항공기용 전자 장비를 위한 방열 시스템 설계 (Design of a Cooling System for the Avionic Equipment)

서지정보

· 발행기관 : 한국유체기계학회
· 수록지 정보 : 한국유체기계학회 논문집 / 21권 / 3호 / 22 ~ 28페이지
· 저자명 : 윤승현, 박정규, 김보성, 조진수

초록

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.

영어초록

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.

참고자료

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