|Table of Contents|

Development of high performance 490 N apogee engine for satellites(PDF)

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

Issue:
2011年06期
Page:
9-13
Research Field:
专论与综述
Publishing date:

Info

Title:
Development of high performance 490 N apogee engine for satellites
Author(s):
JIANG Wen-long;  YANG Cheng-hu;  LIN Qing-guo
Shanghai Institute of Space Propulsion, Shanghai 200233, China
Keywords:
liquid apogee engine;  specific impulse;  progress
PACS:
V434-34
DOI:
-
Abstract:
The progress of the third generation high performance 490 N apogee engine for satellites is elaborated in this paper. The engine design, hot firing test and the key technology research are described. At last the tentative plan for the follow-up development work is introduced.

References:

[1]STECHMAN Carl, KRISTER David. Off-limit testing of the model R-4D 110LBF(490N) bipropellant rocket engine, AIAA2004-3694[R]. USA: AIAA, 2004.
[2]WU P K, WOLL P, STECHMAN Carl. Qualification testing of 2nd generation high performance apogee thruster, AIAA2001-3253[R]. USA: AIAA, 2001.
[3]STECHMAN Carl, WOLL Peter. A high performance liquid rocket engine for satellite main propulsion, AIAA2000-3161 [R]. USA: AIAA, 2000.
[4]SCHOENMAN L, ROSENBERG S D. Test experience，490N high performance[321 Sec Isp] engine, AIAA92-3800 [R]. USA: AIAA, 1992.
[5]张中光, 钟徐. “神舟”号载人飞船轨控发动机的研制[J].上海航天, 2004 (1): 2-9.
[6]HARDING J T, KAZAROFF J M, APPEL M A. Iridium-coated rhenium thrusters by CVD, TM-101309[R]. USA: NASA, 1988.

Memo

Memo:
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