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This paper examines the temperature-dependent behavior of composite materials under axial compression across
a wide temperature range, focusing on buckling mode transitions. Experimental tests were conducted using a
servo-hydraulic MTS system at temperatures from − 20 °C to 80 °C. Load-displacement and load-deflection
data were collected via a 3D DIC system, ensuring accurate characterization of the buckling response. Based on
Classical Laminate Theory (CLT), the temperature-dependent laminate stiffness components were determined,
with particular attention given to D16 and D26, which describe bending–twisting coupling and may influence
the evolution of buckling patterns and the susceptibility of the structure to transitions between competing equi-
librium states. The main novelty of this study is the application of full-field 3D DIC to identify and track the
development of mode-jumping phenomena during loading at different temperatures and to relate the observed
changes to the temperature-dependent bending–twisting stiffness of the laminate. Mode transitions were identi-
fied from the redistribution of the out-of-plane displacement field and changes in the number and location of
longitudinal half-waves. The results demonstrate that temperature significantly affects structural stiffness, defor-
mation capacity, and the evolution of post-buckling patterns. Lower temperatures produced a stiffer structural
response, whereas higher temperatures resulted in greater deformability and larger displacements before failure.
The study provides new experimental insight into the temperature-dependent evolution of buckling patterns
and mode-jumping pathways in thin-walled composite profiles. These findings may support the design and
assessment of CFRP load-bearing components operating under variable temperature conditions, particularly in
aerospace and other high-performance engineering applications.
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