Attitude stability of a spacecraft on a stationary orbit around an asteroid subjected to gravity gradient torque

摘要: Attitude stability of spacecraft subjected to the gravity gradient torque in a central field has been one most fundamental problems space engineering since beginning age. Over last two decades, interest asteroid missions for scientific exploration and near-Earth object hazard mitigation is increasing. In this paper, problem attitude generalized rigid on stationary orbit around uniformly-rotating asteroid. This studied via linearized equations motion, which harmonic coefficients \(C_{20}\) \(C_{22}\) are considered. The necessary conditions conservative system investigated detail with respect three important parameters asteroid, include \(C_{22}\), as well ratio mean radius orbit. We find that, due significantly non-spherical shape rapid rotation domain modified comparison classical predicted by Beletskii–DeBra–Delp method circular field. Especially, when located intermediate-moment principal axis can be totally different from domain. Our results useful design control future missions.