Experimental Nonlinear Control for Flutter Suppression in a Nonlinear Aeroelastic System

Jiffri, Shakir; Fichera, Sebastiano; Mottershead, John E.; Ronch, Andrea Da

doi:10.2514/1.g002519

Journal article 1262 views 216 downloads

Experimental Nonlinear Control for Flutter Suppression in a Nonlinear Aeroelastic System

Shakir Jiffri

, Sebastiano Fichera, John E. Mottershead, Andrea Da Ronch

Journal of Guidance, Control, and Dynamics, Volume: 40, Issue: 8, Pages: 1925 - 1938

Swansea University Author: Shakir Jiffri

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DOI (Published version): 10.2514/1.g002519

Abstract

Experimental implementation of input–output feedback linearization in controlling the dynamics of a nonlinear pitch–plunge aeroelastic system is presented. The control objective is to linearize the system dynamics and assign the poles of the pitch mode of the resulting linear system. The implementat...

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Published in:	Journal of Guidance, Control, and Dynamics
ISSN:	0731-5090 1533-3884
Published:	2017
Online Access:	Check full text
URI:	https://cronfa.swan.ac.uk/Record/cronfa36832
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first_indexed	2017-11-20T14:26:06Z
last_indexed	2021-01-15T03:57:30Z
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spelling	2021-01-14T12:59:56.9092414 v2 36832 2017-11-20 Experimental Nonlinear Control for Flutter Suppression in a Nonlinear Aeroelastic System 1d7a7d2a8f10ec98afed15a4b4b791c4 0000-0002-5570-5783 Shakir Jiffri Shakir Jiffri true false 2017-11-20 AERO Experimental implementation of input–output feedback linearization in controlling the dynamics of a nonlinear pitch–plunge aeroelastic system is presented. The control objective is to linearize the system dynamics and assign the poles of the pitch mode of the resulting linear system. The implementation 1) addresses experimentally the general case where feedback linearization-based control is applied using as the output a degree of freedom other than that where the physical nonlinearity is located, using a single trailing-edge control surface, to stabilize the entire system; 2) includes the unsteady effects of the airfoil’s aerodynamic behavior; 3) includes the embedding of a tuned numerical model of the aeroelastic system into the control scheme in real time; and 4) uses pole placement as the linear control objective, providing the user with flexibility in determining the nature of the controlled response. When implemented experimentally, the controller is capable of not only delaying the onset of limit-cycle oscillation but also successfully eliminating a previously established limit-cycle oscillation. The assignment of higher levels of damping results in notable reductions in limit-cycle oscillation decay times in the closed-loop response, indicating good controllability of the aeroelastic system and effectiveness of the pole-placement objective. The closed-loop response is further improved by incorporating adaptation so that assumed system parameters are updated with time. The use of an optimum adaptation parameter results in reduced response decay times. Journal Article Journal of Guidance, Control, and Dynamics 40 8 1925 1938 0731-5090 1533-3884 1 8 2017 2017-08-01 10.2514/1.g002519 COLLEGE NANME Aerospace Engineering COLLEGE CODE AERO Swansea University 2021-01-14T12:59:56.9092414 2017-11-20T11:13:51.6457978 Faculty of Science and Engineering School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Aerospace Engineering Shakir Jiffri 0000-0002-5570-5783 1 Sebastiano Fichera 2 John E. Mottershead 3 Andrea Da Ronch 4 36832__17548__02d3bb069fb34a57b20c294d41732752.pdf 36832.pdf 2020-06-19T15:03:15.5081045 Output 1228485 application/pdf Accepted Manuscript true false
title	Experimental Nonlinear Control for Flutter Suppression in a Nonlinear Aeroelastic System
spellingShingle	Experimental Nonlinear Control for Flutter Suppression in a Nonlinear Aeroelastic System Shakir Jiffri
title_short	Experimental Nonlinear Control for Flutter Suppression in a Nonlinear Aeroelastic System
title_full	Experimental Nonlinear Control for Flutter Suppression in a Nonlinear Aeroelastic System
title_fullStr	Experimental Nonlinear Control for Flutter Suppression in a Nonlinear Aeroelastic System
title_full_unstemmed	Experimental Nonlinear Control for Flutter Suppression in a Nonlinear Aeroelastic System
title_sort	Experimental Nonlinear Control for Flutter Suppression in a Nonlinear Aeroelastic System
author_id_str_mv	1d7a7d2a8f10ec98afed15a4b4b791c4
author_id_fullname_str_mv	1d7a7d2a8f10ec98afed15a4b4b791c4_***_Shakir Jiffri
author	Shakir Jiffri
author2	Shakir Jiffri Sebastiano Fichera John E. Mottershead Andrea Da Ronch
format	Journal article
container_title	Journal of Guidance, Control, and Dynamics
container_volume	40
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container_start_page	1925
publishDate	2017
institution	Swansea University
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doi_str_mv	10.2514/1.g002519
college_str	Faculty of Science and Engineering
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department_str	School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Aerospace Engineering{{{_:::_}}}Faculty of Science and Engineering{{{_:::_}}}School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Aerospace Engineering
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description	Experimental implementation of input–output feedback linearization in controlling the dynamics of a nonlinear pitch–plunge aeroelastic system is presented. The control objective is to linearize the system dynamics and assign the poles of the pitch mode of the resulting linear system. The implementation 1) addresses experimentally the general case where feedback linearization-based control is applied using as the output a degree of freedom other than that where the physical nonlinearity is located, using a single trailing-edge control surface, to stabilize the entire system; 2) includes the unsteady effects of the airfoil’s aerodynamic behavior; 3) includes the embedding of a tuned numerical model of the aeroelastic system into the control scheme in real time; and 4) uses pole placement as the linear control objective, providing the user with flexibility in determining the nature of the controlled response. When implemented experimentally, the controller is capable of not only delaying the onset of limit-cycle oscillation but also successfully eliminating a previously established limit-cycle oscillation. The assignment of higher levels of damping results in notable reductions in limit-cycle oscillation decay times in the closed-loop response, indicating good controllability of the aeroelastic system and effectiveness of the pole-placement objective. The closed-loop response is further improved by incorporating adaptation so that assumed system parameters are updated with time. The use of an optimum adaptation parameter results in reduced response decay times.
published_date	2017-08-01T03:46:11Z
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Experimental Nonlinear Control for Flutter Suppression in a Nonlinear Aeroelastic System

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