航天推进技术研究院主办
[1]赵万明,罗维民.液体火箭发动机试验流量测量技术研究[J].火箭推进,2017,43(05):74-79.
ZHAO Wanming,LUO Weimin.Research on flow-rate measurement technology for liquid rocket engine test[J].Journal of Rocket Propulsion,2017,43(05):74-79.
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ZHAO Wanming,LUO Weimin.Research on flow-rate measurement technology for liquid rocket engine test[J].Journal of Rocket Propulsion,2017,43(05):74-79.
液体火箭发动机试验流量测量技术研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
43
期数:
2017年05期
页码:
74-79
栏目:
测控与实验
出版日期:
2017-10-15
- Title:
- Research on flow-rate measurement technology for liquid rocket engine test
- Keywords:
- engine test; flow-rate measurement; field calibration; signal accommodation; data analysis
- 分类号:
- V433.9-34
- 文献标志码:
- A
- 摘要:
- 介绍了液体火箭发动机试验推进剂流量测量技术与方法,阐述流量测量系统设计要点、传感器的选择与安装工艺、现场校准技术、信号调理器设计、抗干扰措施、数据分析与提供方法。文中论述的测量技术实现了发动机试验流量参数的准确测量,为发动机性能评价提供准确、可靠的依据。
- Abstract:
- The method and technology of propellant flow-rate measurement in LRE test is introduced in this paper.The design essentials,sensor selection and installation technology,field calibration technology,signal accommodator design,anti-jamming measures,data analysis and data providing methods of flow-rate measurement system is elaborated in this paper.The accurate measurement of flow-rate parameters in the engine test is realized with the flow-rate measurement technology described in this paper,which can provide accurate and reliable data for the engine performance evaluation.
参考文献/References:
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YU H L, CHEN F, ZHENG Q S, et al. Design of monitoring system for cryogenic propellant level[J]. Journal of rocket propulsion, 2010, 36(3): 54-57.
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备注/Memo
收稿日期:2017-05-05; 修回日期:2017-06-09 作者简介: 赵万明(1958—),男,研究员,研究领域为液体火箭发动机试验测量与控制技术
更新日期/Last Update:
2017-11-10