Volume 15, Issue 2 (2015)
MJEE 2015, 15(2): 9-13 |
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Mazinan A H. On High-Precision Three-Axis Attitude Control Scheme through Hybrid Finite-Time Sliding Mode Approach. MJEE 2015; 15 (2) :9-13
URL: http://mjee.modares.ac.ir/article-17-1465-en.html
URL: http://mjee.modares.ac.ir/article-17-1465-en.html
Department of Control Engineering, Faculty of Electrical Engineering, South Tehran Branch, Islamic Azad University (IAU), No. 209, North Iranshahr St., P.O. Box 11365/4435, Tehran, Iran
Abstract: (4887 Views)
High-precision three-axis attitude control scheme is vitally important to deal with the overactuated spacecraft, as long as the overall performance through rapid response can be in general acquired. Due to the fact that the rigid-flexible spacecraft is somehow applicable, in so many academic and real environments, there is a consensus among experts of this field that the new insights in developing the present complicated systems modeling and control are highly recommended with respect to state-of-the-art. The new hybrid control scheme presented here is organized in line with the linear approach, which includes the proportional derivative based quadratic regulator and the nonlinear approach, which includes finite-time sliding mode control, as well. It should be noted that the three-axis angular rates of spacecraft under control are all dealt with in inner closed loop control and the corresponding rotation angles are also dealt with in outer closed loop control, synchronously.
Keywords: hybrid three-axis attitude control scheme, proportional derivative based linear quadratic regulator, finite-time sliding mode control, overactuated spacecraft
Received: 2015/08/31 | Accepted: 2016/09/18 | Published: 2038/01/19
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