In first part of the thesis , by a review of the research on aircraft sonic fatigue , the formulas for calculating natural frequencies of the typical aircraft skin - panel structure with four edges simply - supported or four edges fixed - supported were drawn , the response of displacement and stress was analysed under the condition of random white noise loading with the steady - state or unsteady - state . the procedure how to use data of s - n curve under constant loading for predicating the fatigue life of skin - panel subjected to random loading was shown 通過對聲疲勞問題研究的回顧,根據(jù)典型飛機蒙皮壁板模型,整理了四邊固支,四邊簡支兩種邊界條件下多階模態(tài)固有頻率,非平穩(wěn)及平穩(wěn)隨機白噪聲載荷下的位移和應力響應,以及如何從等幅s ? n曲線求得隨機載荷應力下的疲勞壽命。