Spring-back of Thick Uni-Directional Carbon Fibre Reinforced Composite Laminate for Aircraft Structure Application

The springback phenomena of CFRP after curing process through autoclave manufacturing method results on the out of tolerance for its utilisation in aerospace industry. This paper relates to the measurements of springback for Uni-directional flat laminate as a first steps to the springback study for...

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Bibliographic Details
Published inJournal of physics. Conference series Vol. 1005; no. 1; pp. 12003 - 12009
Main Authors Zakaria, M, Aminanda, Y, Rashidi, S A, Sah, M A Mat
Format Journal Article
LanguageEnglish
Published Bristol IOP Publishing 01.04.2018
Subjects
Aerospace industry
Aircraft
Aircraft structures
Carbon fibers
Fiber composites
Lay-up
Micrometers
Optical scanners
Physics
Production methods
Springback
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Summary:The springback phenomena of CFRP after curing process through autoclave manufacturing method results on the out of tolerance for its utilisation in aerospace industry. This paper relates to the measurements of springback for Uni-directional flat laminate as a first steps to the springback study for the real aircraft composite laminate structures. A flat laminate with dimension of 300 mm x 300 mm, 400 mm x 400 mm and 500mm x 500 mm with different number of ply; 20, 24 and 28 are manufactured. The choice of dimension and number of lay-up corresponds to the dimension and lay-up of rib structure. After process, the springbacks are measured using 3D scanner (optical-based three-dimensional) with an accuracy of 42 micrometers to obtain an accurate measurement. The analysis of the effect of dimension and number of ply to the magnitude of springback are presented within the range of specimen studied in this work.
ISSN:1742-6588
1742-6596
DOI:10.1088/1742-6596/1005/1/012003