Open-cycle liquid oxygen kerosene engine system and use method

Abstract

The invention discloses an open-cycle liquid oxygen kerosene engine system and a use method. The system uses low-cost liquid oxygen and kerosene as propellants to meet starting and ignition functionsof an engine, reduce the production cost of the engine, and meet requirements of non-toxic rocket launch at the same time. The engine system adopts a turbine, a kerosene pump and an oxidant pump, wherein the turbine, the kerosene pump and the oxidant pump are coaxially arranged; an inlet of the oxidant pump communicates with an oxidant supply source, an inlet of the kerosene pump communicates withthe kerosene supply source, and an outlet of the oxidant pump and an outlet of the kerosene pump communicate with a thrust chamber; a gunpowder starter is arranged on the turbine; the turbine communicates with a gas generator through a pipeline, an exhaust pipe is arranged on the turbine, and a pyrotechnic igniter is installed on a head part of the gas generator; one end of an oxidant output secondary pipeline communicates with an oxidant output main pipeline, the other end of the oxidant output secondary pipeline communicates with the gas generator; and one end of a kerosene output secondarypipeline communicates with a kerosene output main pipeline, and the other end of the kerosene output secondary pipeline communicates with the gas generator.

Description

technical field [0001] The invention belongs to the technical field of liquid rocket engines, and in particular relates to an open cycle liquid oxygen kerosene engine system and a use method. Background technique [0002] As a non-toxic and non-polluting propellant combination for launch vehicles, liquid oxygen kerosene has the characteristics of high specific impulse performance, low cost, and convenient use and maintenance, and is widely used in current launch vehicles. Since the current generation of launch vehicle liquid oxygen kerosene main power engine is a supplementary combustion cycle, although the specific impulse performance of the engine is high, due to the high system pressure of the supplementary combustion cycle engine, the engine system is complicated, and the production and testing of components are difficult. The cost of production and use and maintenance is high, and the output is also low. Conventional launch vehicles in active service use conventional p...

AI Technical Summary

Problems solved by technology

Since the current generation of launch vehicle liquid oxygen kerosene main power engine is a supplementary combustion cycle, although the specific impulse performance of the engine is high, due to the high system pressure of the supplementary combustion cycle engine, the engine system is complicated, and the production and testi

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