Pogo Stability Approaches for the Strap-On Launch Vehicle with Staged Combustion Cycle Engines

2020 ◽  
Vol 57 (4) ◽  
pp. 636-641 ◽  
Author(s):  
Tao Liu ◽  
Jin-Fan Liu ◽  
Wen-Bin Di ◽  
Guo-An Tang ◽  
Lin-Yu Song
Keyword(s):  
Launch Vehicle ◽  
Staged Combustion ◽  
Combustion Cycle

scholarly journals Development Trend of Korean Staged Combustion Cycle Rocket Engine

2018 ◽  
Vol 22 (3) ◽  
pp. 109-119 ◽  
Author(s):  
Chae-hyoung Kim ◽  
Yeoung Min Han ◽  
Namkyung Cho ◽  
Seung-Han Kim ◽  
Byungil Yu ◽  
...  
Keyword(s):  
Rocket Engine ◽  
Development Trend ◽  
Staged Combustion ◽  
Combustion Cycle

Combustion Test of Oxidizer-Rich Single Triplex Injector Preburner for Staged Combustion Cycle Rocket Engine

2015 ◽  
Author(s):  
Su-Ji Lee ◽  
In-Sang Moon ◽  
Il-Yoon Moon ◽  
Seong-Up Ha
Keyword(s):  
Combustion Chamber ◽  
Dynamic Pressure ◽  
Rocket Engine ◽  
Rocket Engines ◽  
Fuel Injector ◽  
Staged Combustion ◽  
Combustion Pressure ◽  
The Republic ◽  
Combustion Tests ◽  
Combustion Cycle

In the Republic of Korea, research on staged-combustion cycle liquid propellant rocket engines (LPRE) is proceeding to improve efficiency of rocket engines. Recently oxidizer-rich preburner using single triplex injector is developed in relation to the main injector development and combustion tests have been performed. This preburner is designed to operate in nominal conditions with the combustion pressure of 10 MPa, OF ratio of 60. For a stable ignition, LOx is fed in two steps. Triethylaluminum-Triethylborane (TEAB) is used as hypergolic fuel for ignition, supplied through a fuel injector. Despite the small amount of fuel flow rate and high pressure condition, the combustion pressure was stably maintained around 10 MPa as designed. As a result of Fast Fourier Transform (FFT) of the combustion chamber dynamic pressure, 1L mode frequencies related to the acoustic instability and hydraulic resistance exist in the combustion chamber. But their amplitudes are less than 1% of the combustion pressure and it does not affect the combustion. Therefore combustion test is stably completed. In the near future, coupled tests with uni-element triplex injector preburner and uni-element gas/liquid injector main combustion chamber will be carried out.

scholarly journals A Study on Anti-oxidization Coating for Staged Combustion Cycle Rocket Engines

2018 ◽  
Vol 22 (5) ◽  
pp. 125-131
Author(s):  
Young-June Kim ◽  
Byong-ho Rhee ◽  
Yong-Oh Noh ◽  
Byung-Hyun Bae ◽  
Seong-Yoon Hyun ◽  
...  
Keyword(s):  
Rocket Engines ◽  
Staged Combustion ◽  
Combustion Cycle

Experiments on an Oxidizer-Rich Preburner for Staged Combustion Cycle Rocket Engines

2014 ◽  
Vol 30 (4) ◽  
pp. 1098-1103 ◽  
Author(s):  
Sang Hun Kang ◽  
Ilyoon Moon ◽  
Soo Yong Lee
Keyword(s):  
Rocket Engines ◽  
Staged Combustion ◽  
Combustion Cycle

scholarly journals A Numerical Study on the Simulation of Power-pack Start-up of a Staged Combustion Cycle Engine

2019 ◽  
Vol 23 (3) ◽  
pp. 58-66
Author(s):  
Sunghun Lee ◽  
Seonghui Jo ◽  
Hongjip Kim ◽  
SeongRyong Kim ◽  
SeungJae Yi
Keyword(s):  
Numerical Study ◽  
Staged Combustion ◽  
Start Up ◽  
Combustion Cycle
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