In response to the aerodynamic heating problem of the wing structure of hypersonic vehicles (Ma < 6), the engineering algorithms for the aerodynamic heat flux density in the stagnation point region of the wing leading - edge and general parts are studied. Combining with the finite element analysis method of transient heat transfer, a coupling analysis algorithm for aerodynamic heating and transient heat transfer is designed. Based on the open-software architecture of the domestic structural analysis software SABRE and using the modular software design concept, a calculation module for aerodynamic heat flux density is developed. This module is inserted into the transient heat transfer analysis process to construct a coupling analysis process for aerodynamic heating-transient heat transfer, and a coupling analysis software is developed. A finite element model of a typical wing structure is established, different aerodynamic partitions of the wing are constructed, and a coupling analysis of aerodynamic heating and transient heat transfer is carried out. By comparing with the results in relevant literature, the error of nodal temperature is within 3%, which can provide support for the design of such vehicles.