Since there may be a fatigue problem when a high volume fraction SiCp/Al-based composite material is used in the structure design of a space remote sensor, the fatigue failure behavior of the material is studied. Firstly, several fatigue testing methods are presented. A conventional testing method is selected to test the fatigue strength of the material. The fatigue test is planned. Then, a mathematic model of the key parameters in the S-N curve is established by using a three-parameter exponential function model to process the experimental data. A method for selecting vibration frequency in the vibration test is proposed. Finally, five specimens are tested on a vibrating table. The observed test data are fitted by using the three-parameter exponential function model. The result shows that the material has a fatigue strength of 161 MPa. This result is very helpful to the structure design of space remote sensors.