|Table of Contents|

Development of 1 000 N bipropellant orbit control engine with light weight and high specific impulse(PDF)

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

Issue:
2015年04期
Page:
8-12
Research Field:
研究与设计
Publishing date:

Info

Title:
Development of 1 000 N bipropellant orbit control engine with light weight and high specific impulse
Author(s):
LIU Xiaowei;  YAO Mingming;  LI Jiaming;  CAO Jing;  QU Haijun
Xi’an Aerospace Propulsion Institute, Xi’an 710100, China
Keywords:
orbit control engine;  high specific impulse;  ceramic based composite
PACS:
V434-34
DOI:
-
Abstract:
The development process of the 1 000 N bipropellant orbit control engine with light weight and high specific impulse is introduced. In order to achieve high specific impulse, some measures (selection of suitable injector, injector pair design and cooling design) is adopted. In addition, the design of bipropellant collection cavity, cooling liquid percentage and characteristic length are optimized based on simulation of engine-working process. The ceramic based composite reinforced by carbon fibers (Cf/SiC) is selected for body of the engine due to its characteristic of low density. The ground hot-fire testing is executed. The engine test shows that calculated and measured values of the chamber exterior wall temperature and combustion efficiency are almost same. The combustion efficiency is 96.6% and vacuum specific impulse is 3 169 m/s. After long hot-fire testing, the structure of this engine was still in good condition.

References:

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