Research on cooling technology was carried out considering that the electric actuating mechanism on aircrafts would produce much heat in working. The empirical formula was fitted based on the experiment data. A cooling method for an aircraft electric actuating mechanism was proposed based on the heat pipe-fuel cooling system

and a numerical model describing the flow and heat transfer of the cooling system was established and validated feasibly. The influence of some factors on the cooling performance of the cooling system was studied by numerical simulation. Results showed that the error between numerical simulation and experiment data was within 14.6%. The heat pipe-fuel cooling system could reduce the temperature rise of the electromechanical actuator by 12.61% compared with natural convection. For the driver

the fan cooling method was superior to the heat pipe-fuel cooling method. When the effective thermal conductivity of heat pipes reached 7 000 W/(m·K)

the heat pipe-fuel cooling system could achieve a good cooling performance

and continuously increasing the effective thermal conductivity of heat pipes couldnt effectively improve the cooling performance of the cooling system. This research provides a reference for designing an efficient cooling system for electric actuating mechanisms.