|Table of Contents|

Experimental investigation on LOX/CH4 subscale thrust chamber(PDF)

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

Issue:
2010年04期
Page:
59-63
Research Field:
测控与试验
Publishing date:

Info

Title:
Experimental investigation on LOX/CH4 subscale thrust chamber
Author(s):
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Beijing Aerospace Propulsion Institute, Beijing 100076, China
Keywords:
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PACS:
V433.9
DOI:
-
Abstract:
The firing tests of a LOX/CH4 subscale thrust chamber are presented in this paper. The chamber pressure of the tests is between 7.1 and 7.4MPa. The mixture ratio is between 3.5 and 3.9. Effects of design parameters on the LOX/CH4 coaxial injector combustion and discharge performance are investigated by firing tests. Some key parameters are obtained such as combustion efficiency, discharge coefficient, vibration, ignition and the soot formation characteristics. The firing tests are important base for the development of a LOX/CH4 rocket engine.

References:

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Last Update: 1900-01-01