中文摘要：

针对一类可重复使用飞行器的末端能量管理段制导问题进行研究．末端能量管理系统通过能量一待飞距剖面对飞行器实施制导，并对能量加以控制，引导飞行器到达安全的着陆窗口．采用基于系统线性化和退步设计原理生成纵向的高度控制系数和横向航迹的控制系数，并简化了制导律的设计参数，给出定常的PD控制系数．在完成标称轨迹离线规划的基础上，纵横向综合制导最终使飞行器满足着陆窗口的要求．通过对不同误差条件的仿真分析，显示了该方法对各种偏差摄动条件具有良好的鲁棒性．

英文摘要：

Aiming at one category of reusable launch vehicle, the guidance problem is investigated for ter- minal area energy management phase. For a terminal area energy management system, the energy-range- to-go profile is used to guide the vehicle onto the approach and landing interface, and to control the ener- gy dissipation. The height control coefficients in the longitudinal direction and the track control coeffi- cients in the lateral direction are generated based on the linearization method and back-stepping control. The designed parameters are simplified and the constant PD control coefficients are given. On the basis of the off-line programming of the nominal trajectory, the requirements of the approach and landing interface are satisfied via the longitudinal/lateral integration-guidance. The guidance method is proved to be robust against the disturbances and a series of different errors.