Ultra-large type liquid oxygen thrust chamber for human lunar exploration and Mars exploration rocket

Abstract

The invention relates to an ultra-large type or large-scale liquid oxygen thrust chamber for a human lunar exploration and Mars exploration rocket. Kerosene or liquid hydrogen is adopted as fuel; a regenerative cooling 25-area or 9-area partition board structure is given and can effectively restrain high-frequency rough combustion; a porous conical shell is adopted to rectify rich oxygen after guided into a turbine; double conical shells, double load-bearing connecting pieces or a single load-bearing connecting piece and a high-strength head part of a thick inspirator disc can improve the working reliability; a liquid-gas mutual strike inspirator and a self strike mutual strike inspirator are adopted to facilitate vibration attenuation, protect a panel and improve the combustion efficiency; liquid hydrogen, 50-70% hydrogen peroxide or water is adopted as a regenerative cooling agent of a partition board and a cooling film liquid in the thrust chamber and is excellent in cooling effect, and the thrust chamber becomes a three-component thrust chamber with an uncomplicated structure; and the ultra-large type or large-scale liquid oxygen thrust chamber is simpler in structure, greatly reduces the part number, lowers the technological difficulty, shortens the lead time, reduces the development and preparation expenditure, and is suitable for engines of all levels of the human lunar exploration and Mars exploration rocket and an aerospace integrated aircraft engine which can be repeatedly used.

Description

technical field [0001] The invention relates to a super-large liquid oxygen thrust chamber for a manned moon and Mars rocket, and belongs to the technical field of liquid rocket engines. Background technique [0002] Manned landing on Mars and manned landing on the moon again are the tasks of the international aerospace community at present and in the next few decades. The United States has started the development of super-large engines for manned Mars rockets by using the technology used to launch space shuttles. Among them are 800 tons of total thrust high-pressure supplementary combustion liquid oxygen and liquid hydrogen engines. The RD-180 engine developed by Russia is a high-pressure supplementary combustion liquid oxygen kerosene engine with a thrust of 400 tons, which can be used for manned moon landing rockets. [0003] Existing high-pressure supplementary combustion liquid oxygen liquid hydrogen and liquid oxygen kerosene engines are very advanced, but their stru...

AI Technical Summary

Problems solved by technology

[0003] The existing high-pressure supplementary combustion liquid oxygen liquid hydrogen and liquid oxygen kerosene engines are very advanced, but the structure is complicated and the technology is difficult

The thrust chamber has a four-bottom three-cavity or three-bottom two-cavity structure and thousands of nozzles. It is troublesome to process, the strength of the head is not high, and it is not easy to increase the thrust more.

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