Uncertainty Analysis of Staged Combustion LOX/LH2 Rocket Engine Hot Firing Tests

2004 ◽  
Author(s):  
David Lineberry ◽  
Hugh Coleman ◽  
Ryuichi Sekita
Keyword(s):  
Uncertainty Analysis ◽  
Rocket Engine ◽  
Staged Combustion ◽  
Firing Tests

Uncertainty Analysis of the LE-7A Liquid Oxygen-Hydrogen Rocket- Engine Hot Firing Tests

2005 ◽  
Vol 21 (6) ◽  
pp. 1126-1128
Author(s):  
David M. Lineberry ◽  
Hugh W. Coleman ◽  
Ryuichi Sekita
Keyword(s):  
Uncertainty Analysis ◽  
Rocket Engine ◽  
Liquid Oxygen ◽  
Firing Tests

scholarly journals Determination of receiver consumption characteristics using computer simulation

2020 ◽  
Vol 8 (2) ◽  
pp. 10-14
Author(s):  
S.S. Vasyliv ◽  
◽  
V.S. Zhdanov ◽  
M.V. Yevseyenko ◽  
◽  
...  
Keyword(s):  
Computer Simulation ◽  
Flow Rate ◽  
Rocket Engine ◽  
Flow Characteristics ◽  
Maximum Flow ◽  
Complex Configuration ◽  
Rocket Engines ◽  
Gas Leakage ◽  
Control Forces ◽  
Firing Tests

The problem of implementing the detonation mode of fuel combustion in thermal propulsion systems has been widely studied last decade. There are many works on fundamental and applied research on pulsating detonation. Solid propellant detonation engines can develop significant forces for a short time at low structural masses, and therefore they are ideal for auxiliary systems for the removal of separated rocket parts. In addition, detonation processes can be used to create control forces for correcting the trajectory of aircraft. All these facts determine the relevance of the area of work. For studying detonation installations, it is necessary to create test stands, but the design of test installations is an urgent and complex optimization problem. It is advisable to solve this problem with the help of computer simulation. In the existing experimental methods, for designing, it is necessary to determine in advance the geometric parameters of receivers and pipelines that provide the necessary gas consumption for firing tests of detonation rocket engines. The work is devoted to the development of a method for determining the flow characteristics of a receiver with a pipeline of complex configuration based on the constructed model of the stand. Based on the initial data, a computer simulation of the air leakage process from the receiver was carried out, for which the Solid Works software package was used. The places of pressure drop, maximum flow rate, and air mass flow are determined. The low value of the flow rate factor is due to the complex configuration of the pipeline with numerous bends and two bellows. Comparison of calculation results with experimental data was held. The difference between the experimental and calculated values does not exceed 3.6%. The obtained information is used to select the required value of the oxidizer excess coefficient during firing tests of detonation rocket engine models. Keywords: flow rate, gas leakage, receiver, model.

scholarly journals Pressure Control of Staged Combustion Liquid Rocket Engine

2018 ◽  
Vol 22 (4) ◽  
pp. 18-23
Author(s):  
Changhwan Hwang ◽  
Kwangjin Lee ◽  
Seongphil Woo ◽  
Ji-Hyuk Im ◽  
Junsu Jeon ◽  
...  
Keyword(s):  
Rocket Engine ◽  
Pressure Control ◽  
Liquid Rocket Engine ◽  
Staged Combustion ◽  
Liquid Rocket

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

scholarly journals Design and Experimental Investigation on Gas Oxygen/Kerosene Ejector Rocket for RBCC Application

2018 ◽  
Vol 36 (3) ◽  
pp. 558-564
Author(s):  
Xianggeng Wei ◽  
Fei Qin ◽  
Lei Shi ◽  
Baoqing Zhang ◽  
Guoqiang He
Keyword(s):  
Working Conditions ◽  
Rocket Engine ◽  
Combined Cycle ◽  
Engine Test ◽  
The Core ◽  
Technical Requirements ◽  
Core Components ◽  
Design Requirements ◽  
Working Parameters ◽  
Firing Tests

The ejector rocket is one of the core components of the rocket based combined cycle propulsion system, and must be capable of variable working conditions. In order to meet technical requirements for RBCC application, the variable duty operating ejector rocket using the gas Oxygen/Kerosene was designed based on the gas pressurized propellant feed systems. Hot firing tests of four different working conditions had been completed. Experimental results show that the designed ejector rocket engine was stable and reliable, and the working parameters met the design requirements, and the working conditions were adjusted quickly. It lays a foundation for the study of the RBCC engine test and the engine technology of large adjustment ratio.

scholarly journals Fault Detection of a Reusable Rocket Engine using Phase Plane Trajectory of Feature Vectors

2019 ◽  
Vol 11 (1) ◽  
Author(s):  
Seiji Tsutsumi ◽  
Miki Hirabayashi ◽  
Daiwa Sato ◽  
Masaharu Abe ◽  
Kaname Kawatsu ◽  
...  
Keyword(s):  
Fault Detection ◽  
Present Method ◽  
Phase Plane ◽  
Rocket Engine ◽  
Principal Component ◽  
Sensor Failure ◽  
Plane Trajectory ◽  
Feature Vectors ◽  
Firing Test ◽  
Firing Tests

A bivariate time-series analysis based on the phase plane trajectory of feature vectors extracted by principal component analysis is developed for fault detection in a reusable liquid-propellant rocket engine. Static-firing test results of the reusable rocket engine obtained at the Japan Aerospace Exploration Agency are employed for demonstration of the present method. The present method successfully detected temperature sensor failure from 19 firing tests of 62 sensors, even in the deviation of the engine operational sequence between the static-firing tests. The present method was also able to detect the system failure from 23 firing tests. Furthermore, the ability to distinguish the system and sensor failure was demonstrated.

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.

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