摘要
为了提高制导律的精度和适应性,针对大升阻比再入飞行器的末端能量管理段(TAEM段)的飞行特性,提出一种飞行轨迹制导律.该方法的制导律由标称制导指令和PD控制指令两部分组成,标称制导指令由离线生成的标称轨迹的几何特性结合飞行器的飞行状态实时生成,PD控制指令则由飞行器当前飞行状态与期望飞行状态的误差计算生成.该方法经数学仿真表明,具有较好的控制效果.
In order to enhance the precision and the flexibility of the guidance law, considering the flight characters of the re-entry vehicle with large lift drag ratio during the terminal area energy management （TAEM） phase, a guidance law of planning the trajectory is given. This method is composed of two parts, the nominal control orders and the PD control orders. The nominal control orders are built real- time based on the geometrical characters of the nominal trajectory that are gained off-line and by the cur- rent status of the vehicle at the same time, while the PD control orders are calculated according to the er- ror signals between the current status and the excepted status. After simulating and verifying, the effect and the advantage of this method can be shown.
出处
《空间控制技术与应用》
CSCD
北大核心
2016年第3期58-62,共5页
Aerospace Control and Application
基金
国家自然科学基金资助项目(61333008
61273153)
作者简介
陈阳（1990-），女，硕士研究生，研究方向为航天器导航、制导与控制．
