Abstract
The aerodynamic heating of a high-speed vehicle is destined to lead to a continuous fuselage temperature rise. However, its airborne thermal load rises exponentially. This will severely limit the thermal endurance of the high-speed vehicle and the working time of the electronic equipment. A jet-propelled high-speed vehicle usually uses fuel to generate thrust, so fuel thermal management technology has had much attention paid to it. During the vehicle design, its total amount of fuel should match its flight envelope. However, determining the amount of carried fuel is very difficult because it is affected by many factors. In order to analyze the relationship between the above influence factors and the flight envelope, a typical fuel thermal management system is set up for high-speed vehicles. Its dynamic characteristic equations are built correspondingly. A conception of thermal endurance is further presented to reveal the maximum flight time. Some flight conditions are used to analyze the influence of the main design parameters on the thermal endurance of high-speed vehicles. The results can help to design the parameters of fuel thermal management systems for high-speed vehicles.
Highlights
With the development of the interactive integration of aeronautics and astronautics technology, reusable high-speed vehicles with horizontal take-off and landing have become a hot issue
German established a dynamic model of a fuel thermal management system with or without tank-wall heat transfer in order to study the adaptability of a fuel thermal management system for a certain flight mission [21]
For vehicles, the thermal endurance of fuel will decrease with the increasebut of flight
Summary
With the development of the interactive integration of aeronautics and astronautics technology, reusable high-speed vehicles with horizontal take-off and landing have become a hot issue. German established a dynamic model of a fuel thermal management system with or without tank-wall heat transfer in order to study the adaptability of a fuel thermal management system for a certain flight mission [21] These studies were all carried out when the boundary layer temperature was relatively low and the cumulative effect of aerodynamic heating on the fuselage was not considered. For high Mach number situations, the cumulative effect of aerodynamic heating will cause the tank temperature to rise continuously with the increase of flight time This effect should not be ignored, and it should be carefully considered in the design and research process of fuel thermal management systems in high-speed vehicles
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