Parametric Optimization of Load Bearing Elements for Composite Wing of an Unmanned Aerial Vehicle
This paper describes the optimizing results of structural elements of the composite wing of an unmanned aerial vehicle. The thickness and composite lay-up structure of load-bearing elements and wing skin are determined using the ANSYS software package. The optimal structure is presented using the Pa...
Ausführliche Beschreibung
Autor*in: |
Aung Naing Lin [verfasserIn] Tatarnikov Oleg [verfasserIn] Aung Phyo Wai [verfasserIn] |
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Format: |
E-Artikel |
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Sprache: |
Englisch ; Französisch |
Erschienen: |
2021 |
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Übergeordnetes Werk: |
In: MATEC Web of Conferences - EDP Sciences, 2013, 346, p 03093(2021) |
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Übergeordnetes Werk: |
volume:346, p 03093 ; year:2021 |
Links: |
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DOI / URN: |
10.1051/matecconf/202134603093 |
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Katalog-ID: |
DOAJ051136430 |
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10.1051/matecconf/202134603093 doi (DE-627)DOAJ051136430 (DE-599)DOAJ7fc0927c1b0a402fa41f9c232d582c59 DE-627 ger DE-627 rakwb eng fre TA1-2040 Aung Naing Lin verfasserin aut Parametric Optimization of Load Bearing Elements for Composite Wing of an Unmanned Aerial Vehicle 2021 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier This paper describes the optimizing results of structural elements of the composite wing of an unmanned aerial vehicle. The thickness and composite lay-up structure of load-bearing elements and wing skin are determined using the ANSYS software package. The optimal structure is presented using the Pareto set method of the “ideal center” basing on four criteria: minimum mass, deflection, normal stress, and maximum safety factor of the wing. Verification calculations were carried out to determine the safety factor of the load-bearing wing structure using a geometrically nonlinear model in FEMAP software. Engineering (General). Civil engineering (General) Tatarnikov Oleg verfasserin aut Aung Phyo Wai verfasserin aut In MATEC Web of Conferences EDP Sciences, 2013 346, p 03093(2021) (DE-627)720166209 (DE-600)2673602-0 2261236X nnns volume:346, p 03093 year:2021 https://doi.org/10.1051/matecconf/202134603093 kostenfrei https://doaj.org/article/7fc0927c1b0a402fa41f9c232d582c59 kostenfrei https://www.matec-conferences.org/articles/matecconf/pdf/2021/15/matecconf_icmtmte2021_03093.pdf kostenfrei https://doaj.org/toc/2261-236X Journal toc kostenfrei GBV_USEFLAG_A SYSFLAG_A GBV_DOAJ SSG-OLC-PHA GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 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_95 GBV_ILN_105 GBV_ILN_110 GBV_ILN_151 GBV_ILN_161 GBV_ILN_170 GBV_ILN_213 GBV_ILN_230 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_2014 GBV_ILN_2055 GBV_ILN_4012 GBV_ILN_4037 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4249 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_4335 GBV_ILN_4338 GBV_ILN_4367 GBV_ILN_4700 AR 346, p 03093 2021 |
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10.1051/matecconf/202134603093 doi (DE-627)DOAJ051136430 (DE-599)DOAJ7fc0927c1b0a402fa41f9c232d582c59 DE-627 ger DE-627 rakwb eng fre TA1-2040 Aung Naing Lin verfasserin aut Parametric Optimization of Load Bearing Elements for Composite Wing of an Unmanned Aerial Vehicle 2021 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier This paper describes the optimizing results of structural elements of the composite wing of an unmanned aerial vehicle. The thickness and composite lay-up structure of load-bearing elements and wing skin are determined using the ANSYS software package. The optimal structure is presented using the Pareto set method of the “ideal center” basing on four criteria: minimum mass, deflection, normal stress, and maximum safety factor of the wing. Verification calculations were carried out to determine the safety factor of the load-bearing wing structure using a geometrically nonlinear model in FEMAP software. Engineering (General). Civil engineering (General) Tatarnikov Oleg verfasserin aut Aung Phyo Wai verfasserin aut In MATEC Web of Conferences EDP Sciences, 2013 346, p 03093(2021) (DE-627)720166209 (DE-600)2673602-0 2261236X nnns volume:346, p 03093 year:2021 https://doi.org/10.1051/matecconf/202134603093 kostenfrei https://doaj.org/article/7fc0927c1b0a402fa41f9c232d582c59 kostenfrei https://www.matec-conferences.org/articles/matecconf/pdf/2021/15/matecconf_icmtmte2021_03093.pdf kostenfrei https://doaj.org/toc/2261-236X Journal toc kostenfrei GBV_USEFLAG_A SYSFLAG_A GBV_DOAJ SSG-OLC-PHA GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 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_95 GBV_ILN_105 GBV_ILN_110 GBV_ILN_151 GBV_ILN_161 GBV_ILN_170 GBV_ILN_213 GBV_ILN_230 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_2014 GBV_ILN_2055 GBV_ILN_4012 GBV_ILN_4037 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4249 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_4335 GBV_ILN_4338 GBV_ILN_4367 GBV_ILN_4700 AR 346, p 03093 2021 |
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10.1051/matecconf/202134603093 doi (DE-627)DOAJ051136430 (DE-599)DOAJ7fc0927c1b0a402fa41f9c232d582c59 DE-627 ger DE-627 rakwb eng fre TA1-2040 Aung Naing Lin verfasserin aut Parametric Optimization of Load Bearing Elements for Composite Wing of an Unmanned Aerial Vehicle 2021 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier This paper describes the optimizing results of structural elements of the composite wing of an unmanned aerial vehicle. The thickness and composite lay-up structure of load-bearing elements and wing skin are determined using the ANSYS software package. The optimal structure is presented using the Pareto set method of the “ideal center” basing on four criteria: minimum mass, deflection, normal stress, and maximum safety factor of the wing. Verification calculations were carried out to determine the safety factor of the load-bearing wing structure using a geometrically nonlinear model in FEMAP software. Engineering (General). Civil engineering (General) Tatarnikov Oleg verfasserin aut Aung Phyo Wai verfasserin aut In MATEC Web of Conferences EDP Sciences, 2013 346, p 03093(2021) (DE-627)720166209 (DE-600)2673602-0 2261236X nnns volume:346, p 03093 year:2021 https://doi.org/10.1051/matecconf/202134603093 kostenfrei https://doaj.org/article/7fc0927c1b0a402fa41f9c232d582c59 kostenfrei https://www.matec-conferences.org/articles/matecconf/pdf/2021/15/matecconf_icmtmte2021_03093.pdf kostenfrei https://doaj.org/toc/2261-236X Journal toc kostenfrei GBV_USEFLAG_A SYSFLAG_A GBV_DOAJ SSG-OLC-PHA GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 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_95 GBV_ILN_105 GBV_ILN_110 GBV_ILN_151 GBV_ILN_161 GBV_ILN_170 GBV_ILN_213 GBV_ILN_230 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_2014 GBV_ILN_2055 GBV_ILN_4012 GBV_ILN_4037 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4249 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_4335 GBV_ILN_4338 GBV_ILN_4367 GBV_ILN_4700 AR 346, p 03093 2021 |
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10.1051/matecconf/202134603093 doi (DE-627)DOAJ051136430 (DE-599)DOAJ7fc0927c1b0a402fa41f9c232d582c59 DE-627 ger DE-627 rakwb eng fre TA1-2040 Aung Naing Lin verfasserin aut Parametric Optimization of Load Bearing Elements for Composite Wing of an Unmanned Aerial Vehicle 2021 Text txt rdacontent Computermedien c rdamedia Online-Ressource cr rdacarrier This paper describes the optimizing results of structural elements of the composite wing of an unmanned aerial vehicle. The thickness and composite lay-up structure of load-bearing elements and wing skin are determined using the ANSYS software package. The optimal structure is presented using the Pareto set method of the “ideal center” basing on four criteria: minimum mass, deflection, normal stress, and maximum safety factor of the wing. Verification calculations were carried out to determine the safety factor of the load-bearing wing structure using a geometrically nonlinear model in FEMAP software. Engineering (General). Civil engineering (General) Tatarnikov Oleg verfasserin aut Aung Phyo Wai verfasserin aut In MATEC Web of Conferences EDP Sciences, 2013 346, p 03093(2021) (DE-627)720166209 (DE-600)2673602-0 2261236X nnns volume:346, p 03093 year:2021 https://doi.org/10.1051/matecconf/202134603093 kostenfrei https://doaj.org/article/7fc0927c1b0a402fa41f9c232d582c59 kostenfrei https://www.matec-conferences.org/articles/matecconf/pdf/2021/15/matecconf_icmtmte2021_03093.pdf kostenfrei https://doaj.org/toc/2261-236X Journal toc kostenfrei GBV_USEFLAG_A SYSFLAG_A GBV_DOAJ SSG-OLC-PHA GBV_ILN_20 GBV_ILN_22 GBV_ILN_23 GBV_ILN_24 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_95 GBV_ILN_105 GBV_ILN_110 GBV_ILN_151 GBV_ILN_161 GBV_ILN_170 GBV_ILN_213 GBV_ILN_230 GBV_ILN_285 GBV_ILN_293 GBV_ILN_370 GBV_ILN_602 GBV_ILN_2014 GBV_ILN_2055 GBV_ILN_4012 GBV_ILN_4037 GBV_ILN_4112 GBV_ILN_4125 GBV_ILN_4126 GBV_ILN_4249 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_4335 GBV_ILN_4338 GBV_ILN_4367 GBV_ILN_4700 AR 346, p 03093 2021 |
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Parametric Optimization of Load Bearing Elements for Composite Wing of an Unmanned Aerial Vehicle |
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This paper describes the optimizing results of structural elements of the composite wing of an unmanned aerial vehicle. The thickness and composite lay-up structure of load-bearing elements and wing skin are determined using the ANSYS software package. The optimal structure is presented using the Pareto set method of the “ideal center” basing on four criteria: minimum mass, deflection, normal stress, and maximum safety factor of the wing. Verification calculations were carried out to determine the safety factor of the load-bearing wing structure using a geometrically nonlinear model in FEMAP software. |
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This paper describes the optimizing results of structural elements of the composite wing of an unmanned aerial vehicle. The thickness and composite lay-up structure of load-bearing elements and wing skin are determined using the ANSYS software package. The optimal structure is presented using the Pareto set method of the “ideal center” basing on four criteria: minimum mass, deflection, normal stress, and maximum safety factor of the wing. Verification calculations were carried out to determine the safety factor of the load-bearing wing structure using a geometrically nonlinear model in FEMAP software. |
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This paper describes the optimizing results of structural elements of the composite wing of an unmanned aerial vehicle. The thickness and composite lay-up structure of load-bearing elements and wing skin are determined using the ANSYS software package. The optimal structure is presented using the Pareto set method of the “ideal center” basing on four criteria: minimum mass, deflection, normal stress, and maximum safety factor of the wing. Verification calculations were carried out to determine the safety factor of the load-bearing wing structure using a geometrically nonlinear model in FEMAP software. |
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Parametric Optimization of Load Bearing Elements for Composite Wing of an Unmanned Aerial Vehicle |
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