The effect of manufacture and assembly joining methods on stiffened panel performance

C. Harley, D. Quinn, T. Robinson, S. Goel

Research output: Contribution to conferencePaper

Abstract

This paper describes the simulation of representative aircraft wing stiffened panels under axial compression loading, to determine the effects of varying the manufacturing shape and assembly joining methods on stiffened panel performance. T-stiffened and Z-stiffened panels are modelled in Abaqus simulating integral, co-cured and mechanically fastened joints. The panels are subject to an edge compressive displacement along the stiffener axis until failure and the ultimate failure load and buckling performance is assessed for each. Integral panels consistently offer the highest performance. Co-cured panels demonstrate reduced performance (3-5% reduction in ultimate load relative to integral) caused by localised cohesive failure and skin-stiffener separation. The mechanically fastened panels are consistently the weakest joint (19-25% reduction in ultimate load relative to integral) caused primarily by inter-rivet buckling between fasteners
LanguageEnglish
Number of pages10
Publication statusPublished - 03 Sep 2015
Event32nd International Manufacturing Conference (IMC 32) - Northern Ireland, Belfast, United Kingdom
Duration: 02 Sep 201504 Sep 2015

Conference

Conference32nd International Manufacturing Conference (IMC 32)
CountryUnited Kingdom
CityBelfast
Period02/09/201504/09/2015

Fingerprint

Joining
Buckling
Rivets
Axial compression
Fasteners
Skin

Cite this

Harley, C., Quinn, D., Robinson, T., & Goel, S. (2015). The effect of manufacture and assembly joining methods on stiffened panel performance. Paper presented at 32nd International Manufacturing Conference (IMC 32), Belfast, United Kingdom.
Harley, C. ; Quinn, D. ; Robinson, T. ; Goel, S. / The effect of manufacture and assembly joining methods on stiffened panel performance. Paper presented at 32nd International Manufacturing Conference (IMC 32), Belfast, United Kingdom.10 p.
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Harley, C, Quinn, D, Robinson, T & Goel, S 2015, 'The effect of manufacture and assembly joining methods on stiffened panel performance' Paper presented at 32nd International Manufacturing Conference (IMC 32), Belfast, United Kingdom, 02/09/2015 - 04/09/2015, .

The effect of manufacture and assembly joining methods on stiffened panel performance. / Harley, C.; Quinn, D.; Robinson, T.; Goel, S.

2015. Paper presented at 32nd International Manufacturing Conference (IMC 32), Belfast, United Kingdom.

Research output: Contribution to conferencePaper

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AU - Harley, C.

AU - Quinn, D.

AU - Robinson, T.

AU - Goel, S.

PY - 2015/9/3

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N2 - This paper describes the simulation of representative aircraft wing stiffened panels under axial compression loading, to determine the effects of varying the manufacturing shape and assembly joining methods on stiffened panel performance. T-stiffened and Z-stiffened panels are modelled in Abaqus simulating integral, co-cured and mechanically fastened joints. The panels are subject to an edge compressive displacement along the stiffener axis until failure and the ultimate failure load and buckling performance is assessed for each. Integral panels consistently offer the highest performance. Co-cured panels demonstrate reduced performance (3-5% reduction in ultimate load relative to integral) caused by localised cohesive failure and skin-stiffener separation. The mechanically fastened panels are consistently the weakest joint (19-25% reduction in ultimate load relative to integral) caused primarily by inter-rivet buckling between fasteners

AB - This paper describes the simulation of representative aircraft wing stiffened panels under axial compression loading, to determine the effects of varying the manufacturing shape and assembly joining methods on stiffened panel performance. T-stiffened and Z-stiffened panels are modelled in Abaqus simulating integral, co-cured and mechanically fastened joints. The panels are subject to an edge compressive displacement along the stiffener axis until failure and the ultimate failure load and buckling performance is assessed for each. Integral panels consistently offer the highest performance. Co-cured panels demonstrate reduced performance (3-5% reduction in ultimate load relative to integral) caused by localised cohesive failure and skin-stiffener separation. The mechanically fastened panels are consistently the weakest joint (19-25% reduction in ultimate load relative to integral) caused primarily by inter-rivet buckling between fasteners

M3 - Paper

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Harley C, Quinn D, Robinson T, Goel S. The effect of manufacture and assembly joining methods on stiffened panel performance. 2015. Paper presented at 32nd International Manufacturing Conference (IMC 32), Belfast, United Kingdom.