Abstract: For a three-dimensional hypersonic aircraft configuration, a six-degree-of-freedom integrated modeling method for rigid aircraft is presented. Using the mechanism analysis method, the oblique shock and Prandtl-Meyer flow theory and the aerodynamic theory are used to estimate the aerodynamic force, control surface force, and the aircraft thrust. The control-oriented model is established using the curve-fitting method of gradual regression, and the dynamic characteristics of the model are analyzed. The simulation results show that the curve-fitting model reduces the complexity of the mechanism derivation model and retains the coupling characteristics of aerodynamic and propulsion systems, thus providing a basis for aircraft controller design.