In this paper, the aeroelastic model of composite panel with thermal effects is established using von Karman large deformation strain-displacement relationship, piston theory of aerodynamics and quasi-steady theory of thermal stress.

Study on active vibration control of composite laminated plates;

Nonlinear thermal dynamic response analysis of heated composite laminated plates;

In this paper,the combination of hybrid numerical method(HNM)and reduced-basis method (RBM)is suggested to more effectively analyze the transient displacement response in composite laminated plates.

The compressive failure tests were carried out on the composite laminates after low velocity impact damage to study compressive failure mechanisms of laminates after low velocity impact damage.

The 3D progressive damage theory and finite element method were used to analyze the impact process of composite laminates.

An element failure model in series of composite laminates for the fatigue life prediction under cyclic loading is presented based on the finite element method(FEM).

Effect of multiple delaminations on free vibration characteristic for composite laminates;

Optimal design for natural frequency of composite laminates with multi-lumped mass and spring supports by Genetic Algorithm;

Experimental modal analysis of the composite laminates with temperature variation;

Prediction method for fatigue life of laminated composites after impact under compression-compression loading;

Progressive fatigue damage analysis method of laminated composites;

This research developed the progressive damage theory to simulate the initiation and propagation of all kinds of damage in laminated composites which are subjected to low-velocity impacts.