Optimization of flapping-wing micro aircrafts based on the kinematic parameters using genetic algorithm method
In this paper the optimization of kinematics, which has great influence in performance of flapping foil propulsion, is investigated. The purpose of optimization is to design a flapping-wing micro aircraft with appropriate kinematics and aerodynamics features, making the micro aircraft suitable for t...
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| Format: | Article |
| Language: | English |
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National Institute for Aerospace Research “Elie Carafoli” - INCAS
2013-03-01
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| Series: | INCAS Bulletin |
| Subjects: | |
| Online Access: | http://bulletin.incas.ro/files/abolfazli_esfahani_m__karbasian_h_r__abolfazli_esf.pdf |
| _version_ | 1819096709627641856 |
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| author | Ebrahim BARATI Hamid Reza KARBASIAN Javad ABOLFAZLI ESFAHANI Mahdi ABOLFAZLI ESFAHANI |
| author_facet | Ebrahim BARATI Hamid Reza KARBASIAN Javad ABOLFAZLI ESFAHANI Mahdi ABOLFAZLI ESFAHANI |
| author_sort | Ebrahim BARATI |
| collection | DOAJ |
| description | In this paper the optimization of kinematics, which has great influence in performance of flapping foil propulsion, is investigated. The purpose of optimization is to design a flapping-wing micro aircraft with appropriate kinematics and aerodynamics features, making the micro aircraft suitable for transportation over large distance with minimum energy consumption. On the point of optimal design, the pitch amplitude, wing reduced frequency and phase difference between plunging and pitching are considered as given parameters and consumed energy, generated thrust by wings and lost power are computed using the 2D quasi-steady aerodynamic model and multi-objective genetic algorithm. Based on the thrust optimization, the increase in pitch amplitude reduces the power consumption. In this case the lost power increases and the maximum thrust coefficient is computed of 2.43. Based on the power optimization, the results show that the increase in pitch amplitude leads to power consumption increase. Additionally, the minimum lost power obtained in this case is 23% at pitch amplitude of 25°, wing reduced frequency of 0.42 and phase angle difference between plunging and pitching of 77°. Furthermore, the wing reduced frequency can be estimated using regression with respect to pitch amplitude, because reduced frequency variations with pitch amplitude is approximately a linear function. |
| first_indexed | 2024-12-22T00:03:31Z |
| format | Article |
| id | doaj.art-5804dfdae42340d4b661b65c2ee68432 |
| institution | Directory Open Access Journal |
| issn | 2066-8201 2247-4528 |
| language | English |
| last_indexed | 2024-12-22T00:03:31Z |
| publishDate | 2013-03-01 |
| publisher | National Institute for Aerospace Research “Elie Carafoli” - INCAS |
| record_format | Article |
| series | INCAS Bulletin |
| spelling | doaj.art-5804dfdae42340d4b661b65c2ee684322022-12-21T18:45:38ZengNational Institute for Aerospace Research “Elie Carafoli” - INCASINCAS Bulletin2066-82012247-45282013-03-015131210.13111/2066-8201.2013.5.1.1Optimization of flapping-wing micro aircrafts based on the kinematic parameters using genetic algorithm methodEbrahim BARATIHamid Reza KARBASIANJavad ABOLFAZLI ESFAHANIMahdi ABOLFAZLI ESFAHANIIn this paper the optimization of kinematics, which has great influence in performance of flapping foil propulsion, is investigated. The purpose of optimization is to design a flapping-wing micro aircraft with appropriate kinematics and aerodynamics features, making the micro aircraft suitable for transportation over large distance with minimum energy consumption. On the point of optimal design, the pitch amplitude, wing reduced frequency and phase difference between plunging and pitching are considered as given parameters and consumed energy, generated thrust by wings and lost power are computed using the 2D quasi-steady aerodynamic model and multi-objective genetic algorithm. Based on the thrust optimization, the increase in pitch amplitude reduces the power consumption. In this case the lost power increases and the maximum thrust coefficient is computed of 2.43. Based on the power optimization, the results show that the increase in pitch amplitude leads to power consumption increase. Additionally, the minimum lost power obtained in this case is 23% at pitch amplitude of 25°, wing reduced frequency of 0.42 and phase angle difference between plunging and pitching of 77°. Furthermore, the wing reduced frequency can be estimated using regression with respect to pitch amplitude, because reduced frequency variations with pitch amplitude is approximately a linear function.http://bulletin.incas.ro/files/abolfazli_esfahani_m__karbasian_h_r__abolfazli_esf.pdfFlapping-wing micro aircraftAerodynamicsFlapping foil propulsionoptimizationgenetic algorithm |
| spellingShingle | Ebrahim BARATI Hamid Reza KARBASIAN Javad ABOLFAZLI ESFAHANI Mahdi ABOLFAZLI ESFAHANI Optimization of flapping-wing micro aircrafts based on the kinematic parameters using genetic algorithm method INCAS Bulletin Flapping-wing micro aircraft Aerodynamics Flapping foil propulsion optimization genetic algorithm |
| title | Optimization of flapping-wing micro aircrafts based on the kinematic parameters using genetic algorithm method |
| title_full | Optimization of flapping-wing micro aircrafts based on the kinematic parameters using genetic algorithm method |
| title_fullStr | Optimization of flapping-wing micro aircrafts based on the kinematic parameters using genetic algorithm method |
| title_full_unstemmed | Optimization of flapping-wing micro aircrafts based on the kinematic parameters using genetic algorithm method |
| title_short | Optimization of flapping-wing micro aircrafts based on the kinematic parameters using genetic algorithm method |
| title_sort | optimization of flapping wing micro aircrafts based on the kinematic parameters using genetic algorithm method |
| topic | Flapping-wing micro aircraft Aerodynamics Flapping foil propulsion optimization genetic algorithm |
| url | http://bulletin.incas.ro/files/abolfazli_esfahani_m__karbasian_h_r__abolfazli_esf.pdf |
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