A sliding mode controller for aircraft simulated entry into spin
In this paper, two controllers are presented for commanded departure of an aircraft into spin. The first controller is designed based on the information obtained from the bifurcation analysis results of the aircraft model and trial and error simulation experiments. The second controller is a nonline...
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sg-ntu-dr.10356-1071412019-12-06T22:25:33Z A sliding mode controller for aircraft simulated entry into spin Rao, D. M. K. K. Venkateswara. Sinha, Nandan Kumar. School of Mechanical and Aerospace Engineering In this paper, two controllers are presented for commanded departure of an aircraft into spin. The first controller is designed based on the information obtained from the bifurcation analysis results of the aircraft model and trial and error simulation experiments. The second controller is a nonlinear sliding mode controller also designed using bifurcation analysis results of the aircraft as reference maps. The sliding mode controller design problem is formulated as a trajectory tracking problem, where, the reference trajectory to be tracked is defined by spin simulation. Initial conditions are level-flight trim states, computed using extended bifurcation analysis and final states are stable, steady and flat oscillatory spin states. 2013-11-25T07:02:30Z 2019-12-06T22:25:33Z 2013-11-25T07:02:30Z 2019-12-06T22:25:33Z 2012 2012 Journal Article Rao, D. M. K. K. V. & Sinha, N. K. (2013). A sliding mode controller for aircraft simulated entry into spin. Aerospace Science and Technology, 28(1), 154-163. 1270-9638 https://hdl.handle.net/10356/107141 http://hdl.handle.net/10220/17829 http://dx.doi.org/10.1016/j.ast.2012.10.011 en Aerospace science and technology |
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In this paper, two controllers are presented for commanded departure of an aircraft into spin. The first controller is designed based on the information obtained from the bifurcation analysis results of the aircraft model and trial and error simulation experiments. The second controller is a nonlinear sliding mode controller also designed using bifurcation analysis results of the aircraft as reference maps. The sliding mode controller design problem is formulated as a trajectory tracking problem, where, the reference trajectory to be tracked is defined by spin simulation. Initial conditions are level-flight trim states, computed using extended bifurcation analysis and final states are stable, steady and flat oscillatory spin states. |
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School of Mechanical and Aerospace Engineering |
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School of Mechanical and Aerospace Engineering Rao, D. M. K. K. Venkateswara. Sinha, Nandan Kumar. |
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Article |
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Rao, D. M. K. K. Venkateswara. Sinha, Nandan Kumar. |
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Rao, D. M. K. K. Venkateswara. Sinha, Nandan Kumar. A sliding mode controller for aircraft simulated entry into spin |
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Rao, D. M. K. K. Venkateswara. |
title |
A sliding mode controller for aircraft simulated entry into spin |
title_short |
A sliding mode controller for aircraft simulated entry into spin |
title_full |
A sliding mode controller for aircraft simulated entry into spin |
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A sliding mode controller for aircraft simulated entry into spin |
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A sliding mode controller for aircraft simulated entry into spin |
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sliding mode controller for aircraft simulated entry into spin |
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2013 |
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https://hdl.handle.net/10356/107141 http://hdl.handle.net/10220/17829 http://dx.doi.org/10.1016/j.ast.2012.10.011 |
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