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

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

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

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

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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

Original language	English
Number of pages	10
Publication status	Published - 03 Sept 2015
Event	32nd International Manufacturing Conference (IMC 32) - Northern Ireland, Belfast, United Kingdom Duration: 02 Sept 2015 → 04 Sept 2015

Conference

Conference	32nd International Manufacturing Conference (IMC 32)
Country/Territory	United Kingdom
City	Belfast
Period	02/09/2015 → 04/09/2015

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The effect of manufacture and assembly joining methods on stiffened panel performance
© 2015 The Authors
Accepted author manuscript, 449 KB

http://programme.exordo.com/imc32/delegates/presentation/15/

Simulation intent for multi-fidelity composite structural analysis
Harley, C. (Author), Robinson, T. (Supervisor), Quinn, D. (Supervisor) & Nolan, D. (Supervisor), Jul 2021
Student thesis: Doctoral Thesis › Doctor of Philosophy

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title = "The effect of manufacture and assembly joining methods on stiffened panel performance",

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",

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T1 - The effect of manufacture and assembly joining methods on stiffened panel performance

AU - Harley, C.

AU - Quinn, D.

AU - Robinson, T.

AU - Goel, S.

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Y1 - 2015/9/3

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

T2 - 32nd International Manufacturing Conference (IMC 32)

Y2 - 2 September 2015 through 4 September 2015

ER -

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

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Student theses

Simulation intent for multi-fidelity composite structural analysis

Cite this