Abstract
The attitude motion of a rigid spacecraft is studied in the Earth-Moon circular restricted three-body problem. Firstly, the equilibrium attitude and its stability as functions of the moments of inertia are discussed when the spacecraft is assumed at the libration points. Then, periodic attitudes of a spacecraft with mass distribution given in the stable regions are obtained. Regarding space mission applications, the Sun orientation is discussed, and the orbit-attitude resonances are constructed for spacecrafts working on the libration point orbits by means of a continuation procedure.
Highlights
The natural dynamical revolution may assist, or even replace, the attitude control action [25]. us, to design the spacecraft control system better, an understanding of the coupling orbital and attitude motion is of significance
Kane and Marsh [26] considered the attitude stability of an axial symmetric satellite which is located at the libration points. e satellite is spinning about its axis of symmetry that is normal to the primary bodies’ orbital plane
Robinson [27] studied the attitude stability of a dumbbell satellite located at the equilateral points. e same author [28] considered the attitude stability of an arbitraryshaped rigid satellite which is located at a Lagrangian point, and the author constructed a linear stability diagram about the stable attitude of the satellite
Summary
The dynamics about the libration points in the circular restricted three-body problem (CRTBP) has been studied extensively [1,2,3,4,5,6,7,8,9,10,11,12,13,14,15,16,17], and so far, several libration point missions have been conducted [18,19,20,21,22,23,24] As we know, both orbital and attitude motions of a spacecraft are required to be considered in practical missions.
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Free) 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
