NDLI: Effect analysis and compensation for orbit perturbation of spacecraft using momentum management control

Content Provider	IEEE Xplore Digital Library
Author	Jinzhe Jiang Yanan Gao Lucheng Zhang
Copyright Year	2013
Description	Author affiliation: Beijing Inst. of Control Eng., CAST, Beijing, China (Jinzhe Jiang; Yanan Gao; Lucheng Zhang)
Abstract	This paper uses inertial momentum management control method for long-term on-orbit working stability of large spacecraft which only has small difference in three-axis main inertia. To avoid the accumulation of gravity gradient torque, it should be guaranteed that one inertia axis of spacecraft is strictly perpendicular to its orbital plane. Then, an inertial reference coordinate system for momentum management is established. It is observed that the drift of ascending node right ascension and along-track angle of orbit caused by orbit perturbation has an approximate linear relation to time. This leads to a linear increase of the momentum and causes divergences of attitude and angular momentum. We render analysis to the problem and augment the long-period orbit factors in state equation on the basis of internal model principle in order to compensate the perturbation. Finally, semi-physical simulations are setup to validate the approach. It shows that the compensation method is feasible and long-term stability of attitude and momentum is achieved.
Starting Page	741
Ending Page	746
File Size	417094
Page Count	6
File Format	PDF
ISBN	9781479913343
DOI	10.1109/ICInfA.2013.6720392
Language	English
Publisher	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Publisher Date	2013-08-26
Publisher Place	China
Access Restriction	Subscribed
Rights Holder	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Subject Keyword	Space vehicles Earth Torque the momentum Management perturbation compensation Orbits Mathematical model orbital perturbations Equations Gravity space craft
Content Type	Text
Resource Type	Article

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