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Optimal control of satellite attitude and its stability based on quaternion parameters | ||
| Computational Methods for Differential Equations | ||
| مقالات آماده انتشار، پذیرفته شده، انتشار آنلاین از تاریخ 03 اسفند 1399 اصل مقاله (852.45 K) | ||
| نوع مقاله: Research Paper | ||
| شناسه دیجیتال (DOI): 10.22034/cmde.2021.43439.1854 | ||
| نویسندگان | ||
Mohammad Reza Niknam  1؛ Hossein Kheiri2؛ Nadereh Abdi Sobouhi3
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| 1Department of Mathematics, Islamic Azad University, Khalkhal Branch, Khalkhal, Iran. | ||
| 2Faculty of Mathematical Sciences, University of Tabriz, Tabriz, Iran. | ||
| 3Department of Mathematics, Farhangian University, Tabriz, Iran. | ||
| چکیده | ||
| This paper proposes an optimal control method for the chaotic attitude of the satellite when it is exposed to external disturbances. When there is no control over the satellite, its chaotic attitude is investigated using Lyapunov exponents (LEs), Poincare diagrams, and bifurcation diagrams. In order to overcome the problem of singularity in the great maneuvers of satellite, we consider the kinematic equations based on quaternion parameters instead of Euler angles, and obtain control functions by using the Pontryagin maximum principle (PMP). These functions are able to reach the satellite attitude to its equilibrium point. Also the asymptotic stability of these control functions is investigated by Lyapunov's stability theorem. Some simulation results are given to visualize the effectiveness and feasibility of the proposed method. | ||
| کلیدواژه‌ها | ||
| Optimal control؛ Stability؛ Quaternion؛ Chaotic systems | ||
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آمار تعداد مشاهده مقاله: 32 تعداد دریافت فایل اصل مقاله: 25 |
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