A Novel Sliding-mode Guidance Law Based on Lie-group Method  

作　　者：韩大鹏 孙未蒙 刘昆 

机构地区：[1]College of Aerospace and Material Engineering, National University of Defense Technology [2]Ordnance Revamping Factory of Unit No.92854 [3]College of Mechatronic Engineering and Automation, National University of Defense Technology

出　　处：《Defence Technology（防务技术）》2010年第1期25-34,共10页Defence Technology

基　　金：Sponsored by the National Natural Science Foundation of China (60374006)

摘　　要：Although the channel-decoupling assumption is often used in design of three-dimensional guidance laws, it loses its rationality for aircrafts with strong kinematics coupling because body rotation arises. To overcome this trouble, a novel guiding method was proposed based on Lie-group. After a model of 3D guidance is formulated using vectors, the precision guidance with ending angular constraints can be transformed into a problem involving the relation between directional angles and rotational angular velocities of certain vectors. When the guidance model is imposed a SO(3)-based description, a novel 3D sliding mode guidance law with ending angular constraints can be developed via Lie-group control method and variable structure control theory. Finally, the feasibility and performance of the guidance law were shown by simulating the examples.Although the channel-decoupling assumption is often used in design of three-dimensional guidance laws, it loses its rationality for aircrafts with strong kinematics coupling because body rotation arises. To overcome this trouble, a novel guiding method was proposed based on Lie-group. After a model of 3D guidance is formulated using vectors, the precision guidance with ending angular constraints can be transformed into a problem involving the relation between directional angles and rotational angular velocities of certain vectors. When the guidance model is imposed a SO （3）-based description, a no- vel 3D sliding mode guidance law with ending angular constraints can he developed via Lie-group control method and varia- ble structure control theory. Finally, the feasibility and performance of the guidance law were shown by simulating the examples.

关 键 词：control and navigation technology of aircraft multi-constraint guidance Lie group control sliding-mode control 

分 类 号：V249[航空宇航科学与技术—飞行器设计]