航天推进技术研究院主办
[1]刘万龙,田国华,徐 鑫,等.一种卫星轨控发动机流量校验系统[J].火箭推进,2015,41(04):109-112.
LIU Wanlong,TIAN Guohua,XU Xin,et al.A flow calibration system for orbit-control engine of satellite[J].Journal of Rocket Propulsion,2015,41(04):109-112.
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LIU Wanlong,TIAN Guohua,XU Xin,et al.A flow calibration system for orbit-control engine of satellite[J].Journal of Rocket Propulsion,2015,41(04):109-112.
一种卫星轨控发动机流量校验系统
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
41
期数:
2015年04期
页码:
109-112
栏目:
测控与试验
出版日期:
2015-09-30
- Title:
- A flow calibration system for orbit-control engine of satellite
- 分类号:
- V434-34
- 文献标志码:
- A
- 摘要:
- 针对目前计量部门对质量流量计校验精度只有0.5%且随时间波动的问题，采用称重法对卫星轨控发动机试验用质量流量计进行现场校验，采用真实推进剂作为校验介质，校验时管道和流量计压力与发动机试验时管道和流量计压力一致。通过现场校验，可以提高发动机试验流量测量的精度，可以在符合精度要求的流量计中挑选精度较高的流量计作为试验用主流量计，其他流量计作为备份流量计使用。
- Abstract:
- As the uncertainty of the mass flow meter calibration results is 0.5% in metrology department, a weighing system was built to execute on-line calibration of the mass flow meters used in the test for satellite orbit-control engine. The calibration material used in the test was the true propellant. And the pressure of the propellant pipes and mass flow meters was as same as the pressure in the engine test. By the calibrations, the precision of the flow rate measurement in the test of the engine can be improved. The mass flow meter which has higher precision can be chosen as a main flow meter in the test for the orbit-control engine of satellite and the others can be used as candidates.
参考文献/References:
[1]周红玲, 姜文龙, 刘昌国. 国内外卫星用液体远地点发动机发展综述[J]. 火箭推进，2011, 37(5): 1-8.
[2]张惠军. 科氏力质量流量计在凝胶推进剂火箭发动机试车中的应用[J]. 火箭推进, 2004, 30(6): 55-60.
[3]吴波. Promass83A质量流量计在发动机试验中的应用[J]. 火箭推进, 2005, 31(6): 57-60.
[4]罗凡, 孙玉声. 不同介质对质量流量计的校准误差影响[J]. 中国测试技术, 2007, 33(6): 52-54.
[5]纪纲. 流量测量仪表应用技巧[M]. 北京: 化学工业出版社, 2005.
[6]李长武, 陈平, 袁明, 等. 液体流量仪表在线校准方法及趋势[J]. 计量技术, 2009, (4): 58-61.
[7]周士虎, 张永华. 流量计校验装置在航天发射场加注系统中的应用[J]. 石油工业技术监督, 2001, 17(4): 28-33.
[8]SMITH D M, CARVER D B. Flow calibration of two hypersonic nozzles in the AEDC Heat-H2 high-enthalpy arc-heated wind tunnel, AIAA-1996-0913[R]. USA: AIAA, 1996.
[9]KIRTLEY D E, ENGELMAN S F, FIFE J M. Analysis of xenon flow calibration techniques for electric thruster testing, AIAA-2002-3817 [R]. USA: AIAA, 2002.
[10]钟爱民. 质量流量计自动校验控制系统的设计研究[D].上海: 上海交通大学, 2007.
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备注/Memo
收稿日期：2014-12-26；修回日期：2015-02-27 作者简介：刘万龙（1982—），男，博士，研究领域为火箭发动机试验及测试技术
更新日期/Last Update:
1900-01-01