Based on the principle of conjugate heat transfer between the external and internal chamber

AMESim simulation model was established for the hot air anti-icing system. The change rules of the flux

pressure and skin temperature in different bleeding conditions were researched. The internal flow characteristics and the conjugate heat transfer characteristics of the aircraft wing anti-icing system were calculated using this model. The predictions of the flux

temperature and pressure were verified against those in the flow distribution experimental data of the wing anti-icing system

showing a satisfactory agreement. The maximum error was less than 9%. Its accuracy and validity were validated with the comparison of results. On the basis of modeling

a nacelle hot air anti-icing system was simulated. The transient characteristics of key parameters under a certain flight envelop

such as the heat flux

temperature and heating efficiency

were analyzed. The results can be provided as a reference for design

analysis and optimization of hot air anti-icing system.