A New Angular Acceleration Guidance Law with Estimation Approach based on Sliding Mode Observer against High Maneuvering Target

被引：9
|
作者：
Song, Yuanyun [1 ]
Chen, Wanchun [1 ]
Yin, Xingliang [1 ]
机构：
[1] Beihang Univ, Sch Astronaut, Beijing, Peoples R China
来源：
MECHANICAL AND AEROSPACE ENGINEERING, PTS 1-7 | 2012年 / 110-116卷
关键词：
guidance law; filter; angular acceleration guidance; sliding mode observer; extended kalman filter;
D O I：
10.4028/www.scientific.net/AMM.110-116.5249
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
A new type of guidance law is developed for intercepting high maneuvering target. The law takes angular acceleration of line-of-sight as a primary input in place of the acceleration of target. As the significant required input quantity of the angular acceleration guidance (AAG), the angular acceleration of line-of-sight is estimated by a developed estimation approach based on sliding mode observer (SMO). Simulation results demonstrates advantages of this AAG guidance with the estimation approach based on SMO by comparing with the conventional guidance techniques and extended Kalman filter.
引用
收藏
页码：5249 / 5256
页数：8
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