Initial and progressive failure analysis of a composite wing spar structure / Bruce Ralphin Rose.J and Priyadharshini.S
In the present work, a main spar section of a composite wing structure is analyzed for its structural safety in the course of preliminary aircraft design phase. Spar is a spanwise structural member that is used to carry the bending loads and it deals with the self weight of the wing while the airpla...
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| Language: | English |
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Faculty of Mechanical Engineering & UiTM Press
2017
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| Online Access: | http://ir.uitm.edu.my/id/eprint/21116/ http://ir.uitm.edu.my/id/eprint/21116/1/AJ_Bruce%20Ralphin%20Rose.J%20JME%2017.pdf |
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uitm-21116 |
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eprints |
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uitm-211162018-10-24T02:42:35Z http://ir.uitm.edu.my/id/eprint/21116/ Initial and progressive failure analysis of a composite wing spar structure / Bruce Ralphin Rose.J and Priyadharshini.S Bruce, Ralphin Rose.J S, Priyadharshini Composite materials Mechanics of engineering. Applied mechanics In the present work, a main spar section of a composite wing structure is analyzed for its structural safety in the course of preliminary aircraft design phase. Spar is a spanwise structural member that is used to carry the bending loads and it deals with the self weight of the wing while the airplane is on the ground as well as it carries the lifting loads during flight. Because of the rolling inertia loads and chord wise bending loads caused by aerodynamic effects, spar structure is vulnerable to different structural failures before the end of safe life cycle. Initial and progressive failure analysis of the spar section is done by using the typical properties of composite materials. Carbon epoxy, Graphite epoxy and Boron epoxy materials are analyzed with their standard material properties to determine the crack initiation and propagation characteristics at different time steps with stress increments. A two-dimensional spar cross section (I - section) is designed with shell as element type and the analysis is done in ABAQUS/CAE by using XFEM for crack initiation. The results obtained through the computational analysis show the variation in crack propagation rate for different composites and it can be utilized to study the fracture mechanics in the detailed design phase of an airplane. Faculty of Mechanical Engineering & UiTM Press 2017 Article PeerReviewed text en http://ir.uitm.edu.my/id/eprint/21116/1/AJ_Bruce%20Ralphin%20Rose.J%20JME%2017.pdf Bruce, Ralphin Rose.J and S, Priyadharshini (2017) Initial and progressive failure analysis of a composite wing spar structure / Bruce Ralphin Rose.J and Priyadharshini.S. Journal of Mechanical Engineering, 14 (2). pp. 167-183. ISSN 1823-5514 |
| repository_type |
Digital Repository |
| institution_category |
Local University |
| institution |
Universiti Teknologi MARA |
| building |
UiTM Institutional Repository |
| collection |
Online Access |
| language |
English |
| topic |
Composite materials Mechanics of engineering. Applied mechanics |
| spellingShingle |
Composite materials Mechanics of engineering. Applied mechanics Bruce, Ralphin Rose.J S, Priyadharshini Initial and progressive failure analysis of a composite wing spar structure / Bruce Ralphin Rose.J and Priyadharshini.S |
| description |
In the present work, a main spar section of a composite wing structure is analyzed for its structural safety in the course of preliminary aircraft design phase. Spar is a spanwise structural member that is used to carry the bending loads and it deals with the self weight of the wing while the airplane is on the ground as well as it carries the lifting loads during flight. Because of the rolling inertia loads and chord wise bending loads caused by aerodynamic effects, spar structure is vulnerable to different structural failures before the end of safe life cycle. Initial and progressive failure analysis of the spar section is done by using the typical properties of composite materials. Carbon epoxy, Graphite epoxy and Boron epoxy materials are analyzed with their standard material properties to determine the crack initiation and propagation characteristics at different time steps with stress increments. A two-dimensional spar cross section (I - section) is designed with shell as element type and the analysis is done in ABAQUS/CAE by using XFEM for crack initiation. The results obtained through the computational analysis show the variation in crack propagation rate for different composites and it can be utilized to study the fracture mechanics in the detailed design phase of an airplane. |
| format |
Article |
| author |
Bruce, Ralphin Rose.J S, Priyadharshini |
| author_facet |
Bruce, Ralphin Rose.J S, Priyadharshini |
| author_sort |
Bruce, Ralphin Rose.J |
| title |
Initial and progressive failure analysis of a composite wing spar structure / Bruce Ralphin Rose.J and Priyadharshini.S |
| title_short |
Initial and progressive failure analysis of a composite wing spar structure / Bruce Ralphin Rose.J and Priyadharshini.S |
| title_full |
Initial and progressive failure analysis of a composite wing spar structure / Bruce Ralphin Rose.J and Priyadharshini.S |
| title_fullStr |
Initial and progressive failure analysis of a composite wing spar structure / Bruce Ralphin Rose.J and Priyadharshini.S |
| title_full_unstemmed |
Initial and progressive failure analysis of a composite wing spar structure / Bruce Ralphin Rose.J and Priyadharshini.S |
| title_sort |
initial and progressive failure analysis of a composite wing spar structure / bruce ralphin rose.j and priyadharshini.s |
| publisher |
Faculty of Mechanical Engineering & UiTM Press |
| publishDate |
2017 |
| url |
http://ir.uitm.edu.my/id/eprint/21116/ http://ir.uitm.edu.my/id/eprint/21116/1/AJ_Bruce%20Ralphin%20Rose.J%20JME%2017.pdf |
| first_indexed |
2023-09-18T23:05:52Z |
| last_indexed |
2023-09-18T23:05:52Z |
| _version_ |
1777418479054356480 |