Thermal energy integrated management system suitable for hypersonic flight vehicle and air vehicle

Abstract

The invention discloses a thermal energy integrated management system suitable for a hypersonic flight vehicle and an air vehicle. The thermal energy integrated management system suitable for the hypersonic flight vehicle comprises a cockpit air system, a fuel system, a propulsion system, airborne equipment, a coolant cooling system and a closed circulating cooling system. When the flight Mach number of the air vehicle is a first preset range value, the coolant cooling system and the closed circulating cooling system both do not work; when the flight Mach number of the air vehicle reaches a second preset range value, the coolant cooling system does not work, and the closed circulating cooling system works; and when the flight Mach number of the air vehicle reaches a third preset range value, the coolant cooling system and the closed circulating cooling system both work. According to the thermal energy integrated management system suitable for the hypersonic flight vehicle and the air vehicle, by using the closed circulating cooling system and the coolant cooling system, the thermal of the air vehicle during hypersonic flight is effectively managed, the problems that the performanceof the air vehicle cannot meet requirements and the safety of the air vehicle is lower are solved, and the problem that the payload space of the air vehicle is small is solved.

Description

technical field [0001] The invention relates to the technical field of hypersonic aircraft, in particular to a thermal energy integrated management system and an aircraft suitable for hypersonic aircraft within the flight Mach number range of 0 to 6. Background technique [0002] The development of hypersonic aircraft is an important direction of aircraft development. The hypersonic vehicle flies at a relatively fast speed. Due to the viscosity and aerodynamic effect on the surface of the body, the surface temperature will be as high as 900-1800K. The heat generated by this part cannot be underestimated. With the improvement of aircraft performance, more and more high-power on-board electronic equipment and advanced mission system support are required, which leads to more heat generated by on-board electromechanical equipment. However, the working environment temperature required by the cabin and airborne equipment cannot be too high. [0003] For hypersonic aircraft, pass...

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Problems solved by technology

[0006] In view of this, the first object of the present invention is to provide a thermal energy integrated management system suitable for hypersonic aircraft, to solve the problem of large power consumption of the internal system of the aircraft due to the high heat of the incoming airflow when the aircraft flies at hypersonic speed. The heat load of the aircraft is high, the performance cannot meet the requirements, the safety of the aircraft is low, and the proportion of the fuel volume caused by only using low-volume heat sink fuel as the heat sink is large, which causes the payload space of the aircraft small problem

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