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《Journal of Astronautics》 2009-01
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Mathematical Problems in the Analysis and Control of Spatial Non-Keplerian Orbits

SHE Zhi-kun,LIU Tie-gang,ZHENG Zhi-ming(LMIB and Department of Mathematics,Beihang University,Beijing 100191,China)  
Currently,the research on analysis and optimal control of spatial non-Keplerian orbits becomes a very active topic.Through such research,we can analyze and realize free transitions of satellites among non-Keplerian orbits,arriving at expectation goals such as detective,anti-detective,interception,connection and so on.Since behaviors exhibited by spatial non-Keplerian orbits,in the viewpoint of Mathematics,have dynamical properties,based on our previous research results,we,therefore,in this paper provided a general mathematical model(that is,a dynamical-like system with parameters and constraints,i.e.,a hybrid system) for studying them.Based on this mathematical model,we further disclosed that detective,anti-detective,parametric adjustment and delay control actually correspond to four key mathematical problems in the research area on hybrid systems: stability analysis,safety verification,bifurcation and robust control,respectively.Based on this finding,we also proposed some primitive ideas for studying these problems.
【CateGory Index】: V412.41
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8 ZHANG Chang-sheng~a,b,SUN Ji-gui~a,b,ZHANG Jian~a,b,FAN Wei~ a,b(a.College of Computer Science and Technology;b.Key Laboratory of Symbolic C omputation and Knowledge Engineering of Ministry for Education,Jilin University,Changchun 130012,China);Implementation of Real Time Fight Simulation System[J];Journal of Jilin University(Information Science Edition);2006-05
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10 LIU Zhong~(1,2),LIANG Xiao-geng~2,JIA Xiao-hong~2,CAO Binggang~1(1.Department of Mechanical & Electrical Engineering,Xi'an Jiaotong University,Xi'an 710049,China;2.China Air-to-air Missile Institute,Luoyang 471009,China);Missile Omnidirectional Attitude Motion Errors Based on Quaternion[J];Journal of Ballistics;2006-02
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6 Wang Li-guo,Shen Ping,Zhang Jing-yang (Academy of Frontier Science,Nanjing University of Aeronautics and Astronautics,Nanjing,Jiangsu,210016, China);Computing Sunlight Incidence Angles of Satellite Solar Arrays[A];[C];2010
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4 HOU Xi-yun~(1,2) LIU Lin~(1,2) (1.Astronomy Department,Nanjing University,Nanjing,Jiangsu Province 210093;2.The Institute of Space Environment and Astrodynamics,Nanjing University,Nanjing,Jiangsu Province 210093);On Orbit Control of Spacecraft around Collinear Libration Points[J];;2005-06
5 WANG Meng-li,WANG Fei-xue(Satellite Navigation Research and Development Center,National University of Defense Technology,Changsha 410073,China);Lagrange Insert-value Algorithm′s Analysis of Satellite′s Position and Velocity[J];Aeronautical Computing Technique;2008-04
6 LI Jisu1 MU Xiaogang1 ZHANG Jinjiang1 WANG Xiaolei2 ZONG Hong2 SUN Baoxiang21.National Laboratory of Space Intelligent Control,Beijing Institute of Control Engineering,Beijing 100190,China2.Beijing Institute of Control Engineering,Beijing 100190,China;Application of Air Bearing Table in Satellite Control System Simulation[J];Aerospace Control;2008-05
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8 Gao Huayu,Dong Yunfeng(College of Astronacctics,BUAA,Beijing 100083,China);Full-Physical Simulation Experiment System of Moonlet Attitude Control Based on Air Bearing Test-bed[J];Computer Measurement & Control;2009-06
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