Series of rocket thrust chambers with direct-current heads and cooling discharge partition plates

Abstract

The invention relates to a series of rocket thrust chambers with direct-current heads and cooling discharge partition plates. The rocket thrust chambers are provided with liquid oxygen kerosene or methane, liquid oxygen liquid hydrogen, medium-concentration hydrogen peroxide kerosene or liquid hydrogen or NHMF fuel and other non-toxic double-component propellants. According to the thrust range, the thrust of the medium-sized thrust chambers is 30-150 tons, the thrust of the large thrust chambers is 150-400 tons, and the thrust of the ultra-large thrust chambers is 400-800 tons. The thrust chambers are good in structure universality and very simple. The direct-current heads are high in strength and rigidity, the number of parts is greatly reduced, and a turbine exhaust input device with a double-cone shell is arranged. The cooling discharging partition plates are simple in structure, reliable in work and capable of effectively restraining high-frequency unstable combustion. The technical inheritance of a traditional body is good. An inner cooling improvement mode of an annular gap is given, and the cooling effect is better. The basic type and eight derived type rocket thrust chambers are applicable to rocket engines with the reliability of a single machine improved to 0.9999 and the repeated use frequency reaching 10-200 times.

Description

technical field [0001] The invention relates to a series of rocket thrust chambers with straight-through heads and cooling discharge partitions, and belongs to the technical field of rocket engines such as liquid oxygen kerosene, liquid oxygen methane, liquid oxygen liquid hydrogen, and hydrogen peroxide. Background technique [0002] The development direction of rocket engines is to greatly improve reliability by simplifying the structure and other technical measures, continuously increase thrust according to the needs of rocket launch tasks, and change from one-time use to multiple reuse according to the need to greatly reduce rocket launch costs. For this reason, I proposed "a group of large-diameter rocket thrust chambers with exhaust regenerative cooling partitions" (invention patent application 201711201099.1). This group of rocket thrust chambers has the advantages of relatively simple structure, good versatility, fewer parts, high head strength and rigidity, and can ...

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Problems solved by technology

However, there are also problems that the diameter of the thrust chamber is too large to be 1.7 meters, the propellant does not contain liquid oxygen methane, the partition area is not equal, the partition has end parts, it is not practical to use enriched oxygen for the hydrogen-oxygen thrust chamber, and some collectors are redundant. and other shortcomings

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