Pegasus XL from Orbital Sciences Corporation (2000), insertion error is given in terms of semi-major axis and inclination deltas from the intended values, and ...
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Establishment of Satellite Formation with Initial Uncertainty by Control Lyapunov Function Approach M. Navabi*, M. Barati, Hossein Bonyan Khamseh 6KDKLG%HKHVKWL8QLYHUVLW\*&7HKUDQ,UDQ Abstract:,QUHFHQW\HDUVG\QDPLFVDQGFRQWURORIVDWHOOLWHIRUPDWLRQÀ\LQJKDYHEHHQDFWLYHDUHDVRIUHVHDUFK)URPWKH PLVVLRQSODQQLQJSHUVSHFWLYHWKUHHPDLQDUHDVQDPHO\IRUPDWLRQHVWDEOLVKPHQWPDLQWHQDQFHDQGUHFRQ¿JXUDWLRQKDYH EHHQGLVFXVVHG,QWKLVSDSHUDVWXG\RIIRUPDWLRQHVWDEOLVKPHQWXQGHULQLWLDOXQFHUWDLQW\LVSUHVHQWHG,QWKLVUHJDUG G\QDPLFVRIORZ(DUWKRUELWVDWHOOLWHIRUPDWLRQLVGLVFXVVHG&RQWURO/\DSXQRYIXQFWLRQDSSURDFKLVDGRSWHGWREULQJD GHSXW\VDWHOOLWHZLWKSHUWXUEHGLQLWLDOFRQGLWLRQVLQWRIRUPDWLRQZLWKDFKLHIVDWHOOLWH,QRUGHUWRWDNHDFFRXQWRIWKHLQLWLDO RUELWLQVHUWLRQHUURUXQFHUWDLQW\LQLQLWLDOFRQGLWLRQVRIWKHGHSXW\VDWHOOLWHLVFRQVLGHUHG)RUDFDVHVWXG\DUHODWLYHO\ small formation is adopted, with air-launched Pegasus as the launch vehicle. For several initial conditions, control function and required time to achieve a given mission accuracy are determined, and results are provided as illustration. Keywords:6DWHOOLWH)RUPDWLRQ/\DSXQRY)XQFWLRQ'\QDPLFV&RQWURO
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