Aiming at the application requirements of the composite honeycomb sandwich structure with high temperature resistance and large load bearing for Tianwen-1 Mars probe， a cyanate resin composite honeycomb sandwich structure was proposed based on material matching design and process feasibility. By comparing the high-temperature interlaminate shear properties of M40J/BS-4 cyanate resin composites under different post-treatment processes， it was found that BS-4 cyanate resin composites can be obtained with better high temperature performance after 3 to 5 hours post-treatment at 200 ℃.For M40J/BS-4 cyanate resin composite material after 4 hours post-treatment at 200 ℃， the retention coefficient of various mechanical properties at 170 ℃ reached more than 80% of the room temperature test value. The high-temperature mechanical properties test of the adhesives and the study of the adhesives influence on the high-temperature load-bearing performance of the sandwich structure showed that the two adhesives of the cyanate ester， J-245C and J-389B， have sufficient ability to coordinate the deformation and transfer the load between skins and cores when the temperature does not exceed 200 ℃. The performance degradation of the adhesive at high temperatures will cause the rigidity degradation of the sandwich structure. The test results of bending performance and lateral compression performance of honeycomb sandwich structure of Tianwen-1 mars probe showed that the honeycomb sandwich structure of carbon fiber cyano matrix composite has the large bearing capacity under 170 ℃ high temperature.