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A Novel Sliding-mode Guidance Law Based on Lie-group Method
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作者 韩大鹏 孙未蒙 刘昆 《Defence Technology(防务技术)》 SCIE EI CAS 2010年第1期25-34,共10页
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 t... 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. 展开更多
关键词 control and navigation technology of aircraft multi-constraint guidance Lie group control sliding-mode control
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