Adjustable active thermal protection system for hypersonic aircraft

Abstract

The invention discloses an adjustable active thermal protection system for a hypersonic aircraft. The system comprises an air guide pipe; one end of the air guide pipe is open, the other end of the air guide pipe is closed, the open end is rotationally connected with an aircraft nose cone at a through hole in the axis of the aircraft nose cone, a locking mechanism is arranged at the joint, and a plurality of nozzles are circumferentially and evenly formed in the side wall of the closed end. When the protection system works, the air guide pipe leads low-temperature air out of a high-pressure tank in an aircraft cabin and then sprays the low-temperature air out of a nozzle in the side wall to form lateral jet flow, so that incoming flow with the compressed flow speed reduced through the closed end of the air guide pipe is reduced again, the aerodynamic heating effect of the aircraft nose cone is weakened, and the heat flux of the wall surface of the nose cone is reduced; and meanwhile, the sprayed low-temperature air flows downstream along with the main flow to perform film cooling on the wall surface of the nose cone. The defect that a traditional active thermal protection system islow in thermal protection efficiency in a non-zero attack angle state can be overcome, and lateral jet flow has lower critical total pressure than traditional reverse jet flow and is easier to implement.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to an adjustable hypersonic vehicle active thermal protection system. Background technique [0002] Hypersonic vehicles will suffer severe aerodynamic heating effects during flight, that is, high heat flow exists on the walls of the vehicle. High heat flow can cause a sharp increase in the temperature of the airframe structure, especially the nose cone of the aircraft. If the temperature of the structure exceeds the limit temperature of the material, the structure will be damaged, and the aircraft will have a catastrophic accident. In order to ensure that the temperature of the airframe structure is within the temperature range that the material can withstand, it is necessary to design a thermal protection system on the surface of the aircraft. In the future, the flight Mach number of hypersonic vehicles will be greatly increased. Due to the limitation of high temperature resis...

AI Technical Summary

Problems solved by technology

[0007] The technical problem to be solved by the present invention is to provide an adjustable hypersonic aircraft active thermal protection system for the defects involved in the background technology to solve the problem of excessively high critical total pressure of the jet flow in the traditional active thermal protection system and in Africa. The problem of low heat protection efficiency at zero angle of attack

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