During the development of an aircraft structure design, designers draw out a skin-stringer panel with a skin pad on the basis of a conventional skin-stringer panel(skin is directly connected with stringer by rivets or there was a sheet betweeen skin and stringers) to reduce the manufacturing cost. In this paper, we calculated the SIF of three kinds of skin-stringer panels by FE. And then, we analyze the damage tolerance of these structures by fortran program. Especially we carried out a crack propagation experiment of a skin-stringer panel with a skin pad and compared it with the results of a static analysis. Finally we researched the influence of the thickness of a skin pad on the damage tolerance. According to the researches above we concluded the advantages of the skin-stringer panel with a skin pad on the damage tolerance, and presented some suggestions about the thickness of a skin pad.