固体火箭技术Issue(5)：594-599,605,7.DOI:10.7673/j.issn.1006-2793.2014.05.002
挠性航天器在轨分离冲击缓冲模糊滑模控制研究
Fuzzy sliding mode control for shock absorber of flexible spacecraft on-orbit separation
摘要
Abstract
In order to reduce the influence of the impact load during the on-orbit separation,a Magneto-rheological ( MR) shock absorber was used. The configuration of shock absorber was also introduced.Flexible spacecraft dynamic model with large reference displacement was established based on finite element and Lagrange method,and sliding mode was used to control the output of the MR shock absorber.A new two dimensional fuzzy sliding mode control was proposed to control the reaching coefficient of the reaching law to improve the dynamic characteristics of the MR shock absorber.Numerical simulation results show that MR shock absorber con-trolled by the proposed method obviously decreases the impact influence and reduces the chattering. The coupling of the base and flexible appendages is weakened,and velocity and acceleration of the flexible appendages become smoother.Furthermore,the pro-posed method has a better steady value and tracking characteristic compared with traditional sliding mode control.关键词
挠性航天器/在轨分离/滑模控制/模糊控制/抖振Key words
flexible spacecraft/on-orbit separation/sliding mode control/fuzzy control/chattering分类
航空航天引用本文复制引用
赵刚练,姜毅,陈余军,刘冬..挠性航天器在轨分离冲击缓冲模糊滑模控制研究[J].固体火箭技术,2014,(5):594-599,605,7.基金项目
国家863项目(2012AA7042016)。 （2012AA7042016）
