving the problem. In this part, Firstly, low density collocation points are set in the algorithm to find the feasible trajectory, and then further increase the density of collocation points to optimize to get more information about the state and control of the trajectory points. Finally, several initial parameters of the glide phase are discussed, which have a great influence on the flight performance. Numerical simulation indicates that the effectiveness of the proposed framework for the real task scenarios is amazing.

通常设计和优化的高超音速滑行飞行器的轨迹是一条具有实际任务要求的特殊路径，主要为制导和控制系统的设计提供可行的飞行信息。本文主要提出了HGV的轨迹设计与优化框架，并讨论了设计与优化结果之间的差异。在框架的第一部分中，主要通过编程角度命令来设计轨迹。具体地，考虑俯仰角作为升压阶段的控制变量，以及迎角（AOA）作为滑行阶段的控制变量。然后，建立一个轨迹优化模型，该模型在合理的情况下与轨迹设计部分具有相同的初始条件和最终条件，并附加其他约束条件。应用Legendre-Gauss-Radau（LGR）正交配置方法来解决该问题。在这一部分中，首先，在算法中设置低密度搭配点以找到可行的轨迹，然后进一步增加搭配点的密度以进行优化，以获得有关轨迹点的状态和控制的更多信息。最后，讨论了滑行阶段的几个初始参数，这些参数对飞行性能有很大影响。数值模拟表明，所提出的框架对于实际任务场景的有效性是惊人的。然后进一步增加搭配点的密度以进行优化，以获得有关轨迹点的状态和控制的更多信息。最后，讨论了滑行阶段的几个初始参数，这些参数对飞行性能有很大影响。数值模拟表明，所提出的框架对于实际任务场景的有效性是惊人的。然后进一步增加并置点的密度以进行优化，以获得有关轨迹点的状态和控制的更多信息。最后，讨论了滑行阶段的几个初始参数，这些参数对飞行性能有很大影响。数值模拟表明，所提出的框架对于实际任务场景的有效性是惊人的。