Abstract
Aiming at the temperature control of the liquid cooling system of aircraft electronic equipment, the thermal characteristics of the system under different temperature conditions are analyzed through model simulation, and a calculation method is given for the thermal design of the liquid cooling system. This paper simplifies the system and establishes a numerical calculation model for the heat transfer of the main components (such as liquid storage tanks, gear pumps, radiators, etc.). The temperature changes in the main components of the system within the operating temperature range of the system (-40 °C-50 °C) were calculated, and the thermal characteristics of the cold plate were obtained by using the AMESim software. Further, temperature control schemes of several liquid cooling systems are compared for their working efficiency under low temperature and over-temperature conditions based on the original model. The results show that the temperature index of the airborne liquid cooling system basically meets the technical requirements of the cold plate inlet temperature (5 °C-30 °C) under typical operating conditions. Under low-temperature conditions, the rapid heating of the cold plate can be achieved through the electric heater control scheme. Under high-temperature circumstances, opening the ram air port scheme has a better cooling effect than increasing the fan speed scheme, but the former needs to consider the flight conditions to avoid the cold plate temperature exceeding the target range.
Highlights
With the increasing demand for equipment in the aviation field, traditional airborne cooling equipment is constantly updated and improved
The first is that the use of air as a cooling medium cannot meet the requirements of high heat flux heat transfer of electronic equipment; second, some engines cannot provide an excessively high air intake for the air cooling system [6]
When the ram air port is opened under the flight altitude of 5000 m, the temperature of the cold plate drops to 7.78 ◦C and 10.35 ◦C, and method 1) drops to 19.80 ◦C and 20.79 ◦C
Summary
With the increasing demand for equipment in the aviation field, traditional airborne cooling equipment is constantly updated and improved. Li et al established a mathematical model for the gas-liquid plate-fin heat exchanger with large thermal inertia and calculated and analyzed the temperature characteristics of single-flow and three-flow heat exchangers with Matlab [18]. In the field of aviation applications, Birur et al studied a liquid cooling system based on a micro-mechanical pump to realize the thermal control of micro spacecraft with a power heat flow rate exceeding 25W/cm2 [22]. From the perspective of heat transfer, the research of modeling and simulation on thermal characteristics of the high heat flux components of the system is of great help to the design and practical use of the liquid cooling system. The research provides a more comprehensive system thermal simulation model and calculation method, which can provide a reference for the engineering design, test verification, and system optimization of the airborne liquid cooling system
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