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N20 micro-thruster performance and the nozzle thermo-structure analysis(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2008年05期
Page:
5-9
Research Field:
研究与设计
Publishing date:

Info

Title:
N20 micro-thruster performance and the nozzle thermo-structure analysis
Author(s):
Sun Wei; Fang Jie; Zheng Liming; Cai Guobiao
School of Astronautics，Beijing Univ．of Aeronautics and Astronautics，Beijing 100083，China
Keywords:
nitrous oxide; micro-thruster; nozzle; finite element analysis
PACS:
V439.7
DOI:
-
Abstract:
Performance analysis for monopropellant micro-thruster using nitrous oxide(N20) propellant was conducted based on the thermodynamic computation．Preliminary results show that decomposition rate of nitrous oxide and the expansion ratio of nozzle both effected the specific impulse of the thruster．Finite element analyses on temperature field of micro-nozzle were conducted respectively under vacuum and ground conditions．Subsequently，analysis on stress field of nozzle for ground test Was conducted．Results of simulation show that peak value of temperature and stress both appear at the throat section of the nozzle．Preliminary experiments under ground condition have testiffed the reliability of the micro-nozzle．

References:

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Memo

Memo:
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Last Update: 1900-01-01