Attitude stability of a dual-spin spacecraft on a stationary orbit around an asteroid subjected to gravity gradient torque
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The attitude stability of a dual-spin spacecraft on a stable stationary orbit around an asteroid subjected to gravity gradient torque is studied in this paper, in which the effect of the second order and degree harmonics C20 and C22 of the gravity field of the asteroid is involved. Under some reasonable assumptions, the linearized equations of attitude motion of the dual-spin spacecraft with a nutation damper are presented. Then the necessary and sufficient conditions of attitude stability of the dual-spin spacecraft with a nutation damper are derived. Meantime, the linearized equations of attitude motion and the conditions of attitude stability of the dual-spin spacecraft without a nutation damper are also presented. These results are generalized and encompass a series of special cases, and from which some useful conclusions on the attitude stability of the dual-spin spacecraft are obtained. Examples are given to illustrate the application of these conditions of attitude stability.
KeywordsAttitude stability Dual-spin spacecraft Asteroid Conditions of stability
This work was supported by the National Natural Science Foundation of China under Grant nos. 11125315, 11033009 and 11103086. The authors would like to thank anonymous reviewer for the valuable comments that help to substantially improve the manuscript.
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