基于自适应预测校正的月球软着陆制导控制方法  

A Guidance and Control Method for Moon Soft Landing Based on the Adaptive Predictor-Corrector

作　　者：胡军[1] 周敬 HU Jun;ZHOU Jing(Beijing Institute of Control Engineering, Beijing 100094;Beijing Institute of Aerospace System Engineering, Beijing 100076)

机构地区：[1]北京控制工程研究所,北京100094 [2]北京宇航系统工程研究所,北京100076

出　　处：《飞控与探测》2022年第2期1-13,共13页Flight Control & Detection

摘　　要：应用自适应预测制导方法,研究月球软着陆过程中的制导控制问题。作为一种具有逻辑结构的构造性方法,概述了自适应预测制导方法的实现步骤。针对月球软着陆过程中制导控制量少于被控制量这一欠驱动问题,在已有的基于一阶特征模型的全系数自适应预测校正方法的基础上,将输入输出相等的系统拓展为输入少于输出的欠驱动系统,以满足对位置、速度矢量同时进行制导控制的需要。针对初始状态误差、推力偏差、质量偏差以及比冲偏差下的软着陆过程,进行了蒙特卡罗仿真分析,结果表明,自适应预测制导方法可有效用于月球软着陆过程的制导控制,且具有较高的精度和较强的鲁棒性。An adaptive predictive guidance method is proposed to solve the guidance and control problem of Moon soft landing.As a constructive method with the logical structure,the implementation steps of this method are outlined in this paper.Aiming at the problem of Moon soft landing,the control variables are less than the controlled variables,which is actually an underactuated problem,this paper extends a system with the equal input and output to an underactuated system,based on the existing all-coefficient adaptive predictor-corrector guidance and control method,in order to control the position and velocity vectors simultaneously.Monte Carlo simulations and analysis of Moon soft landing are done,considering the error of initial state,thrust,mass and specific impulse.The results show that the adaptive all-coefficient predictor-corrector guidance method is valid in the guidance and control problem of the Moon soft landing,and it has high accuracy and strong robustness.

关 键 词：月球软着陆 自适应预测制导 欠驱动系统 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]