کنفرانس مهندسی برق ایران

صفحه اصلی / سی امین کنفرانس بین المللی مهندسی برق

Zero control effort approach to perturbed coupled orbit-attitude periodic solution at three-body problem: Earth-Mars system

نویسندگان :

Amirreza Kosari¹ Ehsan Abbasali² Majid Bakhtiari³

1- دانشگاه تهران 2- دانشگاه تهران 3- دانشگاه علم و صنعت ایران

کلمات کلیدی :

Oblate Primaries،Perturbed Periodic Orbit-Attitude Behavior،Three-Body Problem،Poincaré mapping

چکیده :

Periodic solutions of the satellite's coupled orbit-attitude can be obtained by applying a controller to the problem. Minimizing control efforts is one of the critical factors that can make the mission economically justified. Also, the economic costs will be minimized if the problem converges to the desired answer without a controlling effort. Recognizing the proper initial conditions is one way that the problem can converge to periodic responses without any controlling effort. Therefore the main purpose of this article is to identify the proper initial condition that leads to meet periodic attitude responses of the satellite at the periodic Lyapunov orbits at the circular three-body problem considering the perturbations of both oblate primaries. So the Perturbed Orbit-Attitude Correction (POAC) algorithm is proposed to correct the initial guess of the coupled model. The correction algorithm needs a suitable initial guess vector as the number of periodic solutions is limited. As an innovation, the initial guess of the orbital states is identified by the Poincaré mapping method. In previous investigations, this initial guess was suggested to extract from the third-order approximate solution of the unperturbed circular restricted three-body problem requiring complex mathematical calculations. The proposed method will lead to a significant reduction in complex mathematical calculations. The initial guess of attitude dynamic parameters is also recognized by the Poincaré mapping method, concerning these perturbations resulted in a more accurate simulation that aids in understanding the satellite's natural motion. The proposed technique also reduces the control effort to zero, which optimizes the economic costs of the mission.