Abstract: The orbital radiation heat flux received by the spacesuit used for extravehicular activity ( EVA )is analyzed. By Monte Carlo method, the reflection and infrared radiation angle factors are calculated between spacesuit and spacecraft or earth when spacesuit is located at any position relative to the spacecraft or the earth. It shows that the method is applicable and the results obtained are accurate and reliable as compared with data of References, so as to entirely meet the requirement of engineering application.

Key words: thermal control, orbital heat flux, Monte Carlo method, spacesuit, radiation angle factor