再入飞行器末端能量管理段纵向剖面优化方法

doi:10.3969/j.issn.1674-1579.2018.03.005

空间控制技术与应用

再入飞行器末端能量管理段纵向剖面优化方法

龚宇莲，陈上上

1.北京控制工程研究所,北京 100094;2.空间智能控制国家级重点实验室,北京 100094.

出版日期:2018-06-26 发布日期:2018-07-16
作者简介:作者简介：龚宇莲(1985—)女,工程师,研究方向为航天器自适应控制；陈上上(1982—)，男，工程师，研究方向为再入制导控制.
基金资助:
国家自然科学基金资助项目(61333008).

TAEM Vertical Profile Optimization Algorithm for Reentry Vehicle

GONG Yu-Lian, CHEN Shang-Shang

1.Beijing Institute of Control Engineering, Beijing 100094, China;2.Science and Technology on Space Intelligent Control Laboratory, Beijing 100094, China

Online:2018-06-26 Published:2018-07-16
Supported by:
Supported by National Natural Science Foundation of China(61333008).

摘要/Abstract

摘要： 摘要：对于轨道再入飞行器，根据各阶段飞行特性和任务的不同被分为初期再入、末端能量管理以及进场着陆几个阶段.本文提出一种末端能量管理段航程及纵向剖面优选方法，通过对不同的初始航程和纵向剖面进行递推，以阻力板控制裕度最大为优化目标，选出最适应飞行器升阻特性的航程以及相应的高度动压剖面.考虑初始状态误差及气动特性偏差条件下的六自由度仿真验证所设计的纵向剖面的鲁棒性.

关键词: 关键词：轨道再入, 末端能量管理, 航程优化

Abstract: Abstract： The entry flight envelope of orbital reentry vehicle is divided into three phases: the atmospheric entry, terminal area energy management (TAEM) and autolanding. In this paper, a flight range and vertical profile optimization algorithm are developed for the terminal area energy management phase. Through the propagation of the dynamic equation from different initial states, by maximizing the control margin of speed brake, a range which is most fit for the aerodynamic characteristic of the vehicle is generated, and the best heightdynamic profile in correspondence with this range is designed simultaneously. The 6DOF simulations under various initial states deviation and dynamic uncertainties demonstrate that the vertical profile is robust.

Key words: Keywords： orbital reentry, TAEM, range optimization

中图分类号:

中图分类号： V212.1

龚宇莲, 陈上上. 再入飞行器末端能量管理段纵向剖面优化方法[J]. 空间控制技术与应用, 2018, 44(3): 28-35.

GONG Yu-Lian, CHEN Shang-Shang. TAEM Vertical Profile Optimization Algorithm for Reentry Vehicle[J]. , 2018, 44(3): 28-35.

参考文献

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再入飞行器末端能量管理段纵向剖面优化方法

TAEM Vertical Profile Optimization Algorithm for Reentry Vehicle

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