Analysis of Force Distribution of Four Rows of Bolts in Aircraft Fitting Joint
With the help of 3D modeling software and finite element analysis software, the force distribution of four rows of bolts in the aircraft fitting joint is obtained in this paper. In 3D modeling software, the solid model is segmented according to the area and height of the center of gravity of the cro...
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| Main Authors: | , , |
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| Format: | Article |
| Language: | English |
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Wiley
2021-01-01
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| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2021/9962645 |
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| _version_ | 1832560525269008384 |
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| author | Yifang Sun O. G. Grebenikov Chenghu Li |
| author_facet | Yifang Sun O. G. Grebenikov Chenghu Li |
| author_sort | Yifang Sun |
| collection | DOAJ |
| description | With the help of 3D modeling software and finite element analysis software, the force distribution of four rows of bolts in the aircraft fitting joint is obtained in this paper. In 3D modeling software, the solid model is segmented according to the area and height of the center of gravity of the cross-section. In finite element analysis software, the beam elements are used to replace the segmented model to obtain the internal force applied at the end of the segmented model and the stress-strain state of each segment is calculated according to the internal force applied at the end of each segment. Finally, the force distribution of the four rows of bolts is obtained according to the average force difference on the center section between the bolt rows. In order to ensure the validity of this step-by-step calculation result, it was compared with the entire calculation result. It can be concluded that the force distribution of the two calculations is consistent. Under the working conditions of the fitting joint (130 MPa), the force distribution coefficients of the four rows of bolts are 0.182, 0.215, 0.197, and 0.12. Therefore, it is feasible to use the step-by-step method to calculate the force distribution of the four rows of bolts in the fitting joint. Compared with the entire calculation, the step-by-step calculation has the advantages of less calculation amount and faster calculation speed. |
| format | Article |
| id | doaj-art-6bff25f137f843a7a78f51480b7cc582 |
| institution | Kabale University |
| issn | 1687-5966 1687-5974 |
| language | English |
| publishDate | 2021-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Aerospace Engineering |
| spelling | doaj-art-6bff25f137f843a7a78f51480b7cc5822025-02-03T01:27:20ZengWileyInternational Journal of Aerospace Engineering1687-59661687-59742021-01-01202110.1155/2021/99626459962645Analysis of Force Distribution of Four Rows of Bolts in Aircraft Fitting JointYifang Sun0O. G. Grebenikov1Chenghu Li2National Aerospace University “Kharkiv Aviation Institute”, 61070 Kharkiv, UkraineNational Aerospace University “Kharkiv Aviation Institute”, 61070 Kharkiv, UkraineSchool of Aerospace Engineering, Huazhong University of Science and Technology, 430074 Wuhan, ChinaWith the help of 3D modeling software and finite element analysis software, the force distribution of four rows of bolts in the aircraft fitting joint is obtained in this paper. In 3D modeling software, the solid model is segmented according to the area and height of the center of gravity of the cross-section. In finite element analysis software, the beam elements are used to replace the segmented model to obtain the internal force applied at the end of the segmented model and the stress-strain state of each segment is calculated according to the internal force applied at the end of each segment. Finally, the force distribution of the four rows of bolts is obtained according to the average force difference on the center section between the bolt rows. In order to ensure the validity of this step-by-step calculation result, it was compared with the entire calculation result. It can be concluded that the force distribution of the two calculations is consistent. Under the working conditions of the fitting joint (130 MPa), the force distribution coefficients of the four rows of bolts are 0.182, 0.215, 0.197, and 0.12. Therefore, it is feasible to use the step-by-step method to calculate the force distribution of the four rows of bolts in the fitting joint. Compared with the entire calculation, the step-by-step calculation has the advantages of less calculation amount and faster calculation speed.http://dx.doi.org/10.1155/2021/9962645 |
| spellingShingle | Yifang Sun O. G. Grebenikov Chenghu Li Analysis of Force Distribution of Four Rows of Bolts in Aircraft Fitting Joint International Journal of Aerospace Engineering |
| title | Analysis of Force Distribution of Four Rows of Bolts in Aircraft Fitting Joint |
| title_full | Analysis of Force Distribution of Four Rows of Bolts in Aircraft Fitting Joint |
| title_fullStr | Analysis of Force Distribution of Four Rows of Bolts in Aircraft Fitting Joint |
| title_full_unstemmed | Analysis of Force Distribution of Four Rows of Bolts in Aircraft Fitting Joint |
| title_short | Analysis of Force Distribution of Four Rows of Bolts in Aircraft Fitting Joint |
| title_sort | analysis of force distribution of four rows of bolts in aircraft fitting joint |
| url | http://dx.doi.org/10.1155/2021/9962645 |
| work_keys_str_mv | AT yifangsun analysisofforcedistributionoffourrowsofboltsinaircraftfittingjoint AT oggrebenikov analysisofforcedistributionoffourrowsofboltsinaircraftfittingjoint AT chenghuli analysisofforcedistributionoffourrowsofboltsinaircraftfittingjoint |