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Design and experiment of a pulse thruster with high combustion chamber pressure(PDF)

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

Issue:
2009年04期
Page:
8-13
Research Field:
研究与设计
Publishing date:

Info

Title:
Design and experiment of a pulse thruster with high combustion chamber pressure
Author(s):
Liang Shuqiang; Qin Lizi; Lin Zhen; Liu Yu; Liu Yabing; Xie Kan
School of Astronautics，Beijing University of Aeronautics and Astronautics，Beijing 100191，China
Keywords:
pulse thruster; design; dynamic sealing; experiment
PACS:
V433.9
DOI:
-
Abstract:
In order to verify the design of a pulse thruster with high combustion chamber pressure and grasp the combustion characteristic of liquid N20／alcohol，the experiments were carried out．Using O-ring as dynamic sealing of the moving injector．The propellant flow paths ensure pro— pellants flowing from manifold cavities to extrusion cavities without propellants count-flow．Accord— ing to the test results，the sealing of O-rings works well．The time sequence was measured，and the ignition was achieved．The combustion chamber pressure Was 2．58MPa．The ignition pressure peak was high because of N20 having high saturation vapor pressure．

References:

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[3]王积伟，童宏甲，黄谊．液压与气压传动[M]．北京：机 械工业出版社．2005．
[4]高思秘主编．液体推进剂[M]．北京：宇航出版社，1991．
[5]贾月，张浩，李亚．一氧化二氮无毒推进剂催化分解研 究[J]．火箭推进，2008，34(3)：58—62．
[6]霍雪亮，韦迪，李路明．N20单组元推进器预热过程的 建模[J]．推进技术，2005，26(1)：80—83．

Memo

Memo:
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Last Update: 1900-01-01