Aimed for the question of computational efficiency during conceptual design stage, a rapid engineering aero-heating calculation method for complex shaped hypersonic vehicles is established. Firstly the pressure distribution along vehicle’s surface was calculated by modified Newtonian theory. Secondly, the streamline that passes through the target point was calculated with Newtonian steepest decent concept. Then by using the fitted function of high temperature gas parameters, reference enthalpy method and engineering calculation function of aero-heating, the heat current of target point was presented. Finally, the heat flux on the surfaces of blunted cone, lifting body and wave-rider vehicle was calculated The analysis result shows the method used in this paper is fit for complex figure, and can satisfy the aero-heating calculation during conceptual design stage in both efficiency and precision.