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Characteristics tests of pulse liquid rocket engine with high chamber pressure(PDF)

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

Issue:
2009年02期
Page:
12-17
Research Field:
研究与设计
Publishing date:

Info

Title:
Characteristics tests of pulse liquid rocket engine with high chamber pressure
Author(s):
Duan Yi; Liu Yu; Qin Lizi; Liang Shuqiang; Lin Zhen
School of Astronautics，Beijing Univ．of Aeronautics and Astronautics，Beijing 1 00083，China
Keywords:
pulse combustion; high chamber pressure; differential pistons; movable injector;  liquid rocket engine; characteristics tests
PACS:
V434
DOI:
-
Abstract:
Numerous tests using cold flow and hot gas were employed in order to investigate the operating theory，pressurizing principles and pulse characteristics of a Pulse Liquid Rocket Engine (PLRE)with high chamber pressure．A test PLRE with a pressure-fed propellant system was designed and fabricated based on calculations and theoretical analysis．In cold flow tests，water and ni— trogen were employed as working substances．The automatic pulse cycles of the test PLRE show that the differential piston increases chamber pressure when it is applied to the thrust chamber．In hot gas tests，ethanol and oxygen were used as propellants．A sequence of nine automatic pulse circles was obtained with a 0．8 nUll displacement range of the movable injector．The peak chamber pressure Was 5．5 1 1 MPa，which Was higher than propellants feeding pressures(3．76 1 MPa for ethanol and 4．424MPa for oxygen)．The test results show that the PLRE can obviously increase the chamberpressure while the propeUants feeding pressures stays the same as the conventional pressure—fed liq— uid rocket engine．

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Last Update: 1900-01-01