Heat Transfer Analysis For Grooved Heat Pipe Under Dynamic Loads

With the development of Aerospace Technology, supersonic fighter aircrafts are in service one after another, which brings significantly enhances to the combat effectiveness. But the leading edges of wings of supersonic aircraft will encounter severe aerodynamic heating during high-speed flight, and therefore how to effectively reduce the difference in temperature between the wings and the surrounding environment has become one of the key problems in enhancing the ability of infrared stealth of an aircraft. Heat pipe is a mature heat transfer element in the application of thermal protection for an aircraft, which can be used for reducing temperature difference between wings and the background, so that it became one of the key technologies of enhancing Infrared stealth. For fighters, heat transfer ability will be affected for different dynamic loads when flight attitudes are changed. However, for the technical security and some other reasons, there are few publications about the application of heat pipe technology on thermal control on wings of supersonic airplane, and there is no comprehensive program as well. Based on FLUENT, numerical modeling is done and factors affecting the heat transfer are analyzed for grooved heat pipe under dynamic loads in this paper. The results show that under steady state heat transfer and heat pipe tilt angle due to changes in good agreement with the experimental results; in centrifugal force assisted liquid return temperature when the lower wall of heat pipe to help heat pipe heat transfer; in centrifugal liquid return tube obstruction when heat pipe wall temperature with the rotational speed increases, not conducive to the heat pipe heat transfer. These results coincide with the experimental data well so that provide basis for the use of heat pipe in heat-protection area.