Go to the main menu
Skip to content
Go to bottom
REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
> Journal Vol & Issue
Journal of the Korean Society of Propulsion Engineers
Journal Basic Information
Journal DOI :
The Korean Society of Propulsion Engineers
Editor in Chief :
Volume & Issues
Volume 14, Issue 6 - Dec 2010
Volume 14, Issue 5 - Oct 2010
Volume 14, Issue 4 - Aug 2010
Volume 14, Issue 3 - Jun 2010
Volume 14, Issue 2 - Apr 2010
Volume 14, Issue 1 - Feb 2010
Selecting the target year
Development of High Thrust
Monopropellant Thruster for Reaction Control System of Space Launch Vehicles
An, Sung-Yong ; Kim, Jong-Hak ; Yoon, Ho-Seung ; Kwon, Se-Jin ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 1, 2010, Pages 1~10
Design and performance evaluation of
monopropellant thrusters to be used at reaction control of space launch vehicles were presented in this paper. Design thrust level was determined as 100, 250 Newton which is nominal thrust level for commercial space launch vehicles. Qualification thruster models including solenoid valves were developed after the reactor design were evaluated at engineering thruster models. Each thruster was evaluated by measurement of characteristic velocity, thrust, specific impulse, and pulse response times at sea level test condition.
An Approach to Alleviate Cancellation Problem of Temperature Preconditioned Navier-Stokes Equations
Lee, Sang-Hyeon ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 1, 2010, Pages 11~19
An approach to reduce cancellation errors of the temperature preconditioned Navier-Stokes equations is proposed. This approach is also applied to the conventional preconditioning methods. Adiabatic laminar viscous flows around a circular cylinder are calculated at different Mach numbers. It is shown that a redefinition of total enthalpy for reducing magnitude of the enthalpy remarkably alleviates cancellation problems of the temperature preconditioning.
Mixing Augmentation with Cooled Pylon Injection in Scramjet Combustor
Lee, Sang-Hyeon ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 1, 2010, Pages 20~28
The mixing characteristics of pylon injection in a Scramjet combustor and effects of film cooling to protect pylon from air-heating were investigated. Three-dimensional Navier-Stokes equations with
SST turbulence model were used. Fuel hydrogen and air were considered as coolants. There were remarkable improvements of penetration and mixing rate with the pylon injection. There was also over-heating on the front surface of the pylon without film cooling. The coolant injected parallel to the front surface of the pylon protects the pylon from over-heating.
Study on Performance and Optimal Operating Conditions of Regenerative Steam-Injection Gas Turbine Systems
Kim, Kyoung-Hoon ; Kim, Dong-Joo ; Park, Sang-Hee ; Oh, Man-Soo ; Kim, Dong-Myoung ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 1, 2010, Pages 29~39
The system performance of the regenerative gas-turbine cycle with the steam injection into the combustor has been studied through the thermodynamic cyclic analysis. The effects of the pressure ratio, the steam injection ratio, the ambient temperature, and the turbine inlet temperature are investigated on the thermal efficiency, the fuel consumption, and the specific power as well as the operating conditions for the maximum thermal efficiency of the system. The results of the present analysis find that the use of steam injection in the regenerative gas-turbine system can greatly enhance the thermal efficiency and the specific power of the system.
System Design and Fundamental Experiment for Thrust Control of
/PE Hybrid Rocket
Lee, Yong-Wu ; Kang, Wan-Kyu ; Huh, Hwan-Il ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 1, 2010, Pages 40~47
In this study, basic research on the thrust control by controling oxidizer mass flow rate of a
/PE hybrid rocket is presented. For this purpose, hybrid rocket system including oxidizer flow control system and data acquisition system was developed. To control oxidizer mass flow rate, we used needle valve with stepping motor which was controled by LabVIEW program. During the fundamental experiments, this system managed to follow the pre-programmed (20 N - 10 N - 20 N - 0 N) thrust level.
The Prediction of Air Flow and Pressure Loss at Inlet Duct
Lee, Bo-Hwa ; Lee, Kyung-Jae ; Yang, Soo-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 1, 2010, Pages 48~55
The purpose of this paper was to address the methodology of the air flow measurement using duct mach number that was considered area-weighed average obtained by total, static pressure and temperature measured at engine inlet duct. Without installing boundary rake, the prediction of air flow measurement was discussed. Actual air flow measurement and pressure value using pressure loss through inlet seal were described to improve the reliability and operability of altitude engine test facility.
Liquid Rocket Engine System of Korean Launch Vehicle
Cho, Won-Kook ; Park, Soon-Young ; Moon, Yoon-Wan ; Nam, Chang-Ho ; Kim, Chul-Woong ; Seol, Woo-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 1, 2010, Pages 56~64
A system design has been conducted of the liquid rocket engine for Korean launch vehicle (KSLV-II, Korea Space Launch Vehicle II). The present turbopump-fed liquid rocket engine of vacuum thrust 76 ton and vacuum specific impulse 297 sec adopts gas generator cycle. The combustion pressure of the regeneratively cooled combustor is 60 bar. The propellant is LOx/kerosene. The engine is started by pyrostarter and the combustor is ignited by TEA (TriEthylAluminium). The engine system performance and the subsystems performance requirements are given through energy balance analysis. The combustion pressure, specific impulse and the engine mass are analyzed to be reasonable comparing with the published data. The startup analysis method which will be used in the future has been validated against the turbopump-gas generator coupled test. The tuning method for performance variation of the engine which is not actively controled has been prepared by mode analysis and performance deviation analysis.
DARPA's Hypersonic Vehicle and TBCC Engine Programs
Noh, Jin-Hyeon ; Choi, Jeong-Yeol ; Byun, Jong-Ryul ; Gil, Hyun-Yong ; Yoon, Hyun-Gull ; Lim, Jin-Shik ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 1, 2010, Pages 65~78
DARPA carries out several R&D programs for hypersonic vehicles to maintain the U.S. military superiority in air and space. Falcon program is the core of the DARPA's activitiy for the hypersonics including the long-term step-by-step approach from HTV-1, HTV-2, HTV-3X to HCV. Hypersonic Turbo-Based Combined Cycle (TBCC) engine technologies research and development programs, HiSTED, FaCET and Vulcan, are also the parts of their activities. Present article presents the summarized review on the backgrounds, technologies and relationships of those programs.