Composite material is basically the combination of two or more materials and each of them retains its own distinctive property. Studies on the accurate characteristic are required at structural reliability and data verification by the results of experiments and finite element analysis. The specimens used in this experiment are manufactured with composite materials of aluminum foam core and aluminum honeycomb core sandwich. Experimental results about the properties of composite materials are compared with finite element analysis results. Test results show that buckling is occurred at the aluminum foam core and honeycomb core according to the increase of load. At in-plane compression test, the maximum load of aluminum foam specimen is similar with that of honeycomb sandwich. The property of honeycomb is better than that of the foam in consideration of specific gravity. At out-plane compression test, the compression maximum load of aluminum honeycomb sandwich composite is higher than that of aluminum foam sandwich composite. Simulation analysis result obtains the similar behavior with experimental result.

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In this paper, strain and stress on space frame are analyzed at racing car under crash loads. As the deformation is reduced to a minimum during crash and the vulnerable parts are grasped, the safety of driver is ensured. The vehicle frame is modelled with truss structure by inputting the material property of carbon steel on finite element analysis. The increase of impulse momentum is due to speed change at frontal collision. This influence effected on vehicle frame is also analyzed by ANSYS program. The deformation of the frame is studied by applying the crash loads at front, side and rear directions. Though the influence on the seat of driver is small at frontal and rear crash, the deformation due to impact is progressed into this seat. The safety of frame is enhanced by making up for these weak deformations and these results of simulation analysis can be applied to the production of the actual vehicle frame.

In this study, compression analyses of sandwich composites with porous core were carried out. Finite element models of aluminum foam and honeycomb core sandwich composite material were applied solid element. In the case of aluminum foam core, valid equivalence damage model was applied. In the in-plane compression analysis, the maximum load of aluminum foam core sandwich was similar with that of aluminum honeycomb core sandwich. But in case of aluminum honeycomb core sandwich, the load support region becomes longer in comparison with aluminum foam core sandwich. In the out-plane compression analysis, compression maximum load of aluminum honeycomb core sandwich was higher than that of aluminum foam core sandwich. Through these Simulation analysis, obtains the behavior of sandwich composites.