doi: 10.3850/S201042862015001131

Mode Evolution of a Composite Laminated Stiffened Plate with Thermal Environment

Chong-ling Li and Yue-ming Li State Key Laboratory for Strength and Vibration of Mechanical Structures,
Shaanxi Key Laboratory of Service Environment and Control for Advanced Aerocraft,
School of Aerospace Engineering, Xi'an Jiaotong University,
No. 28 Xianning West Road, Xi'an, Shaanxi, 710049, China

ABSTRACT

Composite laminated stiffened plates have been widely used in aerospace industry as the construction of aerocraft due to its light weight and superior material capability. Extensive research efforts were devoted over the past years to study on such structures. In present study, the thermal mode evolution of the composite laminated stiffened plate is numerically analyzed during the both pre- and post-buckling state. Von-Karman strain-displacement relation is utilized to account for the geometrical nonlinearity in post-buckling. A composite laminated stiffened plate is considered with four edges clamped, in which the stiffeners are concentrically or eccentrically placed. Firstly, eigenvalue analysis is performed to get the critical temperature point and to distinguish the pre-buckling range and post-buckling range. Then, the appearance of mode jumping is found and shifts towards lower order mode shapes as the temperature rises, and some mode is missing in thermal post-buckling range. Mechanism of the mode evolution is studied in view of the phenomenons. Afterwards, the effects of stiffener parameters, thermal environment and lamination schemes are also studied on the composite laminated stiffened plate in detail.

Keywords: Composite laminated stiffened plate, Buckling, Mode jumping, Mode missing.

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