Abstract: In the present investigation, use is made of the structural characteristics at different temperatures of coated Cb-752 alloy to simulate the actual heating condition during re-entry. Specimens of coated Cb-752 sheets are successively heated from 1300℃ to 2200℃, the structure of these specimens is determined by optical microscopy, X-ray diffraction and electron micropro-be technique. The structure of the specimen taken from some specific parts of the actual recovered components is then compared with the coated simulated specimens and the temperature of that specific point on the actual components during re-entry assessed. In this way the criteria for analyzing the heating condition of coated structural parts are tentatively established. The method for analyzing the heated structural parts of coated Cb-752 alloy space vehicle during re-entry is also elucidated.