To prevent fatigue failure of the folding wing mechanism, a random vibration fatigue analysis was conducted on a new type of folding wing mechanism used in aerospace. Firstly, the random vibration fatigue damage was simplified based on the three interval method. Then, the modal analysis was conducted on the folding wing mechanism to obtain its natural frequency, and the modal superposition method was used for frequency response analysis and random vibration analysis to obtain the dynamic response of the fatigue high-risk area under specific vibration conditions, as well as the frequency at which resonance was prone to occurring at the damage location. Finally, numerical calculations were performed on the folding wing mechanism to verify whether fatigue damage would occur. The results show that in the ultimate random vibration test in any direction of x, y, z, the fatigue damage was less than 1, indicating that the folding wing mechanism will not experience fatigue damage.