Strength analysis of an aircraft sandwich structure with a honeycomb core : theoretical and experimental approaches
Joint Authors
Jwig, Muhsin Jabr
Sadiq, Sadiq Imad
Bakhy, Sadiq Husayn
Source
Engineering and Technology Journal
Issue
Vol. 39, Issue 1A (31 Jan. 2021), pp.153-166, 14 p.
Publisher
Publication Date
2021-01-31
Country of Publication
Iraq
No. of Pages
14
Main Subjects
Information Technology and Computer Science
Topics
Abstract EN
In this paper, the strength of aircraft sandwich structure with honeycombcore under bending load was evaluated theoretically and experimentallybased on failure mode maps.
A failure mode map for the loading underthree-point bending was constructed theoretically to specify the failuremodes and corresponding load.
Three point bending test for aluminumhoneycomb sandwich beam has been achieved to measure the peak loadand maximum deflection.
The obtained results elucidated a goodagreement between the theoretical solutions and experimental tests, wherethe error ratio was not exceeded 12% .
The core height, the cell size andthe cell wall thickness were selected to explore the effect of honeycombparameters on the strength of sandwich structure.
In order to obtain theoptimum solution of peak load and maximum deflection and energyorption, Response Surface Methodology (RSM) was used.
Resultsshowed that the maximum bending load, minimum deflection, andmaximum energy orption were found at 25 mm core height, 10 mm sizecell and 1 mm cell wall thickness.
The optimal value of maximum bendingload, minimum deflection and maximum energy orption were1975.3415 N, 1.0402 mm and 1.0229 J In this paper, the strength of aircraft sandwich structure with honeycombcore under bending load was evaluated theoretically and experimentallybased on failure mode maps.
A failure mode map for the loading underthree-point bending was constructed theoretically to specify the failuremodes and corresponding load.
Three point bending test for aluminumhoneycomb sandwich beam has been achieved to measure the peak loadand maximum deflection.
The obtained results elucidated a goodagreement between the theoretical solutions and experimental tests, wherethe error ratio was not exceeded 12% .
The core height, the cell size andthe cell wall thickness were selected to explore the effect of honeycombparameters on the strength of sandwich structure.
In order to obtain theoptimum solution of peak load and maximum deflection and energyorption, Response Surface Methodology (RSM) was used.
Resultsshowed that the maximum bending load, minimum deflection, andmaximum energy orption were found at 25 mm core height, 10 mm sizecell and 1 mm cell wall thickness.
The optimal value of maximum bendingload, minimum deflection and maximum energy orption were1975.3415 N, 1.0402 mm and 1.0229 J respectively.
American Psychological Association (APA)
Sadiq, Sadiq Imad& Jwig, Muhsin Jabr& Bakhy, Sadiq Husayn. 2021. Strength analysis of an aircraft sandwich structure with a honeycomb core : theoretical and experimental approaches. Engineering and Technology Journal،Vol. 39, no. 1A, pp.153-166.
https://search.emarefa.net/detail/BIM-1281604
Modern Language Association (MLA)
Sadiq, Sadiq Imad…[et al.]. Strength analysis of an aircraft sandwich structure with a honeycomb core : theoretical and experimental approaches. Engineering and Technology Journal Vol. 39, no. 1A (2021), pp.153-166.
https://search.emarefa.net/detail/BIM-1281604
American Medical Association (AMA)
Sadiq, Sadiq Imad& Jwig, Muhsin Jabr& Bakhy, Sadiq Husayn. Strength analysis of an aircraft sandwich structure with a honeycomb core : theoretical and experimental approaches. Engineering and Technology Journal. 2021. Vol. 39, no. 1A, pp.153-166.
https://search.emarefa.net/detail/BIM-1281604
Data Type
Journal Articles
Language
English
Notes
Includes bibliographical references : p. 165-166
Record ID
BIM-1281604