Modeling and Control Design for Flutter Suppression Using Active Dynamic Vibration Absorber

Background Enhancing the efficiency of modern aeronautic structures necessitates flexibility increasing associated with weight reduction. A consequent possibility of unfavorable unsteady aeroelastic phenomena such as flutter arises due to the interaction between the elastic, aerodynamic, and inertia...
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Autor*in:	Kassem, Mohammed [verfasserIn] Yang, Zhichun [verfasserIn] Gu, Yingsong [verfasserIn] Wang, Wei [verfasserIn]

Format:	E-Artikel
Sprache:	Englisch

Erschienen:	2021

Schlagwörter:	Flutter suppression Active control Dynamic vibration absorber

Anmerkung:	© Krishtel eMaging Solutions Private Limited 2021

Übergeordnetes Werk:	Enthalten in: Journal of vibration engineering & technologies - Singapore : Springer Singapore, 2018, 9(2021), 5 vom: 03. Jan., Seite 845-860
Übergeordnetes Werk:	volume:9 ; year:2021 ; number:5 ; day:03 ; month:01 ; pages:845-860

Links:	Volltext

DOI / URN:	10.1007/s42417-020-00267-6

Katalog-ID:	SPR044957777

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245	1	0	\|a Modeling and Control Design for Flutter Suppression Using Active Dynamic Vibration Absorber
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520			\|a Background Enhancing the efficiency of modern aeronautic structures necessitates flexibility increasing associated with weight reduction. A consequent possibility of unfavorable unsteady aeroelastic phenomena such as flutter arises due to the interaction between the elastic, aerodynamic, and inertia loads. Researchers work hard to suppress it using numerous passive and active techniques. Purpose This paper presents the mathematical model and the optimal control of an active technique for flutter mitigation of an airfoil system undergoing incompressible flow. Methods The proposed active dynamic vibration absorber (ADVA) comprises an active element together with a classical mass–spring–damper system. In the active mode, a controlling force is generated by the active element to actuate the mass using feedback from the vibration responses of the aeroelastic airfoil system. A non-dimensional mathematical model for a typical two-degree-of-freedom aeroelastic airfoil integrated with the ADVA is introduced based on unsteady aerodynamic theory. The effect of the ADVA parameters on the aeroelastic system stability is investigated in different flight conditions. Additionally, two feedback controllers are presented to analyze the closed-loop system. The control gains are optimized based on a genetic algorithm to improve the performance of the proposed ADVA. Results Introducing the passive dynamic absorber increases the flutter speed by about 15%, while activating the ADVA at the new flutter speed stabilizes the system and further expands the airfoil flutter boundaries. Conclusion The proposed ADVA ensures flutter suppression and extends the flutter boundary. Furthermore, the introduced flutter control technique is robust against the variation of the system parameters and the detuning of the ADVA parameters.
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700	1		\|a Yang, Zhichun \|e verfasserin \|4 aut
700	1		\|a Gu, Yingsong \|e verfasserin \|4 aut
700	1		\|a Wang, Wei \|e verfasserin \|4 aut
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allfields	10.1007/s42417-020-00267-6 doi (DE-627)SPR044957777 (SPR)s42417-020-00267-6-e DE-627 ger DE-627 rakwb eng 620 ASE 620 ASE Kassem, Mohammed verfasserin aut Modeling and Control Design for Flutter Suppression Using Active Dynamic Vibration Absorber 2021 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © Krishtel eMaging Solutions Private Limited 2021 Background Enhancing the efficiency of modern aeronautic structures necessitates flexibility increasing associated with weight reduction. A consequent possibility of unfavorable unsteady aeroelastic phenomena such as flutter arises due to the interaction between the elastic, aerodynamic, and inertia loads. Researchers work hard to suppress it using numerous passive and active techniques. Purpose This paper presents the mathematical model and the optimal control of an active technique for flutter mitigation of an airfoil system undergoing incompressible flow. Methods The proposed active dynamic vibration absorber (ADVA) comprises an active element together with a classical mass–spring–damper system. In the active mode, a controlling force is generated by the active element to actuate the mass using feedback from the vibration responses of the aeroelastic airfoil system. A non-dimensional mathematical model for a typical two-degree-of-freedom aeroelastic airfoil integrated with the ADVA is introduced based on unsteady aerodynamic theory. The effect of the ADVA parameters on the aeroelastic system stability is investigated in different flight conditions. Additionally, two feedback controllers are presented to analyze the closed-loop system. The control gains are optimized based on a genetic algorithm to improve the performance of the proposed ADVA. Results Introducing the passive dynamic absorber increases the flutter speed by about 15%, while activating the ADVA at the new flutter speed stabilizes the system and further expands the airfoil flutter boundaries. Conclusion The proposed ADVA ensures flutter suppression and extends the flutter boundary. Furthermore, the introduced flutter control technique is robust against the variation of the system parameters and the detuning of the ADVA parameters. Flutter suppression (dpeaa)DE-He213 Active control (dpeaa)DE-He213 Dynamic vibration absorber (dpeaa)DE-He213 Yang, Zhichun verfasserin aut Gu, Yingsong verfasserin aut Wang, Wei verfasserin aut Enthalten in Journal of vibration engineering & technologies Singapore : Springer Singapore, 2018 9(2021), 5 vom: 03. Jan., Seite 845-860 (DE-627)1030123837 (DE-600)2941414-3 2523-3939 nnns volume:9 year:2021 number:5 day:03 month:01 pages:845-860 https://dx.doi.org/10.1007/s42417-020-00267-6 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_152 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2056 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4328 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 9 2021 5 03 01 845-860
spelling	10.1007/s42417-020-00267-6 doi (DE-627)SPR044957777 (SPR)s42417-020-00267-6-e DE-627 ger DE-627 rakwb eng 620 ASE 620 ASE Kassem, Mohammed verfasserin aut Modeling and Control Design for Flutter Suppression Using Active Dynamic Vibration Absorber 2021 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © Krishtel eMaging Solutions Private Limited 2021 Background Enhancing the efficiency of modern aeronautic structures necessitates flexibility increasing associated with weight reduction. A consequent possibility of unfavorable unsteady aeroelastic phenomena such as flutter arises due to the interaction between the elastic, aerodynamic, and inertia loads. Researchers work hard to suppress it using numerous passive and active techniques. Purpose This paper presents the mathematical model and the optimal control of an active technique for flutter mitigation of an airfoil system undergoing incompressible flow. Methods The proposed active dynamic vibration absorber (ADVA) comprises an active element together with a classical mass–spring–damper system. In the active mode, a controlling force is generated by the active element to actuate the mass using feedback from the vibration responses of the aeroelastic airfoil system. A non-dimensional mathematical model for a typical two-degree-of-freedom aeroelastic airfoil integrated with the ADVA is introduced based on unsteady aerodynamic theory. The effect of the ADVA parameters on the aeroelastic system stability is investigated in different flight conditions. Additionally, two feedback controllers are presented to analyze the closed-loop system. The control gains are optimized based on a genetic algorithm to improve the performance of the proposed ADVA. Results Introducing the passive dynamic absorber increases the flutter speed by about 15%, while activating the ADVA at the new flutter speed stabilizes the system and further expands the airfoil flutter boundaries. Conclusion The proposed ADVA ensures flutter suppression and extends the flutter boundary. Furthermore, the introduced flutter control technique is robust against the variation of the system parameters and the detuning of the ADVA parameters. Flutter suppression (dpeaa)DE-He213 Active control (dpeaa)DE-He213 Dynamic vibration absorber (dpeaa)DE-He213 Yang, Zhichun verfasserin aut Gu, Yingsong verfasserin aut Wang, Wei verfasserin aut Enthalten in Journal of vibration engineering & technologies Singapore : Springer Singapore, 2018 9(2021), 5 vom: 03. Jan., Seite 845-860 (DE-627)1030123837 (DE-600)2941414-3 2523-3939 nnns volume:9 year:2021 number:5 day:03 month:01 pages:845-860 https://dx.doi.org/10.1007/s42417-020-00267-6 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_152 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2056 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4328 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 9 2021 5 03 01 845-860
allfields_unstemmed	10.1007/s42417-020-00267-6 doi (DE-627)SPR044957777 (SPR)s42417-020-00267-6-e DE-627 ger DE-627 rakwb eng 620 ASE 620 ASE Kassem, Mohammed verfasserin aut Modeling and Control Design for Flutter Suppression Using Active Dynamic Vibration Absorber 2021 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © Krishtel eMaging Solutions Private Limited 2021 Background Enhancing the efficiency of modern aeronautic structures necessitates flexibility increasing associated with weight reduction. A consequent possibility of unfavorable unsteady aeroelastic phenomena such as flutter arises due to the interaction between the elastic, aerodynamic, and inertia loads. Researchers work hard to suppress it using numerous passive and active techniques. Purpose This paper presents the mathematical model and the optimal control of an active technique for flutter mitigation of an airfoil system undergoing incompressible flow. Methods The proposed active dynamic vibration absorber (ADVA) comprises an active element together with a classical mass–spring–damper system. In the active mode, a controlling force is generated by the active element to actuate the mass using feedback from the vibration responses of the aeroelastic airfoil system. A non-dimensional mathematical model for a typical two-degree-of-freedom aeroelastic airfoil integrated with the ADVA is introduced based on unsteady aerodynamic theory. The effect of the ADVA parameters on the aeroelastic system stability is investigated in different flight conditions. Additionally, two feedback controllers are presented to analyze the closed-loop system. The control gains are optimized based on a genetic algorithm to improve the performance of the proposed ADVA. Results Introducing the passive dynamic absorber increases the flutter speed by about 15%, while activating the ADVA at the new flutter speed stabilizes the system and further expands the airfoil flutter boundaries. Conclusion The proposed ADVA ensures flutter suppression and extends the flutter boundary. Furthermore, the introduced flutter control technique is robust against the variation of the system parameters and the detuning of the ADVA parameters. Flutter suppression (dpeaa)DE-He213 Active control (dpeaa)DE-He213 Dynamic vibration absorber (dpeaa)DE-He213 Yang, Zhichun verfasserin aut Gu, Yingsong verfasserin aut Wang, Wei verfasserin aut Enthalten in Journal of vibration engineering & technologies Singapore : Springer Singapore, 2018 9(2021), 5 vom: 03. Jan., Seite 845-860 (DE-627)1030123837 (DE-600)2941414-3 2523-3939 nnns volume:9 year:2021 number:5 day:03 month:01 pages:845-860 https://dx.doi.org/10.1007/s42417-020-00267-6 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_152 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2056 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4328 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 9 2021 5 03 01 845-860
allfieldsGer	10.1007/s42417-020-00267-6 doi (DE-627)SPR044957777 (SPR)s42417-020-00267-6-e DE-627 ger DE-627 rakwb eng 620 ASE 620 ASE Kassem, Mohammed verfasserin aut Modeling and Control Design for Flutter Suppression Using Active Dynamic Vibration Absorber 2021 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © Krishtel eMaging Solutions Private Limited 2021 Background Enhancing the efficiency of modern aeronautic structures necessitates flexibility increasing associated with weight reduction. A consequent possibility of unfavorable unsteady aeroelastic phenomena such as flutter arises due to the interaction between the elastic, aerodynamic, and inertia loads. Researchers work hard to suppress it using numerous passive and active techniques. Purpose This paper presents the mathematical model and the optimal control of an active technique for flutter mitigation of an airfoil system undergoing incompressible flow. Methods The proposed active dynamic vibration absorber (ADVA) comprises an active element together with a classical mass–spring–damper system. In the active mode, a controlling force is generated by the active element to actuate the mass using feedback from the vibration responses of the aeroelastic airfoil system. A non-dimensional mathematical model for a typical two-degree-of-freedom aeroelastic airfoil integrated with the ADVA is introduced based on unsteady aerodynamic theory. The effect of the ADVA parameters on the aeroelastic system stability is investigated in different flight conditions. Additionally, two feedback controllers are presented to analyze the closed-loop system. The control gains are optimized based on a genetic algorithm to improve the performance of the proposed ADVA. Results Introducing the passive dynamic absorber increases the flutter speed by about 15%, while activating the ADVA at the new flutter speed stabilizes the system and further expands the airfoil flutter boundaries. Conclusion The proposed ADVA ensures flutter suppression and extends the flutter boundary. Furthermore, the introduced flutter control technique is robust against the variation of the system parameters and the detuning of the ADVA parameters. Flutter suppression (dpeaa)DE-He213 Active control (dpeaa)DE-He213 Dynamic vibration absorber (dpeaa)DE-He213 Yang, Zhichun verfasserin aut Gu, Yingsong verfasserin aut Wang, Wei verfasserin aut Enthalten in Journal of vibration engineering & technologies Singapore : Springer Singapore, 2018 9(2021), 5 vom: 03. Jan., Seite 845-860 (DE-627)1030123837 (DE-600)2941414-3 2523-3939 nnns volume:9 year:2021 number:5 day:03 month:01 pages:845-860 https://dx.doi.org/10.1007/s42417-020-00267-6 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_152 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2056 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4328 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 9 2021 5 03 01 845-860
allfieldsSound	10.1007/s42417-020-00267-6 doi (DE-627)SPR044957777 (SPR)s42417-020-00267-6-e DE-627 ger DE-627 rakwb eng 620 ASE 620 ASE Kassem, Mohammed verfasserin aut Modeling and Control Design for Flutter Suppression Using Active Dynamic Vibration Absorber 2021 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier © Krishtel eMaging Solutions Private Limited 2021 Background Enhancing the efficiency of modern aeronautic structures necessitates flexibility increasing associated with weight reduction. A consequent possibility of unfavorable unsteady aeroelastic phenomena such as flutter arises due to the interaction between the elastic, aerodynamic, and inertia loads. Researchers work hard to suppress it using numerous passive and active techniques. Purpose This paper presents the mathematical model and the optimal control of an active technique for flutter mitigation of an airfoil system undergoing incompressible flow. Methods The proposed active dynamic vibration absorber (ADVA) comprises an active element together with a classical mass–spring–damper system. In the active mode, a controlling force is generated by the active element to actuate the mass using feedback from the vibration responses of the aeroelastic airfoil system. A non-dimensional mathematical model for a typical two-degree-of-freedom aeroelastic airfoil integrated with the ADVA is introduced based on unsteady aerodynamic theory. The effect of the ADVA parameters on the aeroelastic system stability is investigated in different flight conditions. Additionally, two feedback controllers are presented to analyze the closed-loop system. The control gains are optimized based on a genetic algorithm to improve the performance of the proposed ADVA. Results Introducing the passive dynamic absorber increases the flutter speed by about 15%, while activating the ADVA at the new flutter speed stabilizes the system and further expands the airfoil flutter boundaries. Conclusion The proposed ADVA ensures flutter suppression and extends the flutter boundary. Furthermore, the introduced flutter control technique is robust against the variation of the system parameters and the detuning of the ADVA parameters. Flutter suppression (dpeaa)DE-He213 Active control (dpeaa)DE-He213 Dynamic vibration absorber (dpeaa)DE-He213 Yang, Zhichun verfasserin aut Gu, Yingsong verfasserin aut Wang, Wei verfasserin aut Enthalten in Journal of vibration engineering & technologies Singapore : Springer Singapore, 2018 9(2021), 5 vom: 03. Jan., Seite 845-860 (DE-627)1030123837 (DE-600)2941414-3 2523-3939 nnns volume:9 year:2021 number:5 day:03 month:01 pages:845-860 https://dx.doi.org/10.1007/s42417-020-00267-6 lizenzpflichtig Volltext GBV_USEFLAG_A SYSFLAG_A GBV_SPRINGER GBV_ILN_11 GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 GBV_ILN_31 GBV_ILN_32 GBV_ILN_39 GBV_ILN_40 GBV_ILN_60 GBV_ILN_62 GBV_ILN_63 GBV_ILN_65 GBV_ILN_69 GBV_ILN_70 GBV_ILN_73 GBV_ILN_74 GBV_ILN_90 GBV_ILN_95 GBV_ILN_100 GBV_ILN_105 GBV_ILN_110 GBV_ILN_138 GBV_ILN_150 GBV_ILN_151 GBV_ILN_152 GBV_ILN_161 GBV_ILN_170 GBV_ILN_171 GBV_ILN_187 GBV_ILN_213 GBV_ILN_224 GBV_ILN_230 GBV_ILN_250 GBV_ILN_281 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_636 GBV_ILN_702 GBV_ILN_2001 GBV_ILN_2003 GBV_ILN_2004 GBV_ILN_2005 GBV_ILN_2006 GBV_ILN_2007 GBV_ILN_2008 GBV_ILN_2009 GBV_ILN_2010 GBV_ILN_2011 GBV_ILN_2014 GBV_ILN_2015 GBV_ILN_2020 GBV_ILN_2021 GBV_ILN_2025 GBV_ILN_2026 GBV_ILN_2027 GBV_ILN_2031 GBV_ILN_2034 GBV_ILN_2037 GBV_ILN_2038 GBV_ILN_2039 GBV_ILN_2044 GBV_ILN_2048 GBV_ILN_2049 GBV_ILN_2050 GBV_ILN_2055 GBV_ILN_2056 GBV_ILN_2057 GBV_ILN_2059 GBV_ILN_2061 GBV_ILN_2064 GBV_ILN_2065 GBV_ILN_2068 GBV_ILN_2088 GBV_ILN_2093 GBV_ILN_2106 GBV_ILN_2107 GBV_ILN_2108 GBV_ILN_2110 GBV_ILN_2111 GBV_ILN_2112 GBV_ILN_2113 GBV_ILN_2118 GBV_ILN_2122 GBV_ILN_2129 GBV_ILN_2143 GBV_ILN_2144 GBV_ILN_2147 GBV_ILN_2148 GBV_ILN_2152 GBV_ILN_2153 GBV_ILN_2188 GBV_ILN_2190 GBV_ILN_2232 GBV_ILN_2336 GBV_ILN_2446 GBV_ILN_2470 GBV_ILN_2472 GBV_ILN_2507 GBV_ILN_2522 GBV_ILN_2548 GBV_ILN_4035 GBV_ILN_4037 GBV_ILN_4046 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4242 GBV_ILN_4246 GBV_ILN_4249 GBV_ILN_4251 GBV_ILN_4305 GBV_ILN_4306 GBV_ILN_4307 GBV_ILN_4313 GBV_ILN_4322 GBV_ILN_4323 GBV_ILN_4324 GBV_ILN_4325 GBV_ILN_4326 GBV_ILN_4328 GBV_ILN_4333 GBV_ILN_4334 GBV_ILN_4335 GBV_ILN_4336 GBV_ILN_4338 GBV_ILN_4393 GBV_ILN_4700 AR 9 2021 5 03 01 845-860
language	English
source	Enthalten in Journal of vibration engineering & technologies 9(2021), 5 vom: 03. Jan., Seite 845-860 volume:9 year:2021 number:5 day:03 month:01 pages:845-860
sourceStr	Enthalten in Journal of vibration engineering & technologies 9(2021), 5 vom: 03. Jan., Seite 845-860 volume:9 year:2021 number:5 day:03 month:01 pages:845-860
format_phy_str_mv	Article
institution	findex.gbv.de
topic_facet	Flutter suppression Active control Dynamic vibration absorber
dewey-raw	620
isfreeaccess_bool	false
container_title	Journal of vibration engineering & technologies
authorswithroles_txt_mv	Kassem, Mohammed @@aut@@ Yang, Zhichun @@aut@@ Gu, Yingsong @@aut@@ Wang, Wei @@aut@@
publishDateDaySort_date	2021-01-03T00:00:00Z
hierarchy_top_id	1030123837
dewey-sort	3620
id	SPR044957777
language_de	englisch
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A consequent possibility of unfavorable unsteady aeroelastic phenomena such as flutter arises due to the interaction between the elastic, aerodynamic, and inertia loads. Researchers work hard to suppress it using numerous passive and active techniques. Purpose This paper presents the mathematical model and the optimal control of an active technique for flutter mitigation of an airfoil system undergoing incompressible flow. Methods The proposed active dynamic vibration absorber (ADVA) comprises an active element together with a classical mass–spring–damper system. In the active mode, a controlling force is generated by the active element to actuate the mass using feedback from the vibration responses of the aeroelastic airfoil system. A non-dimensional mathematical model for a typical two-degree-of-freedom aeroelastic airfoil integrated with the ADVA is introduced based on unsteady aerodynamic theory. The effect of the ADVA parameters on the aeroelastic system stability is investigated in different flight conditions. Additionally, two feedback controllers are presented to analyze the closed-loop system. The control gains are optimized based on a genetic algorithm to improve the performance of the proposed ADVA. Results Introducing the passive dynamic absorber increases the flutter speed by about 15%, while activating the ADVA at the new flutter speed stabilizes the system and further expands the airfoil flutter boundaries. Conclusion The proposed ADVA ensures flutter suppression and extends the flutter boundary. 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author	Kassem, Mohammed
spellingShingle	Kassem, Mohammed ddc 620 misc Flutter suppression misc Active control misc Dynamic vibration absorber Modeling and Control Design for Flutter Suppression Using Active Dynamic Vibration Absorber
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topic_title	620 ASE Modeling and Control Design for Flutter Suppression Using Active Dynamic Vibration Absorber Flutter suppression (dpeaa)DE-He213 Active control (dpeaa)DE-He213 Dynamic vibration absorber (dpeaa)DE-He213
topic	ddc 620 misc Flutter suppression misc Active control misc Dynamic vibration absorber
topic_unstemmed	ddc 620 misc Flutter suppression misc Active control misc Dynamic vibration absorber
topic_browse	ddc 620 misc Flutter suppression misc Active control misc Dynamic vibration absorber
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title	Modeling and Control Design for Flutter Suppression Using Active Dynamic Vibration Absorber
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title_full	Modeling and Control Design for Flutter Suppression Using Active Dynamic Vibration Absorber
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journal	Journal of vibration engineering & technologies
journalStr	Journal of vibration engineering & technologies
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author_browse	Kassem, Mohammed Yang, Zhichun Gu, Yingsong Wang, Wei
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class	620 ASE
format_se	Elektronische Aufsätze
author-letter	Kassem, Mohammed
doi_str_mv	10.1007/s42417-020-00267-6
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title_sort	modeling and control design for flutter suppression using active dynamic vibration absorber
title_auth	Modeling and Control Design for Flutter Suppression Using Active Dynamic Vibration Absorber
abstract	Background Enhancing the efficiency of modern aeronautic structures necessitates flexibility increasing associated with weight reduction. A consequent possibility of unfavorable unsteady aeroelastic phenomena such as flutter arises due to the interaction between the elastic, aerodynamic, and inertia loads. Researchers work hard to suppress it using numerous passive and active techniques. Purpose This paper presents the mathematical model and the optimal control of an active technique for flutter mitigation of an airfoil system undergoing incompressible flow. Methods The proposed active dynamic vibration absorber (ADVA) comprises an active element together with a classical mass–spring–damper system. In the active mode, a controlling force is generated by the active element to actuate the mass using feedback from the vibration responses of the aeroelastic airfoil system. A non-dimensional mathematical model for a typical two-degree-of-freedom aeroelastic airfoil integrated with the ADVA is introduced based on unsteady aerodynamic theory. The effect of the ADVA parameters on the aeroelastic system stability is investigated in different flight conditions. Additionally, two feedback controllers are presented to analyze the closed-loop system. The control gains are optimized based on a genetic algorithm to improve the performance of the proposed ADVA. Results Introducing the passive dynamic absorber increases the flutter speed by about 15%, while activating the ADVA at the new flutter speed stabilizes the system and further expands the airfoil flutter boundaries. Conclusion The proposed ADVA ensures flutter suppression and extends the flutter boundary. Furthermore, the introduced flutter control technique is robust against the variation of the system parameters and the detuning of the ADVA parameters. © Krishtel eMaging Solutions Private Limited 2021
abstractGer	Background Enhancing the efficiency of modern aeronautic structures necessitates flexibility increasing associated with weight reduction. A consequent possibility of unfavorable unsteady aeroelastic phenomena such as flutter arises due to the interaction between the elastic, aerodynamic, and inertia loads. Researchers work hard to suppress it using numerous passive and active techniques. Purpose This paper presents the mathematical model and the optimal control of an active technique for flutter mitigation of an airfoil system undergoing incompressible flow. Methods The proposed active dynamic vibration absorber (ADVA) comprises an active element together with a classical mass–spring–damper system. In the active mode, a controlling force is generated by the active element to actuate the mass using feedback from the vibration responses of the aeroelastic airfoil system. A non-dimensional mathematical model for a typical two-degree-of-freedom aeroelastic airfoil integrated with the ADVA is introduced based on unsteady aerodynamic theory. The effect of the ADVA parameters on the aeroelastic system stability is investigated in different flight conditions. Additionally, two feedback controllers are presented to analyze the closed-loop system. The control gains are optimized based on a genetic algorithm to improve the performance of the proposed ADVA. Results Introducing the passive dynamic absorber increases the flutter speed by about 15%, while activating the ADVA at the new flutter speed stabilizes the system and further expands the airfoil flutter boundaries. Conclusion The proposed ADVA ensures flutter suppression and extends the flutter boundary. Furthermore, the introduced flutter control technique is robust against the variation of the system parameters and the detuning of the ADVA parameters. © Krishtel eMaging Solutions Private Limited 2021
abstract_unstemmed	Background Enhancing the efficiency of modern aeronautic structures necessitates flexibility increasing associated with weight reduction. A consequent possibility of unfavorable unsteady aeroelastic phenomena such as flutter arises due to the interaction between the elastic, aerodynamic, and inertia loads. Researchers work hard to suppress it using numerous passive and active techniques. Purpose This paper presents the mathematical model and the optimal control of an active technique for flutter mitigation of an airfoil system undergoing incompressible flow. Methods The proposed active dynamic vibration absorber (ADVA) comprises an active element together with a classical mass–spring–damper system. In the active mode, a controlling force is generated by the active element to actuate the mass using feedback from the vibration responses of the aeroelastic airfoil system. A non-dimensional mathematical model for a typical two-degree-of-freedom aeroelastic airfoil integrated with the ADVA is introduced based on unsteady aerodynamic theory. The effect of the ADVA parameters on the aeroelastic system stability is investigated in different flight conditions. Additionally, two feedback controllers are presented to analyze the closed-loop system. The control gains are optimized based on a genetic algorithm to improve the performance of the proposed ADVA. Results Introducing the passive dynamic absorber increases the flutter speed by about 15%, while activating the ADVA at the new flutter speed stabilizes the system and further expands the airfoil flutter boundaries. Conclusion The proposed ADVA ensures flutter suppression and extends the flutter boundary. Furthermore, the introduced flutter control technique is robust against the variation of the system parameters and the detuning of the ADVA parameters. © Krishtel eMaging Solutions Private Limited 2021
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title_short	Modeling and Control Design for Flutter Suppression Using Active Dynamic Vibration Absorber
url	https://dx.doi.org/10.1007/s42417-020-00267-6
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author2	Yang, Zhichun Gu, Yingsong Wang, Wei
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doi_str	10.1007/s42417-020-00267-6
up_date	2024-07-04T02:56:51.474Z
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fullrecord_marcxml	<?xml version="1.0" encoding="UTF-8"?><collection xmlns="http://www.loc.gov/MARC21/slim"><record><leader>01000caa a22002652 4500</leader><controlfield tag="001">SPR044957777</controlfield><controlfield tag="003">DE-627</controlfield><controlfield tag="005">20220112043527.0</controlfield><controlfield tag="007">cr uuu---uuuuu</controlfield><controlfield tag="008">210831s2021 xx \|\|\|\|\|o 00\| \|\|eng c</controlfield><datafield tag="024" ind1="7" ind2=" "><subfield code="a">10.1007/s42417-020-00267-6</subfield><subfield code="2">doi</subfield></datafield><datafield tag="035" ind1=" " ind2=" "><subfield code="a">(DE-627)SPR044957777</subfield></datafield><datafield tag="035" ind1=" " ind2=" "><subfield code="a">(SPR)s42417-020-00267-6-e</subfield></datafield><datafield tag="040" ind1=" " ind2=" "><subfield code="a">DE-627</subfield><subfield code="b">ger</subfield><subfield code="c">DE-627</subfield><subfield code="e">rakwb</subfield></datafield><datafield tag="041" ind1=" " ind2=" "><subfield code="a">eng</subfield></datafield><datafield tag="082" ind1="0" ind2="4"><subfield code="a">620</subfield><subfield code="q">ASE</subfield></datafield><datafield tag="082" ind1="0" ind2="4"><subfield code="a">620</subfield><subfield code="q">ASE</subfield></datafield><datafield tag="100" ind1="1" ind2=" "><subfield code="a">Kassem, Mohammed</subfield><subfield code="e">verfasserin</subfield><subfield code="4">aut</subfield></datafield><datafield tag="245" ind1="1" ind2="0"><subfield code="a">Modeling and Control Design for Flutter Suppression Using Active Dynamic Vibration Absorber</subfield></datafield><datafield tag="264" ind1=" " ind2="1"><subfield code="c">2021</subfield></datafield><datafield tag="336" ind1=" " ind2=" "><subfield code="a">Text</subfield><subfield code="b">txt</subfield><subfield code="2">rdacontent</subfield></datafield><datafield tag="337" ind1=" " ind2=" "><subfield code="a">Computermedien</subfield><subfield code="b">c</subfield><subfield code="2">rdamedia</subfield></datafield><datafield tag="338" ind1=" " ind2=" "><subfield code="a">Online-Ressource</subfield><subfield code="b">cr</subfield><subfield code="2">rdacarrier</subfield></datafield><datafield tag="500" ind1=" " ind2=" "><subfield code="a">© Krishtel eMaging Solutions Private Limited 2021</subfield></datafield><datafield tag="520" ind1=" " ind2=" "><subfield code="a">Background Enhancing the efficiency of modern aeronautic structures necessitates flexibility increasing associated with weight reduction. A consequent possibility of unfavorable unsteady aeroelastic phenomena such as flutter arises due to the interaction between the elastic, aerodynamic, and inertia loads. Researchers work hard to suppress it using numerous passive and active techniques. Purpose This paper presents the mathematical model and the optimal control of an active technique for flutter mitigation of an airfoil system undergoing incompressible flow. Methods The proposed active dynamic vibration absorber (ADVA) comprises an active element together with a classical mass–spring–damper system. In the active mode, a controlling force is generated by the active element to actuate the mass using feedback from the vibration responses of the aeroelastic airfoil system. A non-dimensional mathematical model for a typical two-degree-of-freedom aeroelastic airfoil integrated with the ADVA is introduced based on unsteady aerodynamic theory. The effect of the ADVA parameters on the aeroelastic system stability is investigated in different flight conditions. Additionally, two feedback controllers are presented to analyze the closed-loop system. The control gains are optimized based on a genetic algorithm to improve the performance of the proposed ADVA. Results Introducing the passive dynamic absorber increases the flutter speed by about 15%, while activating the ADVA at the new flutter speed stabilizes the system and further expands the airfoil flutter boundaries. Conclusion The proposed ADVA ensures flutter suppression and extends the flutter boundary. Furthermore, the introduced flutter control technique is robust against the variation of the system parameters and the detuning of the ADVA parameters.</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Flutter suppression</subfield><subfield code="7">(dpeaa)DE-He213</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Active control</subfield><subfield code="7">(dpeaa)DE-He213</subfield></datafield><datafield tag="650" ind1=" " ind2="4"><subfield code="a">Dynamic vibration absorber</subfield><subfield code="7">(dpeaa)DE-He213</subfield></datafield><datafield tag="700" ind1="1" ind2=" "><subfield code="a">Yang, Zhichun</subfield><subfield code="e">verfasserin</subfield><subfield code="4">aut</subfield></datafield><datafield tag="700" ind1="1" ind2=" "><subfield code="a">Gu, Yingsong</subfield><subfield code="e">verfasserin</subfield><subfield code="4">aut</subfield></datafield><datafield tag="700" ind1="1" ind2=" "><subfield code="a">Wang, Wei</subfield><subfield code="e">verfasserin</subfield><subfield code="4">aut</subfield></datafield><datafield tag="773" ind1="0" ind2="8"><subfield code="i">Enthalten in</subfield><subfield code="t">Journal of vibration engineering & technologies</subfield><subfield code="d">Singapore : Springer Singapore, 2018</subfield><subfield code="g">9(2021), 5 vom: 03. Jan., Seite 845-860</subfield><subfield code="w">(DE-627)1030123837</subfield><subfield code="w">(DE-600)2941414-3</subfield><subfield code="x">2523-3939</subfield><subfield code="7">nnns</subfield></datafield><datafield tag="773" ind1="1" ind2="8"><subfield code="g">volume:9</subfield><subfield code="g">year:2021</subfield><subfield code="g">number:5</subfield><subfield code="g">day:03</subfield><subfield code="g">month:01</subfield><subfield code="g">pages:845-860</subfield></datafield><datafield tag="856" ind1="4" ind2="0"><subfield code="u">https://dx.doi.org/10.1007/s42417-020-00267-6</subfield><subfield code="z">lizenzpflichtig</subfield><subfield code="3">Volltext</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_USEFLAG_A</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">SYSFLAG_A</subfield></datafield><datafield tag="912" ind1=" " ind2=" "><subfield code="a">GBV_SPRINGER</subfield></datafield><datafield tag="912" 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