Electric pump pressure type liquid oxygen methane space propelling system

Abstract

The invention provides an electric pump pressure type liquid oxygen methane space propelling system. The electric pump pressure type liquid oxygen methane space propelling system comprises a high-pressure gas cylinder, a liquid oxygen storage tank, a methane storage tank, an electric pump system, an oxygen heat exchange injection rod, a methane heat exchange injection rod and a track control engine; the high-pressure gas cylinder is connected with the liquid oxygen storage tank and the methane storage tank through a first pipeline; the liquid oxygen storage tank and the methane storage tank are connected with an electric pump system through a second pipeline and a third pipeline; the oxygen heat exchange injection rod is arranged in the liquid oxygen storage tank; the methane heat exchangeinjection rod is arranged in the methane storage tank; the electric pump system is connected with the oxygen heat exchange injection rod and the track control engine through a fourth pipeline; and the electric pump system is connected with the methane heat exchange injection rod and the track control engine through a fifth pipeline. The electric pump pressure type liquid oxygen methane space propelling system is suitable for a space aircraft propulsion system, and particularly has obvious application advantages on a space propelling system which has large propellant filling amount and whose track control engine needs to be started for a plurality of times..

Description

technical field [0001] The invention relates to the field of space vehicle power systems, in particular to an electric pump pressure liquid oxygen methane space propulsion system. Background technique [0002] Space chemical propulsion is developing towards high-performance, non-toxic low-temperature chemical propulsion technology. The space propulsion system based on the combination of liquid oxygen / methane propellant has the advantages of high comprehensive performance, good reusability, and utilization of planetary in-situ resources. It has broad application prospects in the fields of high-performance upper stages, planetary landers, star surface base construction, and manned Mars exploration. Existing space propulsion systems mainly adopt high-pressure gas extrusion system solutions, and some use turbo pump booster system solutions. With the rapid development of high-performance lithium battery technology and high-speed lightweight motor technology at home and abroad, e...

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Problems solved by technology

[0003] Aiming at the defects in the prior art, the purpose of the present invention is to provide a method to solve the problems of low specific impulse performance and high operation and maintenance cost of toxic propellant in the prior art, and the extrusion type propulsion system has high tank pressure, pressurized Electric pumped liquid oxygen methane space propulsion system for the problems of large gas consumption, large system structure quality, complex structure of turbo pumped propulsion system, difficulty in multiple starts and depth variable thrust

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