摘要
末端能量管理段制导的主要目的是控制航天器的动能和势能,使航天器最终达到着陆段初始要求。采用能量控制方法来设计制导方案,分析了末端能量管理制导的过程及原理,在制导系统引入能量-射程基准剖面,通过调整飞行距离、动压或速度制动使航天器达到基准的能量状态。将末端能量管理段划分为S-转弯、搜索飞行、航向校正飞行和着陆前飞行4个飞行段进行研究。以某航天器为仿真实例,对末端能量管理段制导过程进行动力学仿真。仿真结果表明所提出的基于能量的制导方案具有良好的制导效果。
The purpose of the terminal area energy management （TAEM） phase guidance is to make the space vehicle meet the original demands of landing phase by controlling the kinetic energy and potential energy of the vehicle. Guidance scheme is designed by Energy controlling while the process and principle of TAEM are analyzed. An energy-range standard profile is shaped in the guidance system to help the vehicle reach its standard energy states through the adjustment of the flight range, dynamic pressure and speed brake. The TAEM phase is further divided into four distinct sub-phases： S-turn phase, acquisition phase, heading alignment cylinder （HAC） phase and pre-fmal approach phase in this paper which takes one reentry vehicle as an example and realizes the dynamic simulation tests to the TAEM phase guidance. The analysis results indicate the effect of this guidance is satisfying.
出处
《导弹与航天运载技术》
北大核心
2006年第3期13-17,共5页
Missiles and Space Vehicles
关键词
再入航天器
末端能量管理
航向校准柱面
能量-射程剖面
制导与控制
Reentry vehicle
Terminal area energy management （TAEM）
Heading alignment cylinder （HAC）
Energy-range profile
Guidance and control
