火星上升器入轨段自适应迭代制导方案设计  

Design of Adaptive Iterative Guidance Scheme for Mars Ascent Vehicle Orbiting Phase

作　　者：宋春 郭延宁[2] 郭敏文[3] 李琨 SONG Chun;GUO Yanning;GUO Minwen;LI Kun(Science and Technology on Space Physics Laboratory,Beijing 100076,China;Department of Control Science and Engineering,Harbin Institute of Technology,Harbin 150001,China;Beijing Institute of Control Engineering,Beijing 100094,China)

机构地区：[1]空间物理重点实验室,北京100076 [2]哈尔滨工业大学控制科学与工程系,哈尔滨150001 [3]北京控制工程研究所,北京100094

出　　处：《深空探测学报（中英文）》2024年第1期31-39,共9页Journal Of Deep Space Exploration

基　　金：国家自然科学基金(61973100,62273118,12150008,61876050)。

摘　　要：针对火星上升器入轨段的制导问题,设计了一种自适应迭代制导策略。为降低初始状态偏差和火星环境不确定性的影响,每个周期内在制导坐标系下迭代计算剩余飞行时间,求解出在上升器推力大小固定情况下满足目标点位置与速度矢量约束的最优控制角,进而实时修正飞行轨迹。仿真结果表明,相较于传统的开环制导方案,提出的方案显著地提升了制导精度,其中高度误差降低3个量级,最大速度误差降低至原开环制导的三分之一,入轨点轨道倾角和偏心率误差均满足基本工程需求,可作为未来火星上升器入轨段制导的一种可靠方案。An adaptive iterative guidance strategy was designed for the guidance of Mars ascent vehicle in the orbiting phase.To reduce the effects of initial state deviation and the uncertainty of the Martian environment,the remaining flight time was calculated iteratively in the guidance coordinate system in each cycle,and the optimal control angle satisfying the constraints of the target point position and velocity vector was solved under the fixed thrust of the ascender,so as to correct the flight trajectory in real time.The simulation results show that compared with the traditional open-loop guidance scheme,the proposed scheme significantly improves guidance accuracy,in which the altitude error is reduced by three orders of magnitude,the maximum velocity error is reduced to one-third of that of the original open-loop guidance,the orbital inclination and eccentricity errors at the entry point satisfy the basic engineering requirements,and it can be used as a reliable scheme for the future guidance of the Mars ascent vehicle in the orbiting phase.

关 键 词：火星上升器 入轨段 迭代制导 最优控制 

分 类 号：V412[航空宇航科学与技术—航空宇航推进理论与工程]