Abstract: In order to evaluate the temperature cycling resistance of vacuum deposition coatings on the carbon fiber substrate antenna reflector of an LEO satellite microwave detection load for ensuring that the performance of the coating can still meet the requirements of the product in orbit after frequent temperature cycling in orbit, a test method is proposed to establish a model to determine the acceleration factor of the temperature cycling based on the environmental stress screening code of aerospace products. Then the temperature cycling test for different sizes of test pieces is carried out. According to the equivalent 8-year in-orbit life, the appearance and the thermal control performance of the coating samples are examined and tested before, during, and after the experiment for a total of fourteen times in an out-of-box way. It is shown that the coating samples remain apparently sound, and the solar absorption and the emission/absorption ratio well meet the specification requirements, thus it can be said that the vacuum deposition coating has excellent performance for orbit use.