Since the subsystems of aerodynamics,propulsion,structure and so on in hypersonic vehicles involve characteristics of nonlinearity,strong coupling and uncertainty,and typical hypersonic vehicles adopt slender-body and wave-rider layout with widely-used lightweight materials,the accuracy of the modeling with a conventional rigid-body assumption is challenged.Therefore,a nonlinear mathematical longitudinal model of a hypersonic vehicle is established with its geometry provided to estimate aerodynamic force and thrust using hypersonic aerodynamics and quasi-one-dimensional flow with heat added and capture vehicle aeroelasticity using a single free-free Bernoulli-Euler beam model.Then the static and dynamic properties of the rigid and rigid-aeroelasticity coupling model are compared via theoretical analysis and numerical simulation under the given flight condition.Finally,a LQR controller for rigid model is designed and the comparable results are obtained to explain the aerolasticity influence on the control effect.The simulation results show that the aeroelasticity mode of slender-body hypersonic vehicles affects short period mode significantly and it cannot be simply neglected. Since the subsystems of aerodynamics, propulsion, structure and so on in hypersonic vehicles involve characteristics of nonlinearity, strong coupling and uncertainty, and typical hypersonic vehicles adopt slender-body and wave-rider layout with widely-used lightweight materials, the accuracy of the modeling with a conventional rigid-body assumption is challenged. Where, a nonlinear mathematical longitudinal model of a hypersonic vehicle is established with its geometry provided to estimate aerodynamic force and thrust using hypersonic aerodynamics and quasi-one-dimensional flow with heat added and capture vehicle aeroelasticity using a single free-free Bernoulli-Euler beam model. The static and dynamic properties of the rigid and rigid-aeroelasticity coupling models are compared by theoretical analysis and numerical simulation under the given flight condition. Finally, a LQR controller for rigid model is designed and the comparable results are obtained to explain the aerolasticity influ ence on the control effect. the simulation results show that the aeroelasticity mode of slender-body hypersonic vehicles affects short period mode significantly and it can not be simply neglected.