2010 年 76 巻 772 号 p. 3323-3329
Vibration test is a method to verify the design of space hardware, which will endure the flight vibration environment. The problem of vibration test is over testing in comparison to the flight environment due to the mounting impedance differences in flight versus test. Force limited vibration test is the one of the popular approach to prevent the unnecessary over testing of space hardware. In this study, we propose a method to estimate the maximum interface force, which is the limit value of vibration test, of flight configuration based on the measurement FRF (Frequency Response Function) of the test hardware by simple experiment, such as impact hammer excitation. The theoretical background is described as well as discussion of experimental process, deviation sources depending on excitation location, are stated in this report.