TY - JOUR
T1 - Assessment of cure-residual strains through the thickness of carbon-epoxy laminates using FBGs Part II
T2 - Technological specimen
AU - Mulle, M.
AU - Collombet, F.
AU - Olivier, P.
AU - Zitoune, R.
AU - Huchette, C.
AU - Laurin, F.
AU - Grunevald, Y. H.
N1 - Funding Information:
The authors wish to thank the DGA (Direction Générale de l’Armement) for its financial support through the upstream program AMERICO and the Hexcel Composites Company for providing us with HexPly® pre-preg material.
PY - 2009/10
Y1 - 2009/10
N2 - This paper is a continuation of our previous study [Mulle M, Collombet F, Olivier P, Grunevald Y-H. Assessment of cure residual strains through the thickness of carbon-epoxy laminates using FBGs, part I: elementary specimen. Compos Part A 2008. doi:10.1016/j.compositesa. 2008.10.008] pertaining to the assessment of autoclave cure-induced strains through the thickness of carbon-epoxy laminates. In this first part, postulates and measurement procedures were established for cure of elementary specimens. Based on these, this study undertakes investigation on what are called technological specimens. These specimens are of the beam type and contain geometrical specificities which represent typical structural issues. In-plane process-induced strains were studied through the thickness of a thick reinforced zone using several optical fibre Bragg gratings (FBGs) sensors embedded at different levels of the ply stack. A non-uniform distribution of residual strains was detected. Once cured, the technological specimen was subjected to a heating test whose cycle was comparable to the cure cycle. Thermally induced strains were measured with the embedded FBGs. The values recorded were compared with those of cure-induced residual strains and FEM simulation. Discrepancies were observed that strongly suggest the possible influence of environmental effects and the need for the calculation to take into account the through-the-thickness variability of thermal properties.
AB - This paper is a continuation of our previous study [Mulle M, Collombet F, Olivier P, Grunevald Y-H. Assessment of cure residual strains through the thickness of carbon-epoxy laminates using FBGs, part I: elementary specimen. Compos Part A 2008. doi:10.1016/j.compositesa. 2008.10.008] pertaining to the assessment of autoclave cure-induced strains through the thickness of carbon-epoxy laminates. In this first part, postulates and measurement procedures were established for cure of elementary specimens. Based on these, this study undertakes investigation on what are called technological specimens. These specimens are of the beam type and contain geometrical specificities which represent typical structural issues. In-plane process-induced strains were studied through the thickness of a thick reinforced zone using several optical fibre Bragg gratings (FBGs) sensors embedded at different levels of the ply stack. A non-uniform distribution of residual strains was detected. Once cured, the technological specimen was subjected to a heating test whose cycle was comparable to the cure cycle. Thermally induced strains were measured with the embedded FBGs. The values recorded were compared with those of cure-induced residual strains and FEM simulation. Discrepancies were observed that strongly suggest the possible influence of environmental effects and the need for the calculation to take into account the through-the-thickness variability of thermal properties.
KW - A. Technological specimen
KW - B. Residual/internal stress
KW - C. FBG sensors
KW - D. Process monitoring
UR - http://www.scopus.com/inward/record.url?scp=70249134880&partnerID=8YFLogxK
U2 - 10.1016/j.compositesa.2009.06.013
DO - 10.1016/j.compositesa.2009.06.013
M3 - Article
AN - SCOPUS:70249134880
SN - 1359-835X
VL - 40
SP - 1534
EP - 1544
JO - Composites Part A: Applied Science and Manufacturing
JF - Composites Part A: Applied Science and Manufacturing
IS - 10
ER -