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タイトルStability Analysis for Constrained Principal Axis Slew Maneuvers
本文(外部サイト)http://hdl.handle.net/2060/20040105588
著者(英)Lim, Kyong B.; Anthony, Tobin C.; Seywald, Hans
著者所属(英)NASA Langley Research Center
発行日1996-01-01
言語eng
内容記述This paper addresses the problem of reorienting a rigid spacecraft from arbitrary initial conditions to prescribed final conditions with zero angular velocity. The control law analyzed is based on quaternion feedback and leaves the user to choose two gains as functions of position, angular rate, and time. For arbitrary initial states, conditions on the controller gains are identified that guarantee global asymptotic stability. For the special case of rest-to-rest reorientations, the control law reduces to earlier results involving a principal axis rotation. The paper also addresses slew rate constraints, both, in terms of the two and infinity norms.
NASA分類Aircraft Stability and Control
権利Copyright, Distribution as joint owner in the copyright
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/88289


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