Design of a Cooling System for the Avionic Equipment

The hybrid electric propulsion system can improve flight efficiency and decrease the problems of carbon emission . However, this system has a temperature limitation due to electronic components, and the Power Management Unit(PMU) that control power of hybrid electric propulsion system has high temperature characteristics. The lifetime of the system can be reduced by temperature issues, and even they can failure the system. To solve these issues, we focused on the design of the cooling system that consist to heat sink with fan. In this study, cooling system was designed shape variables of the heat sink and velocity condition of the commercial fan using matlab program. The weight and the volume of the heat sink and power consumption of the fan are minimized for the avionic equipment. At the result, designed cooling system is satisfied thermal stability of the PMU. Also, it is satisfied as the altitude variation.