航天飞机自动着陆轨迹优化设计

采用沿约束轨迹的推演计算方法及优化原理对航天飞机自动着陆飞行轨迹进行优化设计。首先根据过载、垂直下降率、连续性和平稳性要求确定飞行轨迹的基本形状，然后采用两点边值优化方法对轨迹参数进行优化设计以获得理想的接地动压。与传统的和制导系统联系在一起的轨迹设计方法相比，该方法具有简便、快速、可重复使用、鲁棒性强等特点。

Optimal Design of Autolanding Trajectory for a Space Shuttle

This paper applies the technique of constrained trajectory propagation and optimal theory to design the autolanding trajectory for a space shuttle. First, the geometric shape of flight trajectory can be determined according to the requirements of physical constructions such as loads, vertical descent rate, and continuity and smoothness of trajectory. Then, the optimal method of a two-boundary value problem is used to design geometric parameters of the trajectory to achieve the ideal touchdown dynamic pressure. Compared to a traditional design methodology which is usually combined with a guidance scheme, this methodology is easy, quick, reusable and robust.