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Propellant inlet temperature control for cryogenic rocket engine tests(PDF)

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

Issue:
2009年03期
Page:
52-54
Research Field:
测控与试验
Publishing date:

Info

Title:
Propellant inlet temperature control for cryogenic rocket engine tests
Author(s):
Cao Wenqing; Tan Hailin; Li Wei
Xi"an Aerospace Propulsion Test Technique Institute，Xi'an 710100，China
Keywords:
cryogenic propellant; engine test; inlet temperature; forced dump cooling
PACS:
V434
DOI:
-
Abstract:
Factors affecting the propellant inlet temperatures during liquid rocket engine tests were analyzed．Methods were adopted for reducing the propellant inlet temperature by modification of the test system and forced dump cooling of the propellant．Tests proved that the improved approaches are effective and the propellant inlet temperature meets the requirement very well．

References:

[l]华绍曾，扬学林，编译．实用流体阻力手册[M]．北京：国 防工业出版社．1985．
[2]耿文忠．新型液体火箭发动机试车台起动试验系统方案 设计[J]．火箭推进，2008，34(3)：53—57．
[3]王永忠，王宁．低温阀在液体火箭发动机试验中的应 用[J]．火箭推进，2004，30(：1)：35—40．
[4]王占林．小流量推进剂系统低温试验技术叨．导弹与航 天运载技术。2000(5)：37—39．

Memo

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Last Update: 1900-01-01