The weight of machines such as the aircraft, automobiles and so on has the great affect on the consumption of fuel and electricity. Thus, the enhanced design to make the weight of the aircraft or automobile lighter has been researching. It is quite important and urgent to raise the overall performance for the purpose of reducing the weight of the machine significantly. Based on an epoxy resin, there are fiber reinforced composite materials that use the fibers such as carbon, glass, and aramid. The carbon fiber reinforced plastic (CFRP) among these materials has the excellent material properties as high specific strength, specific elastic modulus, anti-wear, long fatigue life, light weight and environmental safety characteristics by comparing with the normal metal. Hence, these composites are widely used in various industrial areas as airlines, defense, automobiles, and sports. The aim of this study is to analyze the mechanical properties of the aluminum plate sandwich, the carbon fiber reinforced plastic sandwich and aluminum foam specimen through the compression simulation analysis. When the load cell moves as much as the forced displacement of 12 mm at experiment, the maximum loads of the carbon fiber reinforced plastic sandwich, the aluminum sandwich and the aluminum foam specimen become about 49.15kN, 51.2kN and 3.27kN respectively. It is affirmed that the results of simulation and experiment is very similar. At simulation, the equivalent stress of carbon fiber reinforced plastic sandwich is shown to be bigger than the equivalent stress of aluminum plate sandwich. Putting the analysis results together, the maximum load of the carbon fiber-reinforced plastic sandwich is appeared to be greater than the maximum load of the aluminum sandwich. The structure of the carbon fiber-reinforced plastic sandwich that has a lighter weight is thought to be better than that of the aluminum sandwich. Therefore, the analysis results of this study are thought to be applied at the data for design verification of the airframe, the wing of airplane and the rotor blade of helicopter using CFRP, aluminum plate(AL 6061-T6) and aluminum foam. And in order to make the structure with better rigidity, the simulation is carried out by changing the arrangement method of fiber angle at CFRP. As the analysis result during the compression time of 12 sec, the maximum compressive loads of the plates of [0/15/15/0], [0/30/30/0], [0/45/45/0], [0/60/60/0], [0/75/75/0] and [0/90/90/0] are shown to be 43.66kN, 53.139kN, 55.86kN, 61.826kN, 35.52kN and 53.002kN respectively. So, the plate of [0/60/60/0] endures the most load among six plates. The results of experiments and analyses obtained in this study can be applied into the real composite structure with the carbon fiber reinforced plastic sandwich bonded with adhesive and aluminum plate sandwich. And it is possible to predict and verify the structure safety.