{"status":"ok","message-type":"work","message-version":"1.0.0","message":{"indexed":{"date-parts":[[2022,4,1]],"date-time":"2022-04-01T08:38:04Z","timestamp":1648802284314},"reference-count":15,"publisher":"World Scientific Pub Co Pte Lt","issue":"06","content-domain":{"domain":[],"crossmark-restriction":false},"short-container-title":["Int. J. Unc. Fuzz. Knowl. Based Syst."],"published-print":{"date-parts":[[2011,12]]},"abstract":"<jats:p> The spacecraft attitude control systems are becoming more and more sophisticated with the increasing complex system configurations. This paper investigates the problem of three-axis rigid spacecraft maneuver control. The rigid spacecraft model consisting of the dynamic and kinematics equation is firstly provided. This nonlinear model is converted into a Takagi-Sugeno fuzzy model. Then, based on the parallel distributed compensation scheme, a fuzzy state feedback controller is designed for the obtained T-S fuzzy model with considering the decay rate and input constraints. Next, sufficient conditions for the existence of such a controller are derived in terms of linear matrix inequalities and the controller design is cast into a convex optimization problem subject to linear matrix inequalities constraints, which can be readily solved via Matlab LMI toolbox. At last, a design example shows that the time of spacecraft attitude maneuver is shortened and the input constraint is realized. The simulation results show the effectiveness of the proposed methods. <\/jats:p>","DOI":"10.1142\/s0218488511007453","type":"journal-article","created":{"date-parts":[[2011,11,30]],"date-time":"2011-11-30T05:35:49Z","timestamp":1322631349000},"page":"1033-1046","source":"Crossref","is-referenced-by-count":8,"title":["FUZZY CONTROL OF RIGID SPACECRAFT ATTITUDE MANEUVER WITH DECAY RATE AND INPUT CONSTRAINTS"],"prefix":"10.1142","volume":"19","author":[{"given":"XIHAI","family":"ZHANG","sequence":"first","affiliation":[{"name":"Space Control and Inertial Technology Research Center, Harbin Institute of Technology, Harbin, Heilongjiang Province, 150001, P.R. China"},{"name":"Engineering College, Northeast Agricultural University, Harbin, Heilongjiang Province, 150030, P.R. China"}],"role":[{"role":"author","vocabulary":"crossref"}]},{"given":"MING","family":"ZENG","sequence":"additional","affiliation":[{"name":"Space Control and Inertial Technology Research Center, Harbin Institute of Technology, Harbin, Heilongjiang Province, 150001, P.R. China"}],"role":[{"role":"author","vocabulary":"crossref"}]},{"given":"XIAO","family":"YU","sequence":"additional","affiliation":[{"name":"Engineering College, Northeast Agricultural University, Harbin, Heilongjiang Province, 150030, P.R. China"}],"role":[{"role":"author","vocabulary":"crossref"}]}],"member":"219","published-online":{"date-parts":[[2012,1,25]]},"reference":[{"key":"rf1","doi-asserted-by":"publisher","DOI":"10.1109\/9.763225"},{"key":"rf2","doi-asserted-by":"publisher","DOI":"10.1109\/91.481841"},{"key":"rf3","doi-asserted-by":"publisher","DOI":"10.1109\/9.90228"},{"key":"rf4","first-page":"1","volume":"8","author":"Xu Y.","journal-title":"IEEE Trans. Aero. Elec. 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