Calculation of the Hinge Moments of a Folding Wing Aircraft during the Flight-Folding Process
A folding wing morphing aircraft should complete the folding and unfolding process of its wings while in flight. Calculating the hinge moments during the morphing process is a critical aspect of a folding wing design. Most previous studies on this problem have adopted steady-state or quasi-steady-st...
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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/10.1155/2019/9362629 |
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| author | Hao Xu Jinglong Han Haiwei Yun Xiaomao Chen |
| author_facet | Hao Xu Jinglong Han Haiwei Yun Xiaomao Chen |
| author_sort | Hao Xu |
| collection | DOAJ |
| description | A folding wing morphing aircraft should complete the folding and unfolding process of its wings while in flight. Calculating the hinge moments during the morphing process is a critical aspect of a folding wing design. Most previous studies on this problem have adopted steady-state or quasi-steady-state methods, which do not simulate the free-flying morphing process. In this study, we construct an aeroelastic flight simulation platform based on the secondary development of ADAMS software to simulate the flight-folding process of a folding wing aircraft. A flexible multibody dynamic model of the folding wing structure is established in ADAMS using modal neutral files, and the doublet lattice method is developed to generate aerodynamic influence coefficient matrices that are suitable for the flight-folding process. The user subroutine is utilized, aerodynamic loading is realized in ADAMS, and an aeroelastic flight simulation platform of a folding wing aircraft is built. On the basis of this platform, the flight-folding process of the aircraft is simulated, the hinge moments of the folding wings are calculated, and the influences of the folding rate and the aircraft’s center of gravity (c.g.) position on the results are investigated. Results show that the steady-state method is applicable to the slow folding process. For the fast folding process, the steady-state simulation errors of the hinge moments are substantially large, and a transient method is required to simulate the flight-folding process. In addition, the c.g. position considerably affects the hinge moments during the folding process. Given that the c.g. position moves aft, the maximum hinge moments of the inner and outer wings constantly increase. |
| format | Article |
| id | doaj-art-81079f8e33a14eeabba5d6ccd5d513eb |
| 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-81079f8e33a14eeabba5d6ccd5d513eb2025-02-03T00:59:47ZengWileyInternational Journal of Aerospace Engineering1687-59661687-59742019-01-01201910.1155/2019/93626299362629Calculation of the Hinge Moments of a Folding Wing Aircraft during the Flight-Folding ProcessHao Xu0Jinglong Han1Haiwei Yun2Xiaomao Chen3State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, ChinaState Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, ChinaState Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, ChinaState Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, ChinaA folding wing morphing aircraft should complete the folding and unfolding process of its wings while in flight. Calculating the hinge moments during the morphing process is a critical aspect of a folding wing design. Most previous studies on this problem have adopted steady-state or quasi-steady-state methods, which do not simulate the free-flying morphing process. In this study, we construct an aeroelastic flight simulation platform based on the secondary development of ADAMS software to simulate the flight-folding process of a folding wing aircraft. A flexible multibody dynamic model of the folding wing structure is established in ADAMS using modal neutral files, and the doublet lattice method is developed to generate aerodynamic influence coefficient matrices that are suitable for the flight-folding process. The user subroutine is utilized, aerodynamic loading is realized in ADAMS, and an aeroelastic flight simulation platform of a folding wing aircraft is built. On the basis of this platform, the flight-folding process of the aircraft is simulated, the hinge moments of the folding wings are calculated, and the influences of the folding rate and the aircraft’s center of gravity (c.g.) position on the results are investigated. Results show that the steady-state method is applicable to the slow folding process. For the fast folding process, the steady-state simulation errors of the hinge moments are substantially large, and a transient method is required to simulate the flight-folding process. In addition, the c.g. position considerably affects the hinge moments during the folding process. Given that the c.g. position moves aft, the maximum hinge moments of the inner and outer wings constantly increase.http://dx.doi.org/10.1155/2019/9362629 |
| spellingShingle | Hao Xu Jinglong Han Haiwei Yun Xiaomao Chen Calculation of the Hinge Moments of a Folding Wing Aircraft during the Flight-Folding Process International Journal of Aerospace Engineering |
| title | Calculation of the Hinge Moments of a Folding Wing Aircraft during the Flight-Folding Process |
| title_full | Calculation of the Hinge Moments of a Folding Wing Aircraft during the Flight-Folding Process |
| title_fullStr | Calculation of the Hinge Moments of a Folding Wing Aircraft during the Flight-Folding Process |
| title_full_unstemmed | Calculation of the Hinge Moments of a Folding Wing Aircraft during the Flight-Folding Process |
| title_short | Calculation of the Hinge Moments of a Folding Wing Aircraft during the Flight-Folding Process |
| title_sort | calculation of the hinge moments of a folding wing aircraft during the flight folding process |
| url | http://dx.doi.org/10.1155/2019/9362629 |
| work_keys_str_mv | AT haoxu calculationofthehingemomentsofafoldingwingaircraftduringtheflightfoldingprocess AT jinglonghan calculationofthehingemomentsofafoldingwingaircraftduringtheflightfoldingprocess AT haiweiyun calculationofthehingemomentsofafoldingwingaircraftduringtheflightfoldingprocess AT xiaomaochen calculationofthehingemomentsofafoldingwingaircraftduringtheflightfoldingprocess |