The invention discloses an aerothermoelasticity calculation method of multi-field coupling of trajectory status of hypersonic aircraft, and belongs to the field of aircraft aerodynamic-calculation. Inthe engineering fields of aerospace and the like, aircraft structures suffer severe aerodynamic heating effects with increasing of flying speed of the supersonic aircraft; and at the same time, flying trajectories are more complex due to more and more complex mission requirements, and aerodynamic heat environments are also more difficult to predict. Therefore, the aerothermoelasticity problem under the complex trajectories deserves attention. According to the method of the invention, a method of combination of inviscid-external-flow solutions and an engineering method is adopted for aerodynamic heating calculation of the high-speed aircraft, compared with a pure numerical method, the method of combination can save massive memory and calculation time, and reduces calculation costs, and compared with a pure engineering method, the same is wider in an application range, can be adapted to relatively complex shapes, and can also provide relatively-accurate aerodynamic heat solutions at thesame time.