Abstract
This study investigated periodic coupled orbit—attitude motions within the perturbed circular restricted three-body problem (P-CRTBP) concerning the perturbations of a radiated massive primary and an oblate secondary. The radiated massive primary was the Sun, and each planet in the solar system could be considered an oblate secondary. Because the problem has no closed-form solution, numerical methods were employed. Nevertheless, the general response of the problem could be non-periodic or periodic, which is significantly depended on the initial conditions of the orbit-attitude states. Therefore, the simultaneous orbit and attitude initial states correction (SOAISC) algorithm was introduced to achieve precise initial conditions. On the other side, the conventional initial guess vector was essential as the input of the correction algorithm and increased the probability of reaching more precise initial conditions. Thus, a new practical approach was developed in the form of an orbital correction algorithm to obtain the initial conditions for the periodic orbit of the P-CRTBP. This new proposed algorithm may be distinguished from previously presented orbital correction algorithms by its ability to propagate the P-CRTBP family orbits around the Lagrangian points using only one of the periodic orbits of the unperturbed CRTBP (U-CRTBP). In addition, the Poincaré map and Floquet theory search methods were used to recognize the various initial guesses for attitude parameters. Each of these search methods was able to identify different initial guesses for attitude states. Moreover, as a new innovation, these search methods were applied as a powerful tool to select the appropriate inertia ratio for a satellite to deliver periodic responses from the coupled model. Adding the mentioned perturbations to the U-CRTBP could lead to the more accurate modeling of the examination environment and a better understanding of a spacecraft’s natural motion. A comparison between the orbit-attitude natural motions in the unperturbed and perturbed models was also conducted to show this claim.
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Majid Bakhtiari is an assistance professor and the head of the Multi-Satellite Space System Laboratory at the Iran University of Science and Technology. His technical researches focus on formation flying, satellite constellation design, three-body problem, distributed space systems, and space mission analysis. E-mail: bakhtiari_m@iust.ac.ir.
Ehsan Abbasali is currently a Ph.D. candidate in aerospace engineering with a minor in space engineering at the University of Tehran. He has teaching experience as a teacher assistant for three years in the areas of spacecraft’s orbit-attitude motion, optimal control, and advanced optimization methods. His research specialty and interest include satellite orbit-attitude analysis, multi-body dynamics, satellite constellation, numerical computations, evolutionary optimization, and optimal control. E-mail: ehsan.abbasali@ut.ac.ir.
Siavash Sabzy received his master degree in satellite technology engineering from Iran University of Science and Technology, Tehran, Iran, in 2020. His research interest focuses on astrodynamics and celestial mechanics, including spacecraft orbit and attitude dynamics as well as periodic motions within the multi-body systems. E-mail: siavash_sabzy@alumni.iust.ir.
Amirreza Kosari received his B.S. degree from Amirkabir University, Tehran, Iran, in 1998, and his M.S. and Ph.D. degrees from the Sharif University of Technology, Tehran, Iran, in 2001 and 2008, respectively. From 2010 to 2016, he was an assistant professor with the Faculty of New Sciences and Technologies, University of Tehran, Iran. Since 2017, he is an associate professor with the same faculty. His research interests include trajectory optimization, optimal control, cooperative flights, and spacecraft attitude control. He is the author of several papers in the areas indicated above. E-mail: kosari_a@ut.ac.ir.
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Bakhtiari, M., Abbasali, E., Sabzy, S. et al. Natural coupled orbit—attitude periodic motions in the perturbed-CRTBP including radiated primary and oblate secondary. Astrodyn 7, 229–249 (2023). https://doi.org/10.1007/s42064-022-0154-0
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DOI: https://doi.org/10.1007/s42064-022-0154-0