中国科学院大连化学物理研究所机构知识库
Advanced  
DICP OpenIR  > 中国科学院大连化学物理研究所  > 期刊论文
题名: Design and performance characterization of a sub-Newton N2O monopropellant thruster
作者: Cai, Guobiao1;  Sun, Wei1;  Fang, Jie1;  Li, Mao1;  Cong, Yu2;  Yang, Zhe3
关键词: Nitrous oxide ;  Monopropellant ;  Micro-propulsion ;  Self-pressurization ;  Preheating
刊名: AEROSPACE SCIENCE AND TECHNOLOGY
发表日期: 2012-12-01
DOI: 10.1016/j.ast.2011.10.003
卷: 23, 期:1, 页:439-451
收录类别: SCI
文章类型: Article
WOS标题词: Science & Technology ;  Technology
类目[WOS]: Engineering, Aerospace
研究领域[WOS]: Engineering
英文摘要: This paper describes the research at Beihang University for developing a sub-Newton thruster based on catalytic decomposition of nitrous oxide (N2O) for fine attitude control of small spacecrafts. The characteristics of the N2O self-pressurization feeding process as well as the preheating process of a sub-Newton N2O thruster were studied. Experimental and simulated results indicated that the tank pressure decreases during the N2O self-pressurization process. The influence on the preheating process of the surface emissivity, the preheating power, the thickness of combustor chamber and the insulation material, were compared. N2O catalytic decomposition experiments were carried out to evaluate the reaction performance of Iridium impregnated modified alumina catalyst, such as activation temperature and reaction temperature. Successful activation and self-sustaining reaction were achieved at 523 K. It was found that the integral structure of the reactor and the loading factor of the catalyst-bed can influence the reaction effect. Based on further experiments looking for proper catalyst-bed, a thruster with a 4310 mm x 25 mm catalyst-bed was designed and fabricated. The vacuum performance of the thruster at different N2O flow rates was evaluated using a vacuum experimental system, which consists of a vacuum chamber and a sub-Newton-thrust measuring stand. Static vacuum thrusts ranging from around 140 mN to 970 mN were achieved with the flow rates altering from around 0.1 g/s to 0.6 g/s. The highest specific impulse reached 1640 N s/kg. (C) 2011 Elsevier Masson SAS. All rights reserved.
关键词[WOS]: NITROUS-OXIDE
语种: 英语
WOS记录号: WOS:000313380100045
Citation statistics: 
内容类型: 期刊论文
URI标识: http://cas-ir.dicp.ac.cn/handle/321008/143088
Appears in Collections:中国科学院大连化学物理研究所_期刊论文

Files in This Item:

There are no files associated with this item.


作者单位: 1.Beihang Univ, Sch Astronaut, Beijing 100191, Peoples R China
2.Dalian Inst Chem Phys, Lab Catalysis & New Mat Aerosp, Dalian 116023, Liaoning, Peoples R China
3.Chinese Acad Space Technol, Beijing 100086, Peoples R China

Recommended Citation:
Cai, Guobiao,Sun, Wei,Fang, Jie,et al. Design and performance characterization of a sub-Newton N2O monopropellant thruster[J]. AEROSPACE SCIENCE AND TECHNOLOGY,2012,23(1):439-451.
Service
 Recommend this item
 Sava as my favorate item
 Show this item's statistics
 Export Endnote File
Google Scholar
 Similar articles in Google Scholar
 [Cai, Guobiao]'s Articles
 [Sun, Wei]'s Articles
 [Fang, Jie]'s Articles
CSDL cross search
 Similar articles in CSDL Cross Search
 [Cai, Guobiao]‘s Articles
 [Sun, Wei]‘s Articles
 [Fang, Jie]‘s Articles
Related Copyright Policies
Null
Social Bookmarking
  Add to CiteULike  Add to Connotea  Add to Del.icio.us  Add to Digg  Add to Reddit 
所有评论 (0)
暂无评论
 
评注功能仅针对注册用户开放,请您登录
您对该条目有什么异议,请填写以下表单,管理员会尽快联系您。
内 容:
Email:  *
单位:
验证码:   刷新
您在IR的使用过程中有什么好的想法或者建议可以反馈给我们。
标 题:
 *
内 容:
Email:  *
验证码:   刷新

Items in IR are protected by copyright, with all rights reserved, unless otherwise indicated.

 

 

Valid XHTML 1.0!
Powered by CSpace