Gust Load Alleviation including Geometric Nonlinearities Based on Dynamic Linearization of Structural ROM
This paper describes a framework for an active control technique applied to gust load alleviation (GLA) of a flexible wing, including geometric nonlinearities. Nonlinear structure reduced order model (ROM) and nonplanar double-lattice method (DLM) are used for structural and aerodynamic modeling. Th...
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| Main Authors: | , , , |
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| Format: | Article |
| Language: | English |
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Wiley
2019-01-01
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| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2019/3207912 |
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| _version_ | 1832563717313658880 |
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| author | Chao An Chao Yang Changchuan Xie Yang Meng |
| author_facet | Chao An Chao Yang Changchuan Xie Yang Meng |
| author_sort | Chao An |
| collection | DOAJ |
| description | This paper describes a framework for an active control technique applied to gust load alleviation (GLA) of a flexible wing, including geometric nonlinearities. Nonlinear structure reduced order model (ROM) and nonplanar double-lattice method (DLM) are used for structural and aerodynamic modeling. The structural modeling method presented herein describes stiffness nonlinearities in polynomial formulation. Nonlinear stiffness can be derived by stepwise regression. Inertia terms are constant with linear approximation. Boundary conditions and kernel functions in the nonplanar DLM are determined by structural deformation to reflect a nonlinear effect. However, the governing equation is still linear. A state-space equation is established in a dynamic linearized system around the prescribed static equilibrium state after nonlinear static aeroelastic analysis. Gust response analysis can be conducted subsequently. For GLA analysis, a classic proportional-integral-derivative (PID) controller treats a servo as an actuator and acceleration as the feedback signal. Moreover, a wind tunnel test has been completed and the effectiveness of the control technology is validated. A remote-controlled (RC) model servo is chosen in the wind tunnel test. Numerical simulation results of gust response analysis reach agreement with test results. Furthermore, the control system gives GLA efficacy of vertical acceleration and root bending moment with the reduction rate being over 20%. The method described in this paper is suitable for gust response analysis and control strategy design for large flexible wings. |
| format | Article |
| id | doaj-art-8ffa5cd31fe545579bbacfe522787f14 |
| institution | Kabale University |
| issn | 1687-5966 1687-5974 |
| language | English |
| publishDate | 2019-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Aerospace Engineering |
| spelling | doaj-art-8ffa5cd31fe545579bbacfe522787f142025-02-03T01:12:51ZengWileyInternational Journal of Aerospace Engineering1687-59661687-59742019-01-01201910.1155/2019/32079123207912Gust Load Alleviation including Geometric Nonlinearities Based on Dynamic Linearization of Structural ROMChao An0Chao Yang1Changchuan Xie2Yang Meng3School of Aeronautics Science and Engineering, Beihang University, Beijing 100080, ChinaSchool of Aeronautics Science and Engineering, Beihang University, Beijing 100080, ChinaSchool of Aeronautics Science and Engineering, Beihang University, Beijing 100080, ChinaSchool of Aeronautics Science and Engineering, Beihang University, Beijing 100080, ChinaThis paper describes a framework for an active control technique applied to gust load alleviation (GLA) of a flexible wing, including geometric nonlinearities. Nonlinear structure reduced order model (ROM) and nonplanar double-lattice method (DLM) are used for structural and aerodynamic modeling. The structural modeling method presented herein describes stiffness nonlinearities in polynomial formulation. Nonlinear stiffness can be derived by stepwise regression. Inertia terms are constant with linear approximation. Boundary conditions and kernel functions in the nonplanar DLM are determined by structural deformation to reflect a nonlinear effect. However, the governing equation is still linear. A state-space equation is established in a dynamic linearized system around the prescribed static equilibrium state after nonlinear static aeroelastic analysis. Gust response analysis can be conducted subsequently. For GLA analysis, a classic proportional-integral-derivative (PID) controller treats a servo as an actuator and acceleration as the feedback signal. Moreover, a wind tunnel test has been completed and the effectiveness of the control technology is validated. A remote-controlled (RC) model servo is chosen in the wind tunnel test. Numerical simulation results of gust response analysis reach agreement with test results. Furthermore, the control system gives GLA efficacy of vertical acceleration and root bending moment with the reduction rate being over 20%. The method described in this paper is suitable for gust response analysis and control strategy design for large flexible wings.http://dx.doi.org/10.1155/2019/3207912 |
| spellingShingle | Chao An Chao Yang Changchuan Xie Yang Meng Gust Load Alleviation including Geometric Nonlinearities Based on Dynamic Linearization of Structural ROM International Journal of Aerospace Engineering |
| title | Gust Load Alleviation including Geometric Nonlinearities Based on Dynamic Linearization of Structural ROM |
| title_full | Gust Load Alleviation including Geometric Nonlinearities Based on Dynamic Linearization of Structural ROM |
| title_fullStr | Gust Load Alleviation including Geometric Nonlinearities Based on Dynamic Linearization of Structural ROM |
| title_full_unstemmed | Gust Load Alleviation including Geometric Nonlinearities Based on Dynamic Linearization of Structural ROM |
| title_short | Gust Load Alleviation including Geometric Nonlinearities Based on Dynamic Linearization of Structural ROM |
| title_sort | gust load alleviation including geometric nonlinearities based on dynamic linearization of structural rom |
| url | http://dx.doi.org/10.1155/2019/3207912 |
| work_keys_str_mv | AT chaoan gustloadalleviationincludinggeometricnonlinearitiesbasedondynamiclinearizationofstructuralrom AT chaoyang gustloadalleviationincludinggeometricnonlinearitiesbasedondynamiclinearizationofstructuralrom AT changchuanxie gustloadalleviationincludinggeometricnonlinearitiesbasedondynamiclinearizationofstructuralrom AT yangmeng gustloadalleviationincludinggeometricnonlinearitiesbasedondynamiclinearizationofstructuralrom |