Abstract: In view of the light weight requirement of the first integrated aerospace electronic equipment to be used in China’s space station, the performances of two types of PMI foam sandwich structures, the TP and LP structures, are studied by tests with respect to their physical and mechanical properties. A comparative analysis is made between the performances of each sandwich structure and its corresponding basic material, i.e. the simple aluminum alloy or carbon fibers. It is concluded that the PMI foam sandwich structure has better damping and specific stiffness characteristics, with a reduction of 40% of the average weight, and a cut down of the mechanical response by 40 to 50 per cent. The results provide a foundation for the design of light weight space station electronic equipment.