|Table of Contents|

Research on 1 0kN gimbaled regeneratively cooled engine(PDF)

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

Issue:
2009年05期
Page:
8-12
Research Field:
研究与设计
Publishing date:

Info

Title:
Research on 1 0kN gimbaled regeneratively cooled engine
Author(s):
Xu Hui; Yi Qi; Zhong Xu; Jin Guang Ming
Shanghai Institute of Space Propulsion，Shanghm 200233，China
Keywords:
iquid rocket engine; regenerative cooling; gimbaled chamber; firing test
PACS:
434.14
DOI:
-
Abstract:
Main concept and key technologies for a 1 0kN gimbaled rocket engine were intro— duced in this paper．Heat transfer calculation and analysis were performed for main influencing fac— tors such a8 coating and peripheral excess oxidizer coefficient．Axial distribution curves of gas-side wall temperature，liquid-side wall temperature and heat flux were obtained．Boundary condition for engine combustion chamber cooling was established．Two types of injectors with different pressure drops and flow rates for two kinds of propellants combination(N20JMMH；N204／UDMH)were designed．Ground hot tests indicated that the two injectors operated well with high combustion effi— ciency of 95％～96％，which proved the reasonability and feasibility of the engine design concept．

References:

[1]哈杰D T，里尔登F H．液体推进剂火箭发动机不稳定燃烧[M]．北京：国防工业出版社，1980．
[2]刘国球·液体火箭发动机原理·北京：宇航出版社，1993·
[3]加洪 T T.液体火箭发动机机构设计[M].任汉芬，燕子初 译.北京：宇航出版社，1991.
[4]Carl R．Historical Ev。lution of the spaee Shuttle Primaryd Vernier Reaction Contml Rocket Engine Desigens[R]．AIAA 2006--4892．
[5]Michael Hallberg，Torgny Stenholm．Laser Welded Sand．wich Manufacturing Technology for Nozzle Extensions[R]．AIAA 2001—3255．
[6]徐辉，林庆国，汪允武．挤压式低室压推力室再生冷却问题[J]．火箭推进。2006，32(6)12—15．

Memo

Memo:
-
Last Update: 1900-01-01