Electric pump pressure type liquid oxygen methane space propelling system

A technology of liquid oxygen methane and space propulsion, which is applied to the propulsion system devices of aerospace vehicles, jet propulsion devices, motor vehicles, etc. The problem of low specific impulse performance of toxic propellants has achieved the effect of satisfying large-scale thrust adjustment and multiple start-stops, reducing the carrying capacity, and meeting the needs of use

Active Publication Date: 2019-01-29
SHANGHAI INST OF SPACE PROPULSION
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AI Technical Summary

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

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  • Electric pump pressure type liquid oxygen methane space propelling system

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Embodiment Construction

[0049]The present invention will be described in detail below in conjunction with specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those skilled in the art can make some changes and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0050] Such as figure 1 As shown, the electric pump pressure type liquid oxygen / methane space propulsion system provided by the present invention includes a high-pressure gas cylinder 1, a liquid oxygen storage tank 2, a methane storage tank 3, an electric pump system 4, an oxygen heat exchange spray rod 5, a methane thermal Exchanging the injection rod 6 and the track control engine 7, the high-pressure gas cylinder 1 is connected with the liquid oxygen storage tank 2 and the methane storage tank 3 through...

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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...

Claims

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Application Information

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IPC IPC(8): F02K9/46B64G1/40
CPCB64G1/401B64G1/402F02K9/46
Inventor 程诚王浩明田桂李小芳林庆国张志远
Owner SHANGHAI INST OF SPACE PROPULSION
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