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Considering the interaction between flexible and rigid modes caused by the increased aspect ratio and elasticity of spinning missile, the nonlinear equations of motion for elastic spinning missile are developed. The transient coordinate system, in which vibration mode is used to describe the missile’s elastic deformation, is introduced. The slice theory is used to establish an aerodynamics model. Lagrangian equation is used to derive the complete inertial coupling model of elastic spinning missiles. In the model, the influence of elastic deformation on the mass property is considered, and the coupling effect between flexible and rigid modes are fully described. Under different assumptions, the complete inertial coupling model can be simplified to obtain the simplified inertial and non-inertial coupling models. Numerical simulations demonstrate that the main difference on the attitude motion is not negligible, while the difference on the flexible mode is negligible. The influence of inertial coupling must be considered in the modeling and analysis of elastic spinning missile. [ABSTRACT FROM AUTHOR]