چكيده به لاتين
Spacecraft orbital path design leverages multi-body dynamical environment that are generally founded on a comprehension of restricted three-body problem. Given the more accurate and complex dynamical conditions, mission applications may likewise profit by more profound understanding into the spacecraft orientation. In this investigation, the rotational motion are combined with the orbital motion in the Elliptic Restricted Three-Body Problem (ER3BP). In a profoundly delicate dynamical model, such as the orbit-attitude ER3BP, periodic solutions permit description of the fundamental dynamical structures. Periodic behaviors are also a part of motions that are bounded over an infinite time-span, without the necessity to integrate and incorporate over an infinite time interval. Euler's equations of motion and quaternion kinematics describe the attitude motion of the spacecraft, whereas the translation of the center of mass is modeled in the ER3BP equations. Correction algorithms are employed to target orbit-attitude periodic solutions in this model. Application of Poincare mapping, and residual search method to identify initial guesses for the targeting algorithm is described. In the Sun-Earth system and Earth-Moon system, delegate situations are investigated for symmetric spacecraft with various inertia ratios, assuming that the spacecraft revolving in Lyapunov, halo as well as Distant Retrograde Orbits (DRO). A rich structure of conceivable periodic solutions appears to pervade the solution space in the coupled ER3BP. The stability analysis of the elementary periodic solutions is included. Among the computed solutions, marginally stable and slowly diverging rotational behaviors exist and may offer interesting mission applications. Natural periodic solutions are valuable information that facilitate spacecraft orbital and attitude control, however, orbit control and attitude control will be needed anyhow, but, lower control cost eventuate in longer functional lifetime of spacecraft. The problem assumption considered in this paper is much closer to real missions conditions, thus, these results could exert for novel mission design.
