An experimental simulation method of space re-entry environment was presented to investigate a carbon/silicon carbide composite and the effect on its properties. The re-entry environment is simulated by controlling the thermal environment and the stress environment. The thermal environment is provided with a high enthalpy combustion chamber with a temperature range of 600 degrees-1800 degrees C and a partial pressure of oxygen of 10-30 kPa. The stress environment can realize both loading and rotating effects with a maximum torque of 150 N center dot m and a minimum rotation velocity of 32 rpm. Multipurpose testing of a carbon/silicon carbide composite during re-entry can be achieved by this method, such as hot joining, stress-oxidation, creep, and friction behavior.