Rocket ejector and thermal protection structure and method thereof

Abstract

The invention discloses a thermal protection structure and method of utilizing emission and transpiration combined cooling for a TRRE (turbo-aided rocket-augmented ramjet combined cycle engine) rocketejector. The rocket ejector is divided into a front edge head cone and a thrust chamber, and the front edge head cone and the thrust chamber are cooled respectively. Laminate transpiration cooling isadopted by the front edge head cone portion to conduct thermal protection. The mode of combined cooling of emission cooling and transpiration cooling is adopted by the thrust chamber portion, and a spiral cooling channel structure is adopted by the emission cooling. The outer surface and the inner surface of a combustion chamber are cooled through emission cooling at the same time, the cooling effect of a spray pipe portion is poor, and then porous transpiration cooling is conducted on the spray pipe portion. The thermal protection structure and method are good in cooling effect, small in quantity of cooling agents and high in reliability, and can achieve the purpose of being reusable.

Description

technical field [0001] The invention relates to a thermal protection structure and method for ejecting a rocket in a TRRE engine, in particular to performing heat protection on an ejecting rocket in a TRRE engine by using combined cooling of discharge and sweating. Background technique [0002] For a long time, countries all over the world have been increasing the use and development of space resources, but most of them are active in the atmosphere and earth orbit within 20km, and pay attention to the adjacent space (about 20-100km) between the two less. With the development of the level of science and technology and the concept of air-space integrated operations, countries have begun to pay attention to the adjacent space between air and space. As an important tool for fast travel between the sky and the earth, near space vehicles, one of its core technologies is the power system, and put forward higher requirements for it, which need to have high performance, low cost, wi...

AI Technical Summary

Problems solved by technology

The nose cone at the leading edge of the ejection rocket is cooled by lamination to solve the local overheating problem caused by the particles in the gas blocking the cooling channel; the thrust chamber adopts exhaust cooling to make full use of the coolant, and the nozzle part is added with porous sweat cooling to solve the throat Insufficient cooling problem

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