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

作　　者：龚宇莲[1,2] 陈上上 GONG Yulian;CHEN Shangshang(Beijing Institute of Control Engineering,Beijing 100094,China;Sci-ence and Technology on Space Intelligent Control Laboratory,Beijing 100094,China.)

机构地区：[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　　处：《空间控制技术与应用》2018年第3期28-35,共8页Aerospace Control and Application

基　　金：国家自然科学基金资助项目(61333008)~~

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.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.

关 键 词：轨道再入 末端能量管理 航程优化 

分 类 号：V212.1[航空宇航科学与技术—航空宇航推进理论与工程]