Numerical Derivation of Buckling Knockdown Factors for Isogrid-Stiffened Cylinders with Various Shell Thickness Ratios
This study is aimed at providing a numerical derivation of the shell knockdown factors of isogrid-stiffened cylinders under axial compressive loads. The present work uses two different analysis models such as the detailed model with modeling of numerous stiffeners and the equivalent model without mo...
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| Main Authors: | , , , , , |
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| Format: | Article |
| Language: | English |
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Wiley
2020-01-01
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| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2020/9851984 |
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| author | Han-Il Kim Chang-Hoon Sim Jae-Sang Park Keejoo Lee Joon-Tae Yoo Young-Ha Yoon |
| author_facet | Han-Il Kim Chang-Hoon Sim Jae-Sang Park Keejoo Lee Joon-Tae Yoo Young-Ha Yoon |
| author_sort | Han-Il Kim |
| collection | DOAJ |
| description | This study is aimed at providing a numerical derivation of the shell knockdown factors of isogrid-stiffened cylinders under axial compressive loads. The present work uses two different analysis models such as the detailed model with modeling of numerous stiffeners and the equivalent model without modeling of stiffeners for isogrid-stiffened cylinders. The single perturbation load approach is used to represent the geometrically initial imperfection of the cylinder. Postbuckling analyses using the displacement control method are conducted to calculate the global buckling loads of a cylinder. The shell knockdown factor is numerically derived using the obtained global buckling loads without and with the initial imperfection of the isogrid-stiffened cylinder. The equivalent model is more efficient than the detailed model in terms of modeling time and computation time. The present knockdown factor function in terms of the shell thickness ratio (radius to thickness) for the isogrid-stiffened cylinder is significantly higher than NASA’s knockdown factor function; therefore, it is believed that the present knockdown factor function can facilitate in developing lightweight launch vehicle structures using isogrid-stiffened cylinders. |
| format | Article |
| id | doaj-art-c7ec2cac04a44bbda453d46a5b0f3006 |
| institution | Kabale University |
| issn | 1687-5966 1687-5974 |
| language | English |
| publishDate | 2020-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Aerospace Engineering |
| spelling | doaj-art-c7ec2cac04a44bbda453d46a5b0f30062025-08-20T03:24:11ZengWileyInternational Journal of Aerospace Engineering1687-59661687-59742020-01-01202010.1155/2020/98519849851984Numerical Derivation of Buckling Knockdown Factors for Isogrid-Stiffened Cylinders with Various Shell Thickness RatiosHan-Il Kim0Chang-Hoon Sim1Jae-Sang Park2Keejoo Lee3Joon-Tae Yoo4Young-Ha Yoon5Department of Aerospace Engineering, Chungnam National University, Daejeon 34134, Republic of KoreaDepartment of Aerospace Engineering, Chungnam National University, Daejeon 34134, Republic of KoreaDepartment of Aerospace Engineering, Chungnam National University, Daejeon 34134, Republic of KoreaSmall Launcher Team, Future Launcher R&D Program Office, Korea Aerospace Research Institute, Daejeon 34133, Republic of KoreaLauncher Structures and Materials Team, Korea Aerospace Research Institute, Daejeon 34133, Republic of KoreaLauncher Structures and Materials Team, Korea Aerospace Research Institute, Daejeon 34133, Republic of KoreaThis study is aimed at providing a numerical derivation of the shell knockdown factors of isogrid-stiffened cylinders under axial compressive loads. The present work uses two different analysis models such as the detailed model with modeling of numerous stiffeners and the equivalent model without modeling of stiffeners for isogrid-stiffened cylinders. The single perturbation load approach is used to represent the geometrically initial imperfection of the cylinder. Postbuckling analyses using the displacement control method are conducted to calculate the global buckling loads of a cylinder. The shell knockdown factor is numerically derived using the obtained global buckling loads without and with the initial imperfection of the isogrid-stiffened cylinder. The equivalent model is more efficient than the detailed model in terms of modeling time and computation time. The present knockdown factor function in terms of the shell thickness ratio (radius to thickness) for the isogrid-stiffened cylinder is significantly higher than NASA’s knockdown factor function; therefore, it is believed that the present knockdown factor function can facilitate in developing lightweight launch vehicle structures using isogrid-stiffened cylinders.http://dx.doi.org/10.1155/2020/9851984 |
| spellingShingle | Han-Il Kim Chang-Hoon Sim Jae-Sang Park Keejoo Lee Joon-Tae Yoo Young-Ha Yoon Numerical Derivation of Buckling Knockdown Factors for Isogrid-Stiffened Cylinders with Various Shell Thickness Ratios International Journal of Aerospace Engineering |
| title | Numerical Derivation of Buckling Knockdown Factors for Isogrid-Stiffened Cylinders with Various Shell Thickness Ratios |
| title_full | Numerical Derivation of Buckling Knockdown Factors for Isogrid-Stiffened Cylinders with Various Shell Thickness Ratios |
| title_fullStr | Numerical Derivation of Buckling Knockdown Factors for Isogrid-Stiffened Cylinders with Various Shell Thickness Ratios |
| title_full_unstemmed | Numerical Derivation of Buckling Knockdown Factors for Isogrid-Stiffened Cylinders with Various Shell Thickness Ratios |
| title_short | Numerical Derivation of Buckling Knockdown Factors for Isogrid-Stiffened Cylinders with Various Shell Thickness Ratios |
| title_sort | numerical derivation of buckling knockdown factors for isogrid stiffened cylinders with various shell thickness ratios |
| url | http://dx.doi.org/10.1155/2020/9851984 |
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