Abstract: This paper first analyzes the vibration environment at the spacecraft/launch vehicle (SC/LV) interface during the powered flight phase. Second, it proposes a method to enhance satellite panel stiffness. Satellite frequency response analysis examines stiffness compatibility between the satellite (including its components) and the integrated launch stack. The environmental effect equivalence method then determines satellite ground verification test conditions. Ground test responses are compared with SC/LV coupling analysis results to ensure that ground tests envelope the coupling analysis results, confirming the adequacy of ground verification.

Key words: pannel stiffness, vibration environment, satellite dynamic properties