高速飞行器机载综合热管理系统设计与优化

Under the dual effects of aerodynamic heating and high-power electronic equipment heating, the advanced high-speed aircraft heat sink and energy demand are exponentially rising, which seriously restricts the function and performance of the aircraft. In order to improve system cooling and power supply performance and reduce engine performance loss, the optimization design of integrated thermal management system is studied. In this paper, based on the large heat load high-speed aircraft with Mach number (Ma)1-4.4, the optimization design for the three integrated thermal management systems is carried out to optimal match the fuel heat sink, the outer duct convection heat sink, the ram air and flight missions. The equivalent quality method was used to analysis, which equalizes the mass, energy consumption and gas source consumption to the fuel weight penalty, and defined as the objective function. The results reveal that when the Mach number is lower than 2, the outer duct air heat sink mode is more economical. However, with the increasing of the flight speed, the refrigeration cycle pressure ratio significantly increased, which cause the fuel weight penalty increased sharply. When the Mach number is 2-4.5, the fuel heat sink mode is more suitable. Its fuel weight penalty is mainly due to the increasing of flight speed. Compared with engine bleed air, rim air is more suitable for higher Mach number. Thus, for the cruise Mach number below 2, the integrated thermal management system equipped with "external duct bleed air heat sink and engine bleed air" earns less engine performance loss. For the cruise Mach number of 2-4.5, the integrated thermal management system equipped with "fuel heat sink and switchable engine bleed air/rim air" earns better engine performance.