|Table of Contents|

Study on synchronous ignition of dual-thrust chamber engine(PDF)

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

Issue:
2014年04期
Page:
16-21
Research Field:
研究与设计
Publishing date:

Info

Title:
Study on synchronous ignition of dual-thrust chamber engine
Author(s):
LI Cheng;  LIU Zhan-guo;  XU Hao-hai
Xi’an Aerospace Propulsion Institute, Xi’an 710100, China
Keywords:
LOX/kerosene rocket engine;  dual-thrust chamber;  synchronous igni
PACS:
V434-34
DOI:
-
Abstract:
LOX/kerosene staged combustion cycle engine of 500 t thrust level is a new generation high thrust liquid propellant rocket engine with dual-thrust chamber system made in China. To eliminate the asynchronous ignition of the LOX/kerosene staged combustion cycle engine with dual-thrust chamber, a control scheme for fuel pathway is investigated in this paper. A mathematic model describing the start-up process and a start-up simulation platform of the rocket engine with dual-thrust chamber were established. Two control schemes for fuel pathway of the thruster were comparatively analyzed. The results show that a control scheme that two throttle valves are adopted respectively on corresponding branch lines is better for the purpose of reducing the sensitivity of asynchronous ignition of dual-thrust chamber engine. The deviation of the resistance between dual-thrust cooling jackets should be less than 1 MPa if only one throttle valve is used.

References:

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