<p>The rotating sandwich cylindrical shell with bolt connection is a common substructure in aerospace. Due to the complexity of actual working conditions, bolts tend to loosen, resulting in connection detuning. To explore the failure mechanism and variation law of bolt connection detuning, a general semi-analytical dynamic model for the bolted composite sandwich cylindrical–cylindrical shell structure under rotational conditions is established. The model is constructed with a functionally graded porous graphene platelet-reinforced composite (FGP-GPLRC) core and fiber-reinforced composite (FRC) face sheets, which combines the advantages of lightweight, high specific strength, and high stiffness. With the aim of fully investigating the detuning behaviors of the bolt connection, a discontinuous artificial spring method is utilized. Then, the displacement continuity assumption of the layerwise theory and the first-order shear deformation theory (FSTD) are used to establish the equation of motion. According to the Rayleigh–Ritz method, the traveling wave vibration characteristics of the bolted shell structure are solved by the state-space method. Through extensive comparisons with experimental results in the literature, the accuracy and rationality of the model are fully verified. The modeling and solution methods proposed in this paper provide valuable theoretical references and engineering guidance for the application of FGP-GPLRC-FRC cylindrical–cylindrical sandwich shell structures in aerospace.</p>