Thermal analysis of spacecraft propulsion system and its validation

被引：9

作者：

Han, CY ^{[1
]}

Choi, JM ^{[1
]}

机构：

[1] Korea Aerosp Res Inst, Satellite Technol Div, Satellite Core Technol Dept, Taejon 305600, South Korea

来源：

KSME INTERNATIONAL JOURNAL | 2004年 / 18卷 / 05期

关键词：

spacecraft; propulsion system; thermal analysis; heater sizing; thermal vacuum test;

D O I：

10.1007/BF02990304

中图分类号：

TH [机械、仪表工业];

学科分类号：

0802 ;

摘要：

Heaters for the spacecraft propulsion system are sized to prevent propellant from catastrophic freezing. For this purpose, thermal mathematical model (TMM) of the propulsion system is developed. Calculation output is compared with the results obtained from thermal vacuum test in order to check the validity of TMM. Despite a little discrepancy between the two types of results, both of them are qualitatively compatible. It is concluded that the propulsion system heaters are correctly sized and TMM can be used as a thermal design tool for the spacecraft propulsion system.

引用

页码：847 / 856

页数：10

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