long duration cryogenic propellant in-space storage technology

Paper number

IAC-13,D2,5,2,x17982

Author

Mr. Wang Xiaowei, China Academy of Launch Vehicle Technology, China

Coauthor

Mr. Lin Shen, China Academy of Launch Vehicle Technology, China

Coauthor

Mr. Gao Zhaohui, China Academy of Launch Vehicle Technology, China

Coauthor

Mr. Tang Qingbo, China Academy of Launch Vehicle Technology, China

Coauthor

Mr. Shaohua Zhang, China Academy of Launch Vehicle Technology(CALT), China

Year

2013

Abstract

Lunar exploration missions that take advantage of the high Specific Impulse of LO2/LH2 propulsion for in-space transportation have initial mass-to-orbit launch requirements less than half of those using traditional storable propulsion stages. Therefore, the application of long-duration LO2/LH2 in-space propulsion technology will result in significant launch cost savings for space exploration.

The use of LO2/LH2 propulsion for the entire lunar exploration mission provides a ~45\% reduction in initial mass in Low Earth Orbit (LEO) relative to storable system. The efficientcy offered by LO2/LH2 propulsion offers even greater saving for Mars and outer planet missions. To realize the benefits enabled through the use of high Isp LO2/LH2 propulsion one must be able to efficiently store the cryogenic propellant for long durations. The required storage duration is driven by a combination of the planned mission duration and for multilaunch missions, the time required to assemble the mission components in orbit. Therefore, the long duration cryogenic propellant in-space technology has to be solved firstly.

This paper presents some research results on long duration cryogenic propellent in-space storage technology in China. A passive insulation system was design for a upperstage rocket. An outter foam substrate + variable multilayer insulation structure was used, and an inner liquid mixer was desinged to eliminate the heat stratification. And the heat environment of groud hold/ascent flight/on-orbit periods of the upperstage was analyzed and the LO2/LH2 boil-off rate was predicted. And several other methods to reduce the LO2/LH2 boil-off rate are also presented, e.g. using subcooling propellants.

Abstract document

IAC-13,D2,5,2,x17982.brief.pdf

Manuscript document

IAC-13,D2,5,2,x17982.pdf (🔒 authorized access only).

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