火星着陆器进入段轨迹优化与制导研究进展  

A Research Progress Of Trajectory Optimization And Guidance For Mars Lander

作　　者：姚晗诚 齐瑞云[1,2] Yao Hancheng;Qi Ruiyun(College of Automation Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 211100,China;Key Laboratory of Navigation,Control and Health-Management Technologies of Advanced Aerocraft,Ministry of Industry and Information Technology,Nanjing University of Aeronautics and Astronautics,Nanjing 211100,China)

机构地区：[1]南京航空航天大学自动化学院,南京211100 [2]南京航空航天大学先进飞行器导航控制与健康管理工业和信息化部重点实验室,南京211100

出　　处：《航天控制》2021年第4期3-12,共10页Aerospace Control

基　　金：国家自然科学基金(61873127);航空科学基金(2017ZA52013)。

摘　　要：根据火星着陆器在进入段的飞行状况,分析并总结可能遭遇的困难与挑战;在间接法和直接法两方面概述飞行器轨迹优化方法,阐述当前飞行器轨迹优化研究现状以及火星着陆器进入段轨迹优化的应用情况;以标称轨迹制导法和预测校正制导法两方面分析火星着陆器进入段制导研究现状,并比较两种制导方法的优缺点,最后对火星着陆器未来研究方向做了展望。The difficulties and challenges that Mars landers may encounter in the Entry are summarized and analyzed.The trajectory optimization of the spacecraft is summarized in the ways of indirect and direct methods,and the current situation of the study for the trajectory optimization of the spacecraft and the application in the trajectory optimization of the Mars landers is expounded.The current situation of the Mars entry guidance research is analyzed by the two aspects of the calibration method and the prediction correction guidance method,and the advantages and disadvantages between the two guidance methods are compared.At the end of paper,the future research direction of the Mars lander is prospected.

关 键 词：轨迹优化 制导方案 不确定性 标称轨迹制导法 预测校正制导法 

分 类 号：V448[航空宇航科学与技术—飞行器设计]